Accession Number:

AD0411806

Title:

COMPARISON OF HIGH-GAIN-LINEAR AND SELF-ADAPTIVE FLIGHT CONTROL SYSTEMS FOR A TYPICAL WINGED RE ENTRY VEHICLE

Descriptive Note:

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

Report Date:

1963-05-01

Pagination or Media Count:

139.0

Abstract:

To establish the differences between self-adap tive and normal linear designs, both systems are applied to the problem of controlling the short period dynamics of the X-15. The self-adaptive system studied is an early design of the MH-96 Autopilot. The high-gain-linear system is de signed on the basis of selecting the forward branch compensation so that the system is in sensitive to vehicle-parameter variations over the bandwidth of the desired response and a pre filter or feedback-branch compensation is used to obtain the desired command response. The root-locus method is used in the initial design of the system but, the system could not be simu lated on the analog computer. The frequency response method was used for the design of a second system. From this linear analysis of design procedures and response data, it is con cluded that the high- gain-linear system is pre ferred to a self-adaptive system however, an analysis of the effects of system non-linearities and component noise must be made before a fixed gain system can be applied to the physical problem of widely varying vehicle parameters.

Subject Categories:

  • Flight Control and Instrumentation

Distribution Statement:

APPROVED FOR PUBLIC RELEASE