Satellite Engineering PROBA Family
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1 Satellite Engineering PROBA Family Julien Tallineau A presentation to: ULg 09/12/2013 Ir. Julien Tallineau Satellite System Engineer Tel: (general) Tel: (direct) Fax: Julien.tallineau@qinetiq.be Copyright QinetiQ Limited 2012 QinetiQ Proprietary 1
2 0 TABLE OF CONTENT 1. INTRODUCTION 2. PROBA APPROACH 3. PROBA SATELLITE 4. PROBA CASE STUDY 5. CONCLUSION & OPPORTUNITIES 2
3 1 INTRODUCTION 3
4 1 INTRODUCTION What is a small satellite for the industry? 4
5 1 INTRODUCTION What is a small satellite for the industry? ANSWER = A product you can sell for a given price to a customer! NB: small satellite does not have so much of a meaning for industry because they classify their platform not with respect to mass but with respect to application (Sun Imaging, Earth Imaging, ) or product line (P-100; P-200; P-500) 5
6 1 INTRODUCTION What is the price of small satellite? 6
7 1 INTRODUCTION What is the price of small satellite? ANSWER = Varies from 5M up to 300M NB: one shot satellite like Hubble or SOHO is not interesting for the industry. 7
8 1 INTRODUCTION How much profit do you make? ANSWER FOR ESA = 8% Profit is allowed by ESA NB: one shot satellite like Hubble or SOHO is not interesting for the industry. 8
9 1 INTRODUCTION How much profit do you make? ANSWER FOR COMMERCIAL CUSTOMER = Easily 20% with good negociation skills, political environment and the competitor prices NB: one shot satellite like Hubble or SOHO is not interesting for the industry. 9
10 1 INTRODUCTION Mandatory ECSS Usefull ECSS 10
11 1 INTRODUCTION 11
12 1 INTRODUCTION 12
13 1 INTRODUCTION Satellite Engineering 1. Customer Need (Scientist) 2. Creation of System Requirements 3. Phase 0 (CDF Study) 4. Phase A (Feasibility Study) 5. Phase B (Preliminary Design) 6. Phase C (Final Design) 7. Phase D (Manufacturing / Testing) 8. Phase E (Launch / Commissionning & Operations) 9. Phase F (De-orbiting) 13
14 1 INTRODUCTION Satellite Engineering 1. Customer Need (Scientist) 2. Creation of System Requirements 3. Phase 0 (CDF Study) 4. Phase A (Feasibility Study) 14
15 1 INTRODUCTION Satellite Engineering 5. Phase B (Preliminary Design) Detailed System Analysis Preliminary Subsystem Analysis Trade-offs 6. Phase C (Final Design) Detailed Subsystem Analysis Procurement Qualification Testing 15
16 1 INTRODUCTION Satellite Engineering 7. Phase D Manufacturing Acceptance Testing Requirement Verification Shipment to Launch site 16
17 1 INTRODUCTION Satellite Engineering 8. Phase E Launch Commissionning Operations 9. Phase F (De-orbiting/End of Life) None in this case 17
18 2 PROBA APPROACH 18
19 2 PROBA APPROACH PROBA Philosophy PRoject for On-Board Autonomy (PROBA) Missions In Orbit Demonstration PROBA-1 PROBA-2 Earth Observation ESA Low Cost Platform PROBA-V PROBA-ALTIUS 19
20 2 PROBA APPROACH LightSat Approach In-Orbit Demonstration (IOD) aiming at - Demonstrating new techniques that could lead to new space system - Reduced cost Drastic reduction of the number of requirements Keep the system as simple as possible with only limited inter-dependencies Accept higher level of risk MAXIMUM RE-USE 20
21 2 PROBA APPROACH Satellite Engineering Tools 1. Requirement Management Tool (DOORS) 2. Mission Analysis Tool (MATLAB) Orbit propagator (J2, Drag, Third Body, SRP) Attitude Control (Magnetic, Nadir, Sun, Target) Incoming fluxes Ground Stations Visibility In orbit Maintenance In orbit Manoeuvring 21
