The Archimedes Mars balloon project and the MIRIAM test flights Part 1: from Archimedes to MIRIAM

Transcription

1 The Archimedes Mars balloon project and the MIRIAM test flights Part 1: from Archimedes to MIRIAM EMC13-13th European Mars Conference Kai Gehreth Jürgen Herholz Mars Society Deutschland Chart 1

2 Archimedes Mars Balloon Project Unique measurements while descending through the Mars atmosphere Overpressure balloon remains inflated in Mars atmosphere o Mars atmosphere < 10 mbar o balloon inflated in free space to15 20 mbar o overpressure in Mars atmosphere 5.10 mbar o low overpressure allows for lightweight construction of the balloon o low ballistic coefficient (200x smaller than CURIOSITY) leads to slow descent ~ hr o moderate (but maybe destructive) impact velocity ~ 60 m/s (Reference: Dr. Hannes Griebel: "Reaching High Altitudes on Mars With An Inflatable Hypersonic Drag Ballute (Ballute)", ISBN ) Chart 2 2

3 ARCHIMEDES Mission Trajectory Earth-Mars > 6 months Carrier Mars Probe Orbit Satellite Orbit (prior separation of ARCHIMEDES) Apogee~ km Mars atmosphere Link to Earth Carrier Mars Probe with ARCHIMEDES Satellite (here:amsat P5-A) with ARCHIMEDES Apogee ARCHIMEDES Trajectory Km Chart 3

4 ARCHIMEDES De-Orbit and Entry 1 Separation 2 Injection into deceleration/entry orbit 3 Preparation for balloon deployment 4 Balloon deployment and inflation 5 Ballon release for free-flying balloon mission 6 Controlled entry and destruction of the balloon de-orbit and balloon system Link to Earth 3-9 Orbits prior entry Entry at ~200 km Entry Angle 6 7 AMSAT P5-A satellite (design baseline) 1 De-orbit and balloon system with ARCHIMEDES 6 Data Chart 4

5 Altitude [km] Maximum Heat Influx [W/m²] Scientific Research Program (Reference: Dr. Hannes Griebel: "Reaching High Altitudes on Mars With An Inflatable Hypersonic Drag Ballute (Ballute)", ISBN ) Hypersonics and Flight Dynamics Entry Trajectories Entry Angle vs. altitude and mission duration 1.E+05 1.E+04 1.E+03 1.E+02 Entry FPA = -25 Entry FPA = -15 Entry FPA = -9 Entry FPA = -7 Entry FPA = Entry FPA = -6.6 Entry FPA = -6 Heat flux and ballistic coefficient vs. entry angle , Ballistic Coefficient [kg/m²] FPA= -7 FPA= -8 FPA= -9 FPA= -15 ARCHIMEDES ~0.5 CURIOSITY ~200 Entry angle < 7 several Mars atmosphere passes before entry 1.E+01 1.E+01 1.E+02 1.E+03 1.E+04 1.E+05 1.E+06 Time Since Initial Entry [s] Chart 5

6 Scientific Research Program (Reference: Dr. Hannes Griebel: "Reaching High Altitudes on Mars With An Inflatable Hypersonic Drag Ballute (Ballute)", ISBN ) Determination of Ballute Surface Temperature Thermal Loads at hypersonic entry <250 C Chart 6

7 Balloon Materiel Selection Criteria and Tests Weight Rigidity Weldability Foldability Elasticity Dimensional Stability *) Temperature Resistivity (>250 C) Space environment Resistivity *) Long duration Storability in densely packed condition *) Affordability *) requires long duration tests Chart 7

8 Scientific Research Program Balloon Materiel Testing Upilex 25RN Existing Upilex 25 RN selected Chart 8

9 Scientific Research Program Balloon Vibration Testing First Natural Harmonics, Ellipsoid, 85,2 Hz side view oblique view Second Natural Harmonics, 114,4 Hz, Deformation every Chart 9

