Reentry demonstration of deploy able and flexible aeroshell for atmospheric-entry vehicle using sounding rockets

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

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

7 Citations (Scopus)

Abstract

An inflatable decelerator is promising as atmospheric-entry systems in the next generation. Our group focus on a flare-type membrane aeroshell sustained by an inflatable torus, especially, although the various kinds of inflatable decelerators were proposed and researched in past. The flare-type membrane aeroshell may make atmospheric entry systems simple and low-mass easily because the aeroshell can be composed of only thin membrane. As an important milestone of our development, a re-entry demonstration of the flare-type membrane aeroshell was carried out using 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. The membrane aeroshell with the inflatable torus was deployed in the space under the zero gravity and vacuum condition, and the experimental vehicle reentered the earth atmosphere from 150km in altitude. The experimental vehicle accelerated to 1.32km/s due to the gravity force and started to decelerate 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 publicationProceedings of the International Astronautical Congress, IAC
Pages8671-8676
Number of pages6
Volume11
Publication statusPublished - 2012
Externally publishedYes
Event63rd International Astronautical Congress 2012, IAC 2012 - Naples, Italy
Duration: Oct 1 2012Oct 5 2012

Other

Other63rd International Astronautical Congress 2012, IAC 2012
CountryItaly
CityNaples
Period10/1/1210/5/12

Fingerprint

aeroshells
atmospheric entry
Sounding rockets
sounding rockets
reentry
Reentry
vehicles
Demonstrations
membrane
membranes
Membranes
flares
brakes (for arresting motion)
Gravitation
gravity
weightlessness
aerodynamic forces
Earth atmosphere
vehicle
aerodynamics

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering
  • Astronomy and Astrophysics

Cite this

Yamada, K., Nagata, Y., Honma, N., Akita, D., Imamura, O., Abe, T., & Suzuki, K. (2012). Reentry demonstration of deploy able and flexible aeroshell for atmospheric-entry vehicle using sounding rockets. In Proceedings of the International Astronautical Congress, IAC (Vol. 11, pp. 8671-8676)

Reentry demonstration of deploy able and flexible aeroshell for atmospheric-entry vehicle using sounding rockets. / Yamada, Kazuhiko; Nagata, Yasunori; Honma, Naohiko; Akita, Daisuke; Imamura, Osamu; Abe, Takashi; Suzuki, Kojiro.

Proceedings of the International Astronautical Congress, IAC. Vol. 11 2012. p. 8671-8676.

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

Yamada, K, Nagata, Y, Honma, N, Akita, D, Imamura, O, Abe, T & Suzuki, K 2012, Reentry demonstration of deploy able and flexible aeroshell for atmospheric-entry vehicle using sounding rockets. in Proceedings of the International Astronautical Congress, IAC. vol. 11, pp. 8671-8676, 63rd International Astronautical Congress 2012, IAC 2012, Naples, Italy, 10/1/12.
Yamada K, Nagata Y, Honma N, Akita D, Imamura O, Abe T et al. Reentry demonstration of deploy able and flexible aeroshell for atmospheric-entry vehicle using sounding rockets. In Proceedings of the International Astronautical Congress, IAC. Vol. 11. 2012. p. 8671-8676
Yamada, Kazuhiko ; Nagata, Yasunori ; Honma, Naohiko ; Akita, Daisuke ; Imamura, Osamu ; Abe, Takashi ; Suzuki, Kojiro. / Reentry demonstration of deploy able and flexible aeroshell for atmospheric-entry vehicle using sounding rockets. Proceedings of the International Astronautical Congress, IAC. Vol. 11 2012. pp. 8671-8676
@inproceedings{3b3101ace4ee441c9f8cbcaedddb5c38,
title = "Reentry demonstration of deploy able and flexible aeroshell for atmospheric-entry vehicle using sounding rockets",
abstract = "An inflatable decelerator is promising as atmospheric-entry systems in the next generation. Our group focus on a flare-type membrane aeroshell sustained by an inflatable torus, especially, although the various kinds of inflatable decelerators were proposed and researched in past. The flare-type membrane aeroshell may make atmospheric entry systems simple and low-mass easily because the aeroshell can be composed of only thin membrane. As an important milestone of our development, a re-entry demonstration of the flare-type membrane aeroshell was carried out using 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. The membrane aeroshell with the inflatable torus was deployed in the space under the zero gravity and vacuum condition, and the experimental vehicle reentered the earth atmosphere from 150km in altitude. The experimental vehicle accelerated to 1.32km/s due to the gravity force and started to decelerate 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.",
author = "Kazuhiko Yamada and Yasunori Nagata and Naohiko Honma and Daisuke Akita and Osamu Imamura and Takashi Abe and Kojiro Suzuki",
year = "2012",
language = "English",
isbn = "9781622769797",
volume = "11",
pages = "8671--8676",
booktitle = "Proceedings of the International Astronautical Congress, IAC",

}

TY - GEN

T1 - Reentry demonstration of deploy able and flexible aeroshell for atmospheric-entry vehicle using sounding rockets

AU - Yamada, Kazuhiko

AU - Nagata, Yasunori

AU - Honma, Naohiko

AU - Akita, Daisuke

AU - Imamura, Osamu

AU - Abe, Takashi

AU - Suzuki, Kojiro

PY - 2012

Y1 - 2012

N2 - An inflatable decelerator is promising as atmospheric-entry systems in the next generation. Our group focus on a flare-type membrane aeroshell sustained by an inflatable torus, especially, although the various kinds of inflatable decelerators were proposed and researched in past. The flare-type membrane aeroshell may make atmospheric entry systems simple and low-mass easily because the aeroshell can be composed of only thin membrane. As an important milestone of our development, a re-entry demonstration of the flare-type membrane aeroshell was carried out using 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. The membrane aeroshell with the inflatable torus was deployed in the space under the zero gravity and vacuum condition, and the experimental vehicle reentered the earth atmosphere from 150km in altitude. The experimental vehicle accelerated to 1.32km/s due to the gravity force and started to decelerate 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.

AB - An inflatable decelerator is promising as atmospheric-entry systems in the next generation. Our group focus on a flare-type membrane aeroshell sustained by an inflatable torus, especially, although the various kinds of inflatable decelerators were proposed and researched in past. The flare-type membrane aeroshell may make atmospheric entry systems simple and low-mass easily because the aeroshell can be composed of only thin membrane. As an important milestone of our development, a re-entry demonstration of the flare-type membrane aeroshell was carried out using 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. The membrane aeroshell with the inflatable torus was deployed in the space under the zero gravity and vacuum condition, and the experimental vehicle reentered the earth atmosphere from 150km in altitude. The experimental vehicle accelerated to 1.32km/s due to the gravity force and started to decelerate 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.

UR - http://www.scopus.com/inward/record.url?scp=84883513320&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84883513320&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:84883513320

SN - 9781622769797

VL - 11

SP - 8671

EP - 8676

BT - Proceedings of the International Astronautical Congress, IAC

ER -