GB2068311A

GB2068311A - A jet reaction propelled flying body

Info

Publication number: GB2068311A
Application number: GB8041067A
Authority: GB
Original assignee: Dornier GmbH
Current assignee: Dornier GmbH
Priority date: 1980-01-30
Filing date: 1980-12-22
Publication date: 1981-08-12
Also published as: DE3003231A1; IT1167303B; GB2068311B; FR2474439A1; IT8068752A0; SE8100747L; DE3003231C2

Abstract

For improved control of motion about its pitching or yaw axis, a flying body has two or more nozzles (10, 12) with their axes (X%, X%) on a circle concentric with the longitudinal axis (X) of the body and convergent and inclined to the longitudinal axis at equal angles (a). A rotatable spoiler plate (18), (Fig. 3, not shown) with holes may be arranged behind the nozzles, so that the plate can interrupt and deflect the propellant gas jets to generate rolling control moments. <IMAGE>

Description

SPECIFICATION A jet reaction propelled flying body This invention relates to a jet reaction propelled flying body, for example a rocket, having two or more jet reaction driving units, for example regulatable engines with their jet outlet nozzles having jet axes equiangularly spaced on a circle concentric with the longitudinal axis of the flying body.

In such a flying body it is usual to dispose the engines or the outlet nozzles so that the jets emerge parallel with or directed away from the longitudinal axis. This disposition of the engines or of the outlet nozzles makes it possible, by variation of thrust, to control for example pitching of the flying body.

Also, drive systems are known in which the outlet nozzles for controlling the flying body are arranged to be pivotable about the rolling and also about the pitching or yawing axis. In such systems however problems arise with regard to sealing of those parts of a drive system which are movable in relation to one another, i.e. sealing of the outlet nozzles in respect of fixed parts and in respect of an actuating device required for adjusting the nozzles.

It is an object of the invention to provide both an improvement in the detachment of the flow, particularly in the region of the nozzle outlets, and an improvement in the thrust effect with regard to the attainable control moments about yawing and pitching axes.

According to this invention, there is provided a jet reaction propelled flying body having two or more jet reaction driving units with jet outlet nozzles whose jet axes lie on a circle concentric with the longitudinal axis of the flying body, wherein i) each jet axis also lies in a plane which contains the longitudinal axis; and ii) the jet axes are convergent and inclined to the longitudinal axis at equal angles. With this arrangement, the jets of propellant gas which emerge at an angle convergent to the longitudinal axis of the flying body, have, compared with known constructions which have outwardly directed gas jets, for a given distance of the centre of gravity of the flying body from the rear edge thereof, substantially greater lever arms to apply thrust forces, and thus greater control moments about the pitching axis of the yawing axis.Mutual interference of the jets of gas enables higher thrust forces to be achieved.

To generate rolling control moments, the jet outlet nozzles may be disposed to be rotatable about axes inclined in relation to the jet axes.

Also for generation of rolling control moments, there may be associated with the jet outlet nozzles a spoiler plate rotatable about the longitudinal axis of the flying body, the spoiler plate having-holes through which can pass the propellent gas jets, the plate also having jet deflecting surfaces which can be moved into the gas jets. The convergent jet guidance in conjunction with deflection of the propellant gas jets by the spoiler plate results in an increase in roll control moments.

Embodiments of the invention will now be described by way of example, with reference to the drawings, in which: Figure 1 is a diagrammatic side elevation, partly in section, of the rear portion of a rocket-powered flying body; Figure 2 is an end elevation of the flying body of Fig. 1 viewed in the direction of the jet outlet nozzles; Figure 3 is a view similar to Fig. 1 of another embodiment; and Figure 4 is an end elevation of the flying body of Fig. 3 viewed in the direction of the jet outlet nozzles.

Referring to the embodiment shown in Figs.

1 and 2, reference numeral 1 denotes the flying body as a whole, 2 its outer casing and X its longitudinal or rolling axis. Disposed inside the casing 2 in a bundled arrangement are drive systems 3, 4 or 5, 6, for example rocket engines. The longitudinal axes of the engines 3 to 6 and the jet emergence axes X' lie in planes E-E which also contain the axis X. With an arrangement shown, comprising four driving engines, in each case two engines are diametrally opposed to each other, the jet axes X' being equidistant from one another, when viewed in the peripheral direction.

