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HyperPASS Lite - Global Aerospace Corporation

1. 4 FIGURE 2 5 PROPERTIES WINDOW SHORTCUT TAB PPPPPP 4 FIGURE 3 LHYPERPASS GUL J uu suu Ncc 6 EIGURE 3 2 MISSION SETUP GUT cda eret Poe e REX evene diria e s 7 FIGURE 3 4 SIMULATION PARAMETERS GUI UNGUIDED nennen erret nennen nnne nnn 10 FIGURE 3 21 WARNING GUI EXAMPLE 26 FIGURE 3 22 WARNING GUI EXAMPLE 2Z coccccccccnconononononononononononononononononononononononononono nono tenete 26 FIGURE 4 1 HYPERPASS GUI UNGUIDED n eren ttn anni sien nette anas 29 FIGURE 4 2 MISSION SETUP GUI UNGUIDED enne ennt hannis enne tern nnns sse 30 FIGURE 4 3 SIMULATION PARAMETERS GUI UNGUIDED 31 FIGURE 4 4 BALLUTE PARAMETERS GUI UNGUIDEPD 33 FIGURE 4 5 POST SIMULATION GUI 1 1 2422404001 22 0101000000000000000000000 34 FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU RE 8 2 VEHICLE GUIDANCE 68 8
2. 79 1 Introduction The Hypersonic Planetary Aeroassist Simulation System HyperPASS is an aeroassist simulation software package coded using the MATLAB language HyperPASS is intended for doing mission studies of aerocapture systems at planets with atmospheres and for carrying out trade studies to Investigate performance with alternate aeroshell and ballute types varying flight path angle and entry velocity different g load limits angle of attack and angle of bank variations HyperPASS enables users to perform simulations at any of six planetary bodies Venus Earth Mars Jupiter Saturn Titan Uranus or Neptune using pre programmed vehicles or user entered vehicles It allows users to perform trade study simulations without prior knowledge of MATLAB by way of graphical user interfaces GUIs Functions currently implemented include Unguided Aeroassist Simulations Guided Aerocapture Simulations Guided Ballute Aerocapture Simulations Aerobraking Simulations and Orbit Decay Simulations During mission setup the planet atmosphere gravity model and vehicle parameters are chosen Atmosphere models are exponentially interpolated tables HyperPASS includes numerous atmosphere tables or the user can enter his own up to 21 data points Gravity models include inverse square rotating J2 rotating and inverse square non rotating HyperPASS currently assumes that the at
3. 8 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 Figure 3 9 Custom CL CD vs Kn GUI The Custom CL CD vs Kn GUI allows the user to view the currently selected vehicle file and make changes if desired See warning in Section 3 2 about prematurely starting a run before closing this GUL e Number of Data Points Pull down Menu Allows the user to change the number of model data points displayed 2 21 points e AOA Text Box AOA to be used with the CL CD vs Kn vehicle model displayed When the Continue Pushbutton is selected the AOA will appear in the Simulation Parameters GUI e Save Pushbutton Prompts the user to save any changes to the CL CD vs Kn table under different file name The AOA is also saved to the new CL CD vs Kn file e Continue Pushbutton Returns the user to the Simulation Parameters GUI If any changes were made without being saved the filename will be displayed as untitled 13 e Reset Pushbutton Resets the CL CD vs Kn table to its original set of values If no changes were made the values will remain the same 3 5 2 Custom CL CD vs Mach GUI e 7 terpolati C File Edit View Insert Tools Desktop Window Help Filename MachCLCD default 0 15 30 0 0 0 0 0 0 0 0 0 0 0 0
4. 62 RE 8 3 VENUS VIRADAY ATMOSPHERE coccccccnoncnonononononononononononononononononononononononononononnnnnnnononononononononononononininininens 66 RE 8 4 VENUS VIRANIGHT 67 c EET E 68 69 RE 8 7 MARS COSPAR90 70 RE 8 8 JUPITER_ORTON 71 RE 8 9 JUPITER_LONGUSKI 72 RE 8 10 SATURN LONGUSKI 73 RE 8 11 TITAN 74 RE 8 12 TITAN HUNTEN 75 RE 8 13 TITAN LONGUSKI 5 76 RE 8 14 URANUS_LONGUSKI ATMOSPHERE 2 1 77 RE 8 15 NEPTUNE 78 RE 8 16 NEPTUNE_LONGUSKI nnns nsns
5. eese esee eene no non ene enne 10 O E tq 11 X ss 11 12 12 c m TM 13 13 14 3 6 POST SIMULATION UL liada 15 3 6 1 Unguided Simulation Post Simulation GVI eese eene rennen nenne 15 16 e 18 19 EIS 20 37 PLOT OUTPUT 21 3 7 1 Plot Unguided GUL ins 21 23 REN 24 FAGO AA 25 29 m 25 3 8 3 Warning GUIS m 26 EI LU 27 28 dl DESCRIPTIONS S ka da 28 NOTE Guided Simulations are only available in FULL version of HyperPASS 28 41 1 Unguided Simulations uiis stetit 28 28 pd C Rm 29 42 HOW 523 uu
6. 64 64 ti 65 8 4 ATMOSPHERE MODELS cccccccccscccececscccececececscecececececececececscesscacscecscacscevscavscavecacecasecesavavevevevevevaveveveveveveveves 66 66 enn 66 70 ni MEE AG E 71 OD SAHIN us Sa A ERA 73 74 RENTRER 77 SAO NN 78 8 5 HEATING EQUATIONS PPPPPPPP 80 6 5 1 Stagnation Point 80 8 5 2 Free Molecular Heating cc cecccecssccessceessesessceessecescceescecseneeessecesceeescecseneeeaaecsaceeeaaecseeeeeaaeceeeeeenaeceeneeenaeeees 80 8 6 KNUDSEN NUMBER occcccccococonoconononononononononononononnnonnnnnnnnnnnnnnnnnnnonnnnnnnnnnrnnnnnnnnnnnnnnnnnnnnnnnnnnanonnnanannnnnononanenanenenenes 80 9 ADDENDUM 81 111 TABLE OF FIGURES FIGURE 2 1 MATLAB SHORTCUT ICON COURTESY OF MATHWORKS na 3 FIGURE 2 2 e e te 3 BIGURE2 3 RENAME iicet cecinere etre o e e ren ette 3 FIGURE 2 4 SPROPERTIES u
7. Radial Distance km c Lif NJ Alstude km C Drag N Planet Rel Velocity km s i Stag Point Healing Wiom 2 Velooity krus C Dynamic Pressure Nim 2 Latitude deg Tangential Acceleration gees Longitude deg Norral Acoelarabon gees Planet Rel Azimuth deg Binomal Acceleration gees C inertial Azanus deg a Total Acceleralien gees Rel Flight Path Angle deg C Ang Momentum Inertial Fight Path Angle deg C Ang Momentum Y 2 Angle ol Bank deg C Ang Momentum 2 kam 2 Angle of A ack deg Total Ang Momentum kgim 2 27 4 Functions 41 Descriptions NOTE Guided Simulations are only available in FULL version of HyperPASS 411 Unguided Simulations The user controls an unguided simulation by supplying a set of initial stopping conditions for the simulation Once the simulation is complete the user can add an infinite number of simulation transitions in order to achieve the desired results For information on how to run an unguided simulation see Section 4 2 1 There are also three examples given in section 6 Aerocapture See Section 6 1 Aerocapture See Section 6 2 Entry Descent Landing See Section 6 3 4 1 2 Guided Simulations The guided simulation options require the user to enter function specific inputs in order to perform the various tasks 4 1 2 1 Guided Aerocapture HyperPASS sel
8. Nstag Mstag stag 1 where Ostag 15 the stagnation point heating rate in W cm v is velocity in m s C is the stagnation point heating rate coefficient pis density in ke m is the vehicle nose radius in meters 8 5 2 Free Molecular Heating The equation for Free Molecular Heating is shown below Op l 10 where is the free molecular heating rate in W cm 8 6 Knudsen Number Kn A L where is the mean free path m Lis the characteristic length of the vehicle m The mean free path is the average distance between molecular collisions in the atmosphere Its value is calculated based on the atmosphere conditions and composition For more information on calculating mean free path Bird G A Molecular Gas Dynamics and the Direct Simulation of Gas Flows Clarendon Press Oxford New York 1994 80 9 Addendum TBD 81
9. 0 0 0 0 0 0 Figure 3 10 Custom CL CD vs Mach GUI The Custom CL CD vs Mach GUI allows the user to view the currently selected vehicle file and make changes if desired See warning in Section 3 2 about prematurely starting a run before closing this GUL e Number of Data Points Pull down Menu Allows the user to change the number of model data points displayed 2 21 points e AOA Text Box AOA to be used with the CL CD vs Mach vehicle model displayed When the Continue Pushbutton is selected the AOA will appear in the Simulation Parameters GUI e Save Pushbutton Prompts the user to save any changes to CL CD vs Mach table under a different file name The AOA is also saved to the new CL CD vs Mach file 14 3 6 Post Simulation GUI The Post Simulation GUI is displayed after a simulation is completed The information displayed and the post simulation options vary depending on the chosen function The various Post Simulation GUIs are displayed and described in this section 3 6 1 Unguided Simulation Post Simulation GUI This Post Simulation GUI displays the final state including altitude velocity and flight path angle The inertial final state is displayed if inertial initial conditions were entered or if using the non rotating model The planet relative final state is displayed if planet relative initial conditions are entered
10. 3 8 1 Add Transition GUI This GUI is displayed when Add Transition is selected after running an unguided simulation The Transition Parameters GUI pertains only to unguided simulations that do not have an added ballute See Section 3 4 1 Figure 3 19 Add Transition GUI 3 8 2 Cut Ballute GUI This GUI is displayed when Cut Ballute is selected after running an unguided simulation The Cut Ballute GUI pertains only to unguided simulations that have an added ballute See Section 4 2 1 25 E EL RE Mss Speed Ims 7 J o Maw deg Min FPA dog O Gtond Min Gtosd 9 Howling 2 Min 2 Figure 3 20 Cut Ballute GUI 3 8 3 Warning GUIs HyperPASS has numerous built in warnings to assist the user in running a successful simulation Warnings display the appropriate warning message with a red colored background Two examples of possible Warning GUIs are displayed below Target velocity should be less than the initial velocity CLOSE Figure 3 21 Warning GUI example 1 SaveWar Restarting HyperPASS will delete any unsaved simulations Figure 3 22 Warning GUI example 2 26 OTE This option is only available on Windows PC systems with M S Excel installed The Export Excel GUI is displayed when exporting to M S Excel after an Unguided Guided Select Data to Export Almospherio Density kalm 3 Thrust
11. i Unguided if Add is radius of sphere INPUT Sphere ballute dimension radius of spherical ballute selected Guided Ballute Aerocapture Per apsis altitude change when a raise periapsis deltaV is performed If the free molecular heating limit is exceeded during Aerobraking HyperPASS will raise periapsis altitude INPUT automatically back up to the previous apoapse and perform a raise periapsis Aerobraking deltaV maneuver 2 Elliptical raked cone vehicle type 45 degree If selected HyperPASS displays Unguided Guided Aerocapture Raked Cone vehicle type INPUT CL and CD as a function of user entered AOA Guided Ballute Aerocapture Altitude above which atmospheric density is insignificant atmosphere interface simulation altitude INPUT The higher this value the longer it will take to perform Aerobraking and Orbit Decay Aerobraking Orbit Decay simulations Altitude when simulation will terminate Typically this is atmospheric interface simulation stop altitude INPUT altitude and is equal to the initial altitude This is an input when running a Guided r Guided Ballute Aerocapture or Guided Ballute Aerocapture Simulation only erocaptire Time of simulation Simulation time is input when running Unguided simulation time INPUT Simulation If other simulation stopping conditions are specified the simulation will Unguided run until any stopping condition i
