Propelling nozzle for the thrust vector control for aircraft equ

Details Propelling nozzle for the thrust vector control for aircraft equ Propelling nozzle for the thrust vector control for aircraft equ

1991-11-01

1992-12-15

Barefoot, Galen

Aeronautics and astronautics

Aircraft, steering propulsion

Fluid

244 55, 244 125, 23926519, 23926535, B64C 1502

Patent

active

051709643

DESCRIPTION:

BRIEF SUMMARY
BACKGROUND AND SUMMARY OF THE INVENTION

The invention relates to a propelling nozzle for aircraft equipped with jet engines, and particularly for lateral thrust vector control.
Under the name of "Stealth Bomber B-2", an aircraft which is to be largely insensitive to radar and infrared detection is known, for example, from the German Publication DE-Z Fluo Revue, No. 1, January 1988. For the predominant part, the aircraft consists of a relatively far projecting wing unit with fuselage as well as pay load receiving structures integrated into it. For this purpose, by means of tunnel-type air inlets projecting out of the top sides of the wing surfaces, fanjet engines are to be supplied with air which are arranged in the wing structure in a physically inwardly and downwardly retracted manner. In other words, the known case involves a subsonic aircraft concept also because, in order to limit heat emissions resulting from the thrust jet, the thrust jet is a mixture of a hot core jet, relatively high parts of fan air -and additionally taken-in boundary layer air. This is in contrast to conventional aircraft which are designed for supersonic flight, are constructed as combat aircraft or as arms carriers and can be detected relatively easily by, among other devices, infrared sensors, and in the case of which often gas turbine jet engines with a relatively low bypass flow ratio are used in combination with an afterburning system (afterburner) which can be switched on, for example, for the supersonic flight operation.
From the German Patent Document DE-PS 11 44 117, a jet deflection arrangement is known which can be used, in particular, for vertical take-off aircraft and which consists of pipe bend segments which can be pivoted in a telescopic manner, in combination with an additional jet directing cascade that is situated in the pipe bend segment which can be moved the farthest to the outside and that consists of rotary blades which can each be pivoted simultaneously about respective central axes. The remaining jet deflection which is the result of such a jet directing cascade construction and arrangement is connected with a still considerable throttling effect as well as deflecting losses of the exhaust gas jet with the corresponding repercussions on the engine. The telescopic movability of the pipe bend segments is comparatively complicated and not free of susceptibility to trouble (thermally caused pipe warping). Also, in the known case, a response action for a thrust vector control should be expected that is relatively slow with respect to time.
From the German Patent Document DE-GM 70 08426, a thrust jet coupling arrangement is known in which deflecting blades arranged in the manner of a deflecting cascade are to each consist of a fixed inlet section and individual sections which can be pivoted on it continuously in order to thus try to eliminate the disadvantage of the already discussed throttling effect on the engine. It is a prerequisite for the implementability of the known case that corresponding multi-member deflecting blades with their respective first rotating shafts are arranged in the area of a diagonally cut outlet plane of a housing wall end. With respect to an axially symmetrical oncoming flow, no jet deflection or thrust vector control is possible in the known case which takes place on both sides of this oncoming flow in a plane, that is, toward one direction and to a direction that is opposite to it. On the whole, between the deflecting blades, no constant outlet cross-section or narrowest cross-section in the sense of a "convergent nozzle", which always accelerates the flow, is made available in the outlet plane. The adjusting expenditures and the degree of susceptibility to disturbances with respect to linkages between the individual blade segments are relatively high.
A propelling nozzle according to the initially mentioned type is known from the U.S. Pat. No. 3,640,469. In this known case, it is assumed that three flaps exist which are arranged at the same mutual distance in the plane containi

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