In conventional manner, the rocket engines 3 to 6 comprise combustion chambers 8, with corresponding fuel storage containers, and propellant feed means having regulating devices, not shown.

The jet outlet nozzles 10, 11, 12, 1 3 of the rocket engines 3 to 6 and the jet axes X' thereof are inclined by an equal angle a towards the rolling axis X so that the propellant gas jets emerge from the nozzles 10 to 1 3 in a mutually convergent direction. As described, the jet axes X' lie in planes E-E which also include the axis X.

In the embodiment of Fig. 3 and 4, there is associated with the outlet orifices 23 of the jet outlet nozzles 10 to 1 3 a spoiler plate 1 8 having in it holes 1 9 corresponding to the number and diameter of the orifices 23. By means of the holes 19, there are formed on the spoiler plate 1 8 intermediate wall portions 22 which can interrupt the propellant gas jets in order to generate a rolling motion of the body 1 about its longitudinal axis X. The spoiler plate 1 8 is of dished shape and its outer wall face 24 is at the smallest possible distance from the orifices 23.Further, referring to Figs. 1 and 3, a denotes the distance between the centre of gravity C and the rear edge of the flying body, Tdenoting the thrust resultant and h the effective lever arms.

The mode of operation of the embodiment of Figs. 1 and 2 is as follows: The jet of propellant gas emerging at an angle to one another and to the longitudinal axis generate within the interference space 1 5 and in an adjacent zone a thrust-increasing interference effect. For a given distance a between the centre of gravity C and the rear edge of the flying body, the result, for pitch control or yaw control of the flying body 1, is increased pitching moments or yawing moments, by reason of the enlargement of the effective lever arms h in relation to the thrust resultant T, in contrast to the known jet emergence parallel with, ordirected outwardly from, the longitudinally axis.The outer casing 2 may be arranged in a manner (not shown) such that the interference zone 1 5 is at least partly within the casing.

in the embodiment shown of Figs. 3 and 4, in addition to yaw and pitch control, the spoiler plate 1 8 can provide for deflection of the propellant gas jets in such a way as to generate a rolling moment. To produce the rolling moment, the spoiler plate 1 8 is rotated about the axis of a shaft 21 so that the holes 1 9 no longer coincide with the jet outlet orifices 23, but the intermediate wall portions 22 of the spoiler plate 1 8 enter simultaneously and from the same side into the propellant gas jets emerging from the outlet nozzles 10 to 1 3 and produce the required deflection.

This gives rise to a thrust component which acts on the flying body tangentially in a peripheral direction to influence the location of the flying body 1 in relation to its rolling axis.

Claims

1. A jet reaction propelled flying body having two or more jet reaction driving units with jet outlet nozzles whose jet axes lie on a circle concentric with the longitudinal axis of the flying body, wherein i) each jet axis also lies in a plane which contains the longitudinal axis; and ii) the jet axes are convergent and inclined to the longitudinal axis at equal angles.

2. A flying body according to claim 1 wherein the driving units are regulatable engines.

3. A flying body according to claim 1 or claim 2 wherein the jet axes are equiangularly spaced on the said circle.

4. A flying body according to any preceding claim wherein the jet outlet nozzles are disposed so as tobe rotatable about axes inclined to the jet axes, for generating rolling control moments.

5. A flying body according to any of claims 1 to 3, wherein a spoiler plate is associated with the jet outlet nozzles, the spoiler plate i) having holes corresponding to the nozzles for passage of propellant gas, ii) being rotatable about the longitudinal axis of the flying body, and iii) has gas deflecting surfaces which can be moved into the propellant gas jets for deflection thereof, for generating rolling control moments.

6. A flying body according to claim 5 wherein the spoiler plate is of dished form with its convex surface directed towards the jet outlet nozzles.

7. A flying body according to any preceding claim having an outer casing so disposed in relation to the jet outlet nozzles that an interference zone of the propellant gas jets is at least partly located within the outer casing.

8. A jet reaction propelled flying body constructed and arranged substantially as herein described and shown in Figs. 1 and 2 of Figs. 3 and 4 of the drawings.