25 November 1992 Simulation methods for a lightweight acquisition and tracking spacecraft
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Abstract
This paper describes the simulation methods and results used in the design of the control system for a lightweight spacecraft with multi-sensor suites. The design example uses several highly agile gimballed sensor payloads which can be used for the acquisition and tracking of ballistic missiles, both below and above the horizon. Using a control system-based simulation software package interfaced with a multi-body dynamics program a tool was built to add in the design of multi-body spacecrafts. This tool allows the controls engineer to rapidly input the dynamic model of a multi-body system by simply entering the mass, geometry and connection properties. The dynamic/structural and disturbance models can be constantly updated as the hardware matures. One of the ways the simulation model is being used is determining the effects of structural bending and induced disturbances on the sensor focal planes. Simulation results can be used to aid the designer in determining the following key design requirements: actuators, fast steering mirror (if any), command generator, lowest frequency mode, attitude knowledge, etc.. In addition a star map simulation program was developed and can be used in determining star tracker capabilities and requirements for a given orbital inclination and altitude. These simulation packages provide the design engineer with some high fidelity tools with extremely rapid design turnaround capability.
© (1992) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
Douglas V. LaMont, Jack J. Rodden, "Simulation methods for a lightweight acquisition and tracking spacecraft", Proc. SPIE 1697, Acquisition, Tracking, and Pointing VI, (25 November 1992); doi: 10.1117/12.138180; https://doi.org/10.1117/12.138180
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