SDSA – USERS MANUAL
Contents
1. A SDSA User manual 1 SDSA SOFTWARE MAIN FUNCTIONALITIES SDSA MODULES oocnccccccnononcccocnnnoncconccconaccnnoconnss 2 SSA USLE Sate As INTER DAL iria E PECES AS eienineieeannn 2 2A IA PTAC MON TERRA ELEMENTS ias 3 Fe MENUS DUKE REVES sncincnsniania ii A 3 LA E RRA 4 EA MA A A A A IA 5 DA E A a ina 5 ra a E gee ee aoe ee eee RT ERT eee ee eee ae ee eee ee eee ee ee eee en eet tt ore reer TeTeT 6 RE E re SN aa l E AA OTIS AAA RA RA 8 3 1 6 Propulsion system options internal window A e ti 9 EPA A E 9 ERE a AAEN IE EEE A A 10 e AAA A teen cst tamta nnn ab ateeetaned id A ES AN A A AA A een 12 Bi SHOW E AAA PA aceite eee ee A TETA 14 A AE EEEE EEEE ENAERE e ak 15 AA sce cece hace pracnpnn ei oaraetent oveaiesianie tesctatecetctiantaansrietieite dearie viene dhadadnledastanseiney aidan eatea ete ss ntaaasededaapiasnaaeees i AA A A AEE E 20 A E shc ao ceca sien get coat e E a a eee ees s SD OCT COLS UA rd ie PA DE POS ARAS a a a a a a a a a 22 O IN aia cda as Bed SE E a E O ii naiaiatialucasiodnaceialauels 23 O A O rabia 24 EEES AMM E E AEA AE EAEE E EAA EAEE AE A EEEE A EAEE AE 26 SPEER MAMAS 26 AA A a a a ene ne oe esa a7 Aa 28 O rr Rs 29 E a A een eee 30 a AAA A E E 30 A MAA A A 31 IA AO IAS ara E 31 EEN A aa SOGI EG IIS a a Ra a E aa is 32 A U T a PEE E T E TE I E E E I E A IAIA ado E EE S EE AET TTT 32 AS eer eter ee eT meter Meret A ey ret teeter Tere 34 AMPL MENTA TIOS Beira eee neers ii rm nryry ner rT ner Mere2. Compute TAS km B17 2 29 4 as kmh 197 2 607 7 0 85 Active Aero data a sie Flight envelope Compute envelope Altitude step m 1000 N Refining ceiling Theoretical ceiling m 1137105 Selectvariable to show Mach number y Altitude rm Envelope H Ma 0 9 Mach y axis grid Y axis grid Default Data from C Program Files SDSA data Ranger Fig 3 39 SDSA Performance submenu envelope functional window Useful information about Envelope mode features e The envelope results can be presented in terms of altitude and Mach number or speeds TAS IAS amp EAS User can choose the desired X variable from drop down menu e Use Refine ceiling feature to refine the envelope results SDSA Help System 3 5 2 Range and Endurance SimSAC SDSA Simulation and Dynamic Stability Analysis 3 si lol xj Aircraft Simulation Stability FCS Performance Options Output Help 1st Range versus airspeed and altitude Active Aero data 2nd Both Xx variable Mach w kmnh y Y variable Range km y Method Y const simpl Y Altitude range H min m 1000 H max m 3000 H step m 500 Airspeed range min mis 1100 0 Wimax m s 200 0 Y step mis 1 airspeed range from envelope Compute Engine type TURBO JET Specific fuel consumption SFC Use typical SFC M Current SFC 0 50 kg dalh Typic
3. E Seek alelelelele omer SOS 000 0 e 0 elotalateteTetotota oleta oefe tetetete atelaloetetetetete A eL hea at Ha Up Od a lle ES aat deis TET result exceeds ore slelelelc ata fe ateta te a 2222220 necessary thrust qeteteletejeleje ejejojojo e ejejeje le ARA 0J07070 0 0 e c 0 0 0 0 0 0 e e ele i 20 0jc OR RR sfetaletelstelcTolelelctcteletete re islas gt ctotetstotats etetctatatetetst Shad ee HAS OE O aa ers dec des air ds i i 1 Save options TAS rs Envelope var Tas Erts al Maxis grid Y axis grid gt Default Fig 3 34 Internal SDSA LQR window FCS matrices FCS envelope e LOR is the initial method of choice due to its simplicity good robustness ability to delivering desirable stability and performance properties and wide spreading in aerospace community Useful information about create FCS features e Before creating FCS matrices or computing single FCS point user must enter the necessary input data Altitude and Airspeed range with adequate iteration steps see Fig 3 35 Additionally user can setup O amp R vectors for more detailed information see D5 3 1 2 SDSA Help System One airspeed altitude case Altitude range H minim lo H max mi 20000 H step m 500 Altitude m 0 Airspeed range Vmin m s 50 Vmax mis 600 W step mis fi 0 Airspeed m s 150 0 FS file name CE icygwinMhomefgrab simSAC sdsa_apprdataMIbfcs FosMatri
4. Open data from TXT files Ctrl O Open XML data file Shift Ctrl 0 Save data as TXT files Save data as XML file Aerodynamic data F2 ero data type gt Data interpolation options Aero data report Shift F2 Check data options Ctrl F 2 Propulsion data F3 Grid data gt aircraft submenu Exit Fig 3 1 SDSA Aircraft submenu Short cut key mae Description combination P Command Open data from TXT files click to select path to input TXT data files standard Open data from TXT files Ctrl 0 external Windows folder selection window is being displayed see Fig 3 2 click to select the input XML single data file standard D Shift Ctrl O external Windows file selection window is being file n lan Ges Ma 23 click to save data path to input TXT data files standard external Windows save folder location window is being displayed see Fig 3 2 Click to save the input XML single data file standard external Window save file window is being displayed see Fig 3 4 Aerodynamic click to open the internal SDSA aerodynamic input data F2 data review window see Fig 3 5 Save data as TXT files Save data as XML file When the input aerodynamic data is stored in multidimensional array where all coefficients are stored as function of state vector user can select between e Multivariable tables e Stabili
5. Recording functional window see Fig 3 48 click to define and save the capture output JPEG JPEG parameters picture parameters see Fig 3 49 Save options Ctrl S click to save the SDSA options settings click to clean the main application workspace window Clear window F12 and display the start up screen Table 07 SDSA Options submenu description SDSA Help System 3 6 1 Files location Executable files directory Cra FE Browse Plain text data files directory C SimSAC sdsa_app data SDMW Browse XML data files directory Cs Browse Outputfiles directory C SimSAC sdsa_app out Base O K Apply Save Cancel Fig 3 46 SDSA Options submenu SDSA folders selection for files location window 3 6 2 Test flight parameters Test flight options Standard test type Disturbance type Initial state disturbances Dutch roll v standard test v Testturned ON Angle of attack deg lo Control type Control surface selection Sideslip angle dea 30 0 step function Elevator Initial time s fo Airspeed lo Ailerones time of step s fo roll rate deg s lo JL single step Rudder deflection value deg fo pitch rate deg s lo yaw rate dea s lo J cau step roll angle deg lo OK Apply Cancel pitch anale idegio Fig 3 47 SDSA Options submenu SDSA test flight parameters setup window In test flight parameters windo
6. enable localzlib enable Xft Native file chooser can be compiled directly using make command The header files should be next copied into the include FLTK directory usually usr local include FL and main object should be copied into the FLTK library directory usually usr local lib 5 Integration The integration with CEASIOM environment is done by Matlab interface The method of integration is presented on figure below lt CEASIOM gt code gt lt call_ sdsa m gt code call_sdsa data rdir mode prepare data structure reads data structure converts input data to the plain text change directory to the SDSA files which are used by SDSA program main directory sdsadir program puts these files to the appropriate directories runs SDSA exe with 3 parameters call function information call_sdsa data rdir mode data directory run mode changes directory to the rdir directory some CASIOM code here Fig 5 2 The scheme of SDSA CEASIOM integration SDSA Help System References 1 B H Cook Flight Dynamics Principles Butterworth Heinemann Cranfield 1997 2 F A DuL T GOETZENDORF GRABOWSKI Implementation of the basic Linear Quadratic Gaussian control within the Flight Control System SimSAC official deliverable D5 3 1 3 B Erxix Dynamics of Flight Stability and Control John Wiley amp Sons Inc New York 1982 4 T GorerzeNDORF GrRABOWsSKI Modelling of the aircraft motion
