Jet Propulsion Laboratory California Institute of Technology Reconstructed DGB Performance During the & SR2 Supersonic Flight Tests 15 th International Planetary Probes Workshop Clara O Farrell, Bryan Sonneveldt, Ian Clark Jet Propulsion Laboratory California Institute of Technology June 13, 218 218 California Institute of Technology. Government Sponsorship Acknowledged.
The Project Advanced Supersonic Parachute Inflation Research Experiments Project Objectives: Develop testing capability for supersonic parachutes at Mars-relevant conditions. Deliver 21.5m parachutes to low-density, supersonic conditions on a sounding rocket test platform Acquire data sufficient to characterize flight environment, loads, and performance MSL (212) Initial flights focused on testing candidate designs for Mars22: Built-to-print Mars Science Laboratory (MSL) DGB Strengthened version of MSL DGB (identical geometry, stronger materials) MER (24) Parachute Load Purpose Test Date MSL built-toprint 35 klbf (MSL @ Mars) Test architecture shakeout. Ensure test approach doesn t introduce new parameters. Oct. 4 th, 217 SR2 Strengthened 47 klbf Incremental strength test of new design. Mar. 31 th, 218 SR3 Strengthened 7 klbf Strength test of new design July 218 SR4 Strengthened TBD TBD TBD 2
Test Architecture Launch Configuration Start of Experiment Phase Parachute Deployed Configuration Payload (7.54 m) Ballast (jettisoned before splashdown) ~15.5 m 17. 7 m TERRIER BLACK BRANT Aft transition & separation Hardware 2 nd Stage Black Brant IX (5.89 m) 1 st Stage Terrier (4.3 m) Parachute pack Telemetry, electronics pallets, attitude control system Experiment 44 m 36.52 m.72 m 3
Test Articles Target load: 35 klbf SR2 Target load: 47 klbf M22 Built-to-Print M22 Strengthened 4 lb Kevlar Web 6 lb Kevlar Web 1.3 oz/yd 2 Polyester (6 pli) 1.1 oz/yd 2 Nylon (42 pli, cfm) 25 lb Kevlar Web 1.9 oz/yd 2 Nylon (1 pli, 9 cfm) 24 lb Kevlar Web 2 lb Technora cord 32 lb Technora cord Mass: 58 kg Nominal diameter: 21.31 m Geometric porosity: 12.8% Mass: 88 kg Nominal diameter: 21.45 m Geometric porosity: 12.8% 4
Test Conditions Target mortar fire conditions: Mach = 1.74 q = 438 Pa Target peak load q = 473 Pa (MSL @ Mars) Event Time from launch (sec) Mach Dynamic pressure (Pa) Geodetic altitude (km) Total angle of attack (deg) Apogee 119.4 1.19 66 51. 2.1 Mortar Fire 161.41 1.77 453 42.4.5 Line Stretch 162.37 1.79 492 42..6 Peak Load 162.88 1.77 495 41.8.8 Mach 1.4 164.36 1.4 332 41.3 6. (max) Mach 1. 167.2 1 188 4.5 6.9 (max) SR2 Target mortar fire conditions: Mach = 1.72 q = 618 Pa Target peak load q = 678 Pa Event Time from launch (sec) Mach Dynamic pressure (Pa) Geodetic altitude (km) Total angle of attack (deg) Apogee 123.48 1. 33 54.8 4. Mortar Fire 177.59 1.97 667 4.8 1.9 Line Stretch 178.63 2. 746 4.3 2.3 Peak Load 162.8 1.97 748 4. 1. Mach 1.4 18.72 1.4 417 39.3 16.2 (max) Mach 1. 182.86 1 234 38.6 16.8 (max) Dynamic Pressure at Parachute Deploy (Pa) 8 75 7 65 6 55 5 45 M22 Parachute Deploy Conditions (Jezero) SR2 4 1.55 1.6 1.65 1.7 1.75 1.8 1.85 1.9 1.95 2 2.5 Mach at Parachute Deploy 5
Parachute Deployment Lower mortar velocity on SR2 Orderly deployment, no line entanglement No rotation of parachute pack on ; ~135º rotation on SR2 SR2 Mortar exit velocity (flight) 48.5 m/s 46.7 m/s Effective ground velocity (flight) 45.7 m/s 43.2 m/s Mortar velocity (predicted) 45 m/s 44 m/s Time to line-stretch (flight).96 sec 1.4 sec Time to line-stretch (predicted).98 sec.98 sec.15 sec.3 sec.45 sec.65 sec.15 sec.31 sec.7 sec.95 sec.65 sec SR2 Times are from mortar fire 6
