Instructor Gaëtan Kerschen
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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. Give you an overview of the different satellite subsystems and expose you to the inherently multidisciplinary aspect of satellite engineering. 2. Describe you subsystems interactions and introduce you to systems engineering. 6
7 Next Year Mechanisms Deployable structures Telecommunications Space environment Vibrations Space propulsion Composites Bus design Astrophysics Earth observation Optics Payload design Astrodynamics Reentry Mission analysis Launch vehicle design Launch vehicle 7
8 Another Objective of this Course YOU Your Master is unique! 8
9 Course Details (See Document) 9
10 Textbook 10
11 AERO0025 Satellite Engineering Introductory Lecture From Dreams to Technical Challenges 11
12 From Dreams to Technical Challenges Space makes us dream What? Why? Where? When? Who? How? Technical challenges! 12
13 Space Makes Us Dream 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 WHAT DO YOU SEE? 19
20 Space Makes Us Dream 20
21 Space Makes Us Dream 21
22 Space Makes Us Dream Video FlightVS14 22
23 Space Makes Us Dream 23
24 Space Makes Us Dream 24
25 Space Makes Us Dream 25
26 Emphasis of Some Technical challenges Examples of design interaction Failures 26
27 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 27
28 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) 28
29 Satellite #2: ISS Objective: Perform science experiments 29
30 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 30
31 Satellite #3: HST, 1990 Objective: Astronomy Pointing accuracy: Defective mirror and solar panels, recovery thanks to servicing mission 31
32 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 32
33 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 33
34 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 34
35 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) 35
36 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) 36
37 Satellite #6: SOHO, 1995 Objective: Solar exploration and space weather prediction 37
38 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 38
39 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! 39
40 40
41 Satellite #7: OUFTI-1, 2016 Objectives: 1. On-orbit validation of D-STAR 2. New solar cells Entirely designed by students Launched at the fourth attempt! Unknown failure three weeks after launch. 41
42 Satellite #7: Integration March, 2016
43 Satellite #7: Integration March, 2016
44 Satellite #7: Launch on April 25, 2016
45 OUFTI-1: Technical Data 45
46 OUFTI-1: Technical Data 46
47 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, 660 x 450 kms, i= 98 Launch vehicle Vega 47
48 ? 48
49 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 few cms several meters LEO, Halo orbit, asteroid pursuit, Martian, space exploration Soyuz, STS, Delta II, Titan III, Atlas II A 49
50 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 50
51 The Launch Vehicle May Also Fail! 51
52 From Dreams to Technical Challenges Space makes us dream What? How? Technical challenges! 52
53 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 53
54 Goldstone (70m) Madrid (70m) Canberra (70m) Deep space network: 3 ground stations (120 apart around the world ) ESA Redu ground station (Belgium) 54
55 Ariane V Vega Titan III Saturn V Soyuz Space Shuttle 55
56 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=
57 A Satellite Comprises Two Main Elements Payload: motivation for the mission Bus: necessary functions for the payload 57
58 Antennas: planet radio emissions Magnetometer PAYLOAD (CSL, AGO) Cosmic ray detector Plasma detector Photopolarimeter UV and IR spectrometers Cameras 58
59 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 59
60 POWER (THALES ALENIA SPACE) Radioisotope thermoelectric generator (RTG) Sun sensor ATTITUDE CONTROL (KERSCHEN) High-gain antenna Low-gain antenna TELECOMMUNICATIONS (VDB) 60
61 Louvers THERMAL CONTROL (Ulg-CSL) N 2 H 4 thrusters PROPULSION (KERSCHEN) Decagon, 0.6 m high 1.8 m diameter STRUCTURE (ESA) 61
62 ATTITUDE CONTROL (KERSCHEN) Star tracker MECHANISMS Box containing a deployable truss on 62 which the magnetometer is mounted
63 In Summary GROUND SEGMENT SPACE SEGMENT LAUNCH VEHICLE PAYLOAD BUS STRUCTURE & MECH. ATTITUDE CONTROL TELECOMMUNICATIONS PROPULSION POWER THERMAL CONTROL ON-BOARD COMPUTER 63
64 From Dreams to Technical Challenges Space makes us dream When? How? Technical challenges! 64
65 When? HISTORICAL PERSPECTIVE (NEXT LECTURE, SPACE INFORMATION CENTER) 65
66 From Dreams to Technical Challenges Space makes us dream Where? How? Technical challenges! 66
