Aircraft Load Alleviation and Mode Stabilization (LAMS): B-52 System Analysis, Synthesis, and Design
Abstract
The Load Alleviation and Mode Stabilization (LAMS) program was conducted to demonstrate the capabilities of an advanced flight control system (FCS) to alleviate gust loads and control structural modes on a large flexible aircraft using existing aerodynamic control surfaces as force producers. The analysis, design, and flight demonstration of the flight control system was directed toward three discrete flight conditions contained in a hypothetical mission profile of the B-52E test aircraft. The FCS was designed to alleviate structural loads while flying through atmospheric turbulence. The LAMS-FCS was produced as hardware and installed on the test vehicle, B-52E AF56-632. Test vehicle modifications included the addition of hydraulically powered controls, a fly-by-wire (FBW) pilot station, associated electronics and analog computers at the test engineer's stations, instrumentation for system evaluation, and the LAMS flight controller. Flight demonstration of the LAMS-FCS was conducted to provide a comparison of analytical and experimental data. In addition, a LAMS C- 5A study was included in the program. This portion of the program was to analytically demonstrate that the technology developed for the B-52 could be applied to another aircraft. The C-5A study was conducted for one flight condition in the C-5A mission profile.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1969
- Accession Number
- AD0864555
Entities
People
- M. A. Bender
- P. M. Burris
Organizations
- Boeing