Accession Number:

AD0736151

Title:

Generalized Equations for the Position and Attitude of a Multiply Connected Spacecraft. I. The Dynamical Equations.

Descriptive Note:

Technical memo.,

Corporate Author:

JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB

Personal Author(s):

Report Date:

1971-04-01

Pagination or Media Count:

48.0

Abstract:

The nonlinear differential equations for the rotational motion of an earth-orbiting spacecraft are derived in terms of Newtonian mechanics and are put in a form suitable for computer solution. The spacecraft is assumed to have a general configuration consisting of a main body and any number of secondary bodies each of which is gimbaled to the main body. The equations describing the attitude motion of the main body are in terms of a set of Euler angles that relate the orientation of a reference frame fixed in the spacecraft to a reference frame whose orientation can be specified as an arbitrary function of time in inertial space. Properties of general Euler angle rotation matrices and the equations for the Keplerian orbit are contained in the Appendix. Author

Subject Categories:

  • Unmanned Spacecraft
  • Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE