Reentry demonstration of flare-type membrane aeroshell for atmospheric entry vehicle using a sounding rocket

Kazuhiko Yamada, Yasunori Nagata, Takashi Abe, Kojiro Suzuki, Osamu Imamura, Daisuke Akita

Research output: Chapter in Book/Report/Conference proceedingConference contribution

5 Citations (Scopus)

Abstract

An inflatable decelerator is promising as atmospheric-entry systems in the next generation thanks to the aerodynamic heating relaxation and its packing efficiency. Our group focuses on a flare-type membrane aeroshell sustained by an inflatable torus, especially. As an important milestone of our development, a re-entry demonstration of the flare-type membrane aeroshell was carried out using a Japanese S-310 sounding rocket. The experimental vehicle which has a 1.2-meter-diameter membrane aeroshell and 15.6kg in total weight was developed for the re-entry demonstration. In this flight test, the membrane aeroshell with the inflatable torus was deployed at 100km in altitude during a suborbital flight under the zero gravity and vacuum condition, and the experimental vehicle re-entered the earth atmosphere from 150km in altitude. The experimental vehicle accelerated to 1.32km/s and Mach Number 4.5 due to the gravity force and started decelerating due to the aerodynamic force at 70km in altitude. According to the flight data, the experimental vehicle kept intact during the re-entry and the flare type membrane aeroshell achieved the expected decelerating performance. This re-entry demonstration proves that the flare-type membrane aeroshell sustained by the inflatable torus works well as a decelerator for atmospheric-entry vehicles.

Original languageEnglish
Title of host publicationAIAA Aerodynamic Decelerator Systems (ADS) Conference 2013
DOIs
Publication statusPublished - 2013
Externally publishedYes
Event22nd AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013 - Daytona Beach, FL, United States
Duration: Mar 25 2013Mar 28 2013

Other

Other22nd AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013
CountryUnited States
CityDaytona Beach, FL
Period3/25/133/28/13

Fingerprint

Sounding rockets
Reentry
Demonstrations
Membranes
Gravitation
Aerodynamic heating
Earth atmosphere
Mach number
Aerodynamics
Vacuum

ASJC Scopus subject areas

  • Aerospace Engineering
  • Electrical and Electronic Engineering

Cite this

Yamada, K., Nagata, Y., Abe, T., Suzuki, K., Imamura, O., & Akita, D. (2013). Reentry demonstration of flare-type membrane aeroshell for atmospheric entry vehicle using a sounding rocket. In AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013 https://doi.org/10.2514/6.2013-1388

Reentry demonstration of flare-type membrane aeroshell for atmospheric entry vehicle using a sounding rocket. / Yamada, Kazuhiko; Nagata, Yasunori; Abe, Takashi; Suzuki, Kojiro; Imamura, Osamu; Akita, Daisuke.

AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013. 2013.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Yamada, K, Nagata, Y, Abe, T, Suzuki, K, Imamura, O & Akita, D 2013, Reentry demonstration of flare-type membrane aeroshell for atmospheric entry vehicle using a sounding rocket. in AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013. 22nd AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013, Daytona Beach, FL, United States, 3/25/13. https://doi.org/10.2514/6.2013-1388
Yamada K, Nagata Y, Abe T, Suzuki K, Imamura O, Akita D. Reentry demonstration of flare-type membrane aeroshell for atmospheric entry vehicle using a sounding rocket. In AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013. 2013 https://doi.org/10.2514/6.2013-1388
Yamada, Kazuhiko ; Nagata, Yasunori ; Abe, Takashi ; Suzuki, Kojiro ; Imamura, Osamu ; Akita, Daisuke. / Reentry demonstration of flare-type membrane aeroshell for atmospheric entry vehicle using a sounding rocket. AIAA Aerodynamic Decelerator Systems (ADS) Conference 2013. 2013.
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