7. 00 161 01 161 01 tt ee pitch rate 89 33 89 33 0 00 00 00 0 00 0 00 yaw rate 0 00 0 00 0 00 00 95 87 95 180 00 theta 23 10 23 10 117 78 78 00 0 00 0 00 3 phi 0 00 0 00 0 00 00 50 62 50 180 00 4s Fig 3 24 SDSA Internal SDSA eigenvalues window show results output window e User can select between the Stability criteria Stability characteristics or Trim results to being displayed by clicking the correct push button see internal SDSA eigenvalues window right panel see figure below SDSA Help System Eile Edit Class I Small light airplanes such as Light utility Primary trainer Light observation Stability Criteria Stability Characteristics Trim Results Class 11 Medium weight low to medius maneuverability airplanes such as Heavy utility search and rescue Light or medium transport cargo tanker Barly warning electronic counterneasures airborne command control or communications relay Antisubmar ine Assault transport Reconnaissance Tactical bomber Heavy attack Trainer for Class 11 Class Class Class Il m cass ly y Class III Class IY Motion Phugoid Class III Large heavy low to medium maneuverability airplanes such as Heavy transport cargo tanker Heavy bomber Patrol early warning electronic countermeasures airborne command control or communications relay Trainer for Class 111 Short Period rra nr
8. 3 33 SDSA Parameters of SAS systems with actuators setup window SDSA Help System 3 4 4 Linear Quadratic Regulator In Flight Control System mode user can create FCS Matrices FCS envelope for given altitude and airspeed range case or for one computation point Currently FCS 1s based on the classical Linear Quadratic Regulator LQR approach 2 a Gann SOSA Simulation and Dynan Stability Anahreis Aircraft Simulation Stability FCS Preformance Options Help One airspeedalitude case Amude range H min imi o Hmaximi 20000 H step mj 500 Atitude Imi fo Airspeed range Vmin ms 50 Vmax mis 600 v step mis lio Airspeed m s 50 0 I Show results i Compute one point Show results 2 vector R vector i i i aki RH titititittittsstirtistrtrttrtisestttscsas sss a 4 i Z oa i Cari i ae de E EA CA y 52283 E tied III TAE RRA E RRR arar fi arar fi Offs od cod bocnacic S 0000 0 ccd AAASAS dada cada ASAE orar Ri ft AAA SLAC ala a aa A 444 SOOOG OOOO COC SO ShS 55654054658 60644 ete ooo closes cletstoo tet ttt et eee ee eee orar fi 868 oe 58 0 56 6 87 4565565600066 dd WWW fetetototetetetats SOLA ADORA Ads dh dl Ae hs aps fr Rho ft Ade beers forsee fMololotciclotetelsto a fi tie Se sfofalctote sists ari h pielelelalelolelels alela s z aa claejoja elo palate cla pe
9. PP i Altitude m 1000 1000 Ae E ESE i a E ee Ji S i A i e PEETS f e at see eeni y Se E Roll angles deg 030 032 034 036 038 040 042 044 046 048 0 50 0 52 0 54 0 56 0 58 Mach Y 4 X axis grid Y axis grid we Legend Default Data from C cyawin homeftorab SimSAC sdsa_app data Ranger Fig 3 42 SDSA Performance submenu manoeuvres functional window 1st 2nd Both Angle of Attack de Y Mach number TAS km h Radius m time to half turn Normal acceleration Gz Angular rate total rad s gt l roll rate rad s pitch rate rad s yaw rate rad s Active Aero data EAS kmih IAS kmh X variable Y variable Minimum radius Altitude range H min m lO Roll angle deg H max m 5000 Pitch angle deg 11000 Angle of Attack deg hl Sideslip angle deg Airspeed range Elevator deflection deg Vmin m s 100 0 Aileron deflection deg Ymax m s 200 0 Rudder deg Y step m s 10 thrust excess N Required thrust N Gz limit 4 maa gt compute minimum radius turn Fixed roll angle turn show on graph minimum radius turn results Airspeed range defined above Altitude m Roll ang input selection fields gt compute fixed roll angle turn A conose show on graph fixed roll angle turn resu
10. m s 25 SAS Pach Rol au Show results One airspeed altitude case E 7 g amp 1st ompute one poin Airspeed mis 100 0 _ Compute one point p a Ailerons deflection for roll rate test deg 30 0 jata 2nd Altitude m 1000 Both Show results Stability Criteria Stability Characteristics Angle of Attack Trim Results Trim Results Thrust Angle of Attack saneenanuensssansnennsnsnsnnansensnensasensensnenssnsssensosansnssnensssnie t Elevator Deflection Path Angle Sideslip angle Rudder Deflection Aileron Deflection le he de e La niu wu Legend Xx grid Y grid Mach El Select X variable Background Mach y v White Data from C Users Lucas SDSA dataifl 6 Fig 3 22 SDSA Internal SDSA eigenvalues window trim results mode The SDSA eigenvalues mode is fully operational when aircraft input data was loaded Before start of the stability analysis user must enter the necessary input data Altitude and Airspeed range with adequate iteration steps see Fig 3 23 LOR Closed Loop Pilotin the Loop Fitch Roll Yaw SAS Pitch Roll Yaw st gt 2nd Bath H min m 1000 H max m 000 H step m 1000 W step mis 25 Altitude range Airspeed range Yimin m s 100 max ms 250 0 One airspeedaltitude case Airspeed ms 1100 0 Ajlerans deflection for roll rate test deg 30 0 Active Aero data Altitude
11. rr p 000 Fig 3 23 SDSA Internal SDSA eigenvalues window input data panel Additionally user can turn on the LOR closed loop or Pilot in the loop and SAS computations User can also activate the desired Aero data 1 2 or both which will be used to compute the trim and stability results This feature is active only when the loaded computational model has got 2 different aerodynamic input data sets The SDSA offers two computation modes Compute one point for single point stability analysis amp Start stability analysis for speed and altitude range multipoint analysis depending on input data To start computations click one of two push buttons The SDSA prompts Stability analysis finished when stability computations are done and the Show results buttons turn active SDSA Help System e When the stability computations are ended user can watch the stability results on main internal SDSA eigenvalues window main graph panel see Fig 3 20 Fig 3 21 or send them to the external text file Show results see Fig 3 24 File Edit Eigenvalues found with success No Re Im Mode Period Ti 2 UFreq 07486 26 83809 2 short period 0 234 063 29 0334 11 07486 26 83809 2 short period 0 234 063 29 0334 06326 0 12062 1 phugoid 52 092 957 0 1362 06326 0 12062 1 phugoid 092 10 957 0 1362 09408 15 65896 3 Dutch roll 201 331 15 7984 09408 15 65896 3 Dutch roll 401 331 15 7984 67081 0 000
