Aeronautics and astronautics – Aircraft structure – Passenger or cargo loading or discharging
Patent
1986-06-25
1988-05-24
Barefoot, Galen
Aeronautics and astronautics
Aircraft structure
Passenger or cargo loading or discharging
89 154, 89 158, 89 159, B64D 102
Patent
active
047460830
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND OF THE INVENTION
Modern military aircraft carry various loads slung either under the fuselage or under the wings, these loads usually being releasable in flight, mainly when they are bombs or missiles.
To ensure good separation between the load and the aircraft within a wide range of its flight conditions, it is not sufficient to detach the load: it is also necessary to impart to it a linear ejection speed Vz and an angular ejection speed .omega.y. These two quantities Vz and .omega.y are determined by means of ejection tests in a wind tunnel. Their value is not constant, but is a function of the flight parameters: the Mach number, altitude, corrected speed, incidence and load factor. In general, a minimum quantity Vz satisfactory over the entire range can be defined. This is not true of the quantity .omega.y which varies greatly according to the flight conditions.
The ejection systems existing at the present time in aeronautics have to be adjusted on the ground and consequently only have an optimum setting for a single flight condition at the moment of release.
The object of the present invention is the provision of a modular ejection device which is capable, on the one hand, of ensuring a horizontal translational movement of the missile to disconnect it from its rail before ejection and, on the other hand, of adjusting the angular ejection speed as a function of the flight parameters.
The following description referring to the attached drawings and given by way of non-limiting example will make it easy to understand how the invention can be put into practice.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a diagrammatic view, in partial longitudinal section, illustrating an embodiment of the present invention.
FIGS. 2 and 3 are sectional views on a larger scale of an embodiment detail in two operating positions.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
The ejector device illustrated in FIG. 1 consists of an assembly of separate modules, each having a particular function: pressure of a few hundred bars and equipped with a pyrotechnic valve, or a pyrotechnic chamber equipped with a gas generator (for example, with standard fuses); pressurized gas is supplied to its inlet, exerts an ejection force on the load carried 3; source 1 and which performs three functions: of its rails 5--5 attaching it to the aircraft (the translational movement will be an acceleration and stop, in order to bring the translational speed of the load 3 back near to zero after it has been removed from its rails 5 and before ejection); with a double needle 7A-7B, adjusts the pressure distribution between the front jack 2A and rear jack 2B, to impart to the load 3 an angular pitching speed determined in accordance with the instantaneous flight conditions of the aircraft; 2B can only be generated when the movement of acceleration and stop is completed.
These various modules are connected by means of pressurized-gas conduits. More specifically, the energy source 1 is connected to the inlet of the sequential module 4 by means of a conduit 8, whilst the outlets of the latter, downstream of the needles 7A, 7B, are connected respectively to the front jack 2A and to the rear jack 2B by means of conduits 8A and 8B. The double-needle servo slide valve 6 is controlled, in turn, by the intervention of a transmission link 9 from a servo-module 10 programmed to integrate the various flight parameters which are appropriately detected.
The mode of operation of the sequential module 4 described above in relation to FIG. 1 will be understood better by also referring now to FIGS. 2 and 3, in which the same reference numerals have been used to designate the same elements.
In addition to these, the drawings also show a rod 11 for pulling the load 3 forwards to detach it from its rails 5, this rod 11 acting on a boss 3A integral with the load 3 by means of an articulated latch mechanism 11A which, at rest (FIG. 2), is kept engaged by an elastic lever stop 11B and which is guided in its longitudinal travel d (FIG. 3) by a carriage 11C.
REFERENCES:
patent: 1847545 (1932-03-01), Wiley
patent: 3010752 (1961-11-01), Geffuer
patent: 3883097 (1975-05-01), Billot
patent: 4043525 (1977-08-01), Jakubowski
patent: 4187760 (1980-02-01), Holt
patent: 4187761 (1980-02-01), Holt et al.
patent: 4377103 (1983-03-01), Kovalenko
patent: 4388853 (1983-06-01), Griffin et al.
patent: 4399968 (1983-08-01), Stock et al.
Dupin Gerard
DuPont Moise
Avions Marcel Dassault-Breguet Aviation
Barefoot Galen
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