12. Atmosphere Neptune_Hall Gravity Rotation Inverse square rotating Simulation Parameters Neptune_Ballute_example Vehicle Type none 56 57 58 7 Glossary PARAMETER TYPE DESCRIPTION APPLICABLE FUNCTIONS i i Periapsis altitude where aerobraking will start If the V infinity parameter set is ist aerobraking periapsis INPUT selected Aerobraking only a lower periapsis deltaV will be performed to achieve Aerobraking Orbit Decay aititude this 1st aerobraking periapsis altitude Unguided Guided Aerocapture ax g load acceleration force binormal OUTPUT Binormal or lateral acceleration g load over time Guided Ballute Aerocapture binormal i S Unguided Guided Aerocapture acceleration force magnitude OUTPUT Magnitude of acceleration g load over time uba g load Unguided Guided Aerocapture a g load acceleration force normal OUTPUT Normal acceleration g load over time Guided Ballute Aerocapture n 1 A Unguided Guided Aerocapture a g load acceleration force tangential OUTPUT Tangential acceleration g load over time Guided Ballute Aerocaptur
13. Inertial Target Velocity Target Apoapsis Altitude NOTE The chosen target option is achieved at the simulation stop altitude 6 Press Continue in the Mission Setup GUI to start the simulation A simulation progress window will be displayed while the simulation is running When the 43 Initial Flight Path Angle deg Final Altitude km Final Velocity km s Final Flight Path Angle deg Ballute Cut Time sec 5 es 44 Restarts HyperPASS 4 2 4 Aerobraking Simulation Hypersonic Planetary Aeroassist Simulation System Choose a Function Unguided Simulation O Guided Aerocapture Guided Ballute Aerocapture View Previous Simulation Figure 4 16 HyperPASS GUI Aerobraking Select Aerobraking in the HyperPASS GUI and press Continue The Mission Setup GUI will then appear GRAVITY Density Multiplier 1 Rotating Exponential Table Interpolation Qinverse Squave O Plus Venus_ViraNight_short L Plot Atmosphere Aerobraking Parameters Venus Aerobrake example e Change Add Parameters Figure 4 17 Mission Setup GUI Aerobraking 45 Select the desired Planet in the Mission Setup GUI See Section 8 2 Select the desired Atmosphere model in the Mission Setup GUI See Section 8 4 The Gravity model is automatically set to the inverse square model and the simula
14. NOTE If Perform Orbit Circularization is selected HyperPASS will perform a circularization maneuver when the desired apoapsis altitude is achieved 6 Press Continue in the Mission Setup GUI to start the simulation A simulation progress window will be displayed while the simulation is running When the simulation is completed the Post Simulation GUI will appear See warning in Section 4 2 about prematurely starting a run before closing this GUI 47 Orbit Insertion deltaV m s Lower Periapsis deltaV m s of Raise Periapsis deltaV s Circularization deltaV m s Total Time days Plot Output 48 4 2 5 Orbit Decay Simulation 1 Select Orbit Decay in the main HyperPASS GUI and press Continue The Mission Setup GUI will then appear Figure 4 20 Mission Setup GUI Orbit Decay 2 Select the desired Planet in the Mission Setup GUI See Section 8 2 3 Select the desired Atmosphere model in the Mission Setup GUI See Section 8 4 4 The Gravity model is automatically set to inverse square model and the simulation is performed using the non rotating equations of motion 5 Press the Change Add Parameters Pushbutton in the Mission Setup GUI to open the Simulation Parameters GUI and view or change the simulation parameters Save any changes if it is desired to save the parameter set for future simulations and press Continue to return to the Mission Setup GUI Simulation pa
15. See Section 5 5 1 e RESTART o Restarts HyperPASS 34 e ADD TRANSITION opens the Add Transition GUI O The user enter an infinite number of transitions in this manner This is an option if Add Ballute was not selected in the Simulation Parameters GUI Allows the user to add a transition anywhere in the previously completed simulation by changing any of the Vehicle or Guidance parameters Transition time is the time that the transition will begin This value must be less than or equal to the total time of the previously completed simulation Simulation time is the duration of the simulation starting at the transition time Minimum and Maximum stopping conditions can be chosen as before After the transition simulation is completed the Post Simulation GUI will be displayed again The user can add an unlimited number of simulation transitions Figure 4 6 Add Transition GUI Unguided e CUT BALLUTE This is an option if Add Ballute was selected in the Simulation Parameters GUI ADD TRANSITION is not a post simulation option in this case Allows the user to release the ballute anywhere in the previously completed simulation Ballute Cut Time is the time that the ballute will be released This value must be less than or equal to the total time of the previously completed simulation 35 o Simulation Time is the time that the simulation will run after the ballute has
16. been released o Minimum and Maximum stopping conditions can be chosen as before o After the ballute has been released and the simulation completed the Post Simulation GUI will be displayed again Mex 22554 deg Min deg Wer Goud gs Min 95 Husting T ffom 2 Min 2 Figure 4 7 Cut Ballute GUI Unguided 36 Guided Aerocapture Simulation Hypersonic Planetary Aeroassist Simulation System Choose a Function Continue Figure 4 8 HyperPASS GUI Guided Aerocapture Select Guided Aerocapture in the HyperPASS GUI and press Continue The Mission Setup GUI will then appear Density Multiplier Rotating Exponential Table Interpolation Inverse Square O Plus J2 Mars_COS90_short Non Rotating Guided Aerocapture Parameters Mars_GAerocap_example Change Add Parameters Figure 4 9 M sion Setup GUI Guided Aerocapture 37 Select the desired Planet in the Mission Setup GUI See Section 8 2 Select the desired Atmosphere model in the Mission Setup GUI See Section 8 4 Select the desired Gravity rotating or non rotating model in the Mission Setup GUL Press the Change Add Parameters Pushbutton in the Mission Setup GUI to open the Simulation Parameters GUI and view or change the simulation parameters Save any changes if it
17. i 50 100 150 200 250 300 350 400 Altitude km Figure 8 7 Mars_COSPAR90 Atmosphere 8 4 3 2 Mars COS90_short This is a shortened version 21 data points of the Mars COSPAR90 atmosphere model In this version there is a greater altitude change between each data point in the table Ref The Mars Atmosphere Observations and Model Profiles for Mars Missions David E Pitts et al NASA Johnson Space Center report JSC 24455 1990 70 8 4 4 Jupiter The atmosphere temperature profile used for Jupiter_Orton and Jupiter_Longuski atmosphere models is from the Galileo Probe Atmospheric Structure Instrument Jovian Upper Atmosphere Ref http atmos nmsu edu PDS data gp_0001 data asi upperatm lbl http atmos nmsu edu PDS data gp_0001 data asi upperatm tab 8 4 41 Jupiter_Orton 111 data points Ref Atmospheric Structure in the Equatorial Region of Jupiter November 23 1981 Glenn S Orton Current Exponential Atmosphere Profile Density vs Altitude 10 o E a 200 400 600 800 1000 1200 Altitude km Current Exponential Atmosphere Profile Temperature vs Altitude 800 600 400 Temperature K 200 200 400 600 800 1000 1200 Altitude km Figure 8 8 Jupiter_Orton Atmosphere 71 8 4 4 2 Jupiter Orton short This is a shortened version 21 data points of the Jupiter Orton atmosphere model In this version there is a greater altitude change between each data point in th
18. HyperPASS Lite Hypersonic Planetary Aeroassist Simulation System Version 2 0 lite User and Installation Manual June 21 2012 Global Aerospace Corporation ai Aero page Corp 711 W Woodbury Road Suite H Altadena CA 91001 5327 USA Telephone 1 626 345 1200 Fax 626 296 0929 Email global gaerospace com Web http www gaerospace com 1 2 TABLE OF CONTENTS INTRODUCTIONS SO a Na O 1 INSTALLING LY PERPASS E 2 21 SYSTEM 6 25 too e a sasa 2 T AN 2 212 u u ei ee a awaq 2 VAE NS EU UA Gap TEE 2 22 PC INSTALLATION cccccecsesceceessececsssceceesseeecsesaececsceecesaeeecsasaeeecseeeceeaaeeecsesaececsaeecessaeeecsesaeeeseuseeeseneeeesesaeees 2 23 MAC INSTALLATION A 5 2 4 UNIX INSTALLATION 5 GULDESCRIPTIONS S 6 2 1 HYPERPASS GUID ETE 6 2 2 MISSION SETUP iidin 7 3 24 Planetary Bodies i uma i illo tii u asus ile 7 9 22 ede DERE 8 3 2 GTOVIEV mau s ete ertet AS 8 324 Simulation PATGMEIONS aia 8 EET 9 EN b RERO DEN 9 34 SIMULATION PARAMETERS ULSA a 10 3 4 1 Unguided Simulation Parameters GUI
19. PUT See velocity at stop altitude Guided Aerocapture initial magnitude of thrust Directional thrust can be entered by changing the body thrust INPUT fixed thrusting cone and clock angles Unguided T Magnitude of thrust This value will be zero unless otherwise specified during an Unguided Guided Aerocapture thrust Unguided simulation Guided Ballute Aerocapture T A Unguided Guided Aerocapture time OUTPUT Duration of simulation Guided Aerocapture time of deltaV OUTPUT M of each raise periapsis deltaV performed during Aerobraking If selected the user must input the torus dimensions d1 of torus and 42 of torus and the areal density of the ballute material and HyperPass will automatically Unguided if Add is Torus ballute type display the corresponding ballute mass ballute area ballute drag coefficient and selected Guided Ballute Aerocapture ballute nose radius The ballute drag coefficient for the torus is 1 25 e Time to begin transition This value is only needed if Add Transition is selected transition time INPUT after performing an Unguided simulation Unguided The user has the following vehicle type options Raked Cone Viking or Apollo If vehicle Input 906 of these types is selected HyperPass displays the CL and CD as a function Unguided Guided Aerocapture of the user entered AOA 1f no vehicle type is selected the CL CD and AOA are Guided Aerocapture entere
