RENDEZVOUS AND DOCKING OF SPACECRAFT - ESA

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CO-ORDINATE FRAMESTo describe rendezvous orbits and trajectories we usethree different co-ordinate frames:a3NNa = x 1 loa = za = y3 op 2 oporbital motiona = y2 loa1Equatora2EquatoriInclinationAscending Nodea = x1 opa 3 = z loEarthγEarth Inertial FrameOrbital Plane FrameLocal Orbital Frameorbit angles w.r.t.inertial spaceposition&velocitiesin orbitrelative position &velocities to targetDr. W. Fehse – Introduction to RVD – From Ground to Capture – Version 200912
LAUNCH INTO THE ORBIT PLANE OF THE TARGET• OWING TO THE ROTATION OF THE EARTH, TWO TIMES A DAY THELAUNCH SITE MOVES INTO THE ORBITAL PLANE OF THE TARGETVEHICLE.• HOWEVER, BECAUSE OF SAFETY RESTRICTIONS (NO FLIGHT OVERINHABITED AREAS), MOST LAUNCH SITES CAN ONLY LAUNCH IN ONEDIRECTION, e.g. OVER OPEN SEA.• ALSO, WITH A LAUNCH IN EAST-DIRECTION, THE VEHICLEBENEFITS FROM THE ROTATION OF THE EARTH, WHICHPROVIDES A GRATIS ∆V OF ≈ 463 m/s AT THE EQUATOR.• THIS RESULTS IN ONE OPPORTUNITY PER DAY, WHERE THE LAUNCHDIRECTION MEETS THE ORBIT PLANE AND ORBIT DIRECTION.• BECAUSE OF THE DEVIATION OF THE EARTH FROM A TRUE SPHERE,THE ORBIT WILL DRIFT WITH TIME (DRIFT OF NODES).AS A RESULT, THE CHASER SPACECRAFT HAS TO BE LAUNCHED INTOA VIRTUAL TARGET ORBIT PLANE, SUCH THATAT THE TIME OF ARRIVAL, CHASER AND TARGET VEHICLESWILL HAVE DRIFTED INTO THE SAME ORBITAL PLANE.Dr. W. Fehse – Introduction to RVD – From Ground to Capture – Version 200913
Page 1 and 2: RENDEZVOUS AND DOCKING OFSPACECRAFT
Page 3 and 4: PART 1: INTRODUCTION TO RENDEZVOUS
Page 5 and 6: THE SCENARIO IN LEOTHE LEO SCENARIO
Page 7 and 8: THE INTERNATIONAL SPACE STATION (IS
Page 9 and 10: SYSTEM AND FUNCTIONS IN GEO RVD (SC
Page 11: ¨©¡¡¡¡ ¢¢£££¢¢¢£££
Page 15 and 16: DEFINITION OF PHASE ANGLEOrbital Pl
Page 17 and 18: TRAJECTORIES IN EARTH CENTRED ANDTA
Page 19 and 20: Hill EquationsFor circular orbits,
Page 21 and 22: USE OFCLOHESSY-WILTSHIRE EQUATIONSA
Page 23 and 24: IMPULSIVE TRAJECTORIESTANGENTIAL MA
Page 25 and 26: THE PREDOMINANT DISTURBANCES IN LEO
Page 27 and 28: EFFECTS OF THE SOLAR PRESSURE IN GE
Page 29 and 30: DRIVERS FOR RENDEZVOUS STRATEGIES I
Page 31 and 32: DRIVERS FOR RVD STRATEGIES IN THE S
Page 33 and 34: COMMUNICATION RANGE OF GROUND STATI
Page 35 and 36: APPROACH STRATEGY EXAMPLE(JAPANESE
Page 39 and 40: THE PROBLEM OF CAPTURELAW OF CONSER
Page 41 and 42: Shock Attenuation DynamicsBasic Spa
Page 43 and 44: TYPES OF DOCKING MECHANISMTWO BASIC
Page 47 and 48: THE AUTOMATIC ONBOARD CONTROL SYSTE
Page 49 and 50: CLOSED LOOP GNC BLOCK DIAGRAMSENSOR
Page 51 and 52: THE MISSION + VEHICLE MANAGEMENT (M
Page 53 and 54: FAULT TOLERANCE AND RECOVERY CONCEP
Page 55 and 56: COLLISION AVOIDANCE MANOEUVRE (CAM)
Page 57 and 58: THE NAVIGATION REQUIREMENTS FOR ARD
Page 59 and 60: MEASUREMENT PRINCIPLES: RGPSRELATIV
Page 61 and 62: MEASUREMENT PRINCIPLE OF LASER RANG
Page 63 and 64:
PART 1: INTRODUCTION TO RENDEZVOUS
Page 65 and 66:
WHY DO WE WANT TO HAVE AN AUTOMATIC
Page 67 and 68:
THE ROLE OF HUMAN OPERATORS INAUTOM
Page 69 and 70:
THE TASKS OF GROUND OPERATORS IN AR
Page 71 and 72:
RENDEZVOUS CONTROL SYSTEM DISPLAYPH
Page 73 and 74:
WHAT IS DIFFERENT BETWEEN RVD IN GE
Page 75 and 76:
THE MAJOR DIFFERENCES: ORBITAL DIST
Page 77 and 78:
THE MAJOR DIFFERENCES:COMMUNICATION
Page 79 and 80:
THE MAJOR DIFFERENCESGENERAL PROBLE
Page 81 and 82:
ALLOCATION OF TASKS TO SPACE- AND G
Page 83 and 84:
PART 2VERIFICATION & VALIDATION PRI
Page 85 and 86:
GENERAL RVD VERIFICATION ISSUES (co
Page 87 and 88:
DEFINITION OF VERIFICATION AND VALI
Page 89 and 90:
Page 91 and 92:
VERIFICATION AND VALIDATIONIN THE D
Page 93 and 94:
VERIFICATION IN THEFEASIBILITY STUD
Page 95 and 96:
VERIFICATION IN THE EARLY DESIGN PH
Page 97 and 98:
VERIFICATION IN THE FINAL DESIGN PH
Page 99 and 100:
MERGING OF GNC, MVM AND FDIR IN O/B
Page 101 and 102:
CLOSED LOOP GNC SIMULATION WITH O/B
Page 103 and 104:
CLOSED LOOP GNC SIMULATION WITHREAL
Page 105 and 106:
VERIFICATION IN THE FLIGHT ITEMMANU
Page 107 and 108:
Page 109 and 110:
CLOSED LOOP GNC SIMULATION WITHREAL
Page 111 and 112:
STIMULATION FACILITY FOR OPTICAL SE
Page 113 and 114:
Page 115 and 116:
VERIFICATION OF CAPTURE IN THE DOCK
Page 117 and 118:
VERIFICATION OF CAPTURE INTERFACESI
Page 119 and 120:
Page 121 and 122:
CLOSED LOOP SIMULATION WITH O/B COM
Page 123 and 124:
VALIDATION OF SIMULATION MODELS (co
Page 125:
DEVELOPMENT LIFE CYCLE OF A SPACE P
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