CONCEPTUALIZATION OF DESIGN MODIFICATIONS IN RE-ENTRY VEHICLES - VECTORING FOR REDIRECTION OF PLASMA
- Paper number
IAC-14,D1,2,10,x27216
- Author
Mr. Chrishma Singh-Derewa, National Aeronautics and Space Administration (NASA)/Jet Propulsion Laboratory, United States
- Author
Mr. Srikanth Raviprasad, Manipal Institute of Technology, Manipal University, India
- Year
2014
- Abstract
NASA’s Jet Propulsion Laboratory continues to push the boundaries of entry descent and landing with heavier exploratory systems. Our heatshields must dissipate more the 90% of the spacecraft’s kinetic energy and keep the aeroshell interior safe from these extreme temperature gradients. Mars Science Laboratory (MSL) taught JPL many things about this high speed descent as it hurdled to the surface of Mars at nearly a ton. The MSL aeroshell was a 4.5 m diameter spherically-blunted 70-degree half-angle cone made of an ablative material called Phenolic Impregnated Carbon (PICA). The data gathered indicated the urgent need for an optimized entry design increasing the marginal probability of safety. The Reentry dynamics is invariably dominated by the drag coefficient, frontal Area, angle of attack, density of atmosphere, ballistic coefficient and many other less significant parameters. The most popular design produced for the same is the 70° blunted cone design with angle of attack of about 12° to 13° to obtain the optimum value of CdA so as to increase drag and frontal area. The STARSHIELD concept adopted in this technology demonstration will redirect and vector the surrounding plasma by using nozzles built into the shield to allow propulsion free adjustments to trajectory, thereby reducing the velocity during Re-Entry. To obtain the same, supersonic and hypersonic diffusers are strategically mounted along the aeroshell of the vehicle. The general function of diffusers for hypersonic speeds as applied to the STARSHIELD design is presented in the context of modifications to the classic methodology of Doctrine of Successive Refinement (DSR) for its’ development. This concept is universal in the sense it can be employed for non – axis symmetric vehicles as well. A vectorable aeroshell will help compensate for wind shear, provide course directional capabilities and reduce shockwaves across turbulent boundary layers associated with TPS degradation in flight. These capabilities will revolutionize the entry, decent and landing on Mars enabling ever larger payloads to its surface. .
- Abstract document
- Manuscript document
IAC-14,D1,2,10,x27216.pdf (🔒 authorized access only).
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