Instructor Gaëtan Kerschen

Transcription

1 Welcome! 1

2 Instructor Gaëtan Kerschen Contact details Space Structures and Systems Lab (S3L) Structural Dynamics Research Group Aerospace and Mechanical Engineering Department Room: +2/420 (B52 building)

3 AERO0025 Satellite Engineering Gaëtan Kerschen Space Structures & Systems Lab (S3L) 3

4 The University System Natural tendency to create specialists rather than generalists Highly specialized courses in aerospace engineering at ULg and main focus on mechanical/structural aspects A spacecraft designed by structural engineers 4

5 The University System 5

6 My Objectives A well-designed satellite is a sound compromise among the requirements of the different engineering disciplines 1. Introduce you to systems engineering 2. Expose you to the inherently multidisciplinary aspect of satellite engineering 3. Give you an overview of different subsystems and, as much as possible, of their interactions (more details on specific subsystems next year) 6

7 Another Objective of this Course YOU Your Master is unique! 7

8 Course Details 8

9 Textbook 9

10 Course Project 10

11 Course Project For two weeks from Monday, please form groups of 4 persons and mention your top 3. Mention also your favorite mission among the three chosen missions. ESA missions CubeSats Far Infrared Interferometer Solar Orbiter Space Weather Wide Field Imager X-ray Evolving Universe Spectroscopy COMPASS-1 (Aachen, Germany) SwissCube (Lausanne, Switzerland) ( 11

12 AERO0025 Satellite Engineering Introductory Lecture From Dreams to Technical Challenges 12

13 From Dreams to Technical Challenges Space makes us dream What? Why? Where? When? Who? How? Technical challenges! 13

14 Space Makes Us Dream 14

15 Space Makes Us Dream 15

16 Space Makes Us Dream 16

17 Space Makes Us Dream 17

18 Space Makes Us Dream???????????? 18

19 Space Makes Us Dream????????????? 19

20 WHAT DO YOU SEE? 20

21 Space Makes Us Dream 21

22 Space Makes Us Dream 22

23 Space Makes Us Dream Ariane V 23

24 Space Makes Us Dream 24

25 Space Makes Us Dream 25

26 Space Makes Us Dream 26

27 Space Makes Us Dream 27

28 Space Makes Us Dream 28

29 Satellite #1 Hint : beeeeep beeeeep beeeeep 29

30 Satellite #2 Satellite #2 30

31 Hint for Satellite #2 Hint for satellite #2: Automated Transfer Vehicle (ATV) Hint: one of the most famous pictures in astronomy 31

32 Satellite #3 Satellite #3 32

33 Hint for Satellite #3 Hint for satellite #3: one of the most famous pictures in astronomy 33

34 Satellite #5 Satellite #4 34

35 Hint for Hint satellite for #4: Satellite visited several #5 planets and their moons 35

36 Hint for Satellite #5 Hint for satellite #4: Star Trek (1979) 36

37 Satellite #6 Satellite #5 37

38 Hint for Satellite #6 Hint for satellite #5: the satellite discovered a small ice lake 38

39 Satellite #9 Satellite #6 39

40 Hints for Satellite #9 Hint for satellite #6: 1. CSL participated to this mission 2. Name of a London district 40

41 Satellite #10 Satellite #7 41

42 Hint for Satellite #10 Hint for satellite #7 42

43 Hint for Satellite #10 Satellite #8 43 Hint for satellite #8: kéne affaire

44 Answers But Also Emphasis of Some Technical challenges Examples of design interaction Failures 44

45 Satellite #1: Sputnik, 1957 Objective: Identification of high atmospheric layers density First artificial satellite, Oct. 4, 1957 Several failures of the launch vehicle (May, June, July 1957) before the successful flight 45

46 Sputnik: Technical Data Weight 84 kgs Dimensions 0.6 m diameter sphere Power 1 W radio transmitting unit Propulsion ADCS Communications Orbit Launch vehicle 2 antennas, 2.4 m and 2.9 m (spherical radiation pattern) LEO, 950 x 220 kms, i= 65, T=96 mins R-7 Semyorka (Soyuz basis) 46

47 Satellite #2: ISS Objective: Perform science experiments 47

48 ISS: Technical Data Weight Dimensions 470 tons (upon completion) 58m x 73m x 28m Power 110 kw, solar panels Propulsion ADCS Communications Orbit Launch vehicle Zvezda (2 x 3070 N thrusters, N2H4 and N2O4) + Progress + STS + ATV Control moment gyroscopes + thrusters (130 N) + star trackers + infra Red horizon sensors + magnetometers + solar sensors + GPS Ku-band (TV, high-speed data) and S-band (audio) antennas LEO, 339 x 342 kms, i= 51, T=91 mins Soyuz and Space Shuttle 48

