JPS6256798A - 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 provides a stabilizer at a predetermined position in the front half of the fuselage.

It also relates to a flying object that has a steering wing in a predetermined position in the rear half, and when launched from an aircraft on which it is mounted, or when launched from a launcher when it is mounted on a launcher on the ground or on a ship. It is characterized by measures to prevent mechanical interference with a certain aircraft or launcher.

[Conventional technology]

In general, flying vehicles have two stabilizing wings at predetermined positions on the front half of the aircraft in order to have maneuverability and aerodynamic stability.

It also has a steering wheel at a predetermined location on the rear half of the fuselage. The maneuverability is improved by steering the aforementioned steering blades using a steering device built into the aircraft body.

Furthermore, the stable wings provide aerodynamically stable flight performance. In addition, in order to obtain high maneuverability and aerodynamic stability performance, it is sufficient to increase the wing area, but when installed on an aircraft,
Or, in order to store it in the launcher, there are restrictions on the size of the wings, and the wings cannot be enlarged unnecessarily. As a countermeasure against this, some recent flying objects have deployable wings. When launching from an aircraft, or from a launcher on the ground or a ship, the deployable steering wing and deployable stabilizing wing are stored in the steering wing or stabilizing wing before the second launch, and after the second launch, the deployable steering wing and deployable stabilizer wing are deployed. The aim is to expand the wing area by deploying the stabilizing wings to achieve high maneuverability and aerodynamic stability. As mentioned above, the flying object according to the present invention is launched from an aircraft or a launcher on the ground, but in the following description, the case where it is launched from an aircraft will be explained as an example.

FIG. 3 shows an example of a conventional flying object, and its structure will be described below. The body of the flying object (11 is the steering wing (2).

A deployable steering wing (4) and a deployable stabilizing wing (5) are housed inside the stabilizing wing (3), and a locking device f6+ and a wire (7) are housed inside the stabilizing wing (3).
) to prevent them from being expanded. When the aircraft il+ is launched from the mother aircraft, the wire (7) is pulled out from the locking device (6) and the deployable steering wing (4) and the deployable stabilizing wing (5) are deployed. These deployable wings are deployed after a predetermined delay time after the second launch to prevent them from hitting the mother aircraft. As a way to obtain this predetermined delay time,
Conventionally, the length of the wire (7) was long, and the wire ()) was connected to the locking device (
6).

[Problems to be solved by the invention] In the conventional method described above, after one aircraft Ill is launched from the mother aircraft, a long wire (
7), and this wire (7) became entangled with other mechanical parts of the fuselage +11, causing malfunctions such as interfering with one function. This invention was made to solve such problems, and the locking device (
As 6), a hydraulic cylinder is used, and the purpose is to obtain a predetermined delay time from when the wire (7) is pulled out from the locking device (6) until the deployable wing is deployed as the operating time of the hydraulic cylinder. .

[Means for solving problems]

After the guided flying object according to this invention is launched from an aircraft.

A hydraulic cylinder to obtain the delay time until the deployable wings are deployed, a guide to support this hydraulic cylinder, a coil spring to store the energy to drive this hydraulic cylinder, and a hole into which the piston of the hydraulic cylinder is inserted are provided. It is equipped with deployable wings.

[Effect]

In this invention, when launching from an aircraft, the wire is pulled out from a locking device consisting of a hydraulic cylinder, and the piston of the hydraulic cylinder is pulled out after a predetermined delay time by the energy stored in the coil spring. , the deployable wings deploy.

〔Example〕

1 and 2 show an embodiment of a locking device consisting of a hydraulic cylinder, which is a feature of the present invention, and the stabilizing blade (
3) shows the A-A cross section when provided. Figure 1 shows the state before launch.

The hydraulic cylinder (8) is connected to the stabilizing blade (3) via the guide (9).
) is fixed. A wire (force passes through the hole αυ provided in the piston rod α1 of the hydraulic cylinder (8) and the hole a2 provided in the guide (9). Also, the piston rod αC is provided in the deployment stabilizing wing (5). It was inserted into the hole.

