Deployment and Drop Test for Inflatable Aeroshell for Atmospheric Entry Capsule with using Large Scientific Balloon
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1 , Germany Deployment and Drop Test for Inflatable Aeroshell for Atmospheric Entry Capsule with using Large Scientific Balloon Kazuhiko Yamada, Takashi Abe (JAXA/ISAS) Kojiro Suzuki, Naohiko Honma, Yasunori Nagata, Masashi Koyama (The University of Tokyo) Daisuke Abe, Yusuke Kimura, A. Koichi Hayashi (Aoyama Gakuin University) Hitoshi Makino (Tokai University) Daisuke Akita (Tokyo Institute of Technology)
2 CONTENTS Background Membrane aeroshell for atmospheric-entry capsule (MAAC) Advantage and key technology. Past research Aerodynamics of flexible structure. Investigation of Inflatable structure and material performance. Development schedule. Second balloon experiment (MINI-MAAC) Objectives. Experimental vehicle. Results. Conclusions. Future Plan Atmospheric entry demonstration using sounding rocket.
3 Background HAYABUSA capsule returned to the earth with success. From now on, even more sample return missions and planetary entry missions will be proposed. Withstand Aerodynamic heating We weed innovation of atmospheric-entry system for frequent space transportation between space and planet surface. One of the candidates is flexible aeroshell system Avoid Aerodynamic heating Large and light aeroshell is deployed in the space before reentry Flexible aeroshell can be packed in launching and operating in space. Vehicle re-enters into atmosphere with low aerodynamic heating and make soft landing without a parachute
4 Advantage and key technology <Advantages of flexible aeroshell> Significant reduction of aerodynamic heating during reentry. 1) To understand aerodynamic characteristics in whole range of Mach number 2) To develop a large but low-mass flexible aeroshell utilizing inflatable structure Vehicle with large and light aeroshell can decelerate at high altitude where the atmospheric density is very low. Soft landing without additional parachute system or retro jet. Large and light aeroshell also works to reduce terminal velocity same as conventional parachute before landing. <Key technologies of flexible aeroshell> Flare-type membrane aeroshell supported by inflatable torus. Inflatable torus 3) To develop and evaluate flexible material especially thermal durability Thin membrane Capsule (payload)
5 Past research 1 Aerodynamics is first motivation of this research, because behavior of flexible structure was not understand, especially in supersonic flow. Can the flexible aeroshells be used as decelerator of a high speed vehicle like a reentry system? Various wind tunnel test & Numerical simulation Demonstration <First balloon experiment> Transonic Subsonic 1.5m Supersonic Numerical simulation Successful flight!! Vehicle is quit steady. Mach number in flight test is lower than (Subsonic ~ Transonic)
6 Past research 2 After the first balloon flight test, our group started various researches to apply this system to actual mission. Heater (hot wind) <Thermal durability> Laser Structure strength <Inflatable aeroshell> Demonstration Deployment in vacuum chamber Hypersonic wind tunnel test. Demonstration Second balloon test.
7 Development schedule Inflatable aeroshell Aerodynamics *Wind tunnel test *Numerical simulation <1 st Balloon experiment> Subsonic flight demonstration Thermal durability xx *Aeroshell system trade-off *Try and error using prototype *deployment demonstration *Structural strength test *Full scale model demonstration *Wind tunnel test *Numerical simulation <2 nd Balloon experiment> <3 rd Balloon experiment> *Aerodynamics in Hypersonic flow *Aerodynamics in Low speed flow *Aerodynamic in actual condition *Aerodynamics of full scale model <Hypersonic wind tunnel test> <Sounding rocket experiment> <Re-entry demonstration> *Martial testing *Aerodynamics heating environment *Actual condition demonstration <Mars exploration and /or Transportation system from LEO>
8 2 nd balloon experiment MIMI-MAAC Deployment and Drop Test of Inflatable Aeroshell for Atmospheric-entry Capsule
9 MINI-MAAC (2 nd balloon test) <Objectives> To demonstrate deployment and free flight of flare-type aeroshell supported by inflatable torus which is one of the next generation reentry system. To demonstrate the aeroshell deployment in vacuum condition in the air with remote control. To acquire the knowledge of the structural strength of inflatable torus against aerodynamic force during free flight condition. To obtain the aerodynamic characteristics of low-ballistic-coefficient vehicle in subsonic regime in free flight condition. Launch Free drop All flight data is transmitted to ground station. Deployment and Separation Aeroshell is packed Ascend at ALT=25km Vehicle separation from gondola after aeroshell deployment. We does not request recover of experimental vehicle
10 Experimental flight vehicle Capsule Packed aeroshell Deployed aeroshell 64mm 60deg Center of mass CCD camera with fish-eye lens 200mm 1264mm All of device including sensor, telemetry, transmitter and battery is in capsule. Measurement item: Image of aeroshell, Ambient pressure, Inflatable pressure, Position by GPS, Accelerator, Angle velocity and so on Flare part was made of Nylon cloth. Inflatable torus was made of Nylon cloth coated by Urethane rubber. Total mass : 3.375kg
11 Flight operation This experiment was carried out at TARF in 25 th August, This is first fight with user s payload in TARF which is new balloon base in Japan. Electrical compatibility check Just before launch Mechanical compatibility check User s room Successful launch and ascend.