20. Prodator Proy Population Modo Us ino the Proparty Editor Oyariaw of MATLAB Oraphics Editing Object Propertes Cuero MATLAB Graphics LI ef MATLAB Graphics Editing Plote Using Plot Edil Mode ew of MATLAB Graphics Double click an objed to Objects in a Graph Cyaniew of MATLAB Graphics seled it F Many Predators print unctons e Prey Population prin ptintopt MATLAB Functions Will Decline B Y tat MATLAB Funcions Position lobels kgends ond E Y Cut TextProperies MATLAB Furnicbons other objects by clicking ond Setting Object Propames Graphics dragging the m j use Adding Tet Annotations to Graphs Formatting Graph Clear Ami Adding Axis Labels ta Graphs Formatting Graphs Line Width Adding Arrows and Lines to Graphs Formatting Graphs Access objecl spedfic plot Overview of MATLAB Graphics Graphics edit Functions through i Color context sensilive pop up Jl Release Notes menus 0 E Graphics Features MATLAB 6 0 Ralsasa Notas Time t Years 6 Editing Plot Using the Property Editor Save Output in the Post Simulation GUI saves to enter a name for th The user will be prompted 52 change folders while saving HyperPASS automatically opens the correct folder for saved simulations Use the View Previous Simulatio
21. acintosh MATLAB Version 7 8 R2009a or higher HyperPASS may work on earlier versions of MATLAB but has not been tested on any version earlier than indicated 2 1 3 UNIX TBD 2 2 PC Installation NOTE The following steps assume that MATLAB is already installed on the user s system If MATLAB is not installed be sure to install 1t prior to beginning HyperPASS installation EASY INSTALLATION Insert HyperPASS CD ROM into drive and open e Copy HyperPASS folder into the desired location on your computer e tis recommended that you copy it to a location with an easy path i e C HyperPASS e Each time you wish to start HyperPASS first start Matlab and select the HyperPASS folder now saved on your computer as the Matlab Current Directory e To open HyperPASS type startup in the Matlab Command Window ALTERNATE INSTALLATION e Insert HyperPASS CD ROM into drive and open e Copy HyperPASS folder into the desired location on your PC e tis recommended that you copy it to a location with an easy path i e C HyperPASS e Return to your Desktop and Right click on the existing MATLAB shortcut icon and select Create Shortcut The MATLAB shortcut icon is automatically placed on your Desktop when MATLAB is installed Figure 2 1 MATLAB shortcut icon courtesy of MathWorks Open Run as Scan with Norton AntiVirus 3 winzip Pin to Start menu Send To r Cut Copy Create Sh
22. allute simulation i Time of ballute release This value is determined iteratively when running a Guided Unguided if Add Ballute is ballute cut time OUTPUT simulation selected Guided Baliute Aerocapture n Unguided if Add Balie is ballute drag coefficient INPUT Drag coefficient of the selected Guided Ballute Aerocapture CD ballute a i i Unguided if Add Ballute is ballute mass INPUT Mass of the ballute this value does not include vehicle mass Selected Ballute Aerocapture m_ballute Unguided if Add Ballute is ballute nose radius INPUT Nose radius of the ballute selected Guided Ballute Aerocapture Rn_ballute The user has the following options Sphere or Torus If one of these types is selected the user must input the ballute dimensions and the areal density of the ballute t INPUT ballute material and HyperPass automatically displays the corresponding ballute Unguided if Add Baliute is ype mass ballute area ballute drag coefficient and ballute nose radius If no ballute selected Guided Ballute Aerocapture type is selected the ballute s m A CD and Rn are entered independently See Sphere and Torus for more information clock angle INPUT Clock angle of thrusting vector Unguided cone angle INPUT Cone angle of thrusting vector Unguided j i Unguided Guided Aerocapture continuum heating OUTPUT Stagnation point continuum heating rate over time Guided Ballute Aerocaptu
23. and a rotating model is being used e N Post ulatio Lal Inertial Final State Altitude km 16 83119 Velocity km s 0 36728 Flight Path Angle deg 15 799 Add Transition Export to Text Figure 3 11 Post Simulation GUI Unguided e Plot Output see Section 3 7 15 o Opens the Plot Output GUI e Add Transition see Section 0 o Opens the Add Transition GUI o This is not an option if a ballute is added i e Add Ballute is selected in the Simulation Parameters GUI If a ballute is added the user will have the option to Cut Ballute instead of Add Transition e Cut Ballute see Section 0 o Opens the Cut GUI o This is only an option if a ballute is added i e Add Ballute is selected in the Simulation Parameters GUI If no ballute is added the user will have the option to Add Transition instead of Cut Ballute e Save Simulation See Section 4 1 3 o Prompts the user to save the current simulation o Simulation MUST be saved in order to use the View Previous Simulation function The View Previous Simulation function allows the user to reload previously run simulations e Export to Excel See Section 5 4 1 o Allows the user to export user selected simulation data into M S Excel o This option is only available on Windows PC systems with M S Excel installed e Export to Text See Section 5 5 1 o Allows the user to export the simulation data into a tab delimited
24. ayed o Change Add Pushbutton Opens the function specific Simulation Parameter GUI for viewing or to make changes See Sections 3 4 and 4 2 3 33 Atmosphere GUIs 3 3 1 Table Interpolated Atmosphere GUI View Inset Toos Window Number of Dala Points 15 Altitude km Density kglm 3 Filename untitled o 1 225 0 4195 0 08891 0084 0 008995 0 001027 010003096 8281e 005 1 8456 006 3 4160 006 5 604e 007 9 708e 008 22226 08 ss s ON 88388 Figure 3 3 Table Interpolated Atmosphere GUI The Table Interpolated Atmosphere GUI allows the user to view the currently selected atmosphere file and make changes if desired See warning in Section 3 2 about prematurely starting a run before closing this GUI e Number of Data Points Pull down Menu Allows the user to change the number of atmospheric data points displayed 2 21 points e Save Pushbutton Prompts the user to save any changes to the atmosphere table under a different file name e Continue Pushbutton Returns the user to the Mission Setup GUI If any changes were made without being saved the filename will be displayed as untitled e Reset Pushbutton Resets the atmosphere table to its original set of values If no changes were made the values will remain the same 3 4 Simulation Parameters GUIs The format of this GUI will change depending upon the select
25. d independently i Initial speed of the vehicle The user has the choice of entering this value in either velocity INPUT the planet relative or inertial frame ALL M 3 7 3 F Aerobraking 1st periapsis parameter velocity at 1st periapsis INPUT Speed at the user entered 1st aerobraking periapsis altitude set Orbit Decay Target velocity is an input when running a Guided Aerocapture or Guided Ballute i Aerocapture Simulation This target final condition will be met at the simulation Guided Aerocapture Guided Ballute velocity at stop altitude INFAIE stop altitude The user has the option to enter either a velocity at stop altitude or Aerocapture the target apoapse altitude dna If selected HyperPASS displays the CL and CD as a function of user entered Unguided Guided Aerocapture Viking vehicle type INPUT aoa Guided Ballute Aerocapture Unguided Guided Aerocapture infini Approaching v infinity magnitude if the user chooses to give a v infinity speed gt infin v infinity INPUT the initial entry velocity will be calculated at the user entered initial altitude Guided Ballute Aerocapture v infinity Aerobraking Zonal Harmonic J2 PLANET Planetary constant used J2 gravity calculations This is not a user entered input J2 61 8 Appendices 81 Angle Geometry x P X Y Z Planet Inertial Coordinates Zp Planet Rotating Coordinates x y Z Radial East North C
26. d the other containing the delta V maneuver data 54 5 5 Export to Text Selecting Export to Text in the Post Simulation GUI allows the user to export the simulation data to a delimited text txt file The user will be prompted to enter a name for the new text file It is recommended that the file be saved outside HyperPASS program although a folder labeled Text Output does exist just in case All of the text files will include mission setup information such as planet atmosphere file gravity model and vehicle parameters in addition to the output parameters NOTE Currently Export to Excel is limited when compared to the Export to Text option For complete data export it is highly recommended that Export to Text is used The text data can then easily be imported into external programs such as Excel 55 6 Examples LITE VERSION Results for Example 1 Titan Aerocapture can be found in HyperPASS Output User_Output Text_Output The user may also choose to run the example simulations himself by entering the data specified in the following tables 61 Example 1 Unguided Aerocapture Example 1 Unguided Aerocapture Function Unguided Planet Titan Atmosphere Titan_Hunten Gravity Rotation Inverse square non rotating Simulation Parameters Titan_Aerocap_example Example 2 Unguided Ballute Aerocapture Function Unguided Planet Neptune
27. de of each orbit lowest altitude of orbit Aerobraking Orbit Decay SYMBOLS amp PARAMETER TYPE DESCRIPTION APPLICABLE FUNCTIONS ABBREVIATIONS periapsis pass OUTPUT of each periapsis pass starts with 1 at 1st aerobraking periapsis Aerobraking Orbit Decay Average radial distance from the planet s center to surface This is not a user planet radius PLANET entered input ALL R Flight path azimuth angle of the vehicle in the planet relative reference frame over Unguided Guided Aerocapture planet relative azimuth angle OUTPUT Lime Guided Ballute Aerocapture planet relative flight path angle OUTPUT Flight path angle of the vehicle in the planet relative reference frame over time planet relative velocity OUTPUT Speed of the vehicle in planet relative reference frame over time Se eae Nds The rotational of the specified planet moon HyperPASS assumes that planet rotational velocity PLANET the atmosphere rotates with the planet This is not a user entered input ALL R planetary gravitational constant PLANET Used for inverse square gravity calculations This is not a user entered input ALL u GM z Unguided Guided Aerocapture radial distance radius OUTPUT Radial distance of the vehicle over time measured from the center of the planet Guided Aerocapture r
28. dels 8 4 1 Venus The atmosphere temperature profile used for Venus atmosphere models is from Hunten D M et al Venus University of Arizona Press Tuscon AZ 1983 Venus_ViraDay and Venus_Longuski use the Subsolar Noon model and Venus_ViraNight uses the Antisolar Midnight model 8 4 1 1 Venus ViraDay Ref Venus COSPAR 1986 41 data points Current Exponential Atmosphere Profile Density vs Altitude Density kgm 100 200 300 400 500 600 700 800 900 1000 Altitude km ats Current Exponential Atmosphere Profile Temperature vs Altitude 250 200 Temperature K 150 gt 4 100 200 300 400 500 600 700 800 900 1000 Altitude km Figure 8 3 Venus_ViraDay Atmosphere 66 8 4 1 2 Venus ViraNight Ref Venus COSPAR 1986 121 data points Current Exponential Atmosphere Profile Density vs Altitude Density kan 0 200 400 600 800 1000 Altitude kim Current Exponential Atmosphere Profile Temperature vs Altitude Temperature K 200 400 600 800 1000 Altitude krn Figure 8 4 Venus_ViraNight Atmosphere 8 4 1 3 Venus_ViraNight_short This is a shortened version 21 data points of the Venus_ViraNight atmosphere model In this version there is a greater altitude change between each data point in the table Ref Venus COSPAR 1986 67 8 4 2 Earth 8 4 2 1 Earth MSISE90 46 data points Ref http www spenvis oma be spenvis ecss ecss07 ecss07 html run for m
29. e None a Elliptical Raked Cone Viking Apollo o m o Rn o L Mstag o Nstag o C NOTE If vehicle type is selected the CL and CD are displayed as a function of vehicle angle of attack 42 e GUIDANCE o AOA o CL o CD e BALLUTE PARAMETERS o Type None Sphere e radius of sphere e areal density Torus e dl of torus 42 of torus e areal density Ballute Mass Ballute Area Ballute Drag Coefficient equals 0 9 for sphere and 1 37 for torus Ballute Nose Radius Characteristic Length O O O 0 NOTE If Sphere or Torus is selected the user must input the ballute dimensions and the areal density of the ballute material and HyperPASS automatically displays the corresponding ballute mass ballute area ballute drag coefficient and ballute nose radius If no ballute type is selected the ballute s m A CD Rn and L are entered independently e ENTRY CONDITIONS Altitude Longitude Latitude Velocity Azimuth 0000 NOTE Velocity options are planet relative inertial or v infinity If planet relative is chosen azimuth is also planet relative If inertial is chosen azimuth is also inertial If a v infinity is entered azimuth is inertial and the initial velocity is calculated at the initial altitude e Target Conditions o Simulation Stop Altitude usually the same as the entry altitude o Target Options a Planet Relative Target Velocity
30. e tangential A initial altitude above planet surface of vehicle Value should typically be the altitude INPUT planets atmosphere interface ALE Unguided Guided Aerocapture altitude OUTPUT Height of vehicle above the planet surface over time Guided Ballute Aerocapture initial angle of attack of the vehicle Value should be between 90 and 90 degrees Unguk i h guided Guided Aerocapture angie of attack INPUT itno venice nies If a vehicle type is selected the corresponding angle Guided Ballute Aerocapture AOA Angle of attack of the vehicle over time Value will be constant unless changed Unguided Guided Aerocapture angle of attack OUTPUT during an Unguided simulation this is done by adding a transition Guided Ballute Aerocapture AOA angle of bank INPUT of bank of the vehicle Value should be between 180 and 180 Unguided AOB T Unguided Guided Aerocapture angle of bank OUTPUT Angle of bank of the vehicle over time Guided Ballute Aerocapture AOB y Unguided Guided Aerocapture angular momentum X OUTPUT Angular momentum in the inertial X direction over time Guided Ballute Aerocapture hX _ Unguided Guided Aerocapture angular momentum Y OUTPUT Angular momentum in the inertial Y direction over time Guided Aerocapture hY m E Unguided Guided Aerocapture angular momentum Z OUTPUT Angular momentum in the inertial Z direct
31. e Radius o Characteristic Length NOTE If Sphere Torus is selected the user must input the ballute dimensions and the areal density of the ballute material and HyperPASS automatically displays the corresponding ballute mass ballute area ballute nose radius and ballute characteristic length The ballute drag coefficient varies with Kn amp Mach for sphere and varies with Kn for torus If no ballute type is selected the ballute s m A CD Rn and L are entered independently NOTE If ADD BALLUTE is selected the ballute lift coefficient is equal to zero If one desires to run a lifting ballute scenario run an unguided simulation with ADD BALLUTE NOT SELECTED and use Transitions instead 6 Press Continue in the Mission Setup GUI to start the simulation A simulation progress window will be displayed while the simulation is running When the simulation is completed the Post Simulation GUI will appear See warning in Section 4 2 about prematurely starting a run before closing this GUL 33 Inertial Final State Altitude km 16 83119 Velocity km s 0 36728 Flight Path Angle deg 15 799 Add Transition Export to Text Figure 4 5 Post Simulation GUI Unguided e PLOT OUTPUT opens the Plot Output GUI o Allows the user to plot simulation output o See Section 3 7 1for plotting options e EXPORT TO TEXT o Allows the user to export simulation output into a delimited text txt file o
32. e damage to HyperPASS requiring reinstallation Before selecting Continue in the Mission Setup GUI be sure to close any other GUIs e g Simulation Parameters Table Interpolated Atmosphere and Add Ballute by selecting Continue in those respective GUIs When saving new files only use letters numbers and underscores When saving these files avoid including periods brackets spaces etc otherwise the saved files will not be recognized by the program later 3 2 1 Planetary Bodies See Section 8 2 for specific planet moon information and constants Venus Earth Mars Jupiter Saturn Titan Uranus O 00000 o Neptune 3 2 2 Atmosphere see Section 8 4 for default atmosphere information o Density Multiplier Not Included in this version of HyperPASS Allows the user to scale the atmospheric density i e if density multiplier 2 the density is increased by 200 o Plot Atmosphere Pushbutton Plots the currently selected altitude vs density amp temperature profiles o Table Interpolation Select Pushbutton e Prompts the user to select an atmosphere profile from all available table profiles for the selected planet 3 2 3 Gravity o Rotating Planet uses the Rotating Equations of Motion to propagate the trajectory Inverse Square uses the inverse square gravitational model 3 2 4 Simulation Parameters o The filename of the mission s simulation parameters is displ
33. e table Ref Atmospheric Structure in the Equatorial Region of Jupiter November 23 1981 Glenn S Orton 8 4 4 3 Jupiter Longuski 21 data points Ref Longuski James M Puig Suari Jordi Mechalas M Aerobraking Tethers for the Exploration of the Solar System Acta Astronautica Vol 35 No 23 pp 205 214 1995 Current Exponential Atmosphere Profile Density vs Altitude 10 S 419 10 x 2 1079 nu a 1 4 gt 0 100 200 300 400 500 600 700 800 Altitude Current Exponential Atmosphere Profile Temperature vs Altitude Temperature K 100 200 300 400 500 600 700 800 Altitude km Figure 8 9 Jupiter_Longuski Atmosphere 72 8 4 5 Saturn 8 4 5 1 Saturn Longuski 21 data points Ref Longuski James M Puig Suari Jordi Mechalas M Aerobraking Tethers for the Exploration of the Solar System Acta Astronautica Vol 35 No 23 pp 205 214 1995 The atmosphere temperature profile used for the Saturn Longuski atmosphere models is Moses J Photochemistry of Saturn s Atmosphere Icarus 143 pp 244 298 2000 Current Exponential Atmosphere Profile Density vs Altitude Density kgm 0 200 400 600 800 1000 1200 Altitude Current Exponential Atmosphere Profile Temperature vs Altitude 300 200 100 Temperature K 200 400 600 800 1000 1200 Altitude km Figure 8 10 Saturn_Longuski Atmosphere 73 8 4 6 Titan T
34. ean solar activity levels F10 7 F10 7 avg 140 Ap 15 averaged over diurnal and seasonal latitudinal variations Current Exponential Atmosphere Profile Density vs Altitude Density kgm 0 100 200 300 400 500 600 700 800 900 Altitude PP Current Exponential Atmosphere Profile Temperature ys Altitude 800 600 400 Temperature K 200 O 100 200 300 400 500 600 700 800 900 Altitude km Figure 8 5 Earth_MSISE90 Atmosphere 68 8 4 2 2 Earth US1976 21 data points Ref US Standard Atmosphere 1976 Current Exponential Atmosphere Profile Density vs Altitude 10 409 Ie ER aen sansa assqa 5 x A AA Re RR i pu 1079 0 50 100 150 200 Altitude Current Exponential Atmosphere Profile Temperature vs Altitude 800 m 5 600 s 400 5 200 2 0 50 100 150 200 Altitude Figure 8 6 Earth 051976 Atmosphere 69 8 4 5 Mars 8 4 3 1 Mars COSPAR90 154 data points Ref The Mars Atmosphere Observations and Model Profiles for Mars Missions David E Pitts et al NASA Johnson Space Center report JSC 24455 1990 Current Exponential Atmosphere Profile Density vs Altitude 10 10 5 10 a 0 50 100 150 200 250 300 350 400 Altitude km 3m Current Exponential Atmosphere Profile Temperature vs Altitude 300 250 200 Temperature K 150 100 i i i l i
35. ects the appropriate entry flight path angle and modulates the vehicle s bank angle in order to achieve the desired target exit conditions For information on how to run a Guided Aerocapture simulation see 4 2 2 There is also an example given in 6 4 4 1 2 2 Guided Ballute Aerocapture HyperPASS selects the appropriate entry flight path angle and determines the proper ballute cut time in order to achieve the desired target exit conditions For information on how to run a Guided Ballute Aerocapture simulation see 4 2 3 There is also an example given in 6 6 4 1 2 3 Aerobraking HyperPASS performs simulations through the planet s atmosphere until the desired apoapsis altitude is achieved HyperPASS will perform raise periapsis delta V maneuvers as necessary to prevent the free molecular heating limit from being exceeded HyperPASS will perform other delta V maneuvers including orbit insertion delta V and lower periapsis delta V if the initial simulation conditions are entered using the V infinity Parameter Set The user also has the option to perform a circularization delta V maneuver to circularize the orbit when the desired apoapsis altitude is achieved All aerobraking simulations are performed using the inverse square gravity model and the non rotating planet atmosphere For information on how to run an Aerobraking simulation see 4 2 4 There is also an example given in 6 6 28 4 1 2 4 Orbit Decay HyperPASS performs simulations