22 2 PROBA APPROACH Satellite Engineering Tools 1. Thermal Analysis Tool (ESATAN-TMS) 2. Configuration Tool (IRON-CAD/PRO-E) IRON-CAD allows for fast iteration PRO-E is similar to CATIA 3. Structural Analysis Tool (NASTRAN) 22
23 3 PROBA SATELLITES PROBA 1 PROBA 2 PROBA 3 PROBA ALTIUS PROBA V PROBA IT VIETNAM SAT 23
24 3 PROBA SATELLITES PROBA 1 PROBA 2 PROBA 3 PROBA ALTIUS PROBA V PROBA IT VIETNAM SAT 24
25 3 PROBA - 1 PROBA 1 Mission 25
26 3 PROBA - 1 Mission 1. In-orbit demonstration and evaluation of new hardware/software spacecraft technologies and onboard operational autonomy 2. Obrital Parameter 3. Injection Parameter 26
27 3 PROBA - 1 Mission 1. RAAN selected for 10:00 Local Time Descending Node. 27
28 3 PROBA - 1 Mission 1. Launcher is PSLV Nominal separation rate of 2 per sec. Worst Case separation rate of 8 per sec. Inclination accuracy of 0.2 Altitude accuracy of 35km 2. Radiations of 9 krad for 3 years mission Solar maximum is considered 3.5mm of Aluminium considered 28
29 3 PROBA - 1 Mission 1. Ground segment visibility (REDU) 30% of all orbits have contact with the ground station (duration > 0 minutes) more than 6 minutes 10.88% more than 8 minutes The longest time between two passes over the ground station is 11hr 44 min 29
30 3 PROBA - 1 Mission 1. Scenario Launch and Early Operation Phase (LEOP) Boot after separation & De-tumbling First Ground Contact + AOCS/GPS switched ON Commissioning (two months) Nominal Autonomy High Flexibility Nominal Operations High Autonomy 30
31 3 PROBA - 1 Satellite Design - Configuration 1. Single H Structure 2. High Unit Density 3. Body Mounted Solar Panel 4. Cut out in panels: Star-Trackers Instruments 31
32 3 PROBA - 1 Satellite Design - Structure 1. Honeycomb panels Aluminium core Aluminium edge Alumiunium facesheet (Primary structure) CFRP facesheet (Secondary structure) 32
33 3 PROBA - 1 Satellite Design - Mechanics 1. Spacecraft Mass = 95 kg 2. Balance Mass of 2.5kg for CoG Location Requirement 33
34 3 PROBA - 1 Satellite Design - Power 1. Power budget approach could be: Rely on Solar Array (SA) in Sun and on Battery in Eclipse Rely on both Battery and SA when available. 2. Power budget is positive, independently of the scenario. 34
35 3 PROBA - 1 Satellite Design RF COM 1. Downlink (S-Band) Flux margin of 7dB (@max rate = 1Mbps) Flux margin of - 2dB (@min rate = 250kbps) Telemetry Recovery margin of 8dB 2. Uplink (S-Band) Carrier Recovery margin of 26dB Telecommand Recovery margin of 17dB 35
36 3 PROBA - 1 Satellite Design Thermal 1. Passive thermal control Thermal Blankets + MLI Black paint (internal panel+electronic box) 36
37 3 PROBA - 1 Satellite Design Data & memory 1. One Image sequence can be stored before next downlink Mass Memory size = 1Gbit Image sequence size = 5 image x 19 spectral lines x 742 spatial lines x 9 kbit/line = 665 Mbit. 2. Data downlinked = 1140Mbit every 12 hours Max data rate Time 1300sec (Total Ground Visibility) 37
38 3 PROBA - 1 GPS RX km km km Position determination
39 3 PROBA - 1 Magnetometer (2) Measure continuously the Earth Magnetic field and determine itselve where the North is. N Z Position determination
40 3 PROBA - 1 Star-Tracker (3) Takes pictures of stars Compare it with its internat catalog. Compute the satellite orientation/position Orientation/Position
41 3 PROBA - 1 Magnetotorquer (4) Z N N Magnetic Coil Align itself to Magnetic lines Z Orientation/Manoeuvre
42 3 PROBA - 1 Rection Wheel (4) Accelerates or decelerates while momentum conservation implies the PROBA to rotate the other way. Orientation/Manoeuvre