49 Satellite #3: HST, 1990 Objective: Astronomy Pointing accuracy: Defective mirror and solar panels, recovery thanks to servicing mission 49

50 HST: Technical Data Weight 11 tons Dimensions Power 13.2 m high, 4.2 m diameter 4.5 kw, solar panels Propulsion ADCS Reaction wheels, magnetometers, star trackers, gyroscopes, fine guidance sensor (lock onto guide stars), magnetic torquers Communications Orbit Launch vehicle 2 high-gain antennas (S-band) LEO, 600 kms, i= 28, T=96 mins Space Shuttle 50

51 Satellite #4: Voyager, 1977 Objective: Space exploration (planets and their moons) Unique feature: farthest manmade object from earth (100 UA) Jupiter, Saturn, Uranus, Neptune and their moons 23 W radio could transmit data over a distance of 10 9 km Alignment every 176 years + 12 years to meet Neptune 51

52 Voyager: Technical Data Weight Dimensions Power 720 kgs 0.6 m high, 1.8 m diameter (bus) 470 W, 3 RTGs Propulsion ADCS Communications Orbit Launch vehicle Centaur (LH 2 +LOX) + gravity assist + 16 N 2 H 4 thrusters 16 N 2 H 4 thrusters + sun sensors + star tracker 3.7 m high-gain antenna (S band: uplink, X-band: downlink), low-gain antenna Outer planets exploration Titan III + centaur upper stage 52

53 Satellite #5: Mars Express, 2003 Objective: Mars exploration 40-m radar to map the distribution of water Beagle 2 failed to land (problem with the parachuting device) 53

54 Mars Express: Technical Data Weight Dimensions Power Propulsion ADCS Communications 1100 kgs 1.5 x 1.8 x 1.4 m (bus) Solar panels: 12 m tip-to-tip 600 W, solar panels Fregat N main engine with N 2 H 4 and N 2 O 4 (mainly for slowing down!) 8 attitude thrusters (10 N each) + star trackers + gyros + sun sensors + 4 reaction wheels (12 NMs) 1.6 m high-gain antenna m low-gain antenna (X band 7.1 GHz and S-band 2.1 GHz) + UHF antenna (for Beagle 2) Orbit Martian orbit, 259 x kms i= 86 Launch vehicle Soyuz + Fregat upper stage (4th stage) 54

55 Satellite #6: SOHO, 1995 Objective: Solar exploration and space weather prediction 55

56 SOHO: Technical Data Weight 1850 kgs Dimensions 4.3 x 2.7 x 3.7 m (bus) Solar panels: 9.5 m tip-to-tip Power 1500 W, solar panels Propulsion Centaur + 16 N 2 H 4 thrusters (4.2 N) ADCS Communications Orbit Launch vehicle 3 reaction wheels + 16 N 2 H 4 thrusters + 3 gyroscopes + sun sensors + star tracker 0.8 m high-gain and low-gain antennas (S-band) Halo orbit (L1) Atlas II + centaur upper stage 56

57 SOHO s Failure 1. All contact with SOHO was lost during a month! 2. A telescope was used to transmit an S-band signal (580 kw!!!) towards SOHO. The radar echoes heard from Goldstone (Deep Space Network) confirmed its predicted location, and a spin rate of 1 rpm. 3. Telemetry showed that hydrazine in the tank, thrusters and pipes were frozen. 4. Thawing operation using heaters SOHO was recovered! 57

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59 Satellite #7: NEAR Shoemaker, 1996 Objective: First spacecraft to soft-land on an asteroid Several sets of thrusters 59

60 NEAR Shoemaker: Technical Data Weight 805 kgs (318 kgs propellant!) Dimensions Power ADCS 3 m high x 1.7 m diameter (bus) 1800 W (400 W) at 1 AU (2.2 AU) N 2 H 4 thrusters (4 x 21 N + 7 x 3.5 N) + 4 reaction wheels + gyroscopes + star tracker Propulsion 450 N main thruster (N 2 H 4 / N 2 O 4 ) Communications Orbit Launch vehicle 1.5 m X-band high-gain radio antenna Asteroid pursuit Delta II 60

