JPH03236600A - Missile carrying payload such as torpedo - Google Patents

Abstract

PURPOSE:To protect a payload from thermal or mechanical load during flying or upon splashdown by a method wherein the payload is received in a capsule until splashdown while the payload is discharged out of the capsule under water after the splashdown. CONSTITUTION:When a missile 5 continues the flight thereof while being decelerated by a decelerating device 2 and comes immediately before splashdown onto the surface of sea, a sequencer 10 outputs the separation commanding signal of the decelerating device 2 and the decelerating device 2 is separated from the capsule 3, then, is landed on and rushed against the surface of the sea with a comparatively high speed. Then, an acceleration sensor 28 in the sequencer 10 detects a shock upon the splashdown as an acceleration and reads the information into the operating device 26 of the sequencer 10 while a time is monitored by a timer 27 and an igniting signal is outputted to a gas generator 14 with a delay corresponding to the discharging time commanding from the splashdown detecting time. Gas is sent from the gas generator 14 into an air bag 13 in the capsule 3 and a shear pin, connecting a nose cap 4, is sheared whereby a torpedo 8 is discharged out of the capsule 3.

Description

DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to a payload carrying projectile whose payload is a long-range torpedo or the like, which is a weapon for attacking ships.

Conventional technology In order to carry out torpedo operations by launching it from a ship, etc., and flying it through the air, it enters the sea and performs torpedo activities.
There is a structure shown in the figure.

A rocket motor 52 is installed at the rear of the fuselage 51 as a propulsion device, while a torpedo 53 is attached to the front of the fuselage 51 as a payload, which functions as the fuselage body during flight. Nose cab, bu 5
4 is covered.

The fuselage 51 has a structure that can be divided into two parts, and is equipped with wings 55 to maintain stability during flight, as well as a parachute 56 as a deceleration device that is folded and stored.

As shown in FIG. 13, for example, as shown in FIG. 13, a specific method of operating such a conventional flying object is to launch it from a ship 57 and accelerate it using the propulsive force of a rocket motor 52. Separate. From then on, only the torpedo 53 (including the fuselage 51) continues to fly ballistically at subsonic or low supersonic speeds, and before landing on the sea surface 58, the fuselage 51 is split into two and separated from the torpedo 53, and at the same time the parachute 56 Expand. As a result, the torpedo 53 is sufficiently decelerated by the parachute 56 before landing on the water.

Immediately before landing, the parachute 56 is separated, while the impact at the time of landing is absorbed by the nose cap 54 at the tip of the torpedo 53. The nose cap 54 is opened and separated at the same time as the landing, and from then on, the torpedo 53 is underwater. and began torpedo operations toward target 59.

Problems to be Solved by the Invention In the conventional payload carrying body, the side of the torpedo 53 functions as the fuselage body during flight, and moreover, it has a structure that prevents the impact upon landing on water. Since the nose cap 54 absorbs the water, in order to protect the torpedo 53, which is relatively vulnerable to impact, it is necessary to sufficiently reduce the speed at the time of water landing, and as a result, the parachute 56 as a deceleration device becomes large. As a result, the actual water landing point deviates significantly from the target water landing point due to the influence of wind, etc., and the so-called dispersion of water landing points becomes large.

In addition, during flight, aerodynamic heating and aerodynamic bending moment act directly on the torpedo 53, making it difficult to fly at high speed or make large turns, making it difficult to extend the range or shorten the flight time. There were also limits.

The present invention was made in view of the above problems.
The purpose of this is to sufficiently protect payloads such as torpedoes from thermal and mechanical loads during flight and water landing, thereby increasing flight speed and high turning ability. Payloads such as torpedoes are designed to extend range and shorten flight time by carrying them, and at the same time, reduce deceleration when landing on water, shortening deceleration time and improving accuracy of landing points. The purpose is to provide transportation capacity.

Means for Solving the Problems The payload carrying capacity body of the present invention includes a rocket motor for propelling the rocket, and is attached to the tip of the rocket motor to