국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	DEVELOPMENT OF A MARS AIRPLANE ENTRY, DESCENT, AND FLIGHT TRAJECTORY
저자	James E. Murray and Paul V. Tartabini
Keyword	Aircraft design; Atmospheric entry; Flight mechanics; Mars probes; Trajectory optimization
URL	http://www.dfrc.nasa.gov/DTRS/2001/PDF/H-2436.pdf
보고서번호	NASA-TM-2001-209035
발행년도	2001
출처	NASA Dryden Flight Research Center
ABSTRACT	An entry, descent, and flight (EDF) trajectory profile for a Mars airplane mission is defined as consisting of the following elements: ballistic entry of an aeroshell; supersonic deployment of a decelerator parachute; subsonic release of a heatshield; release, unfolding, and orientation of an airplane to flight attitude; and execution of a pullup maneuver to achieve trimmed, horizontal flight. Using the Program to Optimize Simulated Trajectories (POST) a trajectory optimization problem was formulated. Model data representative of a specific Mars airplane configuration, current models of the Mars surface topography and atmosphere, and current estimates of the interplanetary trajectory, were incorporated into the analysis. The goal is to develop an EDF trajectory to maximize the surface-relative altitude of the airplane at the end of a pullup maneuver, while subject to the mission design constraints. The trajectory performance was evaluated for three potential mission sites and was found to be site-sensitive. The trajectory performance, examined for sensitivity to a number of design and constraint variables, was found to be most sensitive to airplane mass, aerodynamic performance characteristics, and the pullup Mach constraint. Based on the results of this sensitivity study, an airplane-drag optimized trajectory was developed that showed a significant performance improvement.