12 Results of MINI-MAAC We acquired a lot of information and technology for flare-type inflatable aeroshell from MINI-MAAC experiment. The data in free flight condition is acquired just only flight test. For example, Deployment demonstration in vacuum condition. Vehicle trajectory in horizontal direction compared with wind profile. Drag coefficient in low speed regime during free flight. Structural strength of inflatable torus against aerodynamic force. Deformation of flare type aeroshell. Attitude of capsule during flight. In this presentation, three topics of them will be introduced.
13 Deployment demonstration The inflatable aeroshell was deployed by injecting gas at altitude 25km. <Compact and simple gas injection system> Vehicle was separated from gondola after deployment Deployment was completed in 0.3 second after gas injection
14 Drag coefficient Drag coefficient during free flight was estimated from altitude history. <Time history of altitude> <Comparison with simulation> Aeroshell was collapsed in 24 min after separation at altitude 4.0km. This is as planned Drag coefficient of vehicle during flight is estimated as In wind tunnel test, CD is measured as 0.9
15 Structural Strength of inflatable torus The inner pressure in inflatable torus is about 60kPaA. The aeroshell was collapsed during flight due to ambient pressure increase <Time history of inflatable pressure> <Collapse of aeroshell> Captured by onboard CCD camera with fish-eye lens 5.2kPa Aeroshell was collapsed when the differential pressure is 5.2kPa in free flight. The results is discussed for the design of the vehicle, comparing with wind tunnel data.
16 Conclusions of MINI-MAAC Our group carried out Deployment and drop test of inflatable aeroshell using large scientific balloon in series of development of membrane aeroshell for new atmospheric-entry system Our group achieved the following results in this test. 1) Successful deployment of inflatable aeroshell in the high altitude condition with remote control. 2) Aerodynamics data (drag coefficient) of vehicle with inflatable aeroshell in free flight condition. 3) Knowledge about structural strength of flare type membrane aeroshell supported by inflatable torus in free flight condition. These data will be very useful for the vehicle design in next phase of development.
17 Future Plan Next milestone : Re-entry demonstration using sounding rocket. 3. Aeroshell is deployment in zero gravity and vacuum condition 2. Fairing open and vehicle separation after rocket engine stopped 4. Aeroshell shape and vehicle attitude become stable by aerodynamic force. Packed aeroshell 5. At altitude about 55km Maximum dynamic pressure: 0.65kPa Maximum Mach number: 4.45 Maximum heat flux: 20.0kW/m 2 Capsule 1. Aeroshell is packed around the capsule in launching 6. Vehicle splash down with 16.8m/s in 1015 sec after top of trajectory. The vehicle floats on the sea with buoyant force of inflatable torus.
18 For sounding rocket experiment We are designing the experimental vehicle for reentry demonstration now. The aeroshell which have high temperature durability is being developed for reentry demonstration 0.2m This experiment is planned to carried out in m
19 Acknowledgement The balloon experiments in this study were carried out with the collaboration of Research and Operation Office for Scientific Ballooning, ISAS / JAXA. We would like to thank to the staff of Research and Operation Office for Scientific Ballooning and Taiki Aerospace Research Field for the appropriate supports and advices.
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