43 3 PROBA - 1 Satellite Design AOCS 1. Guidance = determination of the desired path of travel from the satellite's current location to a designated target GPS Receiver 2. Navigation AOCS Software = determination of the satellite s location, velocity and attitude 3. Control = manipulation of the forces needed to track guidance commands while maintaining satellite stability Head Head Star Tracker (2) Magnetometers (2) - Navigation -Guidance -Control Reaction Wheels (4) Magnetotorquers (4) 43
44 3 PROBA - 1 Satellite Design AOCS ( Pointing Modes) Inertial Pointing Earth Pointing Point and Stare Scanning Modes Inertial pointing Sun Pointing Utilisation: Astronomy Solar Physics On-track Off-track Utilisation: Earth Observation Telecommunications Space Weather On-track Off-track Utilisation: High Resolution Imaging Elevation Modeling Disaster Monitoring Motion compensation Multiple scans 44
45 3 PROBA - 1 Satellite Design AOCS 1. Specifications Errors at 95% confidence level Absolute Pointing Error (APE) Relative Pointing Error (RPE) Absolute Measurement Error (AME) 100 arcsec 5 arcsec over 10 s 10 arcsec 2. AOCS SW Modes Quiscient Magnetic Celestial Terrestrial Quiscient Mode - No AOCS - Most units are OFF 45
46 3 PROBA - 1 Satellite Design AOCS 1. Specifications Errors at 95% confidence level Absolute Pointing Error (APE) Relative Pointing Error (RPE) Absolute Measurement Error (AME) 100 arcsec 5 arcsec over 10 s 10 arcsec 2. AOCS SW Modes Quiscient Magnetic Celestial Terrestrial Magnetic Mode - Sensor: magnetometer - Actuator: magnetotorquers + 1 RW stby (momentum bias) - Guidance: No - Navigation: No - Control: Bdot Algorithms (Kinetic Energy Dumping) 46
47 3 PROBA - 1 Satellite Design AOCS 1. Specifications Errors at 95% confidence level Absolute Pointing Error (APE) Relative Pointing Error (RPE) Absolute Measurement Error (AME) 100 arcsec 5 arcsec over 10 s 10 arcsec 2. AOCS SW Modes Quiscient Magnetic Celestial Terrestrial Celestial Mode - Sensor: Star-tracker + Magnetic mode sensors - Actuator: Reaction Wheels + Magnetic mode actuatord - Guidance: Sun pointing, Inertial pointing - Navigation: Attitude and Orbit evaluator (Kalman Filter) - Control: State feedback, PID, angular momentum control 47
48 3 PROBA - 1 Satellite Design AOCS 1. Specifications Errors at 95% confidence level Absolute Pointing Error (APE) Relative Pointing Error (RPE) Absolute Measurement Error (AME) 100 arcsec 5 arcsec over 10 s 10 arcsec 2. AOCS SW Modes Quiscient Magnetic Celestial Terrestrial Terrestrial Mode - Sensor: GPS + celestial mode sensors - Actuator: Same as Celestial mode - Guidance: Nadir, Fixed-target pointing, Imaging scans - Navigation: Same as Celestial mode - Control: Same as Celestial mode 48
49 3 PROBA - 1 Launched on the 22/10/2001 from India 49
50 3 PROBA - 1 LEOP Activities 1. Rotating Energy is dissipitated progressively using the magneto-torquers. 1,4E-02 (rad/sec) 2 Square angular rate 1,2E-02 1,0E-02 8,0E-03 6,0E-03 4,0E-03 2,0E-03 Five hours to detumble! 0,0E+00 0,00 1,00 2,00 3,00 4,00 5,00 6,00 50
51 3 PROBA - 1 Normal Operations Activities Ile de Ré, France 51
52 3 PROBA - 1 Normal Operations Activities Etna eruption, Sicily,
53 3 PROBA - 1 Normal Operations Activities North Sentinel Island India,
54 3 PROBA - 1 Normal Operations Activities Palm Island Dubai 54
55 3 PROBA - 2 PROBA 2 Mission 55
56 3 PROBA - 2 Mission 1. In orbit Demonstration, PROBA-2 aimed at technological innovation. Altogether, 17 new technological developments and four scientific experiments are being flown on Proba Orbital Parameter 56
