JPH04324099A - Binding device for wing of missile - Google Patents

Abstract

PURPOSE:To prevent the flatter of a wing system, which is generated by the fore wing of a missile, by a method wherein the missile is provided with a binding means, folding and binding the wing of the missile in the loading condition of the same but releasing and deploying the wing of the missile when the missile is accelerated so as to exceed a predetermined value, in the missile with wing, which is loaded on an aircraft or the like. CONSTITUTION:The fore wing of a missile 1 is constituted of a wing 2a and the base unit 3 of the wing, which are attached to a rotatable shaft, while both ends of the shaft 4 are fixed to the wing 2a and the base unit 3 of the wing under a condition that the shaft is provided with a torsion. The wing 2a is provided with a strong torque into the deploying direction thereof at all times by the torsion. The wing 2a of the missile 1 is folded and a retaining metal or the tip end of a weight 7 enters the hole 10 of the wing 2a by the force of a spring 9 whereby the wing 2a is bound in the folded condition thereof. When the missile 1 is launched under this condition and a rearwar inertia force is exerted on the weight 7, the weight 7 moves rearward against the spring 9 whereby the fixing of the wing 2a is released and the wing 2a is deployed.

Description

[Detailed description of the invention]

0001

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a device for releasably restraining a flying object mounted on an aircraft wing or the like at a predetermined acceleration.

0002

BACKGROUND OF THE INVENTION Conventionally, flying objects mounted on airplanes have not had foldable wings. FIG. 3 is a diagram of a conventional example, in which (a) shows a flying object 1 mounted on a launcher 02 equipped at the wing tip of the main wing 01 of an airplane.
(b) is a view of (a) viewed from the rear.

[0003] Some ground-launched flying vehicles have foldable wings, but their deployment mechanism does not utilize G (acceleration) at the time of launch.

0004

[Problems to be Solved by the Invention] The above-mentioned conventional flying object mounting means had the following problems to be solved.

That is, when a flying object is mounted on the wing tip of an airplane, the natural frequency of the wing system generally decreases due to the relationship between the weight of the flying object and the rigidity of the wing. In particular, there is a problem in that the vibration of the front wing of the flying object causes flutter vibration of the entire wing system. Therefore, a proposal has been made to reduce the aerodynamic force acting on the flying object's front wing by folding the flying object's front wing mounted on the wing tip. Although the unfolding of the folded wings after the body is launched is essential, there was a new problem in that the technology that clearly solved this problem had not yet been put to practical use.

SUMMARY OF THE INVENTION An object of the present invention is to provide a flying vehicle wing restraint device that satisfies the above-mentioned folding requirements and can be easily and reliably expanded.

[0007]

[Means for Solving the Problems] As a means for solving the above-mentioned problems, the present invention provides a winged flying object mounted on an aircraft wing, etc., in which the flying object wing does not move when the acceleration of the flying object is below a predetermined value in the flying object launch direction in the mounted state. It is an object of the present invention to provide a restraining device for a flying vehicle wing, which is characterized by comprising a restraining means that restrains the flying vehicle wing by folding and releases and deploys the flying vehicle wing when the acceleration exceeds a predetermined value.

[0008]

[Operations] Since the present invention is constructed as described above, it has the following functions.

That is, when the flying object is mounted on an aircraft wing or the like,
The projectile wing is folded and restrained when the acceleration in the launch direction is below a predetermined value, and is released and deployed when the acceleration exceeds the predetermined value, so it is released from folding when the acceleration occurs during takeoff or longitudinal speed change. It can be released under large acceleration during launch. As a result, the flying object does not cause flutter while being mounted on an aircraft, and when launched, the wings are expanded and the flying object's functions are not hindered.

0010

[Embodiment] An embodiment of the present invention will be described with reference to FIGS. 1 and 2. Note that the same reference numerals are given to the same constituent members as in the conventional example, and the explanation thereof will be omitted.

FIG. 1 shows the main parts of this embodiment, with (a) being a side view and (b) being a view seen from the rear. In the figure, the front wing of a flying vehicle 1 is composed of a wing 2a and a wing base 3, and the wing 2a and the wing base 3 form a rotating pair by a shaft 4. The shaft 4 is fixed at both ends to the wing 2a and the wing base 3 in a twisted state. Due to this twisting, a strong rotational force is constantly applied to the wing 2a in the direction of expansion.

A hole 10 is formed in the trailing edge of the wing 2a so that the weight 7 of the stopper part 5 can be inserted and fixed when the wing 2a is folded, as will be described later.

FIG. 2 shows a longitudinal sectional view of the stopper portion 5. As shown in FIG. This figure shows the wing 2a in a folded state, and the weight 7, which is a stopper, is moved to the case 8 by the force of the spring 9.
A part of the blade has entered the hole 10 of the wing 2a. When the flying object 1 is launched, a backward inertial force acts on the weight 7,
Since this inertial force overcomes the compression force of the spring 9, the weight 7 moves rearward. Therefore, the wing 2a is unfixed and unfolds. Note that 6 is a pivot axis for steering the wing 2a.

[0014] The maximum acceleration in the axis direction due to starting the airplane is approximately 2G, whereas the maximum acceleration due to projectile launch is approximately 17G.
Taking this into consideration, the mass (density) of the weight 7, the spring constant of the spring 9, and the required displacement amount x are selected so that the wing 2a does not expand except when launching a projectile object.

As described above, according to this embodiment, the flying object 1
When mounted on an airplane, fold the wing 2a and attach the weight 7.
This has the advantage that flutter does not occur because it stops at a certain point. Furthermore, when the flying object 1 is launched, the weight 7 is removed by the launch G, so there is an advantage that the wings 2a are reliably deployed.

[0016]

Effects of the Invention Since the present invention is constructed as described above, it has the following effects.

That is, according to the present invention, it is possible to keep the front wings of the flying vehicle folded until the time of launch. Therefore, the mother aircraft can escape from wing system flutter caused by the front wing of the flying object.

[Brief explanation of drawings]

[Fig. 1] Diagrams of one embodiment of the present invention, (a) is a side view, (b)
) is a view from the rear.

FIG. 2 is a longitudinal cross-sectional view of the stopper part 5 of FIG. 1.

FIG. 3 is a diagram of a conventional example, where (a) is a plan view and (b) is a
) seen from the rear.

[Explanation of symbols]

1. Flying object 2a Wings 3 Wing base 4 Shaft 5 Clasp part 6 Swivel axis 7 Weight 8 Case 9 Spring 10 holes

Claims (1)

[Claims] Claim 1: In a winged flying object mounted on an aircraft wing, etc., the flying object wings are folded and restrained when the acceleration in the flying object launch direction is below a predetermined value in the mounted state, and when the acceleration exceeds the predetermined value, the flying object wings are folded and restrained. A restraining device for a flying vehicle wing, comprising a restraining means that is released and deployed.