The deployment mechanism a9 installed between the axis α fixed to the stable Ti1t (3) and the deployment stabilization wing (5) keeps the deployment stability wing (5) in a stowed state. α0 is a piston, and il is a spring for driving the piston.

αg is the oil in the hydraulic cylinder (8), and αg is the O-ring for sealing oil + 1.8.

Figure 2 is a diagram after a predetermined delay time has elapsed after launch from the mother aircraft.After the wire (not shown) is pulled out from the guide (9) and the piston rod α value, the energy stored in the coil spring Qη causes When the piston t1e and the piston rod α1 rise and are pulled out from the hole (I3) provided in the deployment stabilizing vane (5), the deployment stabilizing vane (5) is deployed f
ilft! Expands through the power of 9.

Next, the operation of the above embodiment will be explained with reference to FIGS. 1 and 2. Fig. 1 is an explanatory diagram showing the state before launch, in which the deployed stabilizing wing (5) is locked and stored at piston rod O0, and Fig. 2 is an explanatory diagram showing the state in which the deployed stabilizing wing (5) is locked and stored at piston rod O0. and rise.

FIG. 3 is an explanatory diagram showing the state immediately after the deployment stabilizing wing (5) is unlocked.

First, in Fig. 1, the piston rod ill tries to rise due to the coil spring αη, but the piston rod σ
ω and is locked by a wire (7) passing through the guide (9). On the other hand, the other end of the piston rod α0 is inserted into the hole αj provided in the deployment stabilizing wing (5), and the deployment stabilizing wing a! 19 is obstructing the deployment operation.

Next, when the flying object is launched, the wire (7) is pulled out, and the piston rod a1 enters an upward movement due to the force of the coil spring αη, and is pulled out from the hole αJ provided in the second deployment stabilizing wing (5). Then, the state shown in FIG. 2 is reached, indicating that the extraction is completed. From the start of this withdrawal.

The time it takes to complete the withdrawal is determined by the viscosity of the oil (US) and the size of the gap between the piston αe and the cylinder (8). Viscosity of eel, cylinder (8) and piston α0
By selecting and determining the size of the gap between the two, the deployment gun will be deployed after a predetermined delay time after launch from the mother aircraft.

〔Effect of the invention〕

As explained above, this invention changes the locking device to a hydraulic cylinder, so when the wire is pulled out during launch from an aircraft, the moving speed of the free piston rod is determined by the viscosity of the oil and the size of the gap between the piston and cylinder. It can be set by selecting the optimum value. Furthermore, by deploying the deployable wings after the launch after a predetermined delay time from the first launch to the deployment, there is an effect that the deployable wings of the flying object can be prevented from interfering with the aircraft that is the mother aircraft.

[Brief explanation of drawings]

FIGS. 1 and 2 show an embodiment of a guided flying object according to the present invention, and FIG. 3 shows an example of a conventional guided flying object. In the figure, (3) is a stable wing, (5) is a deployed stable wing, (
7) is wire, (8) is cylinder, (9) is guide, α
1 is a piston rod, aυ, α2. αJ is the hole, H is the shaft,
Kasumi is the deployment mechanism, σe is the piston, αη is the coil spring, Q
l is oil and σ is O-ring. Note that the same reference numerals in the two figures indicate the same or corresponding 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 wings, a deployable stabilizing vane housed within the stabilizing vane, a deployable steering vane housed within the steering vane, and a deployable steering vane installed within the stabilizing vane and within the steering vane, and deploying the deployable vane. and a deployment mechanism for storing the two types of deployable wings in the stabilizing wing and the steering wing, respectively, and configured by a coil spring and a hydraulic cylinder. The two types of deployable wings are stored in the stabilizing wing and the steering wing before launching the flying object.
A guided flying object characterized in that, after launch, the hydraulic cylinder is actuated by the force of the coil spring, and the two types of deployable wings are deployed after a predetermined delay time.