57 3 PROBA - 2 Mission 1. RAAN selected for 6:00 AM Local Time Ascending Node 57
58 3 PROBA - 2 Mission 1. Launcher is Rockot Worst Case separation rate of 8 per sec. Inclination accuracy of 0.05 Altitude accuracy of 12km RAAN accuracy of 3.75 ( 15min LT) 2. Injected via the Breeze upper stage 58
59 3 PROBA - 2 Mission 59
60 3 PROBA - 2 Mission 1. Ground segment visibility REDU KIROUNA 60
61 3 PROBA - 2 Mission 1. Scenario LEOP Commissioning (three months) Nominal Operations 2. Spacecraft Modes Separation Safe Observation Stand-by 61
62 3 PROBA - 2 Mission 62
63 3 PROBA - 2 Satellite Design - Configuration 1. Single H Structure 2. Sun Shield Standard STR Bepi-Colombo STR 3. High Unit Density 4. Deployable Solar Panel (x2) 63
64 3 PROBA - 2 Satellite Design - Mechanics 1. Spacecraft Mass = kg 2. CoG Choice Folded Configuration (LV requirement) Deployed Configuration (GNC requirement) NB: LV I/F Ring Mass included 64
65 3 PROBA - 2 Satellite Design - Power 1. Power budget is positive, independently of the mode Observation (w/o TX) Observation with TX Safe mode with TX (worst Beta-angle). Definition Beta Angle = angle between the Sun-Earth vector and the orbital plane. β = 90 implies max sunlight time β = 0 implies min sunlight time 65
66 3 PROBA - 2 Satellite Design - Power 66
67 3 PROBA - 2 Satellite Design - Power 67
68 3 PROBA - 2 Satellite Design Power 1. Battery DoD (Ah) in function of time 2. Non Regulated bus 28V 68
69 3 PROBA - 2 Satellite Design - Power 1. Power budget while de-tumbling! 2. Trade-off between: Performance (GNC) Time (LEOP schedule) Battery Discharge (Higher DoD) 69
70 3 PROBA - 2 Satellite Design - Avionics 1. System is fully redundant 2. Data & Power centralized (ADPMS) 3. Interface Unit AOCS Module Deployment Module Propulsion Module Thermal Control Module 70
71 3 PROBA - 2 Satellite Design RF COM 71
72 3 PROBA - 2 Satellite Design Data & Processing 1. Processing budget shows how busy is the processor with all the units + instruments. On Software Verification Facility On S/C during System Validation Test 5 72
73 3 PROBA - 2 Satellite Design AOCS 1. Low power resistojet (Xenon) 15W for heater (x2) 50s Isp (min) 20mN Thrust Total V = 2m/s 73
74 3 PROBA - 2 Satellite Design AOCS 1. Sensors 2 Star-tracker 2 GPS RX 2 Magnetor-Meter 2. Actuators 4 Reaction Wheels 3 dual-coil magneto-torquer 74
75 4 CASE STUDY: PROBA-3 The Mission Phase A Phase B 75
76 3 PROBA - 3 Mission 1. The PROBA-3 mission will provide an opportunity to validate and develop The Metrology and Actuation techniques / technologies The Guidance strategies and Navigation and Control algorithms necessary for formation flying. 2. One mission, two spacecrafts: Coronagraph S/C (CSC) Occulter SC (OSC) 76
77 3 PROBA - 3 Mission 1. High Elliptical Orbit (HEO) with 20 hours period Low perturbation in Apogee Low AoP drift (fixed above REDU) Limited Eclipse duration Radition Issue Stringent Constraint on RF Link Delta-V issue. Parameter Value Orbit type HEO Perigee altitude 600km Apogee altitude 60530km Inclination 59 Eccentricity AoP 188 RAAN 173 Epoch Jan 2017 Formation 3km 77
78 3 PROBA - 3 Possible Launchers 1. PSLV Launcher Low Cost Heritage from PROBA-1 Reduced Volume 2. Falcon 9 Launcher High Cost Higher Performance Large Volume No Heritage PSLV Falcon 9 78
79 3 PROBA - 3 Which one of the two shall you design your Spacecraft for? 79
80 3 PROBA - 3 Which one of the two shall you design your Spacecraft for? ANSWER = The Two! But it is up to ESA + Delegates to decide the mission budget 80