Parachute Inflation Inflation predicted by inflation distance model:! "#$ = ( ) * % & ) + Portion of the band leads inflation; stalls inflation remarkably symmetric; SR2 less so Vent band remains circular, suggesting symmetric radial loading After full area, moderate collapse. On extends to disk; less symmetric 4% t FI.15 sec 6% t FI 85% t FI.45 sec % t FI MSL SR2 Inflation time (sec).635.56.456 a 4.6 5.15 4.65.65 sec SR2 7
Peak Load Faster inflation & steeper load rise on SR2 Oscillations around peak before collapse Partial collapse & re-inflation after peak load 2 nd peak was larger than 1 st peak on SR2 Force oscillations were larger than projected area oscillations Force oscillations w/frequency ~2 Hz starting.7 sec after line stretch. Close to system frequency due to Considering the conservation of momentum inside a control volume around the inflating canopy: F peak = k p (2q 1 S p ) k p = fraction of the fluid momentum converted to parachute drag elasticity in rigging.2.4.6.8 1 Time from line stretch (sec) Parachute load (klbf) 5 4 3 2 SR2 MSL SR2 1 st peak 2 nd peak 1 st peak 2 nd peak Load (klbf) 35 32.4 32.3 5.9 55.8 k p.83.77.79.78.93 8
Parachute Aerodynamics C D 1.9.8.7.6 nominal bounds SR2 Pull angle (deg) 7 6 5 4 3 2 SR2 T (deg) 25 2 15.5.4.25.5.75 1 1.25 1.5 1.75 2 Mach 1 5 15 2 25 3 35 4 Time from mortar fire (sec) 5 SR2 5 15 2 25 3 35 4 Time from mortar fire (sec) Pre-flight C D model based on MSL w/corrections for slender-body wake C D vs Mach behavior on & SR2 very similar Good agreement with C D model below M =.75, but over-estimated C D for M >1.15 C D remained constant in transonic region Parachute force vector pull angle larger on SR2, but remained below required deg Wind-relative total angle of attack oscillated about 15 deg for the majority of the flight 9
Post-Flight Inspection Damage to parachute was minimal on both & SR2 Damage on SR2 appears to be mostly deployment related & caused by interaction with the bag or friction between adjacent surfaces Damage was very minimal on & deemed recovery-related at the time. Insights from SR2 suggest some damage may be deployment related Some damage to vent band on SR2 at deployment bag attachment Gore 4 band trailing edge Gore 39 band trailing edge Vent band / bag energy modulator attachments
Conclusions & Future Work & SR2 were extremely successful Ongoing work: 3D canopy shape reconstruction from stereo videography Investigate supersonic C D : CFD with flight-like conditions & geometry Static aerodynamic coefficients & parachute/payload dynamics SR3 launch window opens July 24: Strengthened DGB canopy w/ 7 klbf target load Minor changes to parachute packing & rigging Image: Assateague Island National Seashore 11
jpl.nasa.gov
Backup 13
Test Architecture Rail-launched Terrier Black Brant Spin-stabilized at 4 Hz Ballast (jettisoned before splashdown) Payload (7.54 m) Yo-yo de-spin after 2nd stage burnout 17. 7 m TERRIER BLACK BRANT Aft transition & separation Hardware 2 nd Stage Black Brant IX (5.89 m) 1 st Stage Terrier (4.3 m) Mortar-deployed full-scale DGB Cold gas ACS active from payload separation to before mortar fire Recovery aids: Foam provides buoyancy Nosecone ballast (for additional mass & aerodynamic stability) is jettisoned before splashdown Payload mass: Launch: 1268 kg Post-separation: 1157 kg Splashdown: 495 kg Buoyancy Aid (foam) & electronics Telemetry (sealed) Attitude Control System Experiment IEEE Aerospace Conference 218 14
