From a phone call to a satellite orbiting Earth
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1 From a phone call to a satellite orbiting Earth Xavier Werner Space Structures and Systems Lab. Aerospace & Mechanical Engineering Dept. University of Liège
2 My background 2011: HELMo Gramme, Industrial engineer (electronics) : ULg, OUFTI-1 team member (COMM and payload) : ULg, Project Manager for OUFTI : ULg S3L, Research Engineer: nanosatellite design 2
3 Outline 1. Objectives 2. Space Segment 1. Payloads 2. Orbit and mission analysis 3. Platform 4. Protoflight model 3. Ground segment 4. What s next? 3
4 1. Objectives Decrease size, Increase interactions! 4
5 1. Objectives Primary Goal Hands-on satellite experience for students 5
6 1. Objectives Primary Goal Hands-on satellite experience for students Long-term Goal Series of CubeSats for scientific experiments Formation flying Granular materials 6
7 1. Objectives Primary Goal Hands-on satellite experience for students Long-term Goal Series of CubeSats for scientific experiments Short-term Goal Orbital Utility For Telecommunication Innovation 7
8 Outline 1. Objectives 2. Space Segment 1. Payloads 2. Orbit and mission analysis 3. Platform 4. Protoflight model 3. Ground segment 4. Unique experience for students 5. What s next? 8
9 2.1 Payloads D-STAR Digital-Smart Technology for Amateur Radio Simultaneous data and voice digital transmission Complete routing capacity, including roaming 3 frequencies and 2 data rates - VHF: 144 MHz (2m) 4.8 kbit/sec - UHF: 435 MHz (70cm) 4.8 kbit/sec - SHF: 1.2 GHz (23cm) 4.8 kbit/sec or 128kbit/sec Data : 1200 bps - Voice : 3600 bps Open protocol (! AMBE) GMSK modulation 9
10 2.1 Payloads D-STAR 3 types of communications: Direct visibility 10
11 2.1 Payloads D-STAR 3 types of communications: Repeater zone 11
12 2.1 Payloads D-STAR 3 types of communications: Internet roaming 12
13 2.1 Payloads D-STAR Directly through OUFTI-1 13
14 2.1 Payloads D-STAR Through OUFTI-1 and internet A Extension SAT Relais D-STAR Internet Relais D-STAR B 14
15 2.1 Payloads solar cells High-performance solar cells (30% GaAs triple junction) 15
16 Payloads More and more applications! Technology demonstration ( ) Imaging Communications Earth remote sensing Biology Re-entry Debris removal Security (AIS, ADS-B ) Deep Space 16
17 Outline 1. Objectives 2. Space Segment 1. Payloads 2. Orbit and mission analysis 3. Platform 4. Protoflight model 3. Ground segment 4. Unique experience for students 5. What s next? 17
18 2.2 Orbit and mission analysis CubeSats = secondary payloads Orbit imposed by primary payload Mission analysis = Analyze impact of this imposed orbit designed for Vega maiden flight 1447 x 354 km, i = 71 Very demanding! But finally: Soyuz VS x 683 km, i = 98 More comfortable! 18
19 2.2 Orbit and mission analysis 19
20 2.2 Orbit and mission analysis 20
21 2.2 Orbit and mission analysis 21
22 Outline 1. Objectives 2. Space Segment 1. Payloads 2. Orbit and mission analysis 3. Platform 4. Protoflight model 3. Ground segment 4. What s next? 22
23 2.3 Platform 23
24 2.3 Platform ADCS: requirements Payloads: no specific pointing requirement COMM: max 10 /s (avoid signal modulation) Mass, volume, and power constraints Passive control is sufficient! 24
25 2.3 Platform ADCS: passive magnetic A permanent magnet interacts with the geomagnetic field, producing a restoring torque, which align satellite axis with Earth s magnetic field. The spacecraft will oscillate around energy minima The oscillation are damped out by hysteretic rods. 25
26 2.3 Platform ADCS: orientation 26
27 2.3 Platform ADCS: final design 27
28 2.3 Platform ADCS: flight model 28
29 Surrey Space Center + Stellenbosch University Blue Canyon Technology ADCS State of the Art Actuators: - Magnetorquers - Reaction wheels Sensors: - Magnetometers - Star trackers - Sun/Earth sensors - Gyroscopes Pointing accuracy << 1 + propulsion (cold gas thrusters, pulsed plasma thrusters) 29
30 2.3 Platform COMM: requirements ITU: 30
31 2.3 Platform COMM: IARU All links must be located within the agreed ham band specific space allocations Coordination process 31
32 2.3 Platform COMM: frequency bands Uplink: 70-cm band (435 MHz, UHF) Downlink: 2-m band (145 MHz, VHF) 32
33 2.3 Platform COMM: 3 channels Payload: D-STAR (GMSK, 4800 bauds) TC/TM: AX.25 telecommunication protocol: simple and standard within the ham community 2FSK, 9600 bauds. Beacon: extreme reliability (Morse code). 33
