Title

Re-Entry Vehicle Control System Design and Mechanization

Date

1966

Index Abstract

Coming Soon

Photo Quality

Not Needed

Report Number

AFFDL TR 66-3

Creator

Scharmack, D. K.

Ward, M. D.

Corporate Author

Honeywell, Inc.

Laboratory

Air Force Flight Dynamics Laboratory

Extent

210

NTRL Accession Number

AD485616

Identifier

AD0485616

Access Rights

Export Control

Distribution Classification

1

Contract

AF 33(615)-1858

DoD Project

8225

DoD Task

822501

DTIC Record Exists

Yes

Distribution Change Authority Correspondence

AFFDL LTR

Abstract

A nonlinear optimal feedback control scheme for controlling a vehicle re-entering the earth's atmosphere from lunar return initial conditions is reported. The optimal feedback control law used in the scheme is obtained from a multi-dimensional surface fit of the control function for several optimal trajectories. Partials of the control with respect to the state vector are included in the fitting procedure. The functional minimized by the trajectories is the total (convective plus radiative) stagnation point heat. The feedback control scheme is developed, and several re-entry trajectories are simulated. Modest increasing total heat from optimal values are observed, and large (although tolerable) terminal point errors occur. It is believed that the terminal errors can be greatly reduced, if necessary. A powerful predictor scheme is developed which allows optimal a function of a parameter. This is used to extend the range of an optimal trajectory, to perform an absolute minimum test, and to map the optimal re-entry corridor. Sufficiency tests for a relative minimum are mechanized, and it is shown that the trajectories considered are minimizing paths.

Report Availability

Full text available

Date Issued

1966-04

Provenance

Lockheed Martin Missiles & Fire Control

Type

report

Format

1 online resource