12. Aero data set if there is more than one available e The check data result summary external window will appear when user activates aerodynamic data review feature for the first time see Fig 3 6 and output report window see Fig 3 7 bd Check data result O errors O warnings 2 informations Fig 3 6 SDSA Check data result external window SDSA Simulation and Dynamic Stability Analysis User Manual 6 SDSA Help System Data analysis report Information s 2 Marningq s O Errorfsi O Type Message Information Rolling moment derivative with respect to sideslip angle out of range Typical values are between 0 5000 and 0 5000 1 rad Information Yawing moment derivative with respect to roll rate out of range Typical values are between 0 5000 and 0 5000 1 rad Fig 3 7 SDSA Output aerodynamic data report external window e User can access the aerodynamic data report window see Fig 3 7 by clicking the Aero data report button from Aircraft submenu 3 1 4 Check data options Dermatmes with respect to the airplane s state min Side force derivative with respectto sideslip angle irad 2 00 Rolling moment derivative with respectto sideslip angle irad 0 50 Yawing moment derivative with respectto sideslip angle rad b Lift force derivative with respect to pitch rate 1 rad 5 00 Pitching moment derivative with respectto pitch rate rad 15 00 Lift force derivati
13. every 10 data point Average equidistant zeros fitting Average characteristics of V vs R T_mean 0 394 s Phase_mean 93 45 deg Lyap_mean 2 143857 1 Fig 3 28 SDSA External SDSA time history window Brief information about time history features e The first time user starts time history analysis application prompts for data flight history input file the default data path is set to flight recording data path see chapter 3 6 3 e When input data is loaded after a few seconds depends on computer the main time history window screen will change and the analysis results will be displayed e Important After reading the input data file user can access the variable time history options or use the Time history Refining function to refine results For more detailed information see Time history Software brief user s manual SDSA Help System 3 3 3 Static margins Static margins mode is used to compute the static and controllability margins with stick fixed and free for one more aerodynamic input data sets SimSAC SDSA Simulation and Dynamic Stability Analysis q z Oj x Aircraft Simulation Stability FCS Performance Options Output Help Results for C Program Files SDSAfdatait1 6 1 st Angle of attack range lo 5 0 Mach number range lo 1 0 5 Select x variable Mach number y Active Aero data 2nd Both Graphs selection static margin
14. location file AA zx Save in XML e sE My Recent Documents Desktop gt My Documents e gr My Computer Aa lt NET File name Places Save as type rr Files y Cancel Le Fig 3 4 SDSA XML single input data save file external window SDSA Simulation and Dynamic Stability Analysis User Manual 5 SDSA Help System 3 1 3 Aerodynamic data review SimSAC SDSA Simulation and Dynamic Stability Analysis 0 x Aircraft Simulation Stability FCS Performance Options Output Help Review data from C Program Files SDSA data fl 6 Select x variable Select Y variable e 1st Xvarrange 0 1 2 15 an le of Attack tw Mac Aive Aar data ene g Both Y var range 5 0 20 0 Ma 0 20 Ma 0 50 Ma 0 80 Ma 1 10 Ma 1 40 Ma 1 70 SS ee ee ee ee TTIE TT Angle ar Attack deg y x axis grid Y axis grid La Legend Default Data from C Program Files SDSA data f1 6 Simulation status Fig 3 5 SDSA Review aerodynamic input data internal SDSA window Information about SDSA aerodynamic input data review features e User can choose from the selection list the desired input data to be shown on graph versus selected X and Y variable the type of variable depends on input data e The Xand Y variable range can be defined by filing the appropriate input fields e User can also activate the desired
15. more than one aerodynamic data set is available Simulation commands Command Status Idle Idle Ready Run Run stop stop Pause Pause Fig 3 17 SDSA Simulation commands panel internal simulation SDSA window The Simulation commands panel is divided into two button column groups Command and Status button group Each Status button indicates 1f the Command button is ready to take action When the simulation data is fully loaded both JDLE buttons turn dark grey are pressed Only now user can activate the simulation by clicking the Start button When the status Ready button turns dark grey is pressed user can run the simulation by pressing Run button To pause or stop simulation click the Pause or Stop button from Command button column SDSA Help System 3 2 4 Show results graphs SDSA show results graphs mode enables quick and easy simulation results review 1 SimSAC SDSA Simulation and Dynamic Stability Analysis Aircraft Simulation Stability FCS Preformance Options Help Last simulation Flight file name C SimSAC sdsa_app data outMight bd Browse Show graph Number of variables 2 Al lt coordinate Time s ted Y coordinates 1 v velocity component m s y 2 Heading deal y 00 02 04 06 08 10 12 14 16 8 20 22 24 268 28 Time s y el X axis grid l Y axis grid Legend Default ad Flight OK Fig 3 18 S
16. stick fixed static margin stick free a a ed Ds o e conan mentee meme sat ea anal elon oe Alpha Alpha 0 5 l controlability margin stick fixed controlability margin stick free Alpha 1 0 Alpha 1 5 AA AAA AAA AAA AAA A AA S Alpha 20 Average values Alpha 2 5 p Angle of attack range lo 5 0 Alpha 3 5 Mach number range 0 1 lo 5 i Alpha 4 0 e A AS A A e a o mama LE Static margins of MAC Aero data 1st 2nd stick fixed 6 09 0 00 Alpha stick free 0 00 0 00 j Controlability margins of MAC Aero data 1st 2nd stick fixed 6 59 O 00 stickfree 9 00 0 00 Aero data sets 1st 1 st set 20 2 Mach number y e X axis grid Y axis grid Legend Default Data from C Program Files SDSA data f 6 Fig 3 29 SDSA Internal SDSA static margins window Brief information about static margins features e Before computing the static margins user must load the input data e When input data is loaded user can perform margins computations in respect to Angle of attack range and Mach number range e User can also activate the desired Aero data set for the static margins computations if there is more than one aerodynamic data set defined in the input data e The obtained results are presented on 2D plot Static margins can be displayed in function of Mach number or_Angle
17. 00 4 roll 000 055 12 6708 03781 0 00000 5 spiral 000 18 334 0 0378 An UN gt WH vectors normed to unit 0 009 0 007 0 009 1 000 0 000 000 0 000 0 000 0 000 0 000 0 000 0 000 000 0 000 0 001 999 0 001 0 010 0 000 010 0 000 0 000 000 0 000 0 000 0 000 000 0 000 0 265 003 0 265 0 002 0 000 002 0 000 0 000 000 0 000 0 000 0 000 000 0 000 0 004 008 0 004 0 006 0 012 006 0 012 0 000 0 000 0 000 0 000 0 000 000 0 000 000 0 000 997 0 997 000 0 0 000 085 0 085 000 0 000 006 0 006 000 0 000 003 0 003 1 DODOO0OOOo0OOoOOo0O vectors physically normed short phugoid phugoid Dutch Dutch roll spiral 0107 0 9745 0 9745 0000 0000 0 0000 0 0000 0000 0000 0000 6473 6473 0 0274 0708 9185 0100 0100 0000 0000 0 0000 0000 0000 0000 0000 1277 1277 0 9258 0559 0615 0000 0000 0000 0000 0 0000 0000 0000 0000 0000 2208 2208 0 0096 1386 0093 0150 0150 0000 0000 0 0000 0000 0000 0000 0000 0041 0041 0 0372 0 7348 roll rate pitch rate yaw rate theta phi oooo0o0o0 ooooo o oooo 0o 0o 0oo OSOO0OOOo0O0OoDOo O000Oo0Oo0O Phase shift angles with respect to the most significant variable short short phugoid phugoid Dutch Dutch roll spiral u 52 46 52 46 ee0 aerr una 0 00 0 00 0 00 y 0 00 0 00 0 00 0 00 terra aereas 0 00 y weeeeee tettette 179 86 179 86 0 00 0 00 0 00 roll rate 0 00 0 00 0 00
18. 1 2248 Global wind Control Wind course deg Speed of sound mis 340 3 o dE Wind speed horiz 1 miz WIND focal coordiantes 0 Wind speed vert m s 0 Switches GROUND EFFECT Runway condition WET ICE Wind Shear Turbulence IT LIGHT MEDIUM EXTREME Wind Shear parameters Coordinates of the windshear root Longitude Latitude DEG i 4 0 I me E DEG Hi 4 0 MIN ed 0 f MIN 0 SEC ll 0 I SEC H 0 HDR pi 0 La W HDR 0 Altitude ASL of WS bottom rr o A m Height of ws mm 0 i Airspeed in the root m s a E Diameter m o AAA Ok Apply Cancel Fig 3 13 SDSA external environment window Information about SDSA environment features e User can setup environment features like initial atmosphere parameters air temperature air pressure wind gusts and global wind parameters speed etc runway conditions and turbulence parameters The environment parameters will be used in aircraft simulation process The future version of SDSA will have the Dryden turbulence model implemented SDSA Help System 3 2 3 Run simulation SDSA simulation mode enables to perform aircraft simulation additionally 1t enables to observe the aircraft behaviour and flight data during the simulation process Information about SDSA simulation features 2 SimSAC SDSA Simulation and Dynamic Stability Analysis iol xj Airc
19. 8
20. DSA Internal SDSA show results graphs window Information about SDSA show results graphs features e User can setup in show results window number and type of variables to display on graph load saved simulation results and show them on graph click Browse button to point the results destination folder show last simulation results Last simulation button must be pressed this function 1s only active after the present simulation was finished e To exit the results window click Close button SDSA Help System 3 3 Stability submenu s SimSAC SDSA Simulation and Dynamic Stability Aircraft Simulation FCS Performance Optior F7 Eigenvalues Time history Static margins F8 stability submenu Fig 3 19 SDSA Stability submenu Short cut key combination click to open internal SDSA eigenvalues stability Eigenvalues F7 functional window see Fig 3 20 Fig 3 21 Tine A click to open external SDSA time history application E I is window see Fig 3 28 click to open internal SDSA static margins application window see Fig 3 29 Command Description Static margins F8 Table 04 SDSA Stability submenu description 3 3 1 Eigenvalues The SDSA eigenvalues mode enables user to perform stability and trim and stability linear computations for input aircraft data The GUI of SDSA eigenvalues mode has been prepared to meet the us
21. SDSA stability results to user XML file selected XML file Save envelope as XML _ click to save only SDSA envelope results to user file selected XML file Save turn analysis as XML _ click to save only SDSA turn analysis results to user file selected XML file Save range and endurance _ i click to save only SDSA range and endurance results to as XML file user selected XML file Save all results as TXT click to save all SDSA results to user selected TXT file file Save stability results as _ Click to save only SDSA stability results to user TXT file selected TXT file Save envelope as TXT click to save only SDSA envelope results to user file selected TXT file Save turn analysis as TXT Click to save only SDSA turn analysis results to user file selected TXT file Save range and endurance _ Click to save only SDSA range and endurance results to as TXT file user selected TXT file Click to capture the current active graph window with Save current picture as Shift Ctrl if results to JPEG picture Table 08 SDSA Output submenu description 1st data set Iw select results for data setto save T stability M envelope Y turn l range 2nd data set M select results for data set to save stability M envelope turn M range E Apply Cancel Fig 3 51 SDSA Select results to save window SDSA Help System In Select results to save window user c
22. al SFC 0 50 kg daNh Masses kg Max TO mass 3855 Fuel mass 578 25 4a X axis grid Y axis grid ES Legend Fuel reserve 9 10 Data from CProgram Files SDSA data Ranger Fig 3 40 SDSA Performance submenu range and endurance functional window In Range and Endurance SDSA performance feature user can perform range or endurance analysis for given altitude airspeed range engine type etc To start analysis user must click Compute button Results are presented in the graph window Graph X and Y variable can be selected from the dropdown lists see Fig 3 41 Y 0 ist kmh Active Aero data 2nd knots Xvariable macn_x kmn z Y variable Endurance m 3 Method Range km Altitude range Endurance h H min m 1000 H max m 3000 CL const H step m 500 gt Y const simpl HO Y const Airspeed range Yimin m s 100 0 200 0 Y step m s 1 Ymax m s l airspeed range from envelope Compute gt input selection fields gt compute button gt TURBO PROP Engine type TURBO JET _ Specific fuel consumption SFC TURBO JET Use typical SFC F PISTON PROP Current SFC 0 50 kg daNh TURBO FAN Typical SFC 10 50 kg daNh Masses kg Max TO mass 3855 Fuel mass Fuel reserve 10 Fig 3 41 SDSA Range and Endurance input fields and
23. an be observed in detail by clicking the More results button in Results of simulation panel see Fig 3 14 SDSA Help System During simulation user can access the Control panel and change nitial conditions see Fig 3 16 Control JE E Throttle LOR ws r initial conditions Stick roll 655 OM State ud NM Altitude AGL m 6000 CCA Airspeed mis 250 Yaw Yaw DU S KA Wore initwar Pedals More control Fig 3 16 SDSA Control and Initial conditions panel internal simulation SDSA window More control and More init var button gives access to the Setup and Environment external windows see Fig 3 13 LOR ON button enables the Linear Quadratic Regulator see chapter 3 4 4 during the simulation process LQR works only when the FCS Flight Control System matrices computation was made see chapter 3 4 4 for more detailed information User can also turn on the Pilot Pilot Control Model see chapter 3 4 amp SAS Stability Argumentation System see chapter 3 4 by clicking one of three control channels Pitch Roll amp Yaw The State control button turns yellow when the flight parameters are meeting the desired boundaries User can control the simulation process by clicking the adequate button in Simulation commands panel see Fig 3 17 User can also activate the desired Aero data 1 or 2 set which will be used during the simulation process only when
24. an choose which results to save It is possible to save results from two aero data sets to a single file It is very useful feature when one must make a results comparison 3 8 Help submenu s SIMSAC SDSA Simulation and Dynamic Stability Analysis Aircraft Simulation Stability FCS Performance Options Output Baci Help system gt PDF reader selection gt About help submenu Fig 3 52 SDSA Help submenu Short cut key eae Description combination P Command Help system is a collection of PDF help files about SDSA application see Fig 3 53Fig 3 55 1 General help menu press F1 key en 2 SDSA User manual ES 3 Theoretical basics 4 Main definitions 5 Data files description 6 Data analysis messages 7 Output files description Here user can choose PDF reading software see Fig 3 54 1 No PDF application 2 System default application ENE reader 3 User selected selection SDSA user must point the path see Fig 3 55 to the PDF reader PDF Reader submenu when the User selected option 1s active Sie p click to display the information about the SDSA team see B d Nie znaleziono r d a odwo ania Table 09 SDSA Help submenu description Help systern wa General Help Menu F 1 FOF reader selection P SOSA User manual About Theoretical basics Main definitions Data files description Data analysis messages Output files descr
25. ation options Interpolation options q Extrapolation Flag Pohmomial degree Airspeed W Altitude M Angle of Attack M Sideslip angle M Roll rate Pitch rate Yaw rate Elevator deflection Aleron deflection Rudder deflection TEEPE eee elu Other control deflection Aero data set 1st 2nd Fig 3 9 SDSA Interpolation options external window Information about SDSA interpolation options features e n some cases where input data is poor user can extrapolate the desired parameters e SDSA enables user to choose the data type to be extrapolated by selecting the proper Extrapolation flag and enter Polynomial degree of the extrapolation method e User can also choose the aero date set to be extrapolated 1 _or 2 e The extrapolation is not valid for the aerodynamic derivatives input data for more information see SDSA Input data file structure manual e The interpolation doesn t depend on the aero input data type TXT or XML SDSA Help System 3 1 6 Propulsion system options internal window SimSAC SDSA Simulation and Dynamic Stability Analysis E 0 x Aircraft Simulation Stability FCS Performance Options Output Help Propulsion configuration file Propulsion data cyProgram FilesiSDSA dataifl 6 power cfa Load Save as NO propulsion External data Defined above Thrust file Engines C Program Files SDSAdatalf1 6 thru
26. ayed Useful information e The main application workspace window changes when the user accesses the SDSA modules e Some of the enclosed SDSA modules are being displayed in external stand alone windows e To clean the main application workspace window and display the start up screen go to application menu bar options clear window or press F12 key e Press ESC key on keyboard to kill SDSA application 2 2 SDSA application GUI interface elements GUI interacts with user through several interface elements various push buttons slide rulers radio buttons text fields etc The essential examples with short description are shown on the next page DK SDSA standard functional push button example Air temperature 15 00 SDSA data input fields white background Air temperature C 15 00 SDSA data output fields grey background 5000 k SDSA slider Wind Shear O SDSA radio button Table 01 SDSA GUI elements examples Most of interface elements adapt to the SDSA window resolution 3 SDSA menus quick review The SDSA menu bar is divided into several submenus Each submenu includes button link to the corresponding SDSA application feature SDSA Simulation and Dynamic Stability Analysis User Manual 3 SDSA Help System 3 1 Aircraft submenu SimSAC SDSA Simulation and Dynamic Stability Analysis ene simulation Stability FCS Performance Options Output Help
27. c Stability Analysis Aircraft Simulation Stability FCS Performance Options Output Help Altitude range H min m 1000 H max m 5000 H step m 1000 LOR Closed Loop START stability analysis Pilotin the Loop Pitch Roll Yaw Airspeed range Vmin mis 100 ymax m s 250 0 step mis 25 SAS Pach Rol TE Show results One airspeed altitude case 1st Compute one point Airspeed m s 100 0 Ailerons deflection for roll rate test deg 30 0 Active Aero data 2nd Altitude m 1000 Both Show results Stability Phugoid Stability Criteria ngamped Nat Freq rad s and Damping Ratio E Stability Characteristics Trim Results Stability Characterstics Stability Phugoid Stability Short Period Stability Dutch Roll 71 2 Phugoid 71 2 Short Period T1 2 Dutch Roll T1 2 Roll T1 2 Spiral Period Phugoid Period Short Period Period Dutch Roll 200 300 400 X grid CAS knots Y grid Background Fitting go Select X variable HEC Write gt Default To data cas v E y Data from CUsers Lucas SDSA data f 6 Fig 3 21 SDSA Internal SDSA eigenvalues window stability characteristics mode SDSA Help System Altitude range H min m 1000 H max m 5000 H step m 1000 LAR Closed Loop START stability analysis Pilotin the Loop Pitch Roll Yaw Airspeed range Ymin mis 100 Ymax m s 250 0 Y step
28. ces out Browse Fig 3 35 Internal SDSA create FCS window input data panel e Computing the FCS matrices can take some time depending on the computer chosen airspeed and altitude range and steps Application prompts Envelope analysis finished when envelope computations are finished e User can Save FCS or load Browse FCS by clicking the adequate application button e The quality of envelope results computation needed to create FCS matrices are presented graphically see Fig 3 36 with use of colour marks 66666 Result exceeds necessary thrust 00000 00000 90009 Proper results Result exceeds critical angles of attack Fig 3 36 FCS matrices results colour marks description SDSA Help System 3 4 5 Read LQR Select FCS matrices file 2 x Look in out sE Fe My Recent Documents Desktop sy My Documents pr My Computer L My Network Places File name Files of type out Files r Cancel Fig 3 37 SDSA FCS submenu read LQR matrix load data window e User can read saved LOR Matrix data out file and use it in SDSA simulation mode see chapter 3 4 4 3 5 Performance submenu a SIMSAC SOSA Simulation and Dynamic Stability Analysis Aircraft Simulation Stability FCS Options Output Help Envelope Range and Endurance Manoeuvres External Performance Module perf
29. dropdown lists SDSA Help System 3 5 3 Manoeuvres In Manoeuvres SDSA performance feature user can Compute regular turn _ parameters for given altitude airspeed and roll angle Results are presented in output data fields and in the graph window To start selected analysis user must click Compute button Graph X and Y variable can be selected from the dropdown lists see Fig 3 43 SIMSAC SDSA Simulation and Dynamic Stability Analysis Aircraft Simulation Stability FCS Performance Options Output Help Regular turn parameters k 41st mae Radius m Gz Half turn time s Active Aero data 2nd O Both Airspeed TAS m s 0 0 0 00 50 Compute aerate so El p Exc oo Xvariable Mach number y Roll angle deg E 30 I 0 0 0 00 Required thrust too large Y variable Radius m y Minimum radius Radius m Constant roll angle regular turn Altitude range a ernnd PA o cats eats pa PRO i Phi 45 0 H max m 5000 diia H step m 1000 6000 4 ia a A ei ii sa ae dada Sada ad hi i ES E Airspeed range i i Vmin m s 100 0 5000 A A ARS Ds o due ts 5 Vmax m s 200 0 i A i i i i EE V step m s 10 EOS CNT ANO pea fj oot hope Gzlimit 4 3000 Pad Manages A AAA A Show Compute i pe w Es El Fixed roll angle turn 2000 de sn A A TE stamens prats ke ee eee wt Airspeed range defined above F
30. er requirements Due to its simplicity it is easy to use The trim and stability graph windows are arranged in groups Stability criteria Stability characteristics and Trim results to help user in navigating through the eigenvalues options SDSA Help System SimSAC SDSA Simulation and Dynamic Stability Analysis Aircraft Simulation Stability FCS Performance Options Output Help Altitude range H min m 1000 H max rm 5000 H step m 11000 LAR Closed Loop START stability analysis bs Pilotin the Loop Pitch Roll Yaw Airspeed range Ymin m s 100 Ymax m s 250 0 step m s 25 e e Show results SAS Pitch Roll Yaw One airspeed altitude case o 1st Compute one point Airspeed m s 1100 0 p Ailerons deflection for roll rate test deg 30 0 Active Aero data 2nd Altitude m 1000 Both Sh ow res ults Stability Criteria Stability Characteristics ICAO Recommended Phugoid Characteristics Phugoid Period s Trim Results H H H H H Motion Phugoid Short Period ATISFACTORY Anormal Dutch Roll on ACCEPTABLE Roll for emergency conditions Spiral Roll Spiral UNACCEPTABLE Stability Criteria Phugoid 0 04 0 06 ICAO y 2xzetax omega rad s Select x variable TAS Elms Background Fitting f Siec wi MAR _Defaut Tadaa a Data from C UsersiLucas SDSAsdataitl 6 SimSAC SDSA Simulation and Dynami
31. ick pedals sin correction shift 1 1 normalized In symmetrical case B 0 4 A max control surface deflection ff vo 4 a sin correction Data from C Users Lucas SDSA data Ranger Elevator parameters A 25 0 Idea B J0 deg T 0 05 lag time s 8 fo 20 sin correction Ailerons parameters deg deg T fo o5 lag time s S 0 20 sin correction A 25 0 B 0 Rudder parameters deg deg A 15 0 B 10 T 0 05 lag time s S fo sin correction Cancel Save options Fig 3 31 SDSA Basic FCS parameters setup window SDSA Help System 3 4 2 Pilot model SimSAC SDSA Simulation and Dynamic Stability Analysis Aircraft Simulation Stability FCS Performance Options Help Motoric parameters Pilot pitch control channel Td 0 05 delay time s tl o 1 00 lag time s Adaptive parameters K2 10 000 gain 1 Remnant parameters o 3 Ed frequency 1 s T2 E 00 lag time s cla 43 damping 1 s TA 0 40 lead time s w o 00 amplitude 1 Motoric parameters Pilot roll control channel Td 0 05 delay time s cl o 1 00 lag time s Adaptive parameters Remnant parameters K2 0 000 gain 1 10 3 2 frequency 1 s Y E 00 lag time s cla 43 damping 1 s 13 0 50 lead time s w 0 00 amplitude 1 Mo
32. iption Fig 3 53 SDSA Help system menu SDSA Help System Help system d JAM O No POF application System default application User selected FOF reader Fig 3 54 SDSA PDF reader selection menu Deafult PDF reader Selected PDF reader caPrograrn FilestAdobelAcrobat 7 DAcrobati4crobat exe Browse O K Apply Save Cancel Fig 3 55 SDSA PDF reader selection window SDSA Help System 4 Implementation SDSA was written in C and compiled using GNU C compiler The Makefiles were written in a way that allows compilation of sources under Linux and MS Windows under Cygwin environment as well Compilation under MS Visual Studio is probably possible without any changes but it hasn t been tested SDSA uses some mathematical routines library Alglib http AWwww alglib net all routines are licensed according to the 3 clause BSD Compilation requires also windows widgets library FLTK Fast Light Toolkit http www fltk org and Fl Native File Chooser widget http seriss com people erco fltk Fl_Native File Chooser Both are provided under the terms of the GNU Library Public License Version 2 with exceptions that allow for static linking To compile FLTK library the following configuration commands should be given Under Cygwin configure enable localjpeg enable localpng enable localzlib and under Linux configure enable localjpeg enable localpng
33. lts Fig 3 43 SDSA Manoeuvres input fields and dropdown lists SDSA Help System 3 5 4 External Performance Module EPM io x File Aero Power Performance Settings Output Help Characteristics Power plant Climb Operating envelope Range and Endurance Take off and Landing Settings CL Lift coefficient H 0 00 km m s Current data file C Program Files SDSA data pertfest bd Fig 3 44 SDSA Performance submenu external performance module When External Performance Module is activated the performance program window appears The application is ready and user can work with the performance analysis results for current aircraft data for more information see SDSA External performance module manual 3 6 Options submenu SimS4C 5D5A Simulation and Dynamic Stability Analysis Aircraft Simulation Stability FCS Performance Options Output Help Files location Test flight parameters Recording JPEG parameters Save options Ctrl s options submenu Clear Window F12 Fig 3 45 SDSA Options submenu Short cut key Command ae combination Description click to define folders for SDSA executable data and Files location output files see Fig 3 46 Test flight parameters click to activate the external SDSA test flight parameters functional window see Fig 3 47 click to activate the external SDSA recording
34. ngular velocity rad s Max shaft angular velocity rad s 01 10 2 0 m1 0 02 0 7 gt By pass ratio 0 0 gt 10 0 Moments of inertia kg m2 Moments of inertia kg m2 Jx1 0 Jx2 0 Jx1 0 Jx2 lO Time constant Time constant Default Data from C Program Files SDSA data f 6 Simulation status Fig 3 10 SDSA Propulsion system internal SDSA window Information about SDSA propulsion system options features e User can setup the main propulsion data by setting up the necessary parameters or by loading them from previously saved Propulsion configuration file and Thrust data file e The main propulsion system option window contains 4 Engine panels which turn active in agreement with the Number of Engines parameter value max 4 e There are panels where user can set up the basic Propeller and Jet properties and select the Engine Type e User can compute the thrust with respect to the altitude airspeed range by clicking the Compute thrust button 3 2 Simulation submenu s SIMSAC SDSA Simulation and Dynamic Stability Analysis Aircraft Beem Stability FCS Performance Options Output Initial conditions Environment Run simulation FS Show results graphs F6 simulation submenu Fig 3 11 SDSA Simulation submenu SDSA Help System Short cut key Command a combination Description click to open external SDSA initial conditions setup I
35. nitial conditions window see Fig 3 12 click to open external SDSA environment setup Environment window see Fig 3 13 click to proceed to SDSA simulation module internal Run simulation SDSA simulation window appears see Fig 3 14 click to show the SDSA simulation results presented ra hs F6 on graphs see Fig 3 18 Show results Table 03 SDSA Simulation submenu description 3 2 1 Initial condition Initial values Initial position Altitude AGL rr Predefined coordinates 6000 1 Jo South Pole Airspeed ms Longitude 250 Heading deq DEG AA 0 o MIN td 0 Path angle deg SEC H 0 o HDR 4 0 Roll angle deg ada o DEG 4 90 Ground Start MIN i 0 SSS SSS SS SEC H 0 HDR 4 0 Fuel initial state gai EE Configuration r Fuel value O Payload value O Parload initial state BAUE E Apply Cancel Ok Fig 3 12 SDSA external initial condition setup window Information about SDSA initial conditions features e User can setup initial flight parameters and position values in external setup window e The initial parameter values will be used in aircraft simulation process SDSA Help System 3 2 2 Environment Initial values Current state cin the aircraft position Air temperature C 15 00 Air temperature C 15 00 Air pressure Fa 101325 Air pressure Pa 1101325 Air density kaima
36. nn rra rn nr n nn a nen nn anne road Dutch Roll class IV High maneuverability airplanes such as Pighter interceptor Roll Fightos intars Tactical reconnaissance Observati Spiral Trainer for Class IY Roll Spiral ESDU ICAO Stability Criteria Short Period CAP ESDU y MIL Phase A freq MIL Phase B freq MIL Phase C freq MIL Phases A and C damp MIL Phase B damp ratio Stability Criteria Stability Characteristics Trim Results stability Characterstics Trim Results Stability Phugoid Stability Short Period Stability Dutch Roll Elevator Deflection Path Angle T1f2 Phugoid T1 2 Short Period mE angle TI f2 Dutch Roll Rudder oa Tie Roll Ajleron Deflection Tir Spiral 7 E f Feriod Phugoid Period Dutch Fall select A variable select variable Mach v macn JH 7 Fig 3 26 SDSA Internal SDSA eigenvalues Fig 3 27 SDSA Internal SDSA eigenvalues window Stability characteristics selection window Trim results selection panel panel SDSA Help System 3 3 2 Time history Time History 1s a useful external application for analyzing and identification of the periods damping and phase shift from time response for specified aircraft data run Case SimSAC Identification of periods damping and phases from time response Ble Fe File Refining Options Sample interval t_ nit 0 10 s tend 3 30 s Sampling