61 NEAR Shoemaker s Failure On 20 December 1998, the spacecraft began a series of rendez-vous burns required for capture into orbit around the asteroid Eros. Immediately after the main engine ignited, the burn aborted, demoting the spacecraft into safe mode. Less than 1 min. later, the spacecraft began an anomalous series of attitude motions, and communications were lost for the next 27 hours. Onboard autonomy eventually recovered and stabilized the spacecraft in its lowest safe mode. However, in the process NEAR had performed 15 autonomous momentum dumps, fired its thrusters thousands of times, and consumed 29 kg of fuel. The cause was determined within 2 days of the event: the main engine s normal start-up transient exceeded a lateral acceleration safety threshold that was set too low. 61

62 Satellite #8: OUFTI-1, 2009 Objectives: 1. On-orbit validation of D-STAR 2. Innovative electrical power system 3. New solar cells Entirely designed by students Hopefully none! 62

63 OUFTI-1: Technical Data Weight Dimensions Power ADCS 1 kg 10 cm x 10 cm x 10 cm 1 W Passive (permanent magnets and hysteretic materials) Propulsion None Communications 145 MHz MHz (Ham radio bands) Orbit LEO, 1447 x 354 kms, i= 71 Launch vehicle Vega 63

64 ? 64

65 They Are All Different! Weight Dimensions Power ADCS Communications Orbit Launch vehicle A few kgs several tons A few cms several meters A few watts several kw Many options High gain, low gain UHF, X, S, Ku bands A few cms several meters LEO, Halo orbit, asteroid pursuit, Martian, space exploration Soyuz, STS, Delta II, Titan III, Atlas II 65

66 Failures Are Common! Celebrated Example Due to a navigation error, Mars Climate Orbiter was lost. The error arose because Lockheed Martin used imperial units instead of metric units as specified by NASA 66

67 The Launch Vehicle May Also Fail! 67

68 From Dreams to Technical Challenges Space makes us dream What? How? Technical challenges! 68

69 Definition (Wikipedia) In the context of spaceflight, a satellite is an object which has been placed into orbit by human endeavor. Such objects are sometimes called artificial satellites to distinguish them from natural satellites such as the Moon. Lots of acronyms in space jargon (LEO, GEO, TM/TC, SRB, ADCS, EPS, BOL, EOL, etc.). An extensive list is available in Fortescue et al. p xxi 69

70 An Element Within a Larger System Severe constraints (size, weight, launch site, orbit, vibrations) Telemetry for satellite data and status (TM) Telecommands (TC) Determination of satellite s position Launch vehicle Ground station 70

71 Goldstone (70m) Madrid (70m) Canberra (70m) Deep space network: 3 ground stations (120 apart around the world ) ESA Redu ground station (Belgium) 71

72 Ariane V Vega Soyuz Titan III Saturn V? Space Shuttle??? 72

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74 Satellites Inside the Fairing (Dnepr L.V.) Demeter, Saudisat-2, SaudiComsat-1, Latinsat-C, SaudiComsat-2, Unisat-3, Amsat-Echo and Latinsat-D 74

75 Launch Site Influence Ariane V: 9 tons in GTO, launch site: Kourou, i=5.1 Ariane V: 5 tons in GTO, launch site: Kennedy SC, i=28.4 Ariane V: 3.5 tons in GTO, launch site: Baikonour, i=

76 A Satellite Comprises Two Main Elements Payload: motivation for the mission Bus: necessary functions for the payload 76

77 Antennas: planet radio emissions Magnetometer PAYLOAD (LECTURES 3, 4, CSL, AGO) Cosmic ray detector Plasma detector Photopolarimeter UV and IR spectrometers Cameras 77

78 Bus: Complex Assembly of Subsystems STRUCTURE & MECH. Withstand launch and orbit loads + properly deploy and run mechanisms PROPULSION Spacecraft maneuvers and trajectory THERMAL CONTROL TELECOMMUNICATIONS ATTITUDE CONTROL Withstand temperatures imposed by the harsh space environment Communicate and exchange information with ground Ensure correct orientation in space POWER Powering the subsystems and payloads ON-BOARD COMPUTER The brain of the satellite 78

79 POWER (LECTURE 9, THALES ALENIA SPACE) Radioisotope thermoelectric generator (RTG) Sun sensor ATTITUDE CONTROL (LECTURE 10, KERSCHEN) High-gain antenna Low-gain antenna TELECOMMUNICATIONS (LECTURE 13, SPACEBEL) 79

80 Louvers THERMAL CONTROL (LECTURE 11, CSL) N 2 H 4 thrusters PROPULSION (LECTURE 8, LEONARD) Decagon, 0.6 m high 1.8 m diameter STRUCTURE 80 (LECTURE 12, ESA)

81 ATTITUDE CONTROL (LECTURE 10, KERSCHEN) Star tracker MECHANISMS (LECTURE 15, BOZET) Box containing a deployable truss on 81 which the magnetometer is mounted

