A method of testing attitude control systems during the development phaseA technique, utilized on the Space Telescope Program, and used for testing satellite attitude pointing and control systems during the engineering and development phases is presented. The technique verifies the hardware models used in design phase computer simulations, verifies the interface between the flight hardware and flight software, and uncovers hardware/software switching or mode logic problems. The testing is accomplished in two phases: a dynamic hardware simulator phase using hardware electronic simulators and an electronic vehicle motion simulator; and a second real hardware phase utilizing engineering model gyros and reaction wheels on an airbearing table. Both phases use an engineering model of the flight computer, flight algorithms and software, and a breadboard data management and computer hardware interface for timing simulations. The purpose of each test and the test phases are described, and examples of closed loop test results for both attitude hold and maneuvering models are given.
Document ID
19810048487
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Besonis, A. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Dougherty, H. (Lockheed Missiles and Space Co., Inc. Sunnyvale, Calif., United States)
Levinthal, J. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Meadows, P. (Bendix Corp. Guidance Systems Div., Teterboro, N.J., United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1981
Subject Category
Ground Support Systems And Facilities (Space)
Report/Patent Number
AAS PAPER 81-034
Meeting Information
Meeting: Annual Rocky Mountain Guidance and Control Conference