JPS6047160B2 - Rocket parachute release device - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a parachute release device for a rocket that releases and opens a parachute that gently drops a payload separated from a rocket body and a parachute that slowly drops a rocket body.

2. Description of the Related Art Conventional rocket parachute release devices include those shown in FIGS. 1 and 2, for example.

First, to explain the configuration, in FIG. 1, a nose cone 2 is attached to the tip of a rocket body 1 via a sure pin 3, and a first parachute case 4 and a second parachute case 5 are attached to the tip of the rocket body 1. They are sequentially stored in series with their end surfaces 4a and 5a facing each other in a slidable manner. The rear end portion (not shown) of the rocket body 1 serves as a rocket motor. The first parachute case 4 is attached to a meteorological observation sonde 6 as a payload, and this sonde 6 has a spring 7 inside its nose cone 2.
It is stored in a compressed state. A first parachute is housed in the first parachute case 4 so as to be releasable, and this first parachute allows the sonde 6 to fall slowly. The first parachute case 4 is sealed by a cap 10, and the inside of the first parachute case 4 is maintained at the atmospheric pressure sealed during assembly on the ground. cap 10
The wire 8 is connected to the pin 9a of the wire release mechanism 9 using gunpowder.
The wire release mechanism 9 is connected to a timer (not shown). This timer is set to operate after a predetermined time, and the operation of this timer activates the wire release mechanism "9" to separate and release the pin 9a. A second parachute is housed in the second parachute case 5. This second parachute allows the rocket body 1 to fall slowly.The second parachute case 5
The parachute case 5 is hermetically sealed by caps 1 and 2 that are locked together via a wire 11, and the cap 12 maintains the inside of the second parachute case 5 at atmospheric pressure during assembly on the ground. A piston plate 13 is fitted to the rear end of the second balachute case 5, and both ends of the wire 11 are held between the piston plate 13 and the second balachute case 5. The piston plate 13 has a pin 14 projecting inward, and this pin 14 engages with a hole 15 provided at the rear end of the second balachute case 5. Second
The rear end of the balachute case 5 and the tip of the piston plate 13 are connected by a wire 16 of a predetermined length. The piston plate 13 is slidable in the rocket body 1 in the axial direction via an O-ring 17, and when the first and second balachute cases 4 and 5 are stored, the piston plate 13 is moved by a protrusion 13a provided at its rear end. comes into contact with a partition plate 18 fixed to the rocket body 1. A space serving as a gas chamber 21 is defined between the piston plate 13 and the partition plate 18.
and the partition plate 18 are connected by a wire 22 of a predetermined length housed within the gas chamber 21. A gas generator 20 is attached to the partition plate 18.
is located within the gas chamber 21. Next, the operation will be explained. In FIGS. 1 and 2, when the rocket reaches a high altitude due to the propulsive force of the rocket motor, the gas generator 20 is activated.

The piston plate 13 is pushed forward by this combustion gas. This motion is transmitted to the nose cone 2 via the second balachute case 5 and the first balachute case male spring 7, and the nose cone 2 shears the shear pin 3 and separates it from the rocket body 1. A balachute case 4 and a second balachute case 5 are released from the rocket body 1. Thereafter, the nose cone 2 is accelerated by the elastic force of the spring 7 and moves away from the sonde 6. Further, at this time, the movement of the piston plate 13 is restricted by the wire 22 at the tip of the rocket body 1. Therefore, the second balachute case 5 rotates and deflects around the pin 14 at the tip of the rocket body 1. As a result, both ends of the wire 11 are unlocked, and the cap 12 comes off due to the pressure difference between the outside air and the second balachute case 5 at a high altitude.
The barachute 5b is released, and the rocket body 1 connected to the second barachute 5b via the wire 16 slowly falls. Furthermore, after this, the wire release mechanism 9 is activated by a timer (not shown) with a delay from the release of the second barachute 5b. That is, when the first balachute case 4 is separated from the second balachute case 5, the pin 9a is separated and released by the operation of the wire release mechanism 9, and the locking of the wire 8 is released. As a result, the first balachute case 4
From the outside air at high altitude and the first balachute case 4
Due to the pressure difference inside, the cap 10 comes off, the first barachute 4b is released, and the sonde 6 falls slowly. However, in such a conventional balachute release device, a timer connected to the wire release mechanism 9 and a wire release mechanism are used to prevent the first and second balachute from interfering with each other when released and opened. 9. Since the wires 8 and 11 were used to separate the first balachute case 4 and the second balachute case 5 and deflect the discharge direction,
In addition to requiring precise adjustment of the timer, the ejection device itself was complicated, and it was difficult to compensate for the resulting decrease in reliability. This invention was made in view of these conventional problems, and includes a first barachute that slowly drops the payload separated from the rocket body, which is stored in series so as to be sequentially released into the rocket body. A first balachute case that is releasably stored, and a second balachute that releasably stores a second balachute that allows the rocket body to fall slowly.
A coil spring is inserted between the first balachute case and the first balachute case so as to apply an elastic force eccentrically to a plane including the machine axis, and the first balachute case is tilted with respect to the machine axis. The purpose of the present invention is to solve the above problems by emitting the gas in the opposite direction.

The present invention will be explained below based on the drawings.

Note that the same reference numerals are used in the drawings to denote parts that are the same as those in the prior art, and a detailed description of the invention will be omitted. 3 and 4 are diagrams showing an embodiment of the present invention.