81 3 PROBA - 3 What would you put in your spacecraft? 81
82 3 PROBA - 3 What would you put in your spacecraft? Subsystem Design Structure Aluminium/CFRP/Invar/Titanium? Thermal Passive/Active? Mechanism Body Mounted/Deployable SA? Power Large/Small SA? Large/Small Battery? GNC RF Sensor? Actuator? High/Low Gain COM Antenna? High/Low Gain FF Antenna? 82
83 3 PROBA - 3 Welcome in Phase A! 83
84 3 PROBA 3 Phase A Outcome of Phase A is our STARTING POINT 1. Configuration 2. Mass 3. Power 4. Avionics 5. Thermal 6. Propulsion 7. Link & Data 8. Payload 84
85 3 PROBA 3 Phase A Coronagraph Satellite Overview 1. From Top 2. From Bottom 85
86 3 PROBA 3 Phase A Coronagraph Satellite Overview 1. From Back Left 2. From Back Right 86
87 3 PROBA 3 Phase A Coronagraph Satellite Overview 1. From Front 2. From Inside 87
88 3 PROBA 3 Phase A Coronagraph Satellite Overview 1. Mass Budget Total CSC dry mass including I/F ring with L/V shall be less than 360kg (with margins). Current estimate: kg 2. Power Budget Total CSC maximum power consumption shall be less than 294W (with margins) Current estimate: W 88
89 3 PROBA 3 Phase A Coronagraph Satellite Overview 1. Avionics Centrilized around Advance Data & Power Management System (ADPMS) Support of Interface Electronics PROBA-V ADPMS Flight Model 89
90 3 PROBA 3 Phase A Coronagraph Satellite Overview 1. Thermal Solar array temperature range (-169 C to +79 C). Battery operational temperature range: -10 C minimum operational temperature +40 C maximum operational temperature Star Tracker detector maximum operational temperature Current prediction: 40 C Required: 15 C 90
91 3 PROBA 3 Phase A Coronagraph Satellite Overview 1. Propulsion System (HPGP) Scheme 91
92 3 PROBA 3 Phase A Coronagraph Satellite Overview 1. Propulsion System (HPGP) Scheme What is the cost? 92
93 3 PROBA 3 Phase A Coronagraph Satellite Overview 2. Propulsion System (HPGP) 2x4 thrusters to raise orbit Constrains Pre-warming needs 64W (=2x4x8W) during 30 min Propellant needs to be kept above 10 C (Always) Performance Isp = 202 EoL Thrust = 1N 93
94 3 PROBA 3 Phase A Coronagraph Satellite Overview 3. Propulsion System (Cold Gas) Siwteen thruster for GNC and FF Performance 94
95 3 PROBA 3 Phase A Coronagraph Satellite Overview 1. GNC Sensors 6 Sun Acquisition Sensors 2x3 Gyros 2x3 Acceleromter 3 Star Trackers Head + 2x1 Electronics 2x1 GPS 3. GNC FF Omni-directional RF Sensor (FFRF) Coarse Lateral Sensor Fine Formation Sensor 2. GNC Actuators 3+1 Reaction Wheels Cold Gas thrusters 95
96 3 PROBA 3 Phase A Coronagraph Satellite Overview 1. RF Scheme 96
97 3 PROBA 3 Phase A Coronagraph Satellite Overview 1. Link Budget The CSC shall be able to downlink data at a symbol rates of 256ksps and 2Msps using REDU-3 Ground Station The CSC shall be able to receive TC data at a symbol rates of 64ksps using REDU-3 Ground Station Current estimation: Downlink not closed for 2Msps (@apogee) Uplink not closed for 64ksps (@apogee) 97
98 3 PROBA 3 Phase A SUMMARY 1. Satellite is too heavy 2. Satellite is too power consuming 3. Satellite is too hot or too cold 4. Satellite is too far to close its downlink and uplink 5. Satellite is too far to downlink its science data 6. Satellite is too un-protected wrt radiations (20krad under 2mm Al) 98
99 3 PROBA - 3 What can we do? 99
100 3 PROBA 3 Phase A ANSWER 1. Mass & Power reduction exercise 2. Perform a detailed thermal analysis Active control Electronics Location Radiator size 3. Review Operation concept for U/D link 4. Increase Satellite Shielding + MINIMIZE THE COST! 100
