GAME CHANGING DEVELOPMENT DACCEnabling Project Venus In-Situ Science – Deployable Entry System Technology, Adaptive Deployable Entry and Placement Technology (ADEPT):

A Technology Development Project funded by Game Changing Development Program of the Space Technology Program

P. Wercinski, E. Venkatapathy, P. Gage, B. Yount, D. Prabhu, B. Smith, J. Arnold, A. Makino, K. Peterson, R. Chinnapongse ADEPT • • • • • •

conditions and this allows flexibility for greater and lower inrisk benignenables more architecture entry novel system entry exploration, but… Results ofResults application to mission design We angame-changingpresent alternate, approach (ADEPT) where a Venus is one of the important destinationsplanetary for scientific Concluding Remarks ADEPT – Mechanically Deployable Aeroshell Integrated Approach and Venus Mission Background: The challenge of at Venusentry – –

The combination of extreme entry environment coupled with extreme surface surface extreme with coupled of entry environment extreme The combination VITaL conditions have made mission planning and proposal efforts proposal and planning mission made have conditions very challenging Recommendations Recommendations : Example Venus: Example Science Survey Decadal to meet NRC mission Lander What is this talk about? VITaL missiondesign Outline ADEPT – – –

Content of this presentation was previously given at the IPPW-9 given previously was of this presentation Content NASA this effort is leading Center Ames Research is supported and Development by the Game Changing supported is currently This work (June 2012) in two presentations by ( two presentations in 2012) (June NASA Laboratory. Jet Propulsion and Center Flight Goddard by NASA Center, Research Langley NASA Center,Flight Johnson of the Space Program Technology , Program NASA HQ. ACKNOWLEDGEMENT Venkatapathy , et Glaze al) ADEPT Trajectories at 0.8 Mach terminated V m/CdA( entry • • • • • Rigid (-23.4º) sphere-cone, Steep entry 45º Payload Mass FractionPayload Mass ~0.5 Total LoadJ/cm Heat ~16,000 Stagnation Peak (Total) Rate Heat Peak W/cm ~4000 Peak High-Speed Entry at VenusAtmospheric : = 11.25 km/ β g -load 200-300 -load 200-300 ) = 208 ) kg/m = 208 Traditional Venus Entry: Pessure s

g ’ s 2

( 3.5m ~10 ~10 2 atm

The Challenge diam Net Net Effect: 2 Reduced heat shield carrier structure mass carrier shield heat Reduced capability science Improved G-load Decreasing Increased carbon carbon Increased Load Heat Increasing , 45º sphere-cone, 2100 kg entry mass) 2100 ,sphere-cone, 45º Decreasing Payload Mass Fraction! Payload Decreasing Increasing TPS Mass Fraction! phenolic • • • • • What happens if we at a shallowenter flight path angle Payload Mass FractionPayload Mass ~0.2 Total LoadJ/cm2 Heat ~28,000 Stagnation~1 atm Peak Pressure (Total) Rate Heat Peak W/cm2 ~800 g-load g Peak ~20-30 near skip-outnear with(-8.5º) architecture? the same thickness thickness ’ s

ADEPT • • •

For rigid aeroshell entry: Alternate option:Alternate For Carbon- – – – – –

Entry mass constrained by launch by launch Entry mass constrained shroud by launch constrained Size coefficientBallistic kg/m 200-250 Design entry architecture that entry architecture Design vehicle throw capability capability throw vehicle coefficient load) heat (lower ballistic a lower and loads) (lower angle path flight entry at shallower operate can and to extreme leads mass fraction Payload Balance between between Balance TPS and High-Speed Entry at VenusAtmospheric : G’load Phenolic

heatflux , pressure TPS: g - The Challenge 2

ADEPT Adaptive Adaptive Deployable Entry andTechnology Placement (ADEPT) • • • • •

descent. descent. during for lift vectoring of surface the frontal gimballing and deployment allow mechanisms strutsand Ribs, and heating. entry withstand and drag to fabric generates (2012) (2012) coefficientsballistic in: resulting concept. competitive of the mass viability to prove performed design Designed like an umbrella with flexible carbon carbon flexible with umbrella an like Designed OCT a funded Technology Project Maturation low systems achieve deployed Mechanically as mission as well testing design, Analysis, demonstrated todemonstrated be viable (2010-2011) Missions Mars Mass for Human and Heavy A

