Accession Number:

ADA048850

Title:

Attitude Determination of Triad and TIP-II and -III Gravity-Gradient-Stabilized Satellites.

Descriptive Note:

Technical memo.,

Corporate Author:

JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB

Personal Author(s):

Report Date:

1977-12-01

Pagination or Media Count:

61.0

Abstract:

The attitude of a satellite refers to the rotational orientation of the spacecraft relative to some reference triad of Cartesian axes these being, for the type of spacecraft treated here, the orbit radius vector, the normal-to-the-orbit plane, and the vector cross product of the two. Mathematically, the attitude is usually represented by nine direction cosines andor three Euler angles. The numerical determination of these parameters is the objective of attitude estimation. Various schemes have been developed and used by the Applied Physical Laboratory to determine the attitude performance of its satellites. In recent years, a least-squares technique that involves eigenvalue and eigenvector computation has been added. This report presents the formulation of the technique and discusses its successful application. Attitude estimation results from three orbiting spacecraft are included. Author

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Astronautics
  • Unmanned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE