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Concepts for Aircraft Subsystem Integration
ISSN: 0148-7191, e-ISSN: 2688-3627
Published April 01, 1993 by SAE International in United States
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The Air Force has an initiative entitled, Subsystem Integration Technology (SUIT) to develop and demonstrate integration technology as applied to the traditional aircraft utility subsystems. Utility subsystems perform functions such as auxiliary power generation, environmental control, and fuel management. Commonly these different subsystems are developed independently and then interfaced when building a particular flight vehicle. The SUIT program considers all functions accomplished by the traditional utility subsystems to be responsibilities of a single entity called a utility suite. This suite is designed with overall vehicle level performance objectives rather than trying to maximize the performance of individual functions and is not bound to maintaining the traditional allocation of functions among the hardware labeled as fuel management, environmental control, or secondary power. The SUIT program has the objective of developing and demonstrating design data and assessment capability for a truly integrated subsystem suite. Novel concepts for a utility suite have emerged from recently completed concept studies conducted by several contractor teams. These concept studies showed that significant flight vehicle performance benefits appear to be possible via the utility suite approach as a result of the use of common or shared hardware and fluids to perform required functions, use of waste energy, and better overall energy-management. The utility suite approach reduces weight by having less standby hardware, reduces the acquisition and support cost via hardware commonality, provides for graceful degradation, and better energy management. These concept studies also showed that there is no one concept for structuring a utility suite that maximimizes all flight level performance parameters. This means that the integration design and allocation process of utility functions within the utility suite is a design process in and of itself.
|Technical Paper||SUIT: The Integration of Aircraft Utility Subsystems|
|Technical Paper||Changing the Utility Subsystem Paradigm|
|Technical Paper||SUBSYSTEM INTEGRATION TECHNOLOGY ASSESSMENT METHODOLOGY|
CitationBurkhard, A. and Haskin, W., "Concepts for Aircraft Subsystem Integration," SAE Technical Paper 931377, 1993, https://doi.org/10.4271/931377.
- King, Howard High Reliability Fighter Concept Investigation Study ASDTR- 88-5023 July 1988
- Ostgaard, John et al Architecture Specification for PAVE PILLAR Avionics AFWAL-TR-87-1114 January 1987
- Mattes, Robert et al Integrated Control Law Evaluation WRDC-TR-89- 2090 August 1989
- Seabridge, A. G. Utility Systems Management Aerospace 13 7 1990
- Harrison William III Aircraft Thermal Management: Report of the Joint WRDC/ASD Aircraft Thermal Management Working Group WRDC-TR-90-2021 February 1990
- Hill Bernard Watts, Roland The Impact of VMS In Subsystems Integration 1992 AIAA Aerospace Design Conference, AIAA Papar No. 92-1078 Irvine CA, 3-6 February 1992
- Blanding, David E. et al. Subsystem Integration Technical Assessment SAE AeroTech 1992 Conference, SAE Paper No. 92-2006, Anaheim, CA, 5-8 October, 1992
- Burkhard, Alan Changing the Utility Subsystem Paradigm SAE Third Annual Avionics Systems Division (ASD) Technical Conference Denver 22 April 1993.