JP2615202B2 - Flying object thrust deflection device - Google Patents

Description

Description: FIELD OF THE INVENTION The present invention relates to an improved projectile thrust deflection device.

[Conventional technology]

Conventionally, thrust deflection devices for flying vehicles have been described, for example, on page 12 of "Defense Technology" (February 1989),
When the projectile body 05 is installed in the nozzle of the booster 03 which is a thrust generator shown in FIG. 5, and the thrust deflection is required, the angle of the vane 05 in the nozzle is adjusted by the actuator 01.
And thrust deflection by changing the direction of the jet.

After the propellant in the booster 03 burns, the separation mechanism 04
The booster 03 was separated from the flying body 05.

[Problems to be solved by the invention]

In the above-described thrust deflection device using the conventional vane 05, since the vane deflection mechanism including the vane 05 and the actuator 01 is mounted in a limited space in the booster 03, severe conditions such as space and heat resistance are required. Had been requested.

Further, the assembly work in the booster 03 of these vane deflection mechanisms is also time-consuming. Further, since the jet of the booster 03 acts on the vane 05, the jet for generating thrust is disturbed, and this may cause thrust loss.

SUMMARY OF THE INVENTION An object of the present invention is to provide a flying object thrust deflection device which can solve the above-mentioned problems of the conventional thrust deflection device.

[Means for solving the problem]

For this reason, the thrust deflection device for a flying object according to the present invention includes a thrust generating device that is swingably attached to the flying object body by, for example, a spherical bearing, and both ends of the thrust generating device and the flying object body. And an actuator for swinging the thrust generator.

[Action]

In the present invention, by operating the actuator, the entire thrust generator swings with respect to the projectile body, the direction of the thrust is deflected, and the thrust in the direction required for the projectile direction of the projectile is obtained. Is obtained.

In addition, by providing an actuator for connecting the projectile body and the thrust generator, the thrust can be deflected without changing the inside of the thrust generator such as a booster. It is also possible to avoid being affected by the high-temperature heat generated inside.

Further, since the jet of the thrust generating device does not act on a device that performs thrust deflection such as a vane as in the conventional device, and the flow of the combustion gas is not disturbed,
No thrust loss occurs.

〔Example〕

A first embodiment of the present invention will be described with reference to FIGS.

Reference numeral 5 denotes a flying object main body, and a booster 3 as a thrust generating device is attached to a rear end of the flying object main body 5 via a spherical bearing 2 so as to be able to swing with respect to the flying object main body 5.

Reference numeral 4 denotes a separation mechanism of the booster 3 provided around the rear part of the flying object body 5. The outer wall surface of the flying object body 5 behind the separation mechanism 4 and the outer wall surface of the front end of the booster are:
It is connected by a linear actuator 1 as an actuator via spherical bearings 7,6.

The linear actuator 1 is, as shown in FIG.
Four are provided at equal intervals on the upper, lower, and both sides of the flying object main body 5 at an angle of 90 degrees in the same direction of the flying object main body 5.

The upper and lower two linear actuators 1 are expanded and contracted in the direction indicated by the arrow A in FIG. 2 so that the booster 3 is rotated around the a-axis by the spherical bearing 2 and the flying object body 5 is Perform thrust deflection in the pitch direction,
Further, by expanding and contracting the two linear actuators 1 on both sides in the direction indicated by the arrow B in FIG. 2, the booster 3 is rotated around the b-axis by the spherical bearing 2, and the flying object main body is moved in one direction. Perform thrust deflection. Therefore, by the operation of the linear actuator 1, the booster 3 can be swung about the spherical bearing 2 in a desired direction around the a-axis and the b-axis of the flying object main body 5, whereby
The direction of the thrust of the booster 3 is deflected, and the flying object body 5
Can be deflected in a desired direction.

After the propellant in the booster 3 has burned, the booster 3 is separated from the flying object body 5 by the separation mechanism 4.

As described above, in this embodiment, the operation of the linear actuator 1 causes the booster 3 to fly the flying object body 5.
, The direction of the thrust of the booster 3 can be changed, and the flying direction of the flying object body can be deflected.

Further, the linear actuator 1 is provided outside the booster 3 so as to be connected to the outer wall surface of the flying object body 5, and is prevented from being affected by high-temperature combustion gas generated in the combustion chamber of the booster 3. Further, there is no need to change the internal structure of the booster 3, and the existing booster 3 can be used without any modification.

Further, the jet flow of the booster 3 is not disturbed by acting on a deflecting device such as a vane as in the conventional device, and the generation of thrust loss can be avoided.

 A second embodiment of the present invention will be described with reference to FIG.

The flying object of the present embodiment does not include the booster 3 as the above-described thrust generator.

And the flying body rear part 11 equipped with the rocket motor 10
Is attached to the flying object main body 5 constituting the front of the flying object via a spherical bearing, not shown, as in the first embodiment, and the linear member shown in FIGS. A linear actuator similar to the actuator 1 is connected to the flying object main body 5.

In the present embodiment, similarly to the first embodiment, the thrust of the rocket motor 10 is changed to a desired direction by swinging the rear part 11 of the flying object with respect to the flying object body 5. Thus, the same operation as in the first embodiment can be performed, and the same effect can be obtained.

〔The invention's effect〕

The flying object thrust deflecting device of the present invention has the following effects by adopting the configuration shown in the claims.

(1) The thrust can be deflected in a desired direction by swinging the thrust generator with respect to the flying object body by the actuator.

(2) There is no need to internally change the thrust generator, which requires a large development cost and development period.

(3) No thrust loss occurs due to thrust deflection devices such as vanes.

(4) The actuator is not affected by the high-temperature gas of the thrust generator and does not require strict conditions such as heat resistance.

[Brief description of the drawings]

FIG. 1 is an explanatory view of a main part of a first embodiment of the present invention, FIG. 2 is a perspective view of the same embodiment, FIG. 3 is an explanatory view of a linear actuator part of the same embodiment, and FIG. FIG. 5 (a) is a schematic view of a second embodiment of the present invention, FIG. 5 (a) is an explanatory view of a conventional flying object thrust deflection device, and FIG. It is explanatory drawing of a part. 1 ... linear actuator, 2 ... spherical bearing, 3 ... booster, 4 ... separation mechanism, 5 ... flying object body, 10 ... rocket motor, 11 ... flying object rear part.

Claims (1)

(57) [Claims] 1. A thrust generator attached to a projectile body so as to be swingable, and an actuator connected to both ends of the projectile body and the thrust generator to swing the thrust generator. A flying object thrust deflection device characterized by the following.