منابع مشابه
Self-configuring Network for Launch Vehicle and Satellite Avionics
Under an Air Force Phase II SBIR contract, Microcosm is developing a self-configuring avionics network, scheduled for test on a sounding rocket in late 2003 or early 2004. This system is extendable to spacecraft avionics and housekeeping functions, enabling true plug-and-play capability.
متن کاملMaterials for Launch Vehicle Structures
This chapter concerns materials for expendable and reusable launch vehicle (LV) structures. An emphasis is placed on applications and design requirements, and how these requirements are met by the optimum choice of materials. Structural analysis and qualification strategies, which cannot be separated from the materials selection process, are described. A launch vehicle is an airborne system tha...
متن کاملSelf-scheduled and structured H⋡ synthesis : A launch vehicle application
This paper presents a new application of structured H∞ synthesis to tune self-scheduled controllers. Newly available MATLAB-based tools allow to tune fixed-structure linear controllers while satisfying H∞ constraints. Moreover multi-model synthesis capabilities can extend their application to self-scheduled controllers. This technique is successfully applied to the attitude control of a launch ...
متن کاملEvolution of the Space Shuttle Primary Avionics Software and Avionics for Shuttle Derived Launch Vehicles
As a result of recommendation from the Augustine Panel, the direction for Human Space Flight has been altered from the original plan referred to as Constellation. NASA’s Human Exploration Framework Team (HEFT) proposes the use of a Shuttle Derived Heavy Lift Launch Vehicle (SDLV) and an Orion derived spacecraft (salvaged from Constellation) to support a new flexible direction for space explorat...
متن کاملTrajectory Optimization for a Multistage Launch Vehicle Using Nonlinear Programming
This work is an example of application of nonlinear programming to a problem of three-dimensional trajectory optimization for multistage launch vehicles for geostationary orbit missions. The main objective is to minimize fuel consumption or equivalently to maximize the payload. The launch vehicle considered here, Europa-II, consists of 5 thrust phases and 2 coast phases. Major parameters of the...
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ژورنال
عنوان ژورنال: Journal of the Japan Society for Aeronautical and Space Sciences
سال: 1998
ISSN: 0021-4663
DOI: 10.2322/jjsass1969.46.442