First, to explain the configuration, the first balachute case 4 and the second balachute case are housed in the rocket body 1 in series so that they can be released sequentially.
Between the end faces 4a and 5a facing the balash chute case 5 is a spring unit 3 which is a combination of a plurality of (four in this embodiment) coil springs of equal length as elastic bodies.
0 is compressed and inserted, and as shown in detail in FIG. 4, the spring units 30 are arranged equidistantly apart from each other on the machine axis A. However, the spring unit 30 is divided into two sets 30a and 30b with respect to one plane B including the machine axis A.
The elastic force of the entire set 30a is set larger than the elastic force of the entire set 30b. 31 is the end surface 4a, 5
A is a plurality of cylindrical spacers engaged with the spring unit 30 loosely inserted into the spacers 31.
is held.

First balachute case 4 and second balachute case 5
The spring unit 30 is connected by a plurality of (eg, four) holders 32, and the holders 32 restrict the spring unit 30 from being compressed. These holders 32 are made of elastic pieces curved in a convex shape toward the aircraft axis in a free state, and when the restraint by the inner circumferential surface of the rocket body 1 is released, the holders 32 move into the first and second positions by their own elastic force. It separates from the rose chute cases 4 and 5 in pieces. The piston plate 13 is provided with a groove 33 extending from the rear end surface to the outer peripheral surface.
This groove 33 is connected to the plane B of the spring set 30b.
Located on the side. The sonde 6 of this embodiment shares the nose cone 2. The wire 22 becomes straight when the piston plate 13 is pushed forward and the piston plate B moves to a position where the groove 33 provided in the piston plate 13 at the tip of the rocket body 1, that is, on the side of the shear pin 3 communicates with the outside. . Next, the effect will be explained.

Now, at a high altitude, the gas generator 20 is activated to push the piston plate 13 and shear the shear pin 3 to move the rocket body 1 from the nose cone 2 to the sonde 6 to the first and second balachute cases. When releasing 5,
When the second balachute case 5 protrudes from the rocket body 1 together with the first balachute case 4, the holder 32
It is separated from the second ballast chute cases 4 and 5.

As a result, the spring unit 30 expands and imparts elastic force to the first balachute case 4 to further accelerate it.
Since the elastic force of the spring unit 30 acts eccentrically with respect to the plane B, the first balachute case 4 is accelerated obliquely with respect to its machine axis A, and is deflected forward and obliquely upward in FIG. The Rukoto. Then, when it is sufficiently separated from the rocket body 1, the cap 10 is removed due to the pressure difference between the inside of the first balachute case 4 and the outside air, and the first balachute 4b is ejected diagonally backward and downward in FIG. 3. Thereafter, the sonde 6 as a payload slowly falls due to the opening of the first barachute 4b. On the other hand, the second barachute case 5 is pushed forward by the piston plate 13 and ejected from the rocket body 1. During this ejection process, the piston plate 13 moves the wire 2 at the position where the groove 33 opens to the outside.
2, its movement is regulated. As a result, the gas chamber 21
High-pressure gas filled with gas is ejected from this opening, deflecting the rocket body 1 forward and downward in FIG. Due to this deflection of the rocket body 1, the second balachute case 5
Interference between the rocket body 1 and the rocket body 1 is avoided. Then, the cap 12 comes off due to the pressure difference between the inside of the second balachute case 5 and the outside air, and the second balachute 5b is ejected obliquely forward and downward in FIG. 3. After this, the second rose chute 5
As b opens, the rocket body 1 falls slowly. As described above, the first and second balachute cases 4b and 5b are released in opposite directions, and at the time of release, the first balachute case 4 is accelerated by the spring 30, and the second balachute case 4 is accelerated by the spring 30. 5, the first and second barachutes 4b, 5b
will not interfere. In addition, the spring unit 30
, multiple springs with the same length and spring constant are arranged in different numbers with respect to plane B, or the same number of springs are arranged at different distances from plane B, or It is clear that the elastic force applied to the first balachute case 4 may be made eccentric by making the springs have different lengths with respect to B.

As explained above, according to the present invention, the first balachute case is disposed between the first balachute case and the second balachute case.
Because a coil spring is inserted to apply an elastic force eccentrically to one plane including the axis of the barachute case, time delay devices such as timers that require precise adjustment and various accompanying A simple balachute discharge device that does not use any members can be obtained.

Therefore, it is easy to maintain a high level of reliability, and the ejection device can also be made smaller and lighter.

[Brief explanation of drawings]

FIG. 1 is a longitudinal sectional view showing a conventional rocket balachute release device, FIG. 2 is a schematic diagram showing the operation of the release device shown in FIG. 1, and FIG. 3 is a rocket balachute release device according to the present invention. FIG. 4 is a longitudinal cross-sectional view showing one embodiment of the apparatus, and FIG. 4 is a cross-sectional view taken along the line X--X in FIG. 3. DESCRIPTION OF SYMBOLS 1...Rocket body, 4...First barachute case, 4b...First barachute, 5...Second barachute case, 5b...Second barachute, A...
Machine shaft, B...plane, 30...spring unit,
6...Payload.

Claims (1)

[Claims] 1. A first parachute case that releasably stores a first parachute that slowly drops the payload separated from the rocket body, and a second parachute case that releasably stores a second parachute that slowly drops the rocket body. In a rocket parachute release device that is stored in series in a main body and released sequentially, a parachute is placed between the first parachute case and the second parachute case so that the first parachute case is eccentric to a plane including its axis. A parachute release device for a rocket, characterized in that a coil spring is inserted to impart elastic force to the parachute case, and the first parachute case is released obliquely to the axis of the rocket.