Engineering topics
Publications and source records attributed to Shank, D. E..
The purpose of the Flight Experiment Demonstration System (FEDS) was to show, in a simulated spacecraft environment, the feasibility of using a microprocessor to automate the onboard orbit determination functions. The software and hardware configuration used to support FEDS during the demonstration and the results of the demonstration are discussed.
A prototype for an onboard satellite orbit determination system has been developed at the Goddard Space Flight Center (GSFC) to aid in the research and development of onboard navigation. Two versions of the system, one for laboratory investigation and one for ground demonstration, are being used to gain insight into the feasibility and practicality of microprocessor-based automated orbit determination. This paper describes the mathematical modeling and the software structure of each system and presents the results of laboratory evaluation in terms of computational accuracy and real-time processing performance.
This document presents a functional description of the Flight Experiment Demonstration System (FEDS) and of interfaces between FEDS and external hardware and software. FEDS is a modification of the Automated Orbit Determination System (AODS). FEDS has been developed to support a ground demonstration of microprocessor-based onboard orbit determination. This document provides an overview of the structure and logic of FEDS and details the various operational procedures to build and execute FEDS. It also documents a microprocessor interface between FEDS and a TDRSS user transponder and describes a software simulator of the interface used in the development and system testing of FEDS.
Computational models for the flight experiment demonstration system (FEDS) code 580 were developed. The FEDS is a modification of the automated orbit determination system which was developed during 1981 and 1982. The purpose of FEDS is to demonstrate, in a simulated spacecraft environment, the feasibility of using microprocessors to perform onboard orbit determination with limited ground support.