36. ed function The various Simulation Parameter GUIs are displayed below For additional information on each refer to Section 4 2 How to run each function Also custom vehicle models CL CD vs Kn and CL CD vs Mach can be entered and saved using the Unguided Simultion GUI s vehicle pulldown menus See Section 3 5 See warning in Section 3 2 about prematurely starting a run before closing these GUIs 3 4 1 Unguided Simulation Parameters GUI Figure 3 4 Simulation Parameters GUI Unguided 10 Guided AOA must be between 20 and 20 deg Lift Coet CL 0 6 Drag Coet CD 0 95 9 799 09 Simulation Stop Altitude km 125 Usually the same as the initial altitude 11 Target Conditions Usually the same as the initia atitude inertial Target Velocity at Altitude Velocity at Stop VEHICLE PARAMETERS Mstag Velocity 3 05 Nstag Density 0 5 Stag Heating Coet 9 7488 09 Initial Conditions 1st Periapsis Parameter Set 1st Perlapsis Attitude km 129 5 Velocity at 1st Periapsis km s 7 729 Initial Apoapse Altitude km 2086 47 Aerobraking Parameters 1500 Simulation Ande ar Perform Orbit Circularization 1 0 5 9 748e 09 12 3 5 Vehicle Parameters GUIs 3 5 1 Custom CL CD vs Kn GUI File Edit View Insert Tools Desktop Window Help Filename KnCLCD_default
37. ertial If a v infinity is entered azimuth and FPA are inertial and the initial velocity is calculated at the initial altitude e STOP CONDITIONS Simulation Time Max Min Altitude Max Min Speed Max Min FPA Max Min G load Max Min Heating Max Min Altitude Max Min Speed Max Min FPA Max Min G load O OO OO O O O O O O O O QO QO NOTE Maximum and minimum stopping conditions can be turned on and off by using the corresponding radio buttons e ADD BALLUTE If ADD BALLUTE is selected a ballute will be added to the vehicle The ballute parameters can be changed by pressing the View Change Ballute Pushbutton The simulation is run with the ballute attached m vehicle mass ballute mass CD ballute CD A ballute Area After the simulation is complete the user has the option of releasing the ballute at any time during the simulation by choosing Cut Ballute in the Post Simulation GUI If ADD BALLUTE is not selected the user will have the option of adding a transition by choosing Add Transition in the Post Simulation GUI 32 CONTINUE Figure 4 4 Ballute Parameters GUI Unguided Ballute Type None Sphere e radius of sphere e areal density Torus 41 of torus 42 of torus e ballute areal density Mass Ballute Area Drag Coefficient varies with Kn amp Mach for sphere and varies with Kn for torus Ballute Nos
38. export user selected simulation data into M S Excel o This option is only available on Windows PC systems with M S Excel installed e Export to Text See Section 5 5 3 o Allows the user to export the simulation data into a delimited text txt file e Restart o Restarts HyperPASS o Anyunsaved simulations are deleted when HyperPASS is restarted 3 7 Plot Output GUI This GUI allows the user to view plots of the selected data from the simulation The plotting options vary depending on which function is chosen 3 7 1 Plot Unguided Guided Aerocapture amp Guided Ballute Aerocapture GUI Plot Simulation Plots planet relative latitude longitude azimuth altitude velocity amp FPA as functions of time Also gives values for max min altitude amp delta V Plots stagnation point heating amp dynamic pressure as functions of time Also gives values for max heatup rate amp max dynamic pressure Plots tangential normal amp binormal g loads amp total magnitude of g load as functions of time Also gives max g load value Plots thrust AOA amp AOB as functions of time Figure 3 16 Plot Output GUI Unguided Guided Aerocapture amp Guided Ballute Aerocapture 21 e Plot State o Plots the planet relative latitude longitude azimuth altitude velocity and flight path angle as functions of time e Plot Guidance o Plots thrust Angle of Attack and Angle of Bank as functions of time e Plot G load
39. g plot options are available from x axis and y axis pull down menu s Periapsis Pass Elapsed Time days Periapsis Altitude Apoapsis Altitude Free Molecular Heating at Periapsis Continuum stagnation point Heating Periapsis Inertial Velocity at Periapsis Orbit Period hrs 23 e Plot delta V Data o Allows the user to decide what raise periapsis deltaV variables will be plotted on the x axis and y axis o If no periapsis raise maneuvers occurred during aerobraking no data will be plotted o The following plot options are available from the x axis and y axis pull down menus Orbit Number of raise periapsis maneuver Time of delta V implementation days Delta V magnitude Old periapsis altitude new periapsis altitude 3 7 3 Plot Orbit Decay GUI X Axis Y Axis u B Iperiapsis pass 4 y free molecular heating at peri Y Figure 3 18 Plot Output GUI Orbit Decay e Plot Selected Data o Allows the user to decide what variables will be plotted on the x axis and y axis o The following plot options are available from the x axis and y axis pull down menus Periapsis Pass Elapse Time days Periapsis Altitude Apoapsis Altitude Free Molecular Heating at Periapsis Continuum stagnation point Heating Periapsis Inertial Velocity at Periapsis 24 Orbit Period days 3 8 Other GUIs See warning in Section 3 2 about prematurely starting a run before closing these GUIs
40. he atmosphere temperature profile used for the Titan_Hall Titan_Hunten and Titan_Longuski atmosphere models is Hunten D M Prepared for NASA AMES RC Preliminary Draft 1981 modified by GAC in 2004 to account for appropriate radius and gravity 8 4 6 1 Titan_Hall 11 data points Ref Hall Jeffery L Current Exponential Atmosphere Profile Density vs Altitude Density kgm 0 200 400 600 800 1000 Altitude krn san Current Exponential Atnosphere Profile Temperature vs Altitude 160 140 120 Temperature K 100 80 i i i 0 200 400 500 800 1000 Altitude Figure 8 11 Titan_Hall Atmosphere 74 8 4 6 2 Titan Hunten 1521 data points Ref Prepared for NASA AMES RC Preliminary Draft 1981 modified by GAC in 2004 to account for appropriate radius and gravity 10 Current Exponential Atmosphere Profile Density vs Altitude S 479 AR ae RS eet ey c Bd ha R A es 2 102 d x 0 200 400 600 800 1000 1200 1400 1600 Altitude smi Current Exponential Atmosphere Profile Temperature vs Altitude e 4 150 eee Ie Pee es qe MNT s 3 3 5 5 2 100 vendu usd IAE D ATA EE M B5 5 0 200 400 600 800 1000 1200 1400 1600 Altitude km Figure 8 12 Titan_Hunten Atmosphere 75 8 4 6 3 Titan Long
41. he installation process Double click on the new HyperPASS shortcut icon to begin HyperPASS If the HyperPASS GUI is displayed installation was successful 23 MAC Installation NOTE The following steps assume that MATLAB is already installed on the user s system If MATLAB is not installed be sure to install it prior to beginning HyperPASS installation Insert HyperPASS CD ROM into drive and open Copy HyperPASS folder into the desired location on your computer It is recommended that you copy it to a location with an easy path Each time you wish to start HyperPASS first start Matlab and select the HyperPASS folder now saved on your computer as the Matlab Current Directory To open HyperPASS type startup in the Matlab Command Window 2 4 UNIX Installation TBD 3 GUI Descriptions This section describes all the GUIs used in HyperPASS 3 1 HyperPASS GUI Continue Figure 3 1 HyperPASS GUI The HyperPASS GUI appears when HyperPASS is started or restarted The user selects the desired function and then presses CONTINUE For function specific information see Section 4 3 22 Mission Setup GUI Change Add Parameters Figure 3 2 Mission Setup GUI The Mission GUI appears after selecting a function from the HyperPASS GUI This is where the user sets up the simulation WARNINGS Do NOT attempt to make changes to the MATLAB Command window while using HyperPASS To do so may caus
42. ial reference frame over time aa s ete inertial velocity at periapsis OUTPUT Speed at each periapsis Aerobraking Orbit Decay AERE initial apoapse altitude is automatically calculated and displayed based upon the initial apoapse altitude INPUT user entered Aerobraking or Orbit Decay parameters This is not a user entered Aerobraking Orbit Decay value Period of the initial orbit prior to the lower periapsis deltaV maneuver and the start of aerobraking This is an input when the V infinity parameter set is selected for initial orbit period INPUT Aerobraking Simulation Initial semi major axis and initial orbit period are Aerobraking V infinity parameter set P calculated simultaneously so changing one value will result in the other value changing as well Periapsis altitude of the approaching V infinity trajectory The orbit insertion deltaV will be performed at this altitude to achieve the orbit described by the user entered initial periapsis altitude INPUT initial semi major axis or initial orbit period This value should be above the Aerobraking V infinity parameter set simulation altitude This is an input when the V infinity parameter set is selected for an Aerobraking Simulation Semi major axis of the initial orbit prior to the lower periapsis deltaV maneuver and the start of aerobraking This is an input when the V infinity parameter set is initial semi major axis INPUT selected for an Aerobraking Simulation Initia
43. ided Maximum planet relative flight path angle stopping condition The simulation will max FPA INPUT stop if this FPA is reached This is an optional condition for Unguided Simulations Unguided only Maximum acceleration force magnitude stopping condition The simulation will stop max G load INPUT if this g load is reached This is an optional condition for Unguided Simulations Unguided only Maximum stagnation point continuum heating stopping condition The simulation will stop if this heating limit is reached This is an optional condition for Unguided max heating INPUT Simulations only Aerobraking Simulations have a maximum free molecular heating 9 ded limit not to be confused with this continuum heating limit Maximum planet relative speed stopping condition The simulation will stop if this max speed INPUT speed reached This an optional condition for Unguided Simulations only Unguided Minimum altitude stopping condition The simulation will stop if this altitude is min altitude INPUT reached This is an optional condition for Unguided Simulations only Unguided Minimum planet relative flight path angle stopping condition The simulation will min FPA INPUT stop if this FPA is reached This is an optional condition for Unguided Simulations Unguided only Minimum acceleration force magnitude stopping condition The simulation will stop min G load INPUT if this g load is reached This is an optional condition for Ungu
