국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Test Plan for the Technology Maturation of Supersonic Inflatable Aerodynamic Decelerators
저자	Kelly, Jenny R.;; Cruz, Juan R.
Keyword	AERODYNAMIC BRAKES;; INFLATABLE STRUCTURES;; CONES;; TECHNOLOGY ASSESSMENT;; RESEARCH AND DEVELOPMENT;; FLIGHT TESTS;; HIGH ALTITUDE;; SUPERSONIC WIND TUNNELS;; WIND TUNNEL TESTS;; MACH NUMBER;; MARS LANDING;; DESCENT;; COST REDUCTION;; SUPERSONIC SPEED;; DEPLOYMENT;;
URL	http://hdl.handle.net/2060/20090020432
보고서번호	AIAA Paper 2009-2969;; LF99-8617
발행년도	2009
출처	NTRS (NASA Technical Report Server)
ABSTRACT	Supersonic inflatable aerodynamic decelerators (IADs) are drag devices intended to be deployed at high Mach numbers. In the application considered here they assist in the descent and landing of spacecraft on Mars. Although promising, present IAD technology is not yet sufficiently mature for use in the near future. This paper describes a technology maturation plan for tension cone IADs using subscale test articles to reduce development costs. As envisioned, the proposed test plan includes three phases: wind tunnel tests (subsonic), unpowered high-altitude flight tests (transonic), and powered high-altitude tests (supersonic). This test plan is based on a building block approach in which successful completion of each phase adds to the understanding of the behavior of IADs and reduces the risk of the subsequent, more expensive phases. By properly scaling the IADs, test articles of the same size and nearly the same construction can be used for all three phases. The final phase is a dynamically scaled flight test with IAD deployment at the same Mach number as the full-scale vehicle on Mars. Two full-scale example cases are presented: one for a single-stage system ྯ m dia. IAD to subsonic retropropulsion), and another for a two-stage system ྪ.5 m dia. IAD to subsonic parachute). Using scale factors of 0.333 and 0.476 yield subscale test IADs of 5 m dia. The dynamically scaled powered flight test starts at Mach 4 and an altitude of 33.5 km. Existing balloons and rocket motors are shown to be adequate to meet the required test conditions.