JPS62206390A - Guided missile - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed description of the invention] [Industrial application field] This invention has stabilizing wings at predetermined positions on the front half of two aircraft.

The present invention also relates to improvements in the maneuverability and aerodynamic performance of a flying object having a steering blade at a predetermined position in the rear half.

[Conventional technology]

In general, a flying object has a stabilizing wing at a predetermined position in the front half and a steering wing at a predetermined position in the rear half in order to have maneuverability and aerodynamic stability. Motion performance is achieved by steering the steering blades using a steering device built into the flying object, and aerodynamically stable flight performance is achieved by the stabilizing blades.

An example of a conventional flying object is shown in FIG. In Figure 8 (
1) is the body of the guided flying vehicle, (2) is the steering wing, (3) is the stabilizing wing, (4) is the antenna, and (5) is the antenna drive mechanism.

(6) is the target, and ■ is the flight velocity vector of the guided flying object.

L is a force perpendicular to the direction of flight, hereinafter referred to as lift force. θ is the reference axis, which is usually the angle between the ground and the axis of the guided flying object, and is hereinafter referred to as attitude angle. α is the angle between the flight direction and the axis of the guided flying object, and is hereinafter described as the angle of attack. σ is the angle formed between the direction of the target (6) seen from the tracking device consisting of the antenna (4) and the antenna drive mechanism (5) and the axis of the guided flying object, and is hereinafter described as the oscillation angle. Guided projectile target (
In order to follow the movement in 6) and fly, a lift force is required to change the direction of flight, and the most common method is to use aerodynamic force for lift force. Namely, steering! (By moving 21, the attitude of the aircraft +11 is changed using the lift force acting on the steering IJE (2), creating an angle of attack α, generating lift on the 2 aircraft (1) and the stabilizing wing (3), and flying. In order to obtain high maneuverability and aerodynamic stability for such guided flying objects, it is sufficient to increase the wing area, but in order to be mounted on an aircraft or stored in a launcher, the wing width must be increased. is subject to restrictions.

You can't make your wings bigger unnecessarily. For this reason, conventional guided flying vehicles have been limited in their maneuverability and aerodynamic stability.

[Problem to be solved by the invention] In the example of the conventional flying object shown in Fig. 8, when the target (6) moves at high speed, a large lift force is required to follow it. For this purpose, there is a method of increasing the angle of attack α or increasing the size of the steering blade (2) and the stabilizing blade (3). However, as the angle of attack α increases, the lift force increases (
However, there is a limit to this, and once this limit is exceeded, the lift force will not increase any further and 1. On the contrary, it will decrease. Furthermore, if the angle of attack a is made too large, the swing angle σ will become large, exceeding the swing angle limit of the antenna drive mechanism (5).
There is a risk of losing sight of goal (6).

On the other hand, if the steering blade (2) and stabilizing blade (3) are made too large.

Launcher 2 It becomes difficult to mount it on an aircraft, etc., and it also becomes difficult to handle it. Especially for guided flying vehicles mounted on aircraft.
If the steering wing (2) and the stabilizing wing (3) are large, air resistance increases, which increases the burden on the mother aircraft during carry-over flight, resulting in a reduction in flight performance. As described above, the motion performance and aerodynamic stability performance of conventional guided flying vehicles are limited by the wing area. This invention was made to solve this problem, and when installed on a Launcher 2 aircraft, etc., the conventional steering wing and stabilizing wing accommodate the steering deployable wing and stabilizing deployable wing, respectively, making the two aircraft compact. After the second launch, after a predetermined delay time set as the operating time of the locking device consisting of a hydraulic cylinder and a coil spring, that is, after the two deployable wings reach a distance where they do not mechanically interfere with the mother aircraft or the launcher, The objective is to deploy the deployable wings to obtain a larger wing area than conventional guided flying vehicles, and to obtain large lift, high motion performance, and stability performance.

[Means for solving problems]

The guided flying object according to the present invention has a deployable steering wing for increasing the wing area, a deployable stabilizing wing, a spiral spring that stores torsional torque as energy for deploying these deployable wings, and a spiral spring that stores this torsional torque to the deployable wing. It is provided with a transmission mechanism for transmitting the information, and a deployable wing locking device for storing the deployable wing and deploying the deployable wing after a predetermined delay time after the second firing.