44. ided Simulations Unguided only Minimum stagnation point continuum heating stopping condition The simulation will stop if this heating limit is reached This is an optional condition for Unguided s min heating Simulations only Aerobraking Simulations have a maximum free molecular heating Unguided limit not to be confused with this continuum heating limit Minimum planet relative speed stopping condition The simulation will stop if this mimspeeds o 2M speed is reached This is an optional condition for Unguided Simulations only _ Unguided Velocity power coefficient for stagnation point heating calculation See for Mstag INPUT more information on heating calculations ALL Mstag new periapsis altitude OUTPUT ie resulting from each raise periapsis deltaV performed during Aerobraking nose radius INPUT Nose radius of vehicle This value is used in the stagnation point heating ALL Rn calculation Atmospheric density power coefficient for stagnation point heating calculation Nstag INPUT see Appendix for more information on heating calculations ALL Nstag Periapsis altitude just prior to each raise per apsis deltaV performed during old altitude OUTPUT Aerobraking Aerobraking orbit number of deltaY OUTPUT Orbit number of each raise periapsis deltaW performed during Aerobraking Aerobraking orbit period OUTPUT Duration of each orbit Aerobraking Orbit Decay eriapsis altitude OUTPUT Periapsis altitu
45. ion over time Guided Ballute Aerocapture hz angular momentum E Unguided Guided Aerocapture magnitude OUTPUT Magnitude of angular momentum over time Guided Ballute Aerocapture h apoapsis altitude OUTPUT Apoapsis altitude of each orbit highest altitude of orbit Aerobraking Orbit Decay i if scicotcd HyperPASS displays tho CL and CD as a function of user Unguided Guided Acrocapturc Apollo vehicle type INPUT QA Guided Ballute Aerocapture i altitude vs INPUT preexisting model may be selected or the user may enter his own ALL 4 4 Unguided Guided Aerocapture atmospheric density OUTPUT Atmospheric density over time Guided Ballute Aerocapture p density Initial fight path azimuth angle of the vehicle The user has the choice of entering x azimuth INPUT this value in either the planet relative or inertial frame Value should be between 0 UM ROM AU E and 360 degrees Unguided if Add Ballute is ballute area INPUT Effective area of the ballute selected Guided Ballute Aerocapture A_ballute 5 Unguided if Add Ballute is ballute areal density INPUT Density of the ballute material selected Guided Ballute Aerocapture Time to release the ballute This value is only needed if Cut Ballute is selected cut time INPUT after performing an Unguided simulation This value is determined iteratively when Unguided if Add Balluto is selected running Guided B
46. is desired to save the parameter set for future simulations and press Continue to return to the Mission Setup GUI Simulation parameters are given below Figure 4 10 Simulation Parameters GUI Guided Aerocapture e VEHICLE o Type None Elliptical Raked Cone Viking Apollo m o A o Rn o L o Mstag 38 Nstag gue NOTE If vehicle type is selected the CL and CD are displayed as a function of vehicle angle of attack e GUIDANCE o AOA o CL o CD e ENTRY CONDITIONS Altitude Longitude Latitude Velocity o Azimuth O O 0 0 NOTE Velocity options are planet relative inertial or v infinity If planet relative is chosen azimuth is also planet relative If inertial is chosen azimuth is also inertial If a v infinity is entered azimuth is inertial and the initial velocity is calculated at the initial altitude e Target Conditions o Simulation Stop Altitude usually the same as the entry altitude o Target Options a Planet Relative Target Velocity Inertial Target Velocity Target Apoapsis Altitude NOTE The chosen target option is achieved at the simulation stop altitude 6 Press Continue in the Mission Setup GUI to start the simulation A simulation progress window will be displayed while the simulation is running When the simulation is completed the Post Simulation GUI will appear See warning in Section 4 2 about prematurely starting a run before closing this GUI 39 In
47. itial Flight Path Angle deg Final Altitude km Final Velocity km s Final Flight Path Angle deg METAM 40 gt Guided Ballute Aerocapture Simulation Hypersonic Planetary Aeroassist Simulation System Choose a Function Continue igure 4 12 HyperPASS GUI Guided Ballute Aerocapture 1 Select Guided Ballute Aerocapture the HyperPASS GUI and press Continue The Mission Setup GUI will then appear ATMOSPHERE Density Multiplier Rotating Exponential Table Interpolation O Plus J2 Mars_COS90_short L D Guided Ballute Aerocapture Parameters Mars GBallute example Change Add Parameters 2 Figure 4 13 Mission Setup GUI Guided Ballute Aerocapture Select the desired Planet in the Mission Setup GUI See Section 8 2 41 3 Select the desired Atmosphere model in the Mission Setup GUI See Section 8 4 4 Select the desired Gravity rotating or non rotating model in the Mission Setup GUL 5 Press the Change Add Parameters Pushbutton in the Mission Setup GUI to open the Simulation Parameters GUI and view or change the simulation parameters Save any changes if it is desired to save the parameter set for future simulations and press Continue to return to the Mission Setup GUI Simulation parameters are given below Figure 4 14 Simulation Parameters GUI Guided Ballute Aerocapture e VEHICLE o Typ
48. l semi major axis and initial orbit Aerobraking V infinity parameter set a period are calculated simultaneously so changing one value will result in the other value changing as well initial latitude in the planet reference frame Value should be between 0 and 260 Unguided Guided Aerocapture atitude INPUT degrees Guided Bailute Aerocapture atitude OUTPUT Latitude position in the planet reference frame over time Guided B lufe y m initial coefficient of lift Value can be entered manually if no vehicle type is 5 ift coefficient INPUT selected If a vehicle type is selected the lift coefficient is calculated and Unguided Guided Aerocapture CL a Pons Guided Bailute Aerocapture displayed as a function of initial angle of attack w Unguided Guided Aerocapture ift force OUTPUT Lift over time Guided Ballute Aerocapture L initial East longitude in the planet reference frame Value should be between 0 Unguided Guided Aerocapture ongitude INPUT and 360 degrees Guided Ballute Aerocapture longitude OUTPUT East longitude position in the planet reference frame over time Guided Salle initial mass of the vehicle When running a simulation involving a ballute this is the mass INPUT mass of the vehicle without the ballute ALL m Maximum altitude stopping condition The simulation will stop if this altitude is P max altitude INPUT reached This is an optional condition for Unguided Simulations only Ungu
49. meters 53 Select Data to Export Almesphe o Density kalm 3 Thrust Radial Distance Lift N Aude km Drag N Planet Rel Velocity km s a Stag Point Healing Wiom 2 Velocity km s C Dynamic Pressure Mirm 2 Latitude deg c Tangential Accelera on gees Longliusde deg Normal Acoeleralion gees Planet Rel Azmuth deg Binomal Acceleration gees C heria Azimuth deg a Total Acceleralicn gets Plane Rel Flight Path Angle deg C Ang kal 2 inertial Flight Path Angle deg C Ang Momentum Y kam 2 Angle of Bank deg C Ang Momentum Z 2 Angle of A ack deg Total Momentum 2 Figure 5 2 Select Data To Export 5 4 2 Aerobraking All output data is exported to an M S Excel workbook Output parameters include all parameters that are available for plotting See Section 3 7 2 Three separate worksheets will be created in the Excel workbook one containing the simulation data output another containing the vehicle parameters and the other containing the delta V maneuver data 5 4 3 Orbit Decay All output data is exported to an M S Excel workbook Output parameters include all parameters that are available for plotting See Section 3 7 3 Three separate worksheets will be created in the Excel workbook one containing the simulation data output another containing the vehicle parameters an
50. model in the Mission Setup GUI See Section 8 4 4 Select the desired Gravity rotating or non rotating model in the Mission Setup GUI 5 Press the Change Add Parameters Pushbutton in the Mission Setup GUI to open the Simulation Parameters GUI and view or change the simulation parameters Save any changes if it is desired to save the parameter set for future simulations and press Continue to return to the Mission Setup GUI Simulation parameters are given below 30 Figure 4 3 Simulation Parameters GUI Unguided e VEHICLE o Type None Elliptical Raked Cone Viking Apollo 45 deg cone Sphere Torus Custom CL CD vs Knudsen Number Custom CL CD vs Mach Number m A Rn L Mstag Nstag C Isp 0 O O O NOTE If Raked Cone Viking or Apollo vehicle type is selected the CL and CD are displayed as a function of vehicle angle of attack The 45 deg Cone and Torus have aerodynamic coefficients that vary with Knudsen number The Sphere model calculates CD as a function of both Knudsen and Mach numbers For more information on vehicle models see Section 8 3 31 e GUIDANCE o AOB AOA CL CD INITIAL CONDITIONS Altitude Longitude Latitude Velocity Azimuth o FPA NOTE Velocity options are planet relative inertial or v infinity If planet relative is chosen azimuth and FPA are also planet relative If inertial is chosen azimuth and FPA are also in
51. mosphere rotates with the planet Therefore simulations specifying a non rotating model assume zero atmosphere rotation and zero planet rotation In such cases inertial and planet relative values are equal Vehicles include Apollo Viking Elliptical Raked Cone 45 Half Cone Sphere Torus or user entered Custom models e g aerodynamic coefficients as functions of Knudsen number or Mach number After completing a simulation the simulation data can be saved plotted or exported to another format If the user chooses to save the simulation it can be reloaded at a later time using HyperPASS View Previous Simulation option If any problems are encountered during the use of HyperPASS please send an email to global gaerospace com describing the nature of the problem LITE VERSION HyperPASS capabilities available only in the FULL version of HyperPASS are grayed out in this Manual INCLUDED IN FULL VERSION Earth planet model atmosphere composition J2 gravity thrust options selectable Vehicle Ballute models aerodynamics as a function of Knudsen and Mach numbers infinite trajectory transitions calculation of Mach number Knudsen number and stagnation point heating rate additional data export options 2 Installing HyperPASS 2 1 System Requirements 2 1 1 PC MATLAB Version 7 5 R2007b or higher HyperPASS may work on earlier versions of MATLAB but has not been tested on any version earlier than indicated 2 1 2 M
