Use of the Pseudo-Inverse for Design of a Reconfigurable Flight Control System.

reportActive / Technical Report | Accession Number: ADA111172 | Open PDF

Abstract:

Reconfiguration of the flight control system is achieved using generic inputs and transformation matrices for single primary control surface failure. Pseudo-inverse is used to evaluate appropriate transformation matrices. Design is tested against non-linear six degree-of-freedom model of the A-7D by simulating failure flights. System was found to provide desirable flying qualities upon reconfiguration. Author

Author(s):
Raza, Syed Javed
Author Organization(s):
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Descriptive Note:
Master's thesis,
Pagination:
0156

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
AFIT/GAE/AA/81D-23
 Subject Terms
Joint Capability Areas:
JCA_5_Command and Control; JCA_5.3_Planning; JCA_1_Force Support; JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_1.2_Force Preparation; JCA_1.2.6_Concepts; JCA_4.6_Engineering; JCA_1.2.5_Lessons Learned; JCA_5.5.2_Task; JCA_5.5_Direct
Modernization Areas:
Fully Networked C3
Communities of Interest:
Space
Descriptor(s):
*ATTITUDE CONTROL SYSTEMS, *FLIGHT CONTROL SYSTEMS, *COMPUTER AIDED DESIGN, AERODYNAMIC CONFIGURATIONS, THESES, DEGREES OF FREEDOM, DIGITAL SIMULATION, PSEUDO RANDOM SYSTEMS, AERODYNAMIC CONTROL SURFACES, ATTACK BOMBERS
Field(s)/Group(s):
Bombers, Attack and Fighter Aircraft, Statistics and Probability
Keyword(s):
Pseudo inverse method, A 7D aircraft
Report Date:
1981 Dec 01