34 2.3 Platform COMM: block diagram RX: 435 MHz TX: 145 MHz RF D-STAR AX.25 ADF 7021 Demod D-STAR Zone 1 et 2 ADF 7021 Demod AX.25 MSP430 Codec D-STAR Data MSP430 OBC TC/TM Processing ADF 7021 Modulation AX.25 / D-STAR RF BEACON 42
35 2.3 Platform COMM: low-gain antennas Two monopole (quarter-wave) antennas : 17 and 50 cm 43
36 2.3 Platform COMM: low-gain antennas Two monopole (quarter-wave) antennas : 17 and 50 cm Too short! (non-radiating parts) Re-dimensionning Impact on MECH 44
37 2.3 Platform COMM: propagation 45
38 2.3 Platform COMM: prototypes 46
39 2.3 Platform COMM: flight model 47
40 COMM: State of the art Mainly VHF & UHF S-band X-band (COTS available) Limitations: licensing, power, ground segment Inter-satellites link ISIS 48
41 2.3 Platform EPS: requirements Defined by other subsystems Power needed by client Voltage required by hardware Influenced by orbit Eclipse duration Influenced by the mission Payload operation Power budget 50
42 2.3 Platform EPS: block diagram Power Source Power Storage Unit Power Conditioning Unit Users 51
43 2.3 Platform EPS: solar cells GaInP/GaAs/Ge on Ge substrate Triple junction solar cells At 28ºC 52
44 2.3 Platform EPS: solar arrays 53
45 2.3 Platform EPS: 2 Kokam batteries Kokam SLB H 54
46 2.3 Platform EPS: batteries test 55
47 2.3 Platform EPS: batteries support 56
48 2.3 Platform EPS: conditioning Direct energy transfer Choice of unregulated bus with three DC/DC converters: 5 V redundant 3,3 V Design validated by Thales Alenia Space ETCA 57
49 2.3 Platform EPS: engineering model MECH circuit MHP protection MHP ( T, V, I ) Dissipation system Battery-charger module Solar cells protection Battery protection module 5V 3,3 V (A) 3,3 V (B) 58
50 2.3 Platform EPS: flight model 59
51 EPS: State of the art High efficiency solar cells (28-30 % efficiency) Li-Ion batteries (200 Wh/kg) MPPT: Maximum Power Point Tracking 60
52 2.3 Platform MECH: requirements CubeSat Design Specification: All deployables such as booms, antennas, and solar panels shall wait to deploy a minimum of 30 minutes after the CubeSat s deployment switch(es) are activated from P-POD ejection. Antennas are wound around a guide before deployement Dyneema retention wire is used Retention wire is melted by a thermal knife 61
53 2.3 Platform MECH: flight model ULg JL Wertz 62
54 Credit: Alessandra Babuscia Antenna State of the art Mostly burned wire and spring material Patch antennas for higher frequencies (S, X) Inflatable devices under development 63
55 2.3 Platform OBC: hardware Reliability and simplicity One central processor, handles all tasks Doubled for redundancy: only one active at a time Periodic «heartbeat» signal Texas Instruments MSP430 I/Os 64
56 2.3 Platform OBC: software 65
57 2.3 Platform STRU: launch environment 66
58 2.3 Platform STRU: requirements accelerations, low frequencies 67
59 2.3 Platform STRU: requirements Engines, wind ; high frequencies 68
60 2.3 Platform STRU: requirements Engines, turbulences Fairing jettison, stages separation 69
61 2.3 Platform STRU: models vs reality 70
62 2.3 Platform STRU: models vs reality Modes 1 & 2 71
63 2.3 Platform STRU: electronic cards 72
64 STRU State of the art Aluminum COTS or homemade structures, very similar Composites, 3D printed 3U, 6U, 12U and more 73
65 2.3 Platform THER: requirements 74
66 2.3 Platform THER: hot and colds cases 75
67 2.3 Platform THER: measurements Determination of the frame contact resistance: face 6 is heated up Face 1 Face 3 76
68 2.3 Platform THER: measurements 77
69 2.3 Platform THER: analysis (cold) Battery is too cold! 78
70 2.3 Platform THER: analysis (hot) 79
71 2.3 Platform THER: analysis (hot) Hot spot due to dissipation transistor! 80
72 2.3 Platform THER: thermal control The available surface on the satellite panels is very limited. Difficult to control the overall energy balance between the spacecraft and its environment. 81
73 2.3 Platform THER: conductive links Thermal control can be achieved by an appropriate study and design of the conductive links within the satellite. Copper angle bracket 82
74 2.3 Platform THER: conductive links 83
75 2.3 Platform THER: batteries issue 84
76 2.3 Platform THER: active control Heaters + Thermostats 1 heater per battery 2 x 250mW patch heaters x 35.6 mm Mechanical thermostats 2 thermostats per battery, in series 7.2 C 23.9 C 85
77 2.3 Platform THER: tests POM spacers 86
78 THER State of the art Passive means (MLI, coating, cold finger, ) Heaters for sensitive equipment 87
