Navigation for Future Space Exploration Missions Based on Imaging LiDAR Technologies. Alexandre Pollini Amsterdam,

Transcription

1 Navigation for Future Space Exploration Missions Based on Imaging LiDAR Technologies Alexandre Pollini Amsterdam,

2 Presentation outline The needs: missions scenario Current benchmark in space Requirements resulting from missions scenario From requirements to instrument design Flash (hybrid) imaging LiDAR architecture Hybrid flash imaging LiDAR operation simulation Close future for imaging LiDAR in Space Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 1

3 The needs, missions scenario Space applications: 1. Active Debris Removal 2. Soft-landing 3. Rendezvous, Docking Benchmark, current mission: MSL Future mission: MarcoPolo-R 4. Rover navigation 5. Situational awareness, etc. Common requirements: Automated navigation relative to non-collaborative target, Need distance information to target or better, 3D images of the target (in real time) Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 2

4 Active Debris Removal missions Today 70% Geostationary-orbiting objects are garbage 958 objects Jan.2013 (Space News Oct ) Impact of 1 cm object = energy of exploding hand-grenade objects tracked Larger than 5cm in LEO Larger than 30cm in GEO 6% operational satellites 38% passive objects 56% from fragmentations Space debris recognised as major risk to space missions Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 3

5 Soft-landing on celestial bodies The video is about a deceased mission, the new scenario of the mission is under discussion currently Several space fearing countries or group of countries are currently defining same kind of missions CLICK TO PLAY VIDEO Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 4

6 Soft-Landing on Near Earth Asteroid Asteroid 2008 EV5 400 m Closest position to Earth 8 lunar distance European MarcoPolo-R mission: to land on 2008 EV5 and bring back on Earth ground samples Courtesy: ESA, Astrium Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 5

7 Soft-landing, benchmark NASA: Mars Science Laboratory (MSL) 2012 mission Landing precision within a 20 x 7 km ellipse radar-based Terminal Descent Sensor Features Weight kg 25 Power consumption W 100 Size (estimate) l cm x w cm x h cm 100 x 40 x 20 Altitude range of operation m Maximum range bias m 0.5 Update rate Hz 20 1 m Courtesy NASA/JPL-Caltech. Functionalities Absolute Altitude Absolute Velocity Terrain Relative Navigation capability Hazard Detection capability 3D images of the target Yes Yes No No No Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 6

8 New set of requirements, MarcoPolo-R mission Far global characterisation Radio science experiment Asteroid 2008 EV5 Global characterisation altimeter 6000 > range > 4000 m Ranging accuracy < 1 m (MSL = 0.5) Horizontal resolution < 10 m Measurement rate > 2 Hz Vertical velocity < 1.5 m/s Global characterisation Local characterisation Local characterisation 3D imager / imaging LiDAR 250 m (MSL = not available) 300 > range > 200 m 10 km 5 km Ranging accuracy < 10 cm (MSL = 50) Horizontal resolution < 20 cm Courtesy: ESA, Astrium Measurement rate > 2 Hz Vertical velocity, not defined Data from MarcoPolo-R Mission and System Requirements Documents Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 7

9 Short range requirements MarcoPolo-R 250 m SDR 175 m SAM 50 m Sampling Descent Rehearsal inclinometer 250 > range > 100 m Ranging accuracy < 5 cm (MSL = 50) Horizontal resolution TBD Measurement rate > 2 Hz Velocity < 1.8 m/s Asteroid 2008 EV5 Descent and sampling (5 times) inclinometer 100 > range > 5 m Ranging accuracy < 5 cm (MSL = 50) Horizontal resolution TBD Measurement rate > 2 Hz Velocity < 0.11 m/s Courtesy: ESA, Astrium Data from MarcoPolo-R Mission and System Requirements Documents Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 8

10 Other requirements MarcoPolo-R Environmental requirements Launch 7.5G Micro-vibrations Temperature -27 to 40 deg C Radiation 50 krad Resources and room restriction Mass < 4 kg (MSL = 25kg) Power consumption < 35 W (MSL = 100W) Total dimensions < 25 cm x 30 cm x 25 cm (MSL = 100 x 40 x20) Target features Safe landing area 30 x 30 m (MSL = x 7000) Local slope < 20 Albedo < 0.06 Courtesy NASA/JPL-Caltech. Apollo 15 Lunar Module Landing on sloping ground Tilt is 11 Limit was 12 Data for: Relative navigation spacecraft asteroid, Topography, geodesy Surface hazards detection and avoidance (MSL = not available) Courtesy: ESA, Astrium 1. Slope detection 2. Roughness detection 3. Shadow detection 4. Safe site identification Data from MarcoPolo-R Mission and System Requirements Documents Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 9

11 From requirements to instrument design MSL vs. MarcoPolo-R requirements: Mass divided by 6 Power consumption divided by 3 Size divided by 4 Multiple configurations: altimeter, 3D imager, inclinometer Courtesy: ESA Additional capabilities: 3D images, Hazard avoidance, Terrain Relative Navigation spacecraft Solution: Imaging LiDAR Scanning LIDAR Laser beam Laser beam Flash LIDAR Side view Architecture: flying-spot, flash or hybrid? Scanning angle Laser spots One large laser spot Flying-spot: optical power on small area, spatial and temporal synchronisation between transmitter and receiver. Surface hazards View from the spacecraft Flash: optical power over larger area, temporal synchronisation transmitter-receiver, Several small laser spots One large laser spot lower the amount of mobile parts. Scanning path Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 10

12 Flash (hybrid) imaging LiDAR architecture Key building-block: Time-Of-Flight (TOF) detector array (APD, SPAD, IPPD-CMOS) Flash imaging LiDAR generic architecture System controller Detector array Receiver optics processing, storage and communication Laser source(s) Emitter optics Two methods to determine range per pixel: Direct or Indirect TOF Intensity Intensity Start Stop 0:00:13.34 Timer Range = t c x time 2 j Correlation Range = t c x j 4 x p x f Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 11

13 Hybrid flash imaging LiDAR architecture CW-laser CMOS-IPPD Zoom CMOS-SPAD Q-switched mpulse-laser Flash imaging LiDAR generic architecture System controller processing, storage and communication Detector array Laser source(s) Receiver optics Emitter optics 4 mm x 4 mm MOEMS-mirror Beam divergence Diffractive Optical Element Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 12

14 Examples of the use of hybrid imaging LiDAR components Lunar Orbiter Laser Altimeter (NASA) 50 km Polar orbit 5 beams with DOE beam : 50m footprint on ground 1.25 km between spots Within a spot: range, surface roughness, albedo 50 m 1.25 km Latest space shuttle flights STS-135, STS-133, STS-131, STS-128, STS-127 Assessment of hybrid LiDAR and flash LiDAR Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 13

15 Close future for imaging LiDAR in Space 1. OSIRIS Rex, a NASA Arizona University mission Objective: bring back on Earth > 60 gr Asteroid sample Launch: 2016 Travel 3 years 1 year mission Travel back 3 years Return 2023 Flying-spot imaging LiDAR 2. MarcoPolo R, an ESA mission Objective: bring back on Earth Asteroid samples (from 5 different sites) Class-M mission candidate, selection in February 2014, launch in 2022? flash imaging LiDAR for exploration mission? miniaturization, simplicity 3. Planning of Active Debris Removal missions? Copyright 2013 CSEM Space missions with Imaging LiDAR Technologies Alexandre Pollini Page 14

16 Thank you for your attention! Questions?