37. of attack Additionally the average values of static margins are given directly SDSA Help System 3 4 FCS Flight Control System submenu s SimSAC SDSA Simulation and Dynamic Stability Analysis Aircraft Simulation Stability Performance Options Output Help Basic FCS parameters Pilot model Stability Augmentation System Linear Quadratic Regulator Read LOR matrix Save LOR matrix flight control system submenu Fig 3 30 SDSA FCS submenu Short cut key xt od Description combination P Command click to open internal setup SDSA Basic FCS Basic FCS parameters parameters window see Fig 3 31 click to open Pilot in the Loop model SDSA internal setup window see Fig 3 32 click to open Stability Argumentation System SDSA internal setup window Pilot model Stability Argumentation _ System see Fig 3 33 Linear Quadratic _ click to open main LOR SDSA internal setup Regulator window see Fig 3 34 Read LOR matrix Save LOR matrix 3 4 1 Basic FCS parameters click to read LQR matrix see Fig 3 37 click to save computed LQR matrix activates after the LQR matrices has been created Table 05 SDSA FCS submenu description SimSAC SDSA Simulation and Dynamic Stability Analysis Aircraft Simulation Stability FCS Performance Options Output Help 15 x Basic FCS parameters st
38. ormance submenu Aero data setfor external Performance module Fig 3 38 SDSA Performance submenu Short cut key Command ka combination Arvelo E Range and Endurance _ Aero data set for External Performance FII Manoeuvres F10 External Performance _ Module Module Description click to open internal SDSA envelope functional window see Fig 3 39 click to open internal SDSA range and endurance functional window see Fig 3 42 click to open internal SDSA manoeuvres functional window see Fig 3 42 click to activate external SDSA performance module for more information see SDSA External performance module manual User can select st or 2nd aero data set for external performance module This option turns active if more than one data set is available Table 06 SDSA Performance submenu description 3 5 1 Envelope In envelope mode user can Compute envelope for given altitude range and altitude step Additionally the minimum and maximum airspeed and theoretical ceiling are being computed Results are presented in output data fields and on graph for 1 or 2 data set 1f more than one set is available 2 SimSAC SDSA Simulation and Dynamic Stability Analysis o 0 x Aircraft Simulation Stability FCS Performance Options Output Help Minimum and maximum airspeed Altitude ASL m Minimum Maximum Minimum Maximum Mach max 1st 3000
39. raft Simulation Stability FCS Performance Options Output Help Real time 0 03 simul time 0 00 031 time step Reset Clock Rst on start Simulation commands Command Status Idle Idle Start Ready l Run Run Stop Stop Pause Pause Initial conditions Altitude AGL m Booo Airspeed m s lso 1st Active Aero data S 2nd Control 0 00 Throttle Lor Attitude Results of simulation Altitude AGL m 8000 00 Angle of attack deg 4 1 Ground Speed kmh 900 000 Sideslip angle deg 0 000 Vertical velocity m s 0 000 Heading deg 0 000 Stick roll ON State 0 13 Stick pitch Pilot SAS eee bor tT Data from C Program Files SDSA data B7 47 Simulation status Horizontal velocity m s 250 000 Velocity course deg 0 000 97 Airspeed m s 250 000 Path angle deg o 000 IAS mis 471 946 Max performed Gz fi 00 Mach number 0 81 1 More results Pedals Fig 3 14 SDSA Internal simulation window e The SDSA simulation window is divided into several panels The main panel is reserved for the 3D visualization of simulation process Additionally the position of aircraft during simulation process can be watched on the HIS horizontal situation indicator see Fig 3 15 Fig 3 15 SDSA HIS indicator internal simulation SDSA window e The results of simulation flight parameter values c
40. st cfg i Save as AAA A A A A A a A Number of Engines 4 1 gt Thrust graph parameters b b Altitude range H min m H max m H step m _ Compute thrust f dd dls diaii F Symmetrical configuration Show thrust Airspeed range Ma Ma min lo 00 Ma max 0 00 Ma step 0 00 Engines are the same Engine No 1 Engine No 2 Propulsion configuration Coordinates in BC system m Coordinates in BC system m Engines Tyne x 17 00 Y o Pa 0 00 X 0 Y 0 Z 0 fe tu rho pro p Angles of incidence deg Throttle Thrust kN Angles of incidence deg Throttle Thrust kN turbo jet 0 p lo 10 0 10 0 ce 0 B 0 10 0 10 0 piston propeller Max shaft angular velocity rad s Max shaft angular velocity rad s turbo fan 1 3000 00 22 3000 00 Q1 0 n2 10 Propeler Moments of inertia kg m2 Moments of inertia kg m2 z Jyt 110 00 x2 107 00 Ja 0 J lo Maximum power KA O Time constant Time constant i Altitude power factor lo 00 T1 11 50 T2 2 00 RES T1 10 T2 10 Ea Engine factor min 0 08 max 0 25 Engine No 3 Engine No 4 Typical values from 0 12 to 0 16 Coordinates in BC system m Coordinates in BC system m Jet X 0 Y 10 Z 10 x 10 Y 10 7 0 i i Maximum thrust H 0 Ma 0 N lO Angles of incidence deg Throttle Thrust kN Angles of incidence deg Throttle Thrust kN x 0 B 0 10 0 10 0 Ce 0 B 0 10 0 10 0 Altitude thrust tactor 10 00 o Max shaft a
41. t 36 SIN ERGs TRIN mirarte 36 SDSA Help System 1 SDSA Software main functionalities SDSA modules e Stability analysis eigenvalues analysis Ml sos Ab ES time history identification analysis static margins stick fixed free SDSA package 6 DoF si lati Warsaw 2008 o oF simulation test flights incl trim A response amp LQR e tests incl turbulence Dryden ya i turbulence model future design J m SA C e LQR based Flight Control System ee tests incl Pilot in the Loop model amp Stability Argumentation System e e Performance Dawid Mieszalski envelope range amp endurance AR manoeuvres external performance module e Miscellaneous data check review results review cross plots XML and TEXT file input output data file structure other etc Fig 1 1 SDSA About window screen 2 SDSA User graphical interface 2 1 SDSA main application window menu bar main aplication window status bar Fig 2 1 SDSA Main application window The SDSA main application window is now divided into three main areas menu bar user can access the particular program modules by clicking the proper menu button SDSA Simulation and Dynamic Stability Analysis User Manual 2 SDSA Help System main application window this is the workspace of the SDSA program status bar where the necessary text information is being displ