79 2.3 Platform Configuration UHF antenna Thermal knives VHF antenna Pumpkin structure Solar cells COMM Beacon Batteries EPS MAIN OBC BACKUP OBC (FM430) 88
80 Outline 1. Objectives 2. Space Segment 1. Payloads 2. Orbit and mission analysis 3. Platform 4. Protoflight model 3. Ground segment 4. What s next? 89
81 2.4 Protoflight model: philosophy Engineering model qualification tests + Flight model acceptance tests + Space Protoflight model protoflight tests + Space (= qualification levels with acceptance duration) 90
82 2.4 Protoflight model
83 2.4 Protoflight model Write, test, and correct integration procedures Perform integration at Centre Spatial de Liège (CSL) of ULg
84 2.4 Protoflight model: TVC Tests at ESA/ESTEC thanks to ESA Fly Your Satellite! program ESA 93
85 2.4 Protoflight model: TVC 94
86 2.4 Protoflight model: vibration tests Tests at ESA/ESTEC thanks to ESA Fly Your Satellite! program 95
87 2.4 Protoflight model: vibration tests
88 2.4 Protoflight model: vibration tests 97
89 2.4 Protoflight model: X-rays EM X-rays at ESA/ESTEC thanks to ESA Fly Your Satellite! program FM 98
90 2.4 Protoflight model: ready for launch! 99
91 2.4 Protoflight model: P-POD integration 100
92 2.4 Protoflight model: on ASAP-S 101
93 2.4 Protoflight model: Launched! Soyuz Flight VS14 Centre Spatial Guyanais, Kourou 25 April
94 2.4 Protoflight model: signal received > 500 Beacon messages received from HAM operators 103
95 Outline 1. Objectives 2. Space Segment 1. Payloads 2. Orbit and mission analysis 3. Platform 4. Protoflight model 3. Ground segment 4. What s next? 104
96 3. Ground segment TC / TM channel (AX.25) User channel (D-STAR) Mission Control Center Ground Station 12:05:49 TCP / IP Satellite Extension D-Star Repeater Control segment D-STAR segment 105
97 3. Ground segment UHF Antenna VHF Antenna el az H V H V Rotators controller Phasing line Phasing line FM UHF FM VHF Tracking card CI-V UHF/VHF Transceiver 12:05:49 Pointing data Control AX.25 Mission Control Center TCP / IP Serial Data GS computer Ground Station TNC 106
98 3. Ground segment OUFTI-1 Duplexer Duplexer Tracking System Tx Rx Tx Rx VHF module UHF module UHF/VHF Transceiver Controller D-STAR mod/demod Gateway Internet D-Star Repeater Satellite extension 107
99 Outline 1. Objectives 2. Space Segment 1. Payloads 2. Orbit and mission analysis 3. Platform 4. Protoflight model 3. Ground segment 4. What s next? 108
100 4. What s next? OUFTI-2 1U CubeSat Design improvements based on experience 3 payloads: D-STAR (OUFTI-1 mission) RAD IMU (Sint Pieterscollege Jette, Belgium) 109
101 4. What s next? OUFTI-2 Main payload: D-STAR Digital Smart Technologies for Amateur Radio Digital radio protocol 2 modes : DV (Digital Voice) : Voice + data (145MHz, 435MHz et 1.2GHz) DD (Digital Data) : Data only (1.2GHz) 2 A Extension SAT Relais D-STAR Internet Relais D-STAR B 110
102 4. What s next? OUFTI-2 Secondary payload: RAD Degradation of electronical components by radiations Same experience 3 different shieldings Dose measured by a RADFET 111
103 4. What s next? OUFTI-2 Secondary payload: IMU Developed by secondary school students Free access to space thanks to OUFTI-2 112
104 4. What s next? OUFTI-Next! Smart irrigation strategy of agricultural fields Possibility to detect lack of water by monitoring the leaf surface temperature 69% of water used for agriculture 40% of the fields are irrigated high potential applications 13/12/2017 Satellite Engineering - Nanosatellites 113
105 4. What s next? OUFTI-Next! 50m resolution Daily revisit (constellation) Mid-wave IR 13/12/2017 Satellite Engineering - Nanosatellites 114
106 4. What s next? OUFTI-Next! Mid-wave IR Several days revisit 100m resolution 3U CubeSat Proof of concept + testing payload Credit to ISIS 13/12/2017 Satellite Engineering - Nanosatellites 115
107 Students involvement : 2 master thesis Feasibility studies (payload and platform) : 7 master thesis Thermal aspects (global and sensor) Attitude control Optics (reflective and refractive) Optics: Fresnel lens System 13/12/2017 Satellite Engineering - Nanosatellites 116
108 Thank you for your attention 117
From a phone call to a satellite orbiting Earth
From a phone call to a satellite orbiting Earth Xavier Werner Space Structures and Systems Lab. Aerospace & Mechanical Engineering Dept. University of Liège My background 2011: HELMo Gramme, Industrial
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