국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Guidance, Navigation and Control (GN and C) Design Overview and Flight Test Results from NASA''s Max Launch Abort System (MLAS)
저자	Dennehy, Cornelius J.;; Lanzi, Raymond J.;; Ward, Philip R.
Keyword	AERONAUTICAL ENGINEERING;; FLIGHT TEST VEHICLES;; FLIGHT TESTS;; GUIDANCE (MOTION); NASA PROGRAMS;; NAVIGATION;; PARACHUTES;; RISK;; SAFETY;; SPACECRAFT LAUNCHING;; SYSTEMS ENGINEERING
URL	http://hdl.handle.net/2060/20110000768
보고서번호	NASA/TM-2010-216877
발행년도	2010
출처	NTRS (NASA Technical Report Server)
ABSTRACT	The National Aeronautics and Space Administration Engineering and Safety Center designed, developed and flew the alternative Max Launch Abort System (MLAS) as risk mitigation for the baseline Orion spacecraft launch abort system already in development. The NESC was tasked with both formulating a conceptual objective system design of this alternative MLAS as well as demonstrating this concept with a simulated pad abort flight test. Less than 2 years after Project start the MLAS simulated pad abort flight test was successfully conducted from Wallops Island on July 8, 2009. The entire flight test duration was 88 seconds during which time multiple staging events were performed and nine separate critically timed parachute deployments occurred as scheduled. This paper provides an overview of the guidance navigation and control technical approaches employed on this rapid prototyping activity;; describes the methodology used to design the MLAS flight test vehicle;; and lessons that were learned during this rapid prototyping project are also summarized.