101 3 PROBA - 3 Welcome in Phase B! 101
102 3 PROBA 3 Phase B Mass reduction 1. Who are the biggest contributors? 102
103 3 PROBA 3 Phase B Mass reduction 1. Who are the biggest contributors? Structure Formation Flying Propulsion System Payload 103
104 3 PROBA - 3 What can we do? 104
105 3 PROBA 3 Phase B Mass reduction 1. Structure Shield the spacecraft with outer panels! Remove materials in the Bottom Board! Remove two panels while re-arranging structure Shorten the satellite Consider LV I/F ring as part of system mass margin 2. GNC & Propulsion Remove the Accelerometer Remove Cold Gas Propulsion System (Transfer to OSC) Include 2x4 additional HPGP thruster for 6DoF 105
106 3 PROBA 3 Phase B Mass reduction results 1. Structure has been reinforced (corner bracket) Honeycomb Al-Al-Al (Primary & Secondary Structure ) Honeycomb CFRP-Al-CFRP (Solar Cells accommodation) 2. Satellite has better shielding 3. Mass has decreased to 318kg 106
107 3 PROBA 3 Phase B Power reduction 1. Who are the biggest contributors? Thermal control = 91W (due to propellant thermal constraint) Propulsion (HPGP) = 128W (16x8W after the mass reduction) Payload = 40W (pre-warming) Reaction Wheel = 42W (when 3 accelerating + 1 constant speed) 2. Still to be included within the 294W 30% 43% 13% 13% 99% STR / Gyro / GPS / RF systems / On-Board Computer / Propulsion Electronics / 107
108 3 PROBA 3 Phase B Power reduction 1. Who are the biggest contributors? Thermal control = 91W (due to propellant thermal constraint) Propulsion (HPGP) = 128W (16x8W after the mass reduction) Payload = 40W (pre-warming) Reaction Wheel = 42W (when 3 accelerating + 1 constant speed) 2. Still to be included within the 294W 30% 43% 13% 13% 99% STR / Gyro / GPS / RF systems / On-Board Computer / Propulsion Electronics / What would do a good system engineer? 108
109 3 PROBA 3 Phase B Power reduction 1. Thermal Control Satellite wrapped into MLI Electronics as close as possible to cold points 2. Propulsion Only half of thruster pre-warmed + duty cycle Only less than half the power is given at the same time (longer pre-warming!) 109
110 3 PROBA 3 Phase B Power reduction 1. Thermal Control reduced to 75W (instead of 91W) 2. Propulsion reduced to 33,6W (instead of 128W) 3. Payload reduced to 10W (instead of 40W) 110
111 3 PROBA 3 Phase B Power reduction 1. Thermal Control reduced to 75W (instead of 91W) 2. Propulsion reduced to 33,6W (instead of 128W) 3. Payload reduced to 10W (instead of 40W) What is the next step? 111
112 3 PROBA 3 Phase B Electrical Architecture 1. Power Generation & Storage Solar Array Battery 2. Power Conditioning Distribution Unit ADPMS 3. Connections Safe & Arm Umbilical Connection 112
113 3 PROBA 3 Phase B Solar Array Design 1. Main components Cells Series (TBD) String Parallel (TBD) 6xSection (TBD strings) 2. Secondary components Shunt Selection Dump Resistor 113
114 3 PROBA 3 Phase B Solar Array Design 1. Main components How can we calculate this? Cells Series (TBD) String Parallel (TBD) 6xSection (TBD strings) 2. Secondary components Shunt Selection Dump Resistor 114
115 3 PROBA 3 Phase B Solar Array Design (3G28%) 1. Evaluate the degradation? Coverglass thickness Degradation of Electrical Parameters Degradation of Temp. Coefficient 115
116 3 PROBA 3 Phase B Solar Array Design (3G28%) 1. Evaluate the degradation? Coverglass thickness Degradation of Electrical Parameters Degradation of Temp. Coefficient 116
117 3 PROBA 3 Phase B Solar Array Design 2. Evaluate the number of cells? Max battery voltage to be provided (29.4V) Compute all voltage drop Compute number of cells (MPP) 18 Cells / Strings 117