82 In Summary GROUND SEGMENT SPACE SEGMENT LAUNCH VEHICLE PAYLOAD BUS STRUCTURE & MECH. ATTITUDE CONTROL TELECOMMUNICATIONS PROPULSION POWER THERMAL CONTROL ON-BOARD COMPUTER 82

83 From Dreams to Technical Challenges Space makes us dream When? How? Technical challenges! 83

84 When? HISTORICAL PERSPECTIVE (NEXT LECTURE, SPACE INFORMATION CENTER) 84

85 From Dreams to Technical Challenges Space makes us dream Where? How? Technical challenges! 85

86 VOYAGER ULYSSES NEW HORIZONS MARS EXPRESS GIOTTO SOLAR ORBITER BEPI COLOMBO VENUS EXPRESS EARTH ORBIT SPACECRAFT ENVIRONMENT (LECTURE #4, CSL) Severe constraints (magnetic field, temperatures, atmosphere, launch vehicle, ground station visibility, eclipse duration) 86

87 LAGRAGE POINTS (NONLINEAR DYNAMICS!) BENIGN ENVIRONMENT: PLANCK, JAMES WEBB SPACE TELESCOPE GOOD FOR SUN OBSERVATION: SOHO STABLE: ASTEROIDS 87

88 HEO kms x 7000 kms: XMM GEO MEO kms: METEOSAT, GOES kms: Galileo kms: GPS SATELLITE ORBITS (LECTURE 6, KERSCHEN) GAP LEO 1447 kms x 354 kms: OUFTI kms: SPOT kms: HST 400 kms: ISS 250 kms: GOCE Circular Elliptic

89 Gap? Van Allen Belts SPACECRAFT ENVIRONMENT (LECTURE 5, CSL) 89

90 From Dreams to Technical Challenges Space makes us dream Why? How? Technical challenges! 90

91 Earth Observation: Weather Satellites What s special with Meteosat? Weather satellites see more than clouds: fires, pollution, sand storms Movie: GOES satellite 91

92 Earth Observation: Other Satellites Measurements of the surface height of the oceans to an accuracy of 3.3 cms ENVISAT (SSO) JASON (LEO, i=66 ) In-orbit configuration: 26 m x 10m x 5m (the size of a bus) Information about the earth (land, water, ice and atmosphere) EARTH OBSERVATION (LECTURE 3, CSL) Military satellites (resolution: on the order of 1cm!) -satellite-shootdown.html 92 KH-13

93 Communications and Navigation Eutelsat W3A GPS 2R Eutelsat: 2500 televisions and 1000 radio stations Iridium: a constellation of 66 satellites GPS (USA): 31 satellites in 6 orbital planes spaced equally in their ascending node locations Galileo (Europe), Glonass (Russia) 93

94 GPS Constellation GPS 2R GPS constellation 94

95 Space Observation and Exploration Too many examples! Cassini-Huygens (Saturn), SOHO (Sun), Galileo (Jupiter), Voyager (different planets), HST (universe), Corot (asteroseismology), NEAR shoemaker (asteroid encounter), etc. Observation using different wave lengths (XMM X rays, IRAS infrared) A single mission has not a single instrument (e.g., more than 10 for Galileo) ASTROPHYSICS (LECTURE 4, AGO) 95

96 Space Stations Perform science experiments under microgravity conditions MIR (Russia) ISS 96

97 Service Satellites Tracking and data relay satellite system SMART-OLEV GEO spacecraft constellation: Tracking and data acquisition services between LEO spacecraft and NASA/customer facilities A gas station in space: Up to 12 years life extension for GEO telecommunications satellites 97

98 Space Tourism: Inflatable Hotel! Experimental space habitat GENESIS

99 Entertainment Thanks to Space!

100 From Dreams to Technical Challenges Space makes us dream Who? How? Technical challenges! 100

101 Key Players NASA, JPL, Lockheed-Martin, Northrop-Grumman, Boeing Roscosmos, Energia ESA, CNES, DLR, ASI, EADS-Astrium, Arianespace,Thales Alenia Space Two emerging countries 101

102 Belgium? A Truly Strong Expertise! AMOS, Cegelec, CSL, Euro Heat Pipes, Gillam, Ionic Software, Lambda-X, SABCA, SAMTECH, SONACA, Spacebel, Techspace Aero, ETCA, Verhaert, Vitrociset, Walphot Euro Space Center and ESA Redu ground station ULg: 2 unique Masters + LTAS & AGO UCL: radiation and hyperfrequences ULB: microgravity research center 102