[For production]

In this invention, the wire is withdrawn from the locking device after firing from the launcher or aircraft.

After the locking device is released and a predetermined delay time set by the locking device has elapsed, the deployable wings are deployed by the deployment energy stored in the spiral spring.

〔Example〕

FIGS. 1 and 2 are overall configuration diagrams of an embodiment of a guided flying object according to the present invention.

Figure 1 shows two guided flying vehicles before launch (1)
A steering device (not shown) built into the aircraft, a steering N (2) that is steered by the steering device, and a stabilizing wing (3) fixed to one fuselage (1) are provided, and the steering wing (2) is equipped with a deployable steering wing. (7)
However, in the stable* (3) state, the deployed stabilizing wing (8) is stored by a locking device (9) provided in the space. (10) is a wire for unlocking.

Figure 2 shows the guided flying object after launch, and the wire QO) is pulled out from the locking device (9) at the second launch.

Unlocked 2M opening rudder blade 7) and deployment stabilizing blade (8)
) has been expanded, increasing the wing area.

FIG. 3 is a sectional view taken along the line A-A in FIG. 1, and is composed of one fuselage (11, a steering wing (2), a locking device (9), and a wire OI).

Figure 4 shows the steering blade (
2) and the deployment mechanism built into the stabilizing wing (3), and the inside of the stabilizing wing (3) is shown as an example. In Figure 4, the deployment stabilizer is housed inside the stabilizer wing (3)! (81 and a spiral spring (11) for storing the torsional torque energy for deploying the deployment amount stabilizing wing (8), A pair of gears (1
4) and (15), and is configured to maintain the stored state by a locking device (9).

FIG. 5 is a sectional view taken along line BB of the stable* (3) used in the embodiment of FIG. The spiral spring (11) has one end fixed to the stabilizing blade (3) and the other end fixed to the winding shaft (12).

This winding shaft (12) is rotatably supported by the stabilizing blade (3) by a bearing (16). Further, the m-open center shaft (3) of the expanded i[(8) is also rotatably supported by the stabilizing blade (3) by a bearing (7).

6 and 7 are sectional views taken along the line CC in FIG. 4.

It shows a cross section of the locking device (8). Figure 6 shows the state before launch, and the deployment is stable! 1 (7), a gear (Is), and a shaft (13), which are supported by the stabilizing blade (3). The hydraulic cylinder (18) is fixed to the stabilizing wing (3) via a guide (19). Hydraulic cylinder (18
) The wire a passes through a hole (21) provided in the piston rod (20) and a hole (22) provided in the guide (19).

Also, the piston rod (20) is inserted into the hole (23) provided in the deployable wing stabilizer (7), and the spiral spring (1) shown in FIG.
The torsional torque stored in 1) keeps the deployment stabilizing wing (8) that is about to deploy in the retracted state. (24)
is a piston, and (25) is a spring for driving the piston.

(26) is the oil in the hydraulic cylinder (18), and (27) is an O-ring for sealing the oil (26).

Figure 7 is a diagram after a predetermined delay time has elapsed after launch from the mother machine. 1. After the wire (not shown) has been pulled out from the guide (19) and Vitostone rod (20), the coil spring (2
5) due to the energy stored in.

The piston (24) and piston rod (20) rise.

When it is pulled out from the hole (22) provided in the deployment N (7).

The deployment stabilizing wing (8) is deployed by the force of the torsional torque stored in the spiral spring (11) in FIG. 5 via the gear (15).

Next, the operation of the above embodiment will be explained with reference to FIGS. 1 to 7. Figure 1 shows the deployable steering wing (7) and stable deployment! 31 (An explanatory diagram showing the state in which 81 is stored in the steering blade (2) and the stabilizing vane (3). Figure 2 is an explanatory diagram showing the state in which these are in the H position. Figure 3 is an explanatory diagram showing the state in which they are deployed and stabilized. Wings (8)
Figures 4 and 5 are explanatory diagrams of the interior of the stabilizing wing (3) with the deployed stabilizer H (8) stored, as seen from the front. FIG. 6 is an explanatory diagram showing the state in which the deployed stabilizing wings (8) are locked and retracted by the piston rod (20) before launch, and FIG. FIG. 3 is an explanatory diagram showing the state immediately after the deployment stabilizing wing (8) is unlocked after the robot has risen.

First, in FIG. 4, the torsional torque energy stored in the spiral spring actuates to deploy the deployable wing stabilizer (7) via the (!i vehicle (141, (Is)), but the locking device (9 ) (ζ Therefore, the expansion Un is prevented and the wire is in the storage state shown in Figure 1. At this time, the wire QOI is
The n-wing locking device (9) is penetrated as shown in FIG. 6, and the piston rod (20) attempting to rise is locked by the coil spring (25). On the other hand, the other end of the piston rod (20) is connected to a hole (23) provided in the deployable wing (8).
), which prevents the deployment stabilizing wing (8) from deploying. Next, when the aircraft body (1) is launched from an aircraft or a launcher, the wire αω is pulled out from the locking device (9) by the force of the coil spring (25) as shown in FIG.

The piston rod (20) enters the upward movement and the deployment is stabilized H.
It is pulled out through the hole (23) provided in (8). Then, the state shown in FIG. 7 is reached, which indicates the completion of extraction. The time from the start of the withdrawal to the completion of the withdrawal is determined by the viscosity of the oil (26) and the size of the gap between the piston (24) and the cylinder (18). By selecting and determining the viscosity of the oil (26) used and the size of the gap between the cylinder (18) and the piston (24) so that this time becomes the predetermined delay time described above, the The deployable wings will be deployed after a delay time of .

〔Effect of the invention〕

As explained above, this invention incorporates a deployable wing into the conventional stabilizing wing of a guided flying vehicle, greatly increases the wing area of the steering wing and stabilizing wing compared to the conventional wing area, and after two launches, the coil spring After a preset delay time with a locking device consisting of a hydraulic cylinder, the mother machine or launcher is deployed by the torsional torque stored in the spiral spring.
This has the effect of safely improving interlocking performance and aerodynamic stability while preventing mechanical interference with the vehicle.

[Brief explanation of drawings]

1 and 2 are overall configuration diagrams of an embodiment of a guided flying object according to the present invention, FIG. 3 is a sectional view taken along line A-A in FIG. 1, and FIGS. 4 and 5 are internal configurations of stabilizing wings. 6 and 7 are cross-sectional views of the locking device, and FIG. 8 is a diagram showing an example of a conventional guided flying object. In the figure, (7) is a deployed steering wing, (8
) is the deployable stabilizing wing, (9) is the locking device, and the shout is the wire.
(11) is a spiral spring. (12) is the winding axis, (13) is the development center axis, (14)
and (15) are gears, (1B) and (17) are bearings, (1
8) is the cylinder, (19) is the guide, (20) is the piston rod, (21), (22) and (23) are the holes,
(24) is a piston, (25) is a coil spring,
(26) is oil and (27) is an O-ring. Note that the same reference numerals in the two figures indicate the same or equivalent parts.

Claims (1)

[Claims] A flying object has a fuselage, four stabilizing wings attached to the front half of the fuselage at regular intervals in the circumferential direction of the fuselage, and four stabilizing wings attached to the rear half of the fuselage at equal intervals in the circumferential direction of the fuselage. four steering blades, a deployable stabilizing vane housed in the stabilizing vane, a deployable steering vane housed in the steering vane, and the two types of deployable vanes housed in the stabilizing vane and the steering vane, respectively. a locking device provided on each of the stabilizing blade and the steering blade and configured with a coil spring and a hydraulic cylinder;
comprising a spiral spring attached to the stabilizing wing and the steering wing and storing torsional torque energy for deploying the deployable wing; and a deployment mechanism that transmits the torsional torque of the spiral spring to the deployable wing; Before launching the flying object, the two types of deployable wings are stored in the stabilizing wing and the steering wing, and after the launch, the hydraulic cylinder is operated by the force of the coil spring, and after a predetermined delay time, the two types of deployable wings are stored. A guided flying object characterized in that it is configured to be deployed by torsional torque stored in a spiral spring.