Mechanically Mechanically deployable, low ballistic coefficient concept developed and - - - -

system certification requirements requirements system certification coefficient ballistic low entry systems system aeroshell rigid like more behaves and Lower cost than extensive flight test program testflight program cost extensive than Lower many tests to achieve ground for extensive Allows OCT strategy for alternate risk mitigation requested skin/ribs/struts via that path is predictable Load aerocapture for Human Mars Missionsfor Human Mars , entry and , entry and Mars 40 MT40 LandedMars Payload for all architectures ADEPT Game ChangingGame Approach to Venus Entry with Direct • • • •

magnitude reduced by an order of well considerably loweras and pressureare now feasible sustain W/cm 250 A that can material Peak deceleration can be Peak Corresponding lowered 10x coefficient can be Assume ballistic Assume a a Low Ballistic Aeroshell Concept heatload 2 is

ADEPT • • ADEPT: STP in started FY12 GCD Project (2yr)

functions as a semi-rigid aeroshell system to perform entry descent landing (EDL) functions.(EDL) landing system to entry descent perform aeroshell as a semi-rigid functions deployed, when skin, which fabric carbon woven 3D flexible with struts,and connected ( entry architecture coefficient ADEPT (Adaptable, Deployable, Entry andTechnology) Placement ------ADEPT ADEPT Year 1 – Budget M) ($3.3 ADEPT ADEPT Year 2 – Budget ($3.5M

performance of 3D woven carbon fiber fiber carbon of woven 3D performance Planning Planning Ground Focused Test Development and test(~2m diameter) article ground development characteristics Mechanical and test article ground demonstration requirements/capabilities fabric Characterize thermal and mechanical mechanical and thermal Characterize Initiate Potential Flight Flight Potential Initiate Test and/or and Fabricate Design, Test sub-scale of material woven 3D Continue Thermal for Sub-scale process Start design Develop ADEPT system flight

=> TRLAchieve 5 at end of FY13 m/CdA < kg/m 50 2 ) that consists of a series of deployable ribs ribs ) of that ofdeployable consists a series is a low ballistic ballistic is a low 9 ADEPT • •

Applying ADEPT to a VISE-likeMission: Surface 2 hours of surface and near-surface science science 2 hours andof near-surface surface 1 hour science descent – – – –

Molded C-P Chop Atmospheric dynamics dynamics Atmospheric atmosphere of and surface Interaction of the atmosphere Evolution Physics and chemistry of chemistry the crust and Physics Venus Intrepid C-P Wrapped Tape Tessera Lander( VITaL ) ADEPT angle = high g-loads g-loads = high angle entry steep aeroshell: conventional Optimistic with Entry flight Entry System flight VITaL Instrument Complement

Strawman Camera/Raman/LIBS Fields of ViewFields Camera/Raman/LIBS Science Science Stable Landing Landing Stable 10 ADEPT

Altitude, km 50 75 100 125 150 175 200 ADEPT- 0 29 May 2023 May 2023 29 Atlas V 551 Launch • • • • • Event Begins 0.8: Mach Separation Cut main parachute / VITaL parachute Cut main release VITaL from separation ADEPT parachute main Pilot-deployed Aft release cover parachute pilot Mortar-deployed Mach 2 Mach 2 VITaL Region Alpha Alpha 16 Month Month 16 Trajectory Mission Quick-Look Uncertainty Uncertainty 4 Landing Velocity, km/s 6 29.8 G P q Entry + 110s Deceleration Peak total stag = atm 0.24 122 W/cm122 Cruise stage divert +1 day +1 day divert stage Cruise Release ADEPT for EDL up Spin Deploy ADEPT Targeting maneuver 2 8 19.2 G P q Entry sec + 100 Peak Total Heating Ballistic trajectory trajectory Ballistic γ V = km/s10.8 2024 September 29 Entry Interface total = -8.25º = -8.25º stag = 203 W/cm= 203 = atm 0.16 10 2 12 ADEPT ADEPT- VITaL Design Details •

ADEPT- –

Margined mass estimates for mass estimates Margined ADEPT- configuration are lower than baseline baseline than lower are configuration VITaL Design Results: VITaL VITaL

entry ADEPT • • •

The ADEPT-VITaL Study Addresses: • •

Payload Separation Event ADEPT-VITaL Vehicle Subcomponent Design: Mission Design Elements: 2012. documented are inResults the VISE lander developed by NASA GSFC for Survey’sthe Decadal Inner Planets Panel. for potentialinteractions with adverse other mission suchlaunchelements, as and cruise. Survey’sbenefits for Decadal the NRC Venus In-Situ Explorer (VISE) Mission and checking The ADEPT project chose to study the Venus Intrepid Tessera Lander (VITaL) design, a Study Objective: – – – – – – – –

Materials Materials Mechanisms Structures VITaL lander modifications savings and mass mods. and/ power mass spacecraft impacts Carrier CONOPS Cruise / time of ADEPT deployment design trajectory /Interplanetary launch date Launch vehicle ADEPT- ballistic applications coefficient decelerator The ADEPT Team used Venus robotic most challengingas for lowclass assess the feasibility of assess the ADEPT concept by quantifying potential