103 An Example of Belgium s Know-How ATV Jules Verne EHP: heat pipes ETCA: power conditioning units Spacebel: software Rhea: software Redu: backup ground station Techspace aero: aestus engine valves 103

104 From Dreams to Technical Challenges Space makes us dream What? How? Technical challenges! 104

105 Satisfy Customer s Basic Goals 1. Payload design LECTURES 3, 4 2. Mission analysis (orbit design and resulting environment) LECTURES 5, 6, 7 3. Bus design (all other lectures) LECTURES

106 But Satellite engineering is extremely challenging For at least 7 reasons can you guess some of them? 106

107 Challenge #1: Multidisciplinary Design 107

108 Challenge #1: Voyager Example POWER USING NUCLEAR MATERIALS Deep space mission POLITICAL PROBLEM ELECTRONICS (RADIATION) BUS (ADEQUATE CONFIGURATION) 108

109 Challenge #2: Each Mission is Unique Where? & Why? 109

110 Challenge #3: Orders of Magnitude What is Planck s coldest T? CSL 110

111 Challenge #3: Orders of Magnitude 0.1 K (CSL) the equivalent of the amount of energy exchanged between 2 people 400 kms from each other 7.5 kms of shielded cable kms W

112 Challenge #3: Orders of Magnitude km/h km/h in 2 minutes 112

113 Challenge #3: Not Only the Satellite Solid rocket boosters (SRBs): 10 tons / s 45 GW (electric power in France) 124s 150 db 113

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115 Challenge #3: Not Only the Launcher Vehicle assembly building (Kennedy Space Center) 3.5 times the volume of the Empire State building 115

116 Challenge #3: Not Only the Building $1 billion just to transport the space shuttle over a few kilometers 116

117 Challenge #3: Last but not Least A 3-meter long gator at KSC 117

118 Challenge #4: Complex Mission Profile Inner planetary missions Satellite & launch vehicle in earth orbit Deep space missions Ascent Reentry & landing Launch Transportation Handling & testing 118

119 Challenge #5: Severe Constraints Planning (Voyager: once every 176 years) /kg Weight Volume Fuel Power (Voyager: 470 W) 119

120 Challenge #6: Harsh Environment Low temperatures + unknown Magnetism Rings Meteorites + cosmic ray + vacuum Hot temperatures Voyager did visit Jupiter, Saturn, Neptune and Uranus! 120

121 Challenge #7: Reliable and Robust In most cases, no maintenance! Autonomy is often required for deep space missions (communications may take several minutes if not hours) 121

122 Challenge #1: Multidisciplinary Design Look for the optimal solution for the entire spacecraft (do not look for the optimal solution for your subsystem) This course is intended to give you an overview of the different subsystems, so that you will understand the challenges faced by your colleagues who are expert in power systems telecommunications, etc Concurrent Design Facility, ESTEC-ESA 122

123 Challenge #2: Each Mission is Unique The engineer must fit the requirements 123

124 Challenge #2: Each Mission is Unique Roll-out Whipple shield Hubble Stardust Body mounted Cruise & observation SSETI Express Solar Orbiter 124

125 Challenge #3: Orders of Magnitude The engineer must be creative kms Communications: W Power: 15W/m 2 (Saturne) Nuclear materials 70-meter antenna 125

126 Challenge #4: Complex Mission Profile Virtual prototyping (i.e., predict as many configurations / options / situations as possible using numerical simulations) Finite element model predictions of an antenna support 126

127 Challenge #5: Severe Constraints The engineer must be creative Volume under the fairing is limited Deployable boom ( Voyager) 127

128 Challenge #5: Severe Constraints Fuel Gravity assist 128

129 Challenge #6: Harsh Environment Develop new technologies Whipple shield against comet projections 129

130 Challenge #7: Reliable and Robust Redundancy and proven technologies For each spacecraft: 3 RTGs 2 x 8 thrusters 2 transceivers 2 computers 2 magnetometers Voyager 1 Voyager 2: backup (ultimate redundancy!) 130

131 In Summary Use proven technologies Be creative Conflict is the order of the day Redundancy The resolution of such conflict in a productive manner is precisely the goal of systems engineering Weight constraints (launch) 131

132 1. Quel est le premier être vivant a avoir été envoyé dans l'espace par les Russes? 2. Quel est le premier être vivant a avoir été envoyé dans l'espace par les Américains? 3. Quel est le premier être vivant a avoir été envoyé dans l'espace par les Belges?

133 AERO0025 Satellite Engineering Introductory Lecture From Dreams to Technical Challenges 133