Advanced Aircraft Electrical System Control Technology Demonstrator. Phase I. Analysis and Preliminary Design.
Abstract
This report summarizes Task 1-Requirements Analysis and Task 2-Conceptual Design and documents the results of Task 3, Phase I, of this two-phase program. Task 3 is the preliminary design of an advanced aircraft electrical system (AAES). The AAES is designed to meet the requirements of a 1990 time frame two-engine tactical aircraft with multi-mission capability. The AAES performs the functions of power generation, distribution and control of power to loads, system protection, and load management. Key characteristics of the AAES are: Integrated avionics and power data bus configuration consisting of Digital Avionics Information System (DAIS) standard elements (MIL-STD-1750 processor, MIL-STD-1553B data bus, controls and displays, and remote terminals (RT)). Intelligent Electrical Load Management Centers (ELMC) capable of controlling power to loads; Built-in-test (BIT) capability to isolate faults to the module level. BIT includes both circuit and data monitoring checks. Solid State Power Controllers (SSPC) to replace circuit breakers and power control switches. SSPCs are turned on/off via computer control. Generator control, protection and status monitoring by a Generator Control Unit (GCU) compatible with DAIS hardware and software. Multimission data information system through programmable system processors, ELMCs and standard DAIS elements. Automatic load management for increased aircraft survivability and probability of mission completion.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1982
- Accession Number
- ADA113633
Entities
People
- D. E. Hankins
- G. L. Dunn
- I. S. Mehdi
- P. J. Leong
- T. R. Boldt
Organizations
- Boeing Military Aircraft