52. n option in the HyperPASS GUI to reload a chosen saved simulation After the saved data is reloaded the Post Simulation GUI will be displayed as if the simulation was just completed 5 4 Export to Excel This option is only available on Windows PC systems with M S Excel installed Selecting Export to Excel in the Post Simulation GUI allows the user to export the simulation data to a M S Excel workbook The user will be prompted to enter a name for the new Excel workbook it is recommended that the workbook be saved outside the HyperPASS program although a folder labeled Excel Output does exist just in case NOTE Currently Export to Excel is limited when compared to the Export to Text option For complete data export it is highly recommended that Export to Text is used instead The text data can then easily be imported into external programs such as Excel 541 Unguided Guided Aerocapture amp Guided Ballute Aerocapture The user selects what output parameters to export using the Export Excel GUI Output parameters include most parameters that are available for plotting See Section 3 7 1 Two separate worksheets will be created in the Excel workbook one containing the simulation data output and another containing the vehicle parameters All of the Excel workbooks will include mission setup information such as planet atmosphere file gravity model and vehicle parameters in addition to the output para
53. o Plots tangential normal and binormal acceleration forces and total magnitude of acceleration forces as functions of time e Pressure Plots and dynamic pressure as functions of time e Plot Selected Data o Allows the user to decide what variables will be plotted on the x axis and y axis o The following plot options are available from the x axis and y axis pull down menus Time Altitude Latitude Longitude Planet Relative Velocity Inertial Velocity Planet Relative Flight Path Angle Inertial Flight Path Angle Planet Relative Azimuth Angle Inertial Azimuth Angle Thrust Angle of Attack Angle of Bank Free Molecular Heating Rate Acceleration force tangential Acceleration force normal Acceleration force binormal Acceleration force magnitude force Drag force Angular Momentum X Angular Momentum Y Angular Momentum Z Angular Momentum magnitude atmospheric density Atmospheric Density 22 Mach Number Drag Coefficient Lift Coefficient Mass Aerodynamic cross section area Nose Radius Characteristic Length 3 7 20 Plot Aerobraking GUI X Axis Y Axis abscissa ordinate pariapsis pass 8 apoapsis altitude Y Axis ordinate deltav magnitudo Figure 3 17 Plot Output GUI Aerobraking e Plot Selected Data o Allows the user to decide what variables will be plotted on the x axis and y axis o The followin
54. oordinates Figure 8 1 HyperPASS Coordinate Systems 2 1 i y as 4 Tangential Acceleration Normal Acceleration p d aw 7 Binormal Acceleration AOA T Thrust Vector L Lift Vector D Drag Vector Figure 8 2 Vehicle Guidance Angles 62 8 2 Planetary Information Planetary data for Saturn and Uranus will be documented in the next version of this user s manual Table 8 1 Planetary Information Planet planet rotational gravitational 12 atm surface Moon radius R velocity parameter Oblateness composition gravity km rad s GM km 52 constant m s 2 Venus 6 051 80 2 9924E 07 324 858 5988 8 87003 Mars 3 396 20 7 0776 05 42 828 3100 3 71317 Jupiter 71 492 00 1 7585E 04 1 266865E 08 24 78652 Saturn 60 268 00 1 6379E 04 3 793100E 07 10 44289 Titan 2 575 00 0 0000E 00 8 978 2000 1 35405 Uranus 25 559 00 1 0124E 04 5 794000E 06 8 86933 Neptune 24 764 00 1 0834E 04 6 835107E 06 11 14561 NOTE Vehicle amp Ballute Models are only available in FULL version of HyperPASS 63 8 3 2 Viking vehicle Viking is a vehicle model available during Unguided Guided Aerocapture and Guided Ballute Aerocapture simulations When Viking is chosen the CL and CD are calculated and displayed based on the user entered angle of attack AOA Once the AOA is chosen the CL CD and AOA are fixed fo
55. ortcut Delete Rename Properties Figure 2 2 Create Shortcut 2 e Right click on the newly created shortcut and select Rename Rename the shortcut HyperPASS Open Run as Scan with Norton AntiVirus Al Winzip Pin to Start menu Send To Cut Copy Create Shortcut Delete Rename Properties Figure 2 3 Rename e Right click on the newly created HyperPASS shortcut and select Properties e Select the Shortcut Tab in the Properties Window Open Run as Scan with Norton AntiVirus tS winzip to Start menu Send To Cut Copy Paste Create Shortcut Delete Rename Figure 2 4 Properties HyperPASS Properties General HyperPASS Target type Target Start in Shortcut key Run Comment Application Targetlocation win32 CAMATLAB6p5 bin win32 matlab exe Shortcut 7YYYYY CAHyperPASS None Minimized Find Target Change Icon Advanced Figure 2 5 Properties Window Shortcut Tab Where 1t says Start in type the path where HyperPASS is located If the path is incorrect HyperPASS will not run Click Apply If the path is typed incorrectly a warning will appear Once the path is correct click OK to close the Properties Window This completes t
56. osphere temperature profile used for Neptune_Hall and Neptune_Longuski atmosphere models is Ref Lunine J I The Atmospheres of Uranus and Neptune Annu Rev Astron Astrophys No 31 pp 217 263 1993 8 4 8 1 Neptune_Hall 21 data points Ref Hall Jeffery L and Lee Andrew K Aerocapture Trajectories for Spacecraft with Large Towed Ballutes AAS 01 235 Current Exponential Atmosphere Profile Density vs Altitude a Density kgm 0 500 1000 1500 Altitude krn Current Exponential amp tmosphere Profile Temperature vs Altitude 600 400 200 Temperature 500 1000 1500 Altitude km Figure 8 15 Neptune_Hall Atmosphere 78 8 4 8 2 Neptune Longuski 21 data points Ref Longuski James M Puig Suari Jordi Mechalas M Aerobraking Tethers for the Exploration of the Solar System Acta Astronautica Vol 35 No 23 pp 205 214 1995 Current Exponential Atmosphere Profile Density vs Altitude sE 2 10 i i 500 1000 1500 Altitude Current Exponential Atmosphere Profile Temperature vs Altitude 400 3 200 8 500 1000 1500 Altitude Figure 8 16 Neptune_Longuski Atmosphere 79 8 5 Heating Equations Refer to the Glossary for symbol definitions 8 5 1 Stagnation Point Heating The equation for Stagnation Point Heating also called Continuum Heating is shown below O 22
57. r the simulation 8 3 3 Apollo vehicle Apollo is a vehicle model available during Unguided Guided Aerocapture and Guided Ballute Aerocapture simulations When Apollo is chosen the CL and CD are calculated and displayed based on the user entered angle of attack AOA Once the AOA is chosen the CL CD and AOA are fixed for the simulation 8 3 4 45 Half Cone vehicle The 45 Half Cone is a vehicle model available during Unguided simulations only When 45 Half Cone is chosen the axial and normal force coefficients are calculated for the user entered angle of attack AOA Once the AOA is chosen the CL and CD vary during the simulation based on the varying Knudsen Number value and fixed AOA Ref Mitcheltree R A et al Aerodynamics of the Mars Microprobe Entry Vehicles Paper 97 3658 1997 8 3 5 Sphere vehicle or ballute Sphere is a vehicle model available during Unguided simulations only When Sphere is chosen the AOA and CL are set to zero and the CD varies during the simulation as a function of both Knudsen number and Mach number For continuum flow Kn lt 0 001 we use a CD vs Mach model for supercritical Reynolds numbers Ref Nebiker R R Feasibility Study of an Inflatable Type Stabilization and Deceleration System for High Altitude and High Speed Recovery Goodyear Aircraft Corporation Akron OH 1961 Sphere is also a ballute model available during Unguided and Guided Ballute Aerocapt
58. rameters are given below 49 Venus_Decay_example Figure 4 21 Simulation Parameters GUI Orbit Decay e VEHICLE PARAMETERS o m o A o Rn o Mstae Nstag a o CD e INITIAL CONDITIONS o 1 Parameter Set no delta V maneuvers performed prior to aerobraking 1 Periapsis Altitude Velocity at 1 Periapsis NOTE The initial apoapsis altitude is automatically recalculated and displayed if initial conditions are changed e ORBIT DECAY PARAMETERS o Desired Apoapsis Altitude o Simulation Altitude 6 Press Continue in the Mission Setup GUI to start the simulation A simulation progress window will be displayed while the simulation is running When the simulation is completed the Post Simulation GUI will appear See warning in Section 4 2 about prematurely starting a run before closing this GUI 50 Orbit insertion deltaV m s Lower Periapsis deltaV m s of Raise Periapsis deltaV s Circularization deltaV m s Total Time days Plot Output NET uiii ean 51 5 Output Options 5 1 Plot Data Selecting Plot Data in the Post Simulation GUI opens the Plot Output GUI For complete lists of output data available for plotting See Section 3 7 5 2 Editing Plots Plots are created using MATLAB MATLAB contains a variety of options for editing plots For more information on editing plots open the MATLAB Help Navigator by selecting Help MATLAB Help from
59. re continuum heating at periapsis OUTPUT Stagnation point continuum heating at each periapsis Aerobraking Orbit Decay g at Torus ballute dimension distance from center of torus to the center of the torus s Unguided if Add Ballute is 41 of torus INPUT tube selected Guided Ballute Aerocapture a 7 Unguided if Add Ballute is d2 of torus INPUT Torus ballute dimension diameter of the torus s tube selected Guided Ballute Aerocapture d2 delta V magnitude OUTPUT Magnitude of each raise periapsis deltaV performed during Aerobraking Aerobraking desired apoapse altitude INPUT ERE and Orbit Decay simulations will stop once this apoapse altitude is Aerobraking Orbit Decay Initial coefficient of drag Value can be entered manually if no vehicle type is drag coefficient INPUT selected If a vehicle type is selected the drag coefficient is calculated and ALL displayed as function of initial angle of attack Unguided Guided Aerocapture drag force OUTPUT Drag over time Guided Ballute Aerocapture effective area INPUT Effective cross sectional surface area of the vehicle ALL A elapsed time OUTPUT Time of each periapsis pass Aerobraking Orbit Decay Initial fight path angle of the vehicle The user has the choice of entering this flight path angle INPUT value in either the planet relative or inertial frame This value is determined Unguided y iteratively when running a Guided Aerocaptu
60. re or Guided Ballute Aerocapture simulation Value is typically a negative 59 SYMBOLS amp 60 PARAMETER TYPE DESCRIPTION APPLICABLE FUNCTIONS ABBREVIATIONS free molecular heating at 2 8 periapsis 9 OUTPUT Free molecular continuum heating at each periapsis Aerobraking Orbit Decay Qin if the free molecular heating rate exceeds this limit during Aerobraking HyperPASS inn limi will automatically back up to the previous apoapse and perform a raise periapsis free molecular heating limit INPUT qeltaV maneuver The periapsis altitude change during this maneuver is Aerobraking determined by the user entered raise periapsis altitude hos Unguided Guided Aerocapture g load OUTPUT See acceleration force Guided Ballute Aerocapture g load Vehicle flight path heading angle Heading angle is not a user entered input heading angle INPUT instead the user inputs azimuth angle 90 azimuth ALL inertial azimuth angle OUTPUT Flight path azimuth angle of the vehicle in the inertial reference frame over time Sine Suite Unguided Guided Aerocapture inertial flight path angle OUTPUT Flight path angle of the vehicle in the inertial reference frame over time Guided Ballute Aerocapture inertial velocity OUTPUT Speed of the vehicle in inert
61. s met or until the simulation time is reached specific impulse INPUT Specific impulse of the body fixed thrust Unguided Isp selected the user must input the sphere dimension radius of sphere and the areal density of the ballute materia and HyperPass will automatically display the Unguided if Add Ballute is Sphere ballute type INPUT corresponding ballute mass ballute area ballute drag coefficient and ballute nose selected Guided Ballute Aerocapture radius The ballute drag coefficient for the sphere is 0 9 i i Coefficient for stagnation point heating calculation See for more information on stagnation heating coefficient INPUT heating calculations ALL 5 Unguided Guided Aerocapture stagnation point heating OUTPUT Stagnation point continuum heating rate over time Sed Ballute point heating at OUTPUT Stagnation point continuum heating at each periapsis Aerobraking Orbit Decay Qua This target final condition will be met at the simulation stop altitude when running Guided Aerocapture Gu ded Ballute target apoapse altitude INPUT a Guided Aerocapture or Guided Ballute Aerocapture Simulation The Aerobraking Aerocapture Aerobraking Orbit and Orbit Decay Simulations will stop once this apoapse altitude is achieved Decay i a a z Guided Aerocapture Guided Ballute target velocity inertial INPUT velocity at stop altitude Aerocapture target velocity planet relative IN
62. text txt file e Restart o Restarts HyperPASS o Anyunsaved simulations are deleted when HyperPASS is restarted 3 6 2 Guided Aerocapture Post Simulation GUI This Post Simulation GUI displays the initial flight path angle and final state including altitude velocity and flight path angle Inertial results are displayed if inertial initial conditions are entered or if using the non rotating model Planet relative results are displayed if planet relative initial conditions are entered and a rotating model is being used 16 Initial Flight Path Angle deg Final Altitude km Final Velocity km s Final Flight Path Angle deg METAM 17 Initial Flight Path Angle deg Final Altitude km Final Velocity km s Final Flight Path Angle deg Ballute Cut Time sec sesion 18 Orbit Insertion deltaV m s Lower Periapsis deltaV m s of Raise Periapsis deltaV s Circularization deltaV m s Total Time days ii ete nsn ene 19 Orbit Insertion deltaV m s Lower Periapsis deltaV m s of Raise Periapsis deltaV s Circularization deltaV m s Total Time days ICT 20 o Simulation MUST be saved in order to use the View Previous Simulation function The View Previous Simulation function allows the user to reload previously run simulations e Export to Excel See Section 5 4 3 o Allows the user to
63. the menu at the top of the MATLAB Command Window Search for using plot editing mode under the Search tab Edt Go Web Window Help Help Navigator 5 gt 3 Product mer 8 O i sia Getting Started Graphics Using Plot Editing Mode Add to Favorites J Corteres index Search Damos Fawames Seer ch type Ful Taxt Getting Started manen Search tor Ling Plot Eli ode Using Plot Editing Mode Example printing AND MOT exporting The MATLAB figure window supports a point and click style editing MABE that you can use to customize the appearance of your graph The folloveing illustration shows figure window with plat editing MARE enabled and labels the main plol editing features Tite Section MATLAB Use these toolbar buttons to add text arrows and lines lo 0 graph Using PlotEdiling Made rar Click this button lo slart plot t 5 1 Editing Plots Graphics edit mode Using the Property Editor Graphics Adding Plots Statshes to Grapns Formatting Graphs Editing Test Anriolalions Formatting Graphs Use the Edit Insert and Tools ri Using the Tte Option on the inser Menu Formatting Graphs b odd objects or edil OSM 4G Using the Property Editor ta a Till Coman Ghani existing objects in the graph Steg har p Adde Tig Lotka Voltorra
64. through the planet s atmosphere until the desired apoapsis altitude is achieved All orbit decay simulations are performed using the inverse square gravity model and the non rotating equations of motion For information on how to run an Orbit Decay simulation see 4 2 5 4 1 3 View Previous Simulation The user is prompted to choose between previously saved simulations HyperPASS then loads the selected simulation and displays the appropriate Post Simulation GUI The user can then view or export the data Only simulations saved by selecting Save Simulation in the Post Simulation GUI will be available using View Previous Simulation See Section 5 3 42 How To Run Each Function The following sections describe how to run each function WA RNING Before selecting Continue in the Mission Setup GUI be sure to close any other GUIs e g Simulation Parameters Table Interpolated Atmosphere and Add Ballute by selecting Continue in those respective GUIs 4 2 1 Unguided Simulation Hypersonic Planetary Aeroassist Simulation System Choose a Function Continue Figure 4 1 HyperPASS GUI Unguided 29 1 Select Unguided Simulation in the HyperPASS GUI and press Continue The Mission Setup GUI will then appear Change Add Parameters Figure 4 2 Mission Setup GUI Unguided 2 Select the desired Planet in the Mission Setup GUI See Section 8 2 3 Select the desired Atmosphere
65. tion is performed using the non rotating planet atmosphere Press the Change Add Parameters Pushbutton in the Mission Setup GUI to open the Simulation Parameters GUI and view or change the simulation parameters Save any changes if it is desired to save the parameter set for future simulations and press Continue to return to the Mission Setup GUI Simulation parameters are given below Figure 4 18 Simulation Parameters GUI Aerobraking e VEHICLE PARAMETERS o m o A o Rn o Mstag Nstag o C o CD e INITIAL CONDITIONS 2 parameter set options st 1 Periapsis Parameter Set no delta V maneuvers performed prior to aerobraking 46 1 Periapsis Altitude Velocity at 1 Periapsis V infinity Parameter Set orbit insertion delta V and lower periapsis delta V maneuvers performed prior to aerobraking V infinity Initial Periapsis Altitude Initial Semi major Axis Initial Orbit Period 1 Aerobraking Periapsis Altitude NOTE The initial apoapsis altitude is automatically recalculated and displayed if initial conditions are changed The initial semi major axis and the initial orbit period are calculated simultaneously so if either value is changed the other is calculated and displayed AEROBRAKING PARAMETERS O Desired Apoapsis Altitude Free Molecular Heating Limit Raise Periapsis Altitude Simulation Altitude Perform Orbit Circularization optional
66. tree erede ea ts 29 11 421 Unguided SIMULATION Sa Su eee 29 NI ERE ETE 37 p CETT EE ERE 41 CT TR 45 P 49 5 OUTPUT OPTIONS 52 31 52 32 EDITING PLOTS u uuu 52 52 aa 53 53 aa 54 54 5 9 EXPORT TO DEXT eret eee tete e eta 55 55 Poe xL 55 mM INE NE 55 Os EXAMPLES T P I PD 56 6 1 EXAMPLE 1 UNGUIDED 8 56 56 57 iia 57 tai diia 57 aaa ERE 58 T GLOSSARY 59 8 APPENDICES a asssssscssqasqsqassasssqssaasssss ascasacsassassssusqaqassqasasaassasasssasasassaqasssa sasa ssssssssasssssssasasesssessesssassssssssesse 62 Sal Y o 62 82 PLANETARY INFORMATION 63 p 63 NOTE VEHICLE amp BALLUTE MODELS ARE ONLY AVAILABLE IN FULL VERSION OF HYPERPASS 63 9n 63 64 nC 64
67. ure simulations When Sphere Ballute is chosen the ballute mass is calculated from user entered sphere radius and material areal density values For an Unguided simulation the AOA and CL are set to zero and the CD varies during the simulation as a function of both Knudsen Number and Mach Number When Sphere Ballute is chosen for a Guided Ballute Aerocapture simulation the AOA and CL are set to zero and the CD is set to 0 9 1 e for Guided Ballute simulations the CD is constant not a function of Kn or Mach 64 8 3 6 Torus vehicle or ballute Torus is a vehicle model available during Unguided simulations only When Torus is chosen the AOA and CL are set to zero and the CD varies during the simulation as a function of Knudsen Number Ref Riabov V V Numerical Study of Hypersonic Rarefied Gas Flows About a Torus AIAA Paper 98 0778 1998 Torus is also a ballute model available during Unguided and Guided Ballute Aerocapture simulations When Torus Ballute is chosen the ballute mass is calculated from user entered torus dimensions and material areal density values For an Unguided simulation the AOA and CL are set to zero and the CD varies during the simulation as a function of Knudsen Number When Sphere Ballute is chosen for a Guided Ballute Aerocapture simulation the AOA and CL are set to zero and the CD is set to 1 37 i e for Guided Ballute simulations the CD is constant not a function of Kn or Mach 65 84 Atmosphere Mo
68. uski 1521 data points Ref Longuski James M Puig Suari Jordi Mechalas M Aerobraking Tethers for the Exploration of the Solar System Acta Astronautica Vol 35 No 23 pp 205 214 1995 Current Exponential Atmosphere Profile Density vs Altitude 10 Density kgm 100 200 300 400 500 600 700 800 800 Altitude wie Current Exponential Atmosphere Profile Temperature vs Altitude 150 100 Temperature K 50 x 2 100 200 300 400 500 600 700 800 900 Altitude km Figure 8 13 Titan_Longuski Atmosphere 76 8 4 7 Uranus 8 4 7 1 Uranus Longuski 21 data points Ref Longuski James M Puig Suari Jordi Mechalas M Aerobraking Tethers for the Exploration of the Solar System Acta Astronautica Vol 35 No 23 pp 205 214 1995 The atmosphere temperature profile used for the Uranus Longuski atmosphere model is Ref Lunine J I The Atmospheres of Uranus and Neptune Annu Rev Astron Astrophys No 31 pp 217 263 1993 Current Exponential Atmosphere Profile Density vs Altitude o Density kgm o D e 200 4001 600 800 1000 1200 1400 1600 1800 Altitude km Current Exponential Atmosphere Profile Temperature vs Altitude e 400 300 200 Temperature K 100 0 200 400 600 800 1000 1201 1400 1600 1800 Altitude Figure 8 14 Uranus_Longuski Atmosphere 71 8 4 8 Neptune The atm

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