42. theory and application in Optimalsteuerungsprobleme von Hyperschall Flugzeugsystemen Workshop des Sonderforshungsbereichs 255 Greifswald Munchen 1997 pp 21 34 5 T GoETZENDORF GRABOWSKI Numerical Calculation of Stability Derivatives of an Aircraft Journal of Theoretical and Applied Mechanics No 3 32 Warsaw 1994 pp 591 606 6 T GoETZzENDORF GRABOWSKI Influence of Stability Derivatives on Quality of Simulation supersonic flow Journal of Theoretical and Applied Mechanics No 4 32 Warsaw 1994 pp 773 791 7 T GorrzeNDORF GRABOWSKI Selection of the Numerical Method for Integration of Differential Equations of Motion Derived Using Quaternion Algebra in Polish Proceedings of VII Conference on Mechanics in Aeronautics Warsaw 1996 53 68 8 T GoETZzENDORF GRABOWSKI Simulation and Dynamic Stability Analyser SDSA Graphical User Interface Manual SimSAC official deliverable D5 4 1 9 T GorTzZENDORF GRABOWSKI Static and Dynamic Stability Analyser SDSA Core module to calculate modes of motion Roll response module SimSAC official deliverable D5 2 1 10 Z Goras Calculations of equilibrium manoeuvrability and stability of an aircraft in subsonic range of speed in Polish Warsaw University of Technology Warszawa 1984 11 B L Stevens F L Lewis Aircraft Control and Simulation John Wiley amp Sons Inc New York 1992 12 R C NeLson Flight Stability and Automatic Control second edition McGraw Hill 199
43. toric parameters Pilot yaw control channel Td 0 05 delay time s tl o 1 00 lag time s Adaptive parameters tp com K2 0 000 gain 1 Save options Cancel Remnant parameters 013 2 frequency 1 s 2 0 1 DD lag time s cla 43 damping 1 s T3 0 50 lead time s w o 00 amplitude 1 Data from CJProgram Files SDSAdata Horizon1 100 Simulation status Flight OK Fig 3 32 SDSA Pilot in the loop parameters setup window 3 4 3 Stability Argumentation System SimSAC SDSA Simulation and Dynamic Stability Analysis Aircraft Simulation Stability FCS Performance Options Help SAS parameters Pitch SAS parameter KSq 0 00 q gain radi 1 s Range 5 0 9 of deflection PARAMETERS OF SAS SYSTEMS WITH ACTUATOR Ue com Roll SAS parameters a KSp fo p gain radi 1 s TauSp 0 050 p lag time s Range 5 0 of deflection Yaw SAS parameters KSr lo p gain radi 1 s TauSr 0 050 p lag time s Range 5 0 of deflection Actuator parameters Elevator Kae 1 00 gain 1 Tause fo o5 lag time s Aileron Kaa 1 00 gain i Tau a Joos lag time s Rudder Kar fi 00 p gain 1 Tauar 0 05 lag time s Cancel Save options Data from C Program Files SDSA data Horizon1 100 Simulation status Flight OK Fig
44. ty derivatives Aero data type to use during computations in SDSA software for more information see SDSA Input data file structure manual Data interpolation _ click to open the internal SDSA interpolation options options window see Fig 3 9 ce nee Shif F2 Click to generate the SDSA aero data report port see Fig 3 7 Check data Ctrl F click to open the internal SDSA check data options options window see Fig 3 8 click to open the internal SDSA propulsion system p l l i Propulsion data options window see Fig 3 10 click to choose the grid file default or selected by user Guada gt ait Exit Alt X click to completely exit SDSA application Table 02 SDSA Aircraft submenu description SDSA Simulation and Dynamic Stability Analysis User Manual 4 SDSA Help System 3 1 1 Open data location file Browse For Folder E ax Select data Files directory li B74 _quess_new a Fiz i F12 WUT Folder data Make New Folder Cancel AA Fig 3 2 SDSA TXT input data files folder location selection external window Read XML data file Look in E xml e eE My Recent Documents E Desktop gt My Documents My Computer Gam e AE File name X Places Files of type ml Files X Cancel Fig 3 3 SDSA XML single input data file selection external window 3 1 2 Save data
45. ve with respectto Alpha dot 1frad 2 00 Pitching moment derivative with respectto Alpha dot 1frad 4 00 Roling moment derivative with respect to roll rate 1 rad 0 950 Rolling moment derivative with respectto yaw rate Hrad 0 50 i Yawing moment derivative with respectto roll rate 1 rad 0 500 10 500 lo 0 50 0 50 0 50 0 50 o o 210 oso 0 500 ae Yawing moment derivative with respect to yaw rate 1frad 1 000 0 005 Derivatives with respect to the control surfaces deflection min max Lift force derivative with respectto elevator deflection rad oO 4 00 Pitching moment derivative with respectto elevator deflection 1frad 3 00 b Roling moment derivative with respectto ailerons deflection 1 rad 1 50 b Rolling moment derivative with respectto rudder deflection 1 rad 010 0 10 Yawing moment derivative with respectto rudder deflection irad 0 50 b Side force derivative with respectto rudder deflection 1 rad o 1 00 OK Apply Cancel Fig 3 8 SDSA Check data options external window Information about SDSA check data options features e User can setup the min and max values of derivatives with respect to the airplanes state and the control surfaces deflections e These derivative values will be used to check the correctness of the loaded input aerodynamic data see chapter 3 1 3 SDSA Simulation and Dynamic Stability Analysis User Manual 7 3 1 5 Data interpol
46. w In JPEG Parameters window user can setup the quality optimization options of the capture JPEG see also chapter 3 7 3 7 Output submenu de Sims AC 5D5A Simulation and Dynamic Stability Analysis Aircraft Simulation Stability FCS Performance Options Help Save selected results as XML file Save selected results as TXT file Select results to save Save all results as XML file Save stability results as XML file Save envelope as XML file Save turn analysis as XML file Save range and endurance as XML file Save all results as TXT file Save stability results as THT file Save envelope as TAT file Save turn analysis as TXT file Save range and endurance analysis as TXT file output submenu Save current picture as Shift Ctrl 8 Fig 3 50 SDSA Output submenu SDSA Help System Short cut key Command a Description Save selected results as_ Click to save all previously selected SDSA results to XML file one XML file Save selected results as_ Click to save all previously selected SDSA results to TXT file one TXT file Click to open SDSA window see Fig 3 51 where user Select results to save can select the results to save Selected results will be written into one TXT ore XML file Save all results as XML _ i click to save all SDSA results to user selected XML file file Save stability results as_ Click to save only
47. w user can setup the desired flight Disturbance type The Test turned On button must be pushed in to activate the flight test The effects of disturbance can be observed in simulation mode window see chapter 3 2 Useful information about test flight parameters mode features e In the test flight parameters mode user can choose the control surface to be used during the disturbance control type step function single step double step disturbance type initial state parameters SDSA Help System 3 6 3 Recording Flight file name cuSDSAF light Recordingiflight_01 Browse start of recording s lo end of recording s 50 length of recording 50 Recording OK Apply Cancel Fig 3 48 SDSA Options submenu SDSA flight recording setup window In flight recording window user can setup the flight recording options like flight recording file name and destination folder start of recording time end of recording time and length of recording The Recording button must be pushed in to activate flight recording mode during simulation The recorded flight simulation results recorded in file can be displayed in Show results graphs see chapter 3 2 4 3 6 4 JPEG Parameters hoy high Quality 80 j small large W Progressive Display W Optimize for Size Options Show this dialog box each time Fig 3 49 SDSA Options submenu SDSA JPEG Parameters setup windo
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