67 VOYAGER ULYSSES NEW HORIZONS MARS EXPRESS GIOTTO SOLAR ORBITER BEPI COLOMBO VENUS EXPRESS EARTH ORBIT SPACECRAFT ENVIRONMENT (CSL) Severe constraints (magnetic field, temperatures, atmosphere, launch vehicle, ground station visibility, eclipse duration) 67
68 LAGRAGE POINTS (NONLINEAR DYNAMICS!) BENIGN ENVIRONMENT: PLANCK, JAMES WEBB SPACE TELESCOPE GOOD FOR SUN OBSERVATION: SOHO STABLE: ASTEROIDS 68
69 HEO kms x 7000 kms: XMM GEO MEO kms: METEOSAT, GOES kms: Galileo kms: GPS SATELLITE ORBITS (KERSCHEN) GAP LEO 1447 kms x 354 kms: OUFTI kms: SPOT kms: HST 400 kms: ISS 250 kms: GOCE Circular Elliptic
70 Gap? Van Allen Belts SPACECRAFT ENVIRONMENT (CSL) 70
71 From Dreams to Technical Challenges Space makes us dream Why? How? Technical challenges! 71
72 Earth Observation: Weather Satellites Weather satellites see more than clouds: fires, pollution, sand storms Movie: GOES satellite 72
73 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 (CSL) Military satellites (resolution: on the order of 1cm!) -satellite-shootdown.html 73 KH-13
74 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) 74
75 GPS Constellation GPS 2R GPS constellation 75
76 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 (AGO) 76
77 Space Stations Perform science experiments under microgravity conditions MIR (Russia) ISS 77
78 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 78
79 Space Tourism: Inflatable Hotel! Experimental space habitat GENESIS
80 Entertainment Thanks to Space!
81 From Dreams to Technical Challenges Space makes us dream Who? How? Technical challenges! 81
82 Key Players NASA, JPL, Lockheed-Martin, Northrop-Grumman, Boeing Roscosmos, Energia ESA, CNES, DLR, ASI, EADS-Astrium, Arianespace,Thales Alenia Space Two emerging countries 82
83 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 83
84 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 84
85 From Dreams to Technical Challenges Space makes us dream What? How? Technical challenges! 85
86 Satisfy Customer s Basic Goals 1. Payload design 2. Mission analysis (orbit design and environment) 3. Bus design But the design of a satellite is associated with a number of unique challenges. 86
87 Challenge #1: Multidisciplinary Design 87
88 Challenge #1: Voyager Example POWER USING NUCLEAR MATERIALS Deep space mission POLITICAL PROBLEM ELECTRONICS (RADIATION) BUS (ADEQUATE CONFIGURATION) 88
89 Solution: 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 89
90 Challenge #2: Each Mission is Unique Where? & Why? 90
91 Solution: Fit the Requirements 91
92 Solution: Fit the Requirements Roll-out Whipple shield Hubble Stardust Body mounted Cruise & observation SSETI Express Solar Orbiter 92
93 Challenge #3: Orders of Magnitude What is Planck s coldest T? CSL 93
94 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 kms W 0.007
95 Challenge #3: Orders of Magnitude km/h km/h in 2 minutes 95
96 Challenge #3: Not Only the Satellite
97 Challenge #3: Not Only the Launcher Vehicle assembly building (KSC): 3.5 times the volume of the Empire State building Largest self powered land vehicle in the world 97
98 Solution: The Engineer Must Be Creative kms Communications: W Power: 15W/m 2 (Saturne) Nuclear materials 70-meter antenna
99 Challenge #4: Severe Constraints Planning (Voyager: once every 176 years) /kg Weight Volume Fuel Power (Voyager: 470 W) 99
100 Solution: The Engineer Must Be Creative Limited volume Deployable boom ( Voyager) Propergols constraints Gravity assist 100
101 Challenge #5: Harsh Environment Low temperatures + unknown Magnetism Rings Meteorites + cosmic ray + vacuum Hot temperatures Voyager did visit Jupiter, Saturn, Neptune and Uranus! 101
102 Solution: Develop New Technologies Thermal blanket (temperatures) Whipple shield against comet projections 102
103 Challenge #6: No Maintenance! For each spacecraft: 3 RTGs 2 x 8 thrusters 2 transceivers 2 computers 2 magnetometers Voyager 1 Voyager 2: backup (ultimate redundancy!) 103
104 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) 104
105 AERO0025 Satellite Engineering Introductory Lecture From Dreams to Technical Challenges 105
Contact details. Space Structures and Systems Lab (S3L) Structural Dynamics Research Group Aerospace and Mechanical Engineering Department
Welcome! 1 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)
Instructor Gaëtan Kerschen
Welcome! 1 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)
Instructor Gaëtan Kerschen
Welcome! 1 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)
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