NDLI: Trajectory optimization and guidance law development for transatmospheric vehicles

Content Provider	IEEE Xplore Digital Library
Author	Corban, J.E. Calise, A.J. Flandro, G.A.
Copyright Year	1989
Description	Author affiliation: The Georgia Institute of Technology (Corban, J.E.)
Abstract	The problems of on-board trajectory optimization and real-time guidance law synthesis are addressed for an air-breathing, single-stage-to-orbit vehicle. The particular objective of fuel-optimal ascent is examined in the hypersonic regime using a simple vehicle model representative of the aerospace plane concept. This model includes a dual-mode propulsion system composed of SCRAMJET and rocket engines. An energy state approximation is applied to a four-state dynamic model for flight of a point mass in a vertical plane over a spherical non-rotating Earth. Optimal climb profiles for the unconstrained and dynamic pressure constrained cases result from further reduction in model order. An analytic switching condition is derived for optimal transition to rocket powered flight as orbital velocity is approached. Simple feedback guidance laws for both the unconstrained and dynamic pressure constrained cases are derived via a combination of singular perturbation and feedback linearization techniques. Lastly, the performance of the resulting nonlinear feedback guidance laws is presented in a numerical simulation of ascent to orbit.
Starting Page	460
Ending Page	465
File Size	704869
Page Count	6
File Format	PDF
DOI	10.1109/ICCON.1989.770559
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	1989-04-03
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Rockets Weight control Navigation Differential algebraic equations Differential equations Open loop systems Control systems Fuels Vehicle dynamics Engines
Content Type	Text
Resource Type	Article

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