118 3 PROBA 3 Phase B Solar Array Design 3. Evaluate the number of strings? Max current allowed by ADPMS (12A) Compute string current EoL ( di/dt < 0) Minimum Solar Cste (di/dc > 0) Operating temperature (di/dt>0 but du/dt<<0) Operating point 118
119 3 PROBA 3 Phase B Solar Array Design 3. Evaluate the number of strings? Max current allowed by ADPMS (12A) Compute string current EoL ( di/dt < 0) Minimum Solar Cste (di/dc > 0) Operating temperature (di/dt>0 but du/dt<<0) Operating point 23 (+1) Strings 119
120 3 PROBA 3 Phase B Solar Array Design 4. Evaluate the Power available? Power = Current * Voltage 1 String Failure Tolerance 120
121 3 PROBA 3 Phase B Solar Array Design 4. Evaluate the Power available? Power = Current * Voltage 1 String Failure Tolerance 121
122 3 PROBA - 3 What if GNC has a failure? 122
123 3 PROBA - 3 What if GNC has a failure? ANSWER = Needs to be taken into account if pointing accuracy of SUN POINTING is decreased! 123
124 3 PROBA 3 Phase B Battery Design 1. Main components Cells Series (TBD) String Parallel (TBD) 2. Secondary components Internat heaters Thermistors 124
125 3 PROBA 3 Phase B Battery Design 1. Main components How can we calculate this? Cells Series (TBD) String Parallel (TBD) 2. Secondary components Internat heaters Thermistors 125
126 3 PROBA 3 Phase B Battery Design 1. Evaluate the number of cells? Nominal non regulated bus voltage (28V) Cells characteristics (4.2V EoC) 7 Cells / String Cell Level EMF (V) Discharge EMF State of Charge (%) Charge EMF 126
127 3 PROBA 3 Phase B Battery Design 2. Evaluate the number of strings? Approach decision Battery for both Sun & Eclipse Battery for Eclipse only Check Power Budget (Wst Case) Detumbling (200W / 1hr) Eclipse (240W / 30min) Long Eclipse (190W / 3.5hrs) 127
128 3 PROBA 3 Phase B Battery Design 2. Evaluate the number of strings? Capacity used = Power * Time Capacity required = Capacity Used /(1-DoD Allowed ) Capacity of 1 string = Nb Cells *Capacity Cell One String Failure Tolerance Scenario Used Capacity (Wh) Detumbling 200 Eclipse 120 Long Eclipse 665 Scenario DoD choice Required Capacity (Wh) Detumbling 20% 240 Eclipse 20% 148 Long Eclipse 60% (+1) Strings Parameter Value Nb Cells 7 Capacity Cell 5,4 Wh Capacity 1 string 37,8 Wh 128
129 3 PROBA 3 Phase B U/D Operational Concept Problems 1. Downlink not closed at apogee at Max Rate 2. Uplink not closed at apogee at Max Rate 3. Data not able to be downlinked below 50kkm at max rate (coverage) 4. Data not able to be downlinked at min rate (coverage) 129
130 3 PROBA - 3 What can we do? 130
131 3 PROBA 3 Phase B U/D Operational Concept Solutions 1. Use more Ground Segment 2. Use more Space Segment 3. Use one/several high gain Space Segment 4. Use variable data rate Low Rate (Uplink & Downlink) when at apogee High rate (Uplink & Downlink) when at perigee 131
132 3 PROBA 3 Phase B U/D Operational Concept Solutions 1. Use more Ground Segment What is the consequence? 2. Use more Space Segment 3. Use one/several high gain Space Segment 4. Use variable data rate What is the consequence? Low Rate (Uplink & Downlink) when at apogee High rate (Uplink & Downlink) when at perigee 132
133 3 PROBA - 3 Results! 133
134 3 PROBA 3 Phase B Updated Block Diagram 134
135 3 PROBA 3 Phase B Updated Configuration 135
136 3 PROBA 3 Phase B Updated Configuration 136
137 3 PROBA 3 Phase B Updated Configuration 137
138 3 PROBA 3 Phase B Final Stack Configuration 1. Occulter Spacecraft 2. Coronagraph Spacecraft 138
139 3 PROBA - 3 How would you now further reduce the cost? 139
140 3 PROBA - 3 How would you now reduce the cost? ANSWER = Increase the risk! 140
141 4 CONCLUSION 141
142 4 CONCLUSION Satellite System Engineering 1. Follows the Project Life Cycle Starts with Mission Concept Prepares System Requirements Proposes System Designs based on Trade-Offs (Technical + Programmatics) Manufacture the S/C Verify Requirements (Review of Design / Analysis / Test) Launch it! 2. Iterative Multi-disciplinary approach + Massive Communication 142
143 4 OPPORTUNITIES QinetiQ Space 1. Proposes Fast Learning Curve on Satellite Systems 2. Offers possibility to built international network quickly 3. Provides opportunity to be known at the European Space Agency 143
144 4 OPPORTUNITIES INTERNSHIPS / SUMMER JOB 1. Mission design and analyst Orbit1: SSO 450km from 10:00 & 11:00 Orbit2: Semi-Equatorial (incl = 10 max) at 450km Lifetime: 7 years Target: < 1 m resolution (GeoEye Arizona USA 10/01/2009) 144
145 4 OPPORTUNITIES INTERNSHIPS / SUMMER JOB 1. Mission design and analyst Launch Vehicle Selection (Current Generation) Launch Vehicle Selection (Next Generation) Orbit selection, and injection, propagation and drift analysis Ground Visibility & Data downlink assessment Incoming Power analysis based on assumed attitude for mission Propulsion Operations and scheduling 145
146 4 OPPORTUNITIES INTERNSHIPS / SUMMER JOB 1. System Engineering on PROBA-NEXT & VNREDSAT-1B platform 146
147 4 OPPORTUNITIES INTERNSHIPS / SUMMER JOB 1. System Engineering on PROBA-NEXT & VNREDSAT-1B platform Mission analysis follow-up Spacecraft accommodation contribution & follow-up Mass, Power, Link, Data downlink, Pointing, delta-v, processing, memory budgets Spacecraft database contribution & maintenance Development approach assessment (what test shall we do? When? ) Team management & organization of meetings 147
148 4 OPPORTUNITIES 1. GNC & Propulsion System Engineering Hydrazine Propellant HPGP Green Propellant (6% more efficient than Hydrazine) Available thrust = 1N Available delta V = 100m/s 2. Cold Gaz Nitrogen Propellant Available thrust = 80mN Available delta-v = 2m/s Propulsion integrator (OHB-SE) 148
149 4 OPPORTUNITIES 1. GNC & Propulsion System Engineering Xenon propellant Available thrust = 7mN Available delta-v = 300m/s Propulsion integrator (RAFAEL) 149
150 4 OPPORTUNITIES INTERNSHIPS / SUMMER JOB 1. GNC & Propulsion System Engineering Propulsion sizing based on Mission analysis Propulsion detailed simulations on commanding and control (duty cycles) Propulsion mass & power estimations based on simulations Integration of propulsion simulations into MATLAB Mission Analysis Tool GNC Loop impacts & modifications for propulsion system Propulsion requirement preparation Propulsion supplier follow up Strength Weakness, Opportunities and Treats of proposed system (SWOT) 150
151 4 OPPORTUNITIES INTERNSHIPS / SUMMER JOB 1. Communication Engineering on PROBA-NEXT platform (RF & Optical) 151
152 4 OPPORTUNITIES INTERNSHIPS / SUMMER JOB 1. Communication Engineering on PROBA-NEXT platform (RF & Optical) Operations considering Mission analysis visibility Optical COM detailed simulations on commanding and control (duty cycles) Optical COM mass & power estimations based on supplier data Integration of Optical COM into RF architecture Optical COM requirement preparation Optical COM supplier follow up Strength Weakness, Opportunities and Treats of proposed system (SWOT) 152
153 153
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