10 MIRIAM-2 ARCHIMEDES/MIRIAM Scientific Instrumentation Measurement Composition of the Mars atmosphere Critical hypersonic data during approach and entry 3-axis accelerations during approach and entry for trajectory reconstruction and characterisation of outer atmosphere layers Very weak residual Mars magnetic field High resolution images during descent to the Mars surface Instrument Provider ATMOS-B Finnish Meteorological Institute Compare Institute for Space Systems, TU Stuttgart MSD MIRIMag Technical University Braunschweig DLR Berlin X X X X X Instrument flown also on MIRIAM Chart 10

11 ARCHIMEDES Development Overview 5 m Balloon 13,5 m Balloon Airbus A-300 Parabolic Flight Test Balloon Storage&Release System Flight Test REGINA Balloon Release System MIRIAM 1 Development, Test, Mission Airbus A-300 Flights Flight on REXUS 3 Flight on REXUS 4 Balloon Packaging Balloon Inflation Balloon Manufacturing Chart 11

12 MIRIAM as ARCHIMEDES Simulation Mission Windsock Balloon Inflation 1) MIRIAM 1+2 : no descent function >> unguided parabolic flight trajectory Descent&Inflation Module 1) Science&Avionics Module ARCHIMEDES Overall Configuration Balloon Construction Balloon Diameter Balloon Materiel Balloon Instrument and avionics unit (pod) Entry conditions o o o Trajectory Flight dynamics Thermal loads Balloon behavior during deployment and inflation MIRIAM 1+2 (10 vs. 4m) Arch=7, MIR=45 comparable *) in limited flight domain *) flight data will be translated into ARCHIMEDES conditions Chart 12

13 MIRIAM as ARCHIMEDES Simulation Mission ARCHIMEDES Balloon storage and deployment system o Storage container design ( blossom ) o Balloon deployment method Orbit injection system Balloon inflation system Balloon release system Separation of inflation system Data acquisition and communications MIRIAM 1+2 n/a to MIRIAM-2 (parabolic entry trajectory) = - identical function and architecture - different detailed design - different data content and structure Chart 13

14 MIRIAM 1 -Miriam 1 and 2 follow the same Design Principles- Helium Tanks Pipes to thrust nozzles RF-Transmitter Video camera Video boom -RF -- -Video boom Ballute inside Antenna Clamp ring Separation mechanism Thrust nozzle -Computers and Computers and power supply inside Balloon storage container Blossom opening for balloon deployment Chart 14

15 The MIRIAM-1 Flight Test Program o Partial simulation of the ARCHIMEDES Marsmission during a sounding rocket flight test in the high Earth atmosphere 175 km altitude rocket shared with additional payloads technical and mission scheduling constraints tight development schedule o only partial mission success due to delayed separation of MIRIAM-1 from the rocket Chart 15

16 MIRIAM 1 at the Launch Site Chart 16

17 MIRIAM 1 in Space in October 2008 MIRIAM in Space in 175 Km Altitude Chart 17

18 From MIRIAM-1 to MIRIAM-2 Chart 18

19 Major Improvements over MIRIAM-1 Launcher and launch campaign (provided by DLR-Moraba) 1. Dedicated launcher increased altitude longer mission duration more planning flexibility Apogee Mission Duration *) MIRIAM km 4.5 min MIRIAM km 5.8 min 2. Dedicated nosecone avoids nosecone separation 3. Standard separation device > proven reliable separation *) above 90 km Consideration of Lessons Learned during the MIRIAM-1 Program Development since 2009 >> more development and test time advanced balloon design approaching ARCHIMEDES needs design improvements (see separate presentation) Chart 19

20 Balloon deployment,inflation(~20mbar),separation s 200 km Service S/C MIRIAM 2 Mission Profile MIRIAM-B Mission Phase s MIRIAM-B Service S/C deceleration and destructive entry MIRIAM-B MIRIAM 2 Separation 70 s camera/transmitter boom deployment 63 s Begin of Reentry 380 s 100 km Despin s Primary Mars Mission Simulation Phase 380- (air density to Mars atmosphere) 450 s End of thrust at 35 s in 42 km altitude 2-stage MAPHEUS sounding rocket Launch ~October 2014 Balloon compressed, then accelerated below ~40 km s 0 -Ground impact -Recovery of Video Recording 800 s 0=Launch 450 s 800 s Chart 20

21 End of Part 1 Thank You For Your Attention Chart 22