National Aeronautics and Space Administration Flight Analysis of an Autonomously Navigated Experimental Lander Jeffrey Chin, Justin Niehaus, Debra Goodenow NASA Glenn Research Center Storm Dunker, David Montague Airborne Systems 1 www.nasa.gov Flight Objectives Increase the reusability of high altitude balloon gondolas after landing Goals Objectives Launch and land a gondola using 1.1 damage reduction method Demonstrate a method to 1.0 reduce damage to the gondola Collect and retrieve load data during during landing 1.2 the operation of the damage reduction method Demonstrate a method to Perform a controlled landing of a 2.0 increase recoverability of the 2.1 gondola to a specified target region gondola after landing 2 NASAFly System •  Developed by Airborne Systems •  Guided Precision Aerial Delivery 3 New Challenges •  Tex=le tolerance to radia=on exposure •  Opera=ng systems at combined low densi=es and temperatures •  Safely, reliably, and cleanly separa=ng from the host vehicle and ini=a=ng drogue inﬂa=on •  Stability during a transonic free-‐fall •  Use of GPS sensors near their al=tude and speed limits •  Mission planning for balloon ﬂights with highly variable trajectories 4 ANGEL Payload 5 Balloon Flight System (BFS) •  Monitors ﬂight and landing condi=ons •  Sensors include: –  GPS –  3-‐axis Accelerometers –  3-‐axis Gyro –  3-‐axis Magnetometer –  Thermocouples –  Barometers –  Cameras –  Current/voltage Monitoring –  Telemetry 6 Separation System Design ANGEL 7 Separation System – Section View Payload Housing Bearing Bearings 8 Separation System – Section View ShaV Retracted Drogue Cord 9 Flight Profile 0.04 129,689 -‐29 Time at Float determined by 0.07 117,956 Float Host Vehicle -‐39 Range Safety Oﬃcer (2 hour Separa=on from 0.10 110,396 Con=nues Mission -‐39 max based on mission proﬁle) Host Vehicle 0.15 102,412 -‐42 Drogue Parachute D 0.29 87,326 -‐51 r Deploys 0.04 78,775 o -‐56 g 0.73 68,271 u -‐62 1.00 61,528 e -‐68 D 1.40 54,621 -‐73 e 2.10 46,606 s -‐61 c 2.90 40,569 -‐48 e e ( psi ) 34..6300 e ( ft ) 3351,,655468 Emxipne. cNtoed le Asssc tehnatn R 7a5t0e Vof/ m10in0 0 V/ nt Drogue Parachute Terminated -‐-‐4306 re ( C ) r d u ressu 55..1800 Altitu 2274,,977753 Paraglider Deployed -‐-‐2270 perat P m 6.50 21,873 -‐13 e T 7.25 19,214 -‐7 7.90 16,759 -‐3 8.70 14,479 2 9.40 12,354 4 10.10 10,359 Pre-‐launch 8 10.80 8,477 11 Touchdown 11.60 6,701 12 11.90 5,851 13 Launch 12.30 5,024 14 Recovery 12.70 4,219 15 Ground 25 Mission Time (hrs) 1 _ 2 3 4 5 6 7 8 9 10 11 12 10

NASA Technical Reports Server (NTRS) 20160010274: Flight Analysis of an Autonomously Navigated Experimental Lander PDF

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National Aeronautics and Space Administration Flight Analysis of an Autonomously Navigated Experimental Lander Jeffrey Chin, Justin Niehaus, Debra Goodenow NASA Glenn Research Center Storm Dunker, David Montague Airborne Systems 1 www.nasa.gov Flight Objectives Increase the reusability of high altitude balloon gondolas after landing Goals Objectives Launch and land a gondola using 1.1 damage reduction method Demonstrate a method to 1.0 reduce damage to the gondola Collect and retrieve load data during during landing 1.2 the operation of the damage reduction method Demonstrate a method to Perform a controlled landing of a 2.0 increase recoverability of the 2.1 gondola to a specified target region gondola after landing 2 NASAFly System •  Developed by Airborne Systems •  Guided Precision Aerial Delivery 3 New Challenges •  Tex=le tolerance to radia=on exposure •  Opera=ng systems at combined low densi=es and temperatures •  Safely, reliably, and cleanly separa=ng from the host vehicle and ini=a=ng drogue inﬂa=on •  Stability during a transonic free-‐fall •  Use of GPS sensors near their al=tude and speed limits •  Mission planning for balloon ﬂights with highly variable trajectories 4 ANGEL Payload 5 Balloon Flight System (BFS) •  Monitors ﬂight and landing condi=ons •  Sensors include: –  GPS –  3-‐axis Accelerometers –  3-‐axis Gyro –  3-‐axis Magnetometer –  Thermocouples –  Barometers –  Cameras –  Current/voltage Monitoring –  Telemetry 6 Separation System Design ANGEL 7 Separation System – Section View Payload Housing Bearing Bearings 8 Separation System – Section View ShaV Retracted Drogue Cord 9 Flight Profile 0.04 129,689 -‐29 Time at Float determined by 0.07 117,956 Float Host Vehicle -‐39 Range Safety Oﬃcer (2 hour Separa=on from 0.10 110,396 Con=nues Mission -‐39 max based on mission proﬁle) Host Vehicle 0.15 102,412 -‐42 Drogue Parachute D 0.29 87,326 -‐51 r Deploys 0.04 78,775 o -‐56 g 0.73 68,271 u -‐62 1.00 61,528 e -‐68 D 1.40 54,621 -‐73 e 2.10 46,606 s -‐61 c 2.90 40,569 -‐48 e e ( psi ) 34..6300 e ( ft ) 3351,,655468 Emxipne. cNtoed le Asssc tehnatn R 7a5t0e Vof/ m10in0 0 V/ nt Drogue Parachute Terminated -‐-‐4306 re ( C ) r d u ressu 55..1800 Altitu 2274,,977753 Paraglider Deployed -‐-‐2270 perat P m 6.50 21,873 -‐13 e T 7.25 19,214 -‐7 7.90 16,759 -‐3 8.70 14,479 2 9.40 12,354 4 10.10 10,359 Pre-‐launch 8 10.80 8,477 11 Touchdown 11.60 6,701 12 11.90 5,851 13 Launch 12.30 5,024 14 Recovery 12.70 4,219 15 Ground 25 Mission Time (hrs) 1 _ 2 3 4 5 6 7 8 9 10 11 12 10

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