Flight Sequence Apogee L+119 s (51 km) Mortar Fire L+161 s Alt: 42 km q : 453 Pa Mach: 1.77 Peak Load MF +1.47 s q : 495 Pa Mach: 1.77 Nosecone sep. L + ~26 min Alt: 3 km Image from high speed camera (flattened) Range 55 km Launch 6:45 EDT. Wallops Island, VA 1 st stage burnout L+6.2 s (1 km) Splashdown L + ~24 min 15
Atmosphere 4x meteorological balloons carrying radiosondes: He-filled 3g latex balloon (Totex TA3) Launched at L-3 hrs, L-2:15 hrs, L-1:45 hrs, L-1 hrs, 12 minute ascent time Min. burst altitude: 35 km, Max. burst altitude: 39.9 km LMS-6 radiosonde: chip thermistor, capacitive humidity sensor, GPS GEOS-5: Real-time analysis generated by GMAO @ GSFC 75 min after launch Winds, density, temperature pressure from to 65 km Excellent agreement w/radiosonde mean, but does not capture small-scale variations Below 4 km: Nominal based on L-1:45 radiosonde Uncertainties based on measurement error + variation among radiosondes Above 4 km: Nominal based on GEOS Uncertainties based on max. observed difference between Radiosondes & GEOS L- atmosphere was atypical for October: Almost no East-West wind Slightly colder (and denser) atmosphere than expected 16
Atmosphere Reconstruction 17
Atmosphere Reconstruction 18
Parachute-Payload Dynamics Payload attitude throughout descent Pitch a T Parachute pull angle 45 45 45 4 35 Mortar fire Mach 1 4 35 Mortar fire Mach 1 Mean 95%-ile 5%-ile 4 35 Mortar fire Mach 1 Payload pitches over by ~35 km and then oscillates about vertical Altitude (km) 3 25 2 Altitude (km) 3 25 2 Altitude (km) 3 25 2 a T increases to ~15 deg and remains constant until ~7km Increase in pitch and a T below 7 km 15 5 Mean 95%-ile 5%-ile Nosecone sep. 15 5 Nosecone 15 5 Mean 95%-ile 5%-ile Nosecone sep. Pull angle remains small throughout System largely behaves as a rigid body -9-8 -7-6 -5-4 Pitch (deg) 2 3 4 5 6 T (deg) 1 2 3 4 5 Pull angle (deg) 19
ENU Parachute-Payload Dynamics Euler angles (pitch-yaw-roll sequence) wrt to East-North-Up frame: -2-2 Straight down -1 - -9-8 -7-6 -5-4 ENU Motion in North-Up Plane ENU -2-2 Mortar fire to 35 km: Pitch-over motion ENU -2-2 35 km to 7 km: Chaotic motion about (-9,) Motion in East-Up Plane -1 - -9-8 -7-6 -5-4 ENU - -9-8 -7 ENU 7 km to 4.5 km: Planar pendulum motion 4.5 km to 3 km: Planar pendulum motion 3 km to splashdown: Nosecone drop increases amplitude -2-2 -2 - - - ENU ENU ENU 2 2 2 - -9-8 -7 ENU - -9-8 -7 ENU - -9-8 -7 ENU 2
Parachute Inflation % t FI.15 sec 112% t FI 124%.45 t FI sec 141% t FI 135% t FI 142% t FI.65 sec SR2 % t FI 7% t FI 21
SR3: Changes to Parachute Assembly Deployment bag: Reduce length & mass of deployment bag energy modulators Remove Teflon outer layer to reduce bag mass Add Teflon tape to beckets on deployment bag Packing: Ensure a more uniform mass distribution in bag (minimize rotation) S-fold canopy to slow down inflation Canopy: Increase number of bag/vent band attachment locations to 8 (from 4) Use Nylon bag attachment cords (previously Technora) Riser: Change dispersion keeper stitching to Nylon (from Kevlar) Triple bridle: Use Nylon bridle legs & sabot net load elements to reduce snatch loads (previously Kevlar) 22