- Close collaboration with Venus Mission Stakeholder (GSFC: Glaze) - Technology identifieddevelopment risks - Fully mission addressed feasibility VITaL ADEPT-VITaL Mission Feasibility Report Mission Feasibility Report • • •

Operating environments: deployed configuration Operating environments: stowed configuration TradeKey Studies: – – – – – – –

Aerodynamic stability Aerodynamic and flight dynamics loadsStructural and aeroelastic loads Aerothermodynamic Cruise coldsoak Launch vibro-acoustic trades and Structures mechanisms Entry shape / trajectory , dated July 13

ADEPT • •

Objectives: Objectives: Test Results: Bi-axial Loaded Mechanical (BLAM) TestAerothermal – – – – – –

Data shows that the carbon fabric is able to maintain load at load to maintain is able fabric that the carbon shows Data of different as a function loss the rate of layer Evaluate combined fabric’s the carbon Evaluate combined under integrity structural Fabric tested easily withstood a heat load of kJ/cm 15.7 load a heat withstood tested easily Fabric effectlittle had direction the warp/weft Flipping loss the rate of on layer to little no has lbs/in to 750 lbs/in from the cloth 188 in load Biaxial above the 11above kJ/cm fabric. of the carbon fabric. of loss the carbon the rate of on layer impact temperature. loads. of the ADEPT from (far the ribs) away vehicle loading. biaxial and aerothermal Carbon Fabric Capability Demonstration ADEPT ADEPT Year-1 Major Accomplishment: 2 expected for a Venus expected mission. Intended to be a unit test for the acreage testto a unit be for the acreage Intended 2 . This is well

ADEPT Deployment Deployment & Load Tests Ground Test Article ADEPT ADEPT Year-2 Technical Plan Highlights *GTA items lead of long procurement by accelerating earlier occur tests could FY 13 Flight Compone Radiant GTA Test nt Testing Testing Test Plan Kick-off ADEPT/ Oct SRR SRR VITaL Nov

PDR PDR ADEPT/ Dec PDR PDR VITaL Radiant Testing CDR C-Cloth/CDR Procurement Thermal Thermal Tests

Jan s C-Cloth Tests Load DACC/NASA Only Distribution CDR SDR SDR CDR Feb BLAM-2 BLAM-2 PDR PDR Mar Mar Database Database Materials Materials C-Cloth Apr SRR SRR C - Fabric Seam TestsFabric Seam Radiant BLAM-2 BLAM-2 BLAM-2 BLAM-2 Test-1 CDR May May Jun Seam TestsSeam BLAM-2 BLAM-2 ADEPT/ *Deployment *Deployment Final Report Testing Jul VITaL

Flight Test Planning Aug Testing *Load ADEPT/ MCR MCR Sep VITaL 15

ADEPT TRL Maturation ADEPT ADEPT Project ADEPT ADEPT Technology Maturation and FY’12 – FY’14 OCT Project FY’11 and Design Studies Mission Mars Mass Human/ Heavy Mission Applications Timeline Sounding Rocket Flight Test FY’2015 FY’2015 ADEPT ADEPT Lifting -TRL Maturation Project (FY’14 – FY’17) Lifting Concept Flight Demos ( > FY’2022) Venus, Saturn New New Frontier & Flagship Class (~2020) (~2020) Robotic Mars Ballistic for ADEPT Parachute Parachute Non-Lifting, Subsonic High altitude access MER/MSL class Science Science Robotic (~2020) (~2020) (~2035) (~2035) Mars Human ADEPT • • •

System System is Changer: a Game Architecture including Venus technology, has broad payoff Explorationfor Solar System and Science ADEPT, a Low Ballistic Coefficient, Mechanically Deployable Entry Continued Technology Maturation of will ADEPT concept by 2015/2016 inGCD investment ADEPT, deployablemechanically aeroshell – – – – – – –

Use of flight qualified instrumentation for lower for lower instrumentation of qualified Use flight instrumentation sensitive and of use delicate Enables due conditions of severity the entry environment decreases Dramatically Continue Deployable Entry Concept development for Mars robotic and and for Mars robotic development Entry Concept Deployable Continue VenusEnable to a top be science comprehensive more with Missions and is matured the technology Cost, once and Risk Mission reduced considerably mass are the launch Entry mass and demonstrated, will be reduced considerably considerably reduced be will demonstrated, elsewhere deceleration altitude to high eventual human exploration missions missions exploration human eventual Frontier of New for the next round contenders AO Concluding Remarks g -load at Mars and at Mars and -load