JPH0466399A - Rocket holding mechanism - Google Patents

Abstract

PURPOSE:To obtain positive constraint and facilitate the release of constraint by forming a hook for locking the step part of a rocket into approximately U-shape, and adjusting the fulcrum position of the U-shape hook by slide mechanism. CONSTITUTION:Rocket holding mechanism 12 is provided with constraining mechanism 15 formed of slide mechanism 16 provided at a fixed launch mount 14, a hinge pin 17, an approximately U-shape hook 18, and a driving spring 19 for rotating the hook 18. A slit 21, in which the hinge 17 is slid, is provided at the bottom part of the hook 18, and the hinge pin 17 is held by the slide mechanism 16. When the slider 23 of the slide mechanism 16 is moved into a release position and the hinge pin 17 is moved into the rear end position of the slit 21 in the hook 1,8, the hook 18 is rotated around the hinge pin 17 as a fulcrum by the driving spring 19, and the lock state between the step part 13 of a rocket 11. and the lock part 20 of the hook 18 is released.

Description

DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to a rocket holding mechanism that restrains and fixes two objects subject to a tensile load, such as a rocket and a launch pad, and releases the restraint at a necessary time.

Conventional technology Conventionally, as a means for holding and fixing a rocket, a third
A rocket holding mechanism as shown in the figure is known.

In FIG. 3, 1 is a rocket, and 2 is a rocket holding mechanism 2. The rocket l has a step 3. The rocket holding mechanism 2 also includes a launch fixing base 4 that supports the weight of the rocket 1. This launch station 4 has a hinge pin 5.
A hook 6 is provided which is pivotally supported by. This hook 6 has a locking portion 7 that locks the stepped portion 3 of the rocket 1.

Further, although not shown, a force applying device is provided on the hook 6, which applies a force F to the hook 6 to cause it to rotate in the direction A so as to press the locking portion 7 against the stepped portion 3 of the rocket 1. connected.

Note that when the rocket 1 separates from the fixed launch platform 4 in the vertical direction, that is, when a tensile load is applied between the rocket 1 and the fixed launch platform 4, the stepped portion 3 of the rocket 1 is not engaged with the hook 6. By pulling the stop portion 7 in the upward direction a, the hook 6 is rotated in the release direction B.

In such a configuration, in order to prevent the rocket 1 from falling down, a
The locking portion 7 of the hook 6 is hooked. And hook 6
A force F is applied to the hook 6 by the force applying device so as to press the locking portion 7 of the rocket 1 against the stepped portion 3 of the rocket 1.

As described above, the stepped portion 3 of the rocket 1 is restrained, and the rocket 1 is also held. Then, when the rocket 1 is launched, the force F by the force applying device is weakened. Since a tensile load P is acting between the rocket 1 and the fixed launch platform 4,
The stepped portion 3 of the rocket 1 pulls the locking portion 7 of the hook 6. Then, the hook 6 rotates about the hinge bin 5 as a fulcrum, and the locked state between the stepped portion 3 of the rocket 1 and the locking portion 7 of the hook 6 is released. Then, rocket 1 is launched.

Problem to be Solved by the Invention However, according to the conventional example described above, when an excessive external force is applied in a direction that causes the rocket 1 to fall, the force that pulls the stepped portion 3 of the rocket 1 in the upward direction a is also excessive. becomes.

Then, the stepped portion 3 of the rocket 1 will pull the locking portion 7 of the hook 6 with excessive force. When the locking portion 7 of the hook 6 is pulled upward in the upward direction a by this excessive force, a rotational force acting against the applied force F by the applying device acts on the hook 6 itself.

When this rotational force exceeds the applied force F of the applying device, the hook 6 rotates in the release direction B and snaps. As the rotation angle of the hook 6 increases, the locked state between the stepped portion 3 of the rocket 1 and the locking portion 7 of the hook 6 is finally released. In other words, the locking part 7 of the hook 6 no longer restrains the rocket 10 stage part 3. Therefore, it becomes impossible to hold the rocket 1.

After all, if an excessive external force is applied in a direction that would cause the rocket 1 to fall, there is a possibility that the hook 6 will naturally slip from the locking part 7 or the stepped part 3 of the rocket 1, causing the rocket 1 to fall. Ru.

The present invention has been made to solve the problems of the prior art, and even when an excessive external force is applied in a direction that would cause the rocket to fall, the locking part of the hook or the stepped part of the rocket can be removed. It is an object of the present invention to provide a rocket holding mechanism which can prevent the rocket from falling off and can surely avoid unnecessary overturning of the rocket.

Means for Solving the Problems In order to solve the above problems, the present invention provides a launch fixture that supports the weight of a rocket, a hook provided on the launch fixture, and a hinge bin that pivotally supports the hook. In the rocket holding mechanism that holds the rocket by locking the stepped portion of the rocket with the locking portion of the hook, the hook has a double-shaped shape, and the hook further includes a slit through which the hinge bin slides. , a slide mechanism for slidingly holding the hinge bin, and a driving spring for rotating the hook.

According to the above-mentioned means, the hook that locks the step part of the rocket is made into a double-shape, and the hinge bin that pivotally supports the hook is held by a slit, and furthermore, according to the operating situation, the hook is held by a sliding mechanism. The position of the fulcrum of the double-shaped hook has been changed. Therefore, the stage part of the rocket can be structurally restrained. In other words, even if an excessive external force is applied, no rotational force is applied to the double-shaped hook to release the restraint.

Therefore, even when compared with the conventional example in which a force applying device is applied, a reliable restraint can be obtained, and the restraint can be easily released.

EXAMPLE Hereinafter, an example of the present invention will be described in detail with reference to FIGS. 1 and 2.

In FIG. 1, 11 is a rocket, 12 is a rocket holding mechanism 12. The rocket 11 holds the step part 13. Also, the rocket holding mechanism 12 is a launch fixture that supports the weight of the rocket 1j. 14 and the step part of rocket 11]
It has a restraint mechanism 15 that restrains 3.

This restraint mechanism 15 includes a slide mechanism 16 provided on the launch station 14, a hinge bin 17, and a double-shaped hook 18.
and a driving spring 19 that rotates the double-shaped hook 18.

The upper part of the mouth-shaped hook 18 is a locking part 20 that locks the stepped part I3 of the rocket 11. In addition, a hinge pin 1 is provided at the bottom of the F-shaped hook 18 from the tip to the rear end.
A slit 21 is provided in which 7 slides. The hinge pin 17 is held by a slide mechanism 16. The slide mechanism 16 includes a slit 22 provided parallel to the firing station 14 and a slider 23 that slides in the slit 22.

The slider 23 has a hinge pin 17 or a slide for sliding.

24 ports are provided. And launch fixed bases 14 and 3
A driving spring 19 for rotating the three-shaped hook 18 is provided between it and the bottom of the three-shaped hook 18.

In such a configuration, in order to prevent the rocket 11 from falling, as shown in FIG. to bound. This state is realized by moving the slider 23 to the position closest to the rocket 11 (hereinafter referred to as the restraining position). And slider 2
3 is in the restraining position, the hinge pin 17 is also at the tip of the slit 21 of the 3-shaped hook 18. In this state, the locking part 20 of the two-shaped flap 18 and the rocket 1
The connecting portion X with the step portion 13 of No. 1 and the hinge pin 17 are on a vertical line Y with respect to the launch station 14.

Therefore, even if the locking portion 20 of the 3-shaped hook 18 is pulled upward by an excessive external force that would cause the rocket 11 to fall, no rotational force to release the 3-shaped hook 18 is generated.

Therefore, the locking portion 20 of the 3-shaped hook 18 will not naturally slip off from the stepped portion 13 of the rocket 11 due to excessive external force.

Next, when the rocket 11 is launched, as shown in FIG. 2, the restraint of the step part 13 of the rocket 11 by the locking part 20 of the three-shaped hook 18 is released.

This state is achieved by moving the slider 23 to a position farthest from the rocket 11 (hereinafter referred to as the release position). When the slider 23 is moved to the release position, the hinge pin 17 is also moved to the rear end position of the slit 21 of the three-shaped hook 18. Then, the 3-shaped hook 18
is rotated about the hinge pin 17 as a fulcrum by a drive spring 19 that rotates the three-shaped hook 18 in a direction that releases the locking portion 20 of the stepped portion 13 of the rocket 11 . Then, the locked state between the stepped portion 13 of the rocket 11 and the locking portion 20 of the 3-shaped hook 18 is released.

As a result of the above, the rocket 11 is released from its restraint and becomes ready for launch.

According to this embodiment having such a configuration, the hook is connected to the 3-shaped hook 18 without applying a force applying device as in the past.
In addition, the hinge pin 17 is held by the slit 21. For this reason, depending on the operating situation, the 3-shaped hook 1
By changing the position of the fulcrum 8, that is, the position of the hinge pin 17, the restraint state and release state of the stepped portion 13 of the rocket 11 can be structurally adjusted. Therefore, reliable restraint can be obtained and the restraint can be easily released.

Effects of the Invention As described above, according to the present invention, the step part of the rocket is structurally restrained by using a three-shaped hook with a variable fulcrum position, without using a force applying device as in the conventional example. Therefore, a reliable restraint can be obtained, the unnecessary overturning of the rocket can be reliably prevented, and excellent effects such as a restraint release operation can be performed easily.

[Brief explanation of the drawing]

1 and 2 show an example of the location/separation holding mechanism according to the present invention, in which FIG. 1 is a sectional view showing the location/node restraint state, and FIG. 2 is a sectional view showing the rocket released state. , FIG. 3 is a sectional view showing a conventional example. 11. Rocket, 12. Rocket holding mechanism, 13.
・Stepped portion, 14... Launching fixing platform, 15... Restraint mechanism, 16
...Slide mechanism, 17.. Hinge pin, 18.. Hook, 19.. Drive spring, 20.. Locking part, 21.22
...Slit, 23...Slider, 24...Suri Soto.

Claims (1)

[Claims] The rocket has a fixed launch platform that supports the weight of the rocket, a hook provided on the fixed launch platform, and a hinge pin that pivotally supports the hook, and the step part of the rocket is locked by the locking part of the hook. In a rocket holding mechanism for holding a rocket, the hook has a U-shape, the hook is further provided with a slit through which the hinge pin slides, a slide mechanism for slidingly holding the hinge pin, and a drive for rotating the hook. A rocket holding mechanism characterized by being equipped with a spring for use.