1002. Methodologies for Predicting Avionic System Capability and Weight in CTOL and VTOL Fighter/Attack Aircraft – 1975 to 1995


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W A Falkenstein: 1002. Methodologies for Predicting Avionic System Capability and Weight in CTOL and VTOL Fighter/Attack Aircraft – 1975 to 1995. 1974.



There is a continuing need in advanced conceptual studies for tools and techniques that extend or provide methodologies for useful application in design of fighter/attack aircraft. This paper presents two methodologies for predicting avionic system gross capability and weight in these military aircraft in the 1975 to 1995 time frame.
An historical background is presented that illustrates the nature of technological advances in electronic circuitry. The effect has been a tremendous reduction in size and weight of individual circuit elements. Unfortunately for the weights engineer, no weight saving has been achieved in the overall avionic systems of conventional takeoff and landing (CTOL) fighter/attack aircraft. This is due to the ever growing demand for increased capability. The consequent functional proliferation is responsible for maintaining design weight of the avionic system in fixed proportion to the design weight empty of the aircraft. This is established empirically. A methodology is developed for determining the increased functional growth or capability that will prevail in the time period 1975 to 1995. Generalizations are established for expected transformation of these future functions into gross system features. Extrapolation of a current avionic system capability is accomplished at constant weight by this methodology. An example is given.
A second methodology is suggested by the first and is developed to allow extrapolation of avionic system weight, assuming capability is unchanged. Application to conventional takeoff and landing (CTOL) aircraft avionic systems is contrary to the established evidence that supports the previous methodology. However for vertical takeoff and landing (VTOL) aircraft, higher weight sensitivity may result in capability restrictions on the avionic system. Using this methodology, then, the advanced system designer can determine weight savings expected in an avionic system having constant capability with time. An example is given.
Other areas, such as cost and performance, are suggested for future work to expand the utility of those two methodologies.


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