HYDRAULIC SYSTEM VULNERABILITY STUDY
Abstract
Aircraft hydraulic systems are presently designed with emphases placed on satisfying performance requirements with minimum penalties in weight, reliability, maintenance, and costs. Results from limited war analyses have indicated the vulnerability of current hydraulic systems. Vulnerable areas of these systems were then protected with armorplate, resulting in mission penalties. A hypothetical airplane was defined, based on the F-8 configuration, with twin engines and a weight of 45,000 pounds. Conceptual system designs for this airplane were defined with increased redundancy incorporating backup or isolation features without the use of armorplate. These systems were assessed for vulnerability/survivability, reliability, maintainability, weight, performance, and system cost. These assessments provided system rating values and inputs for operational costs. The increase in redundancy (increase over the baseline system) resulted in most of the systems having probabilities of survival greater than the baseline system with armorplate. Further increase in probability of survival was achieved with the use of isolation and backup systems. A five-year development plan was prepared involving component development, system evaluation, and flight test evaluation.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1968
- Accession Number
- AD0833150
Entities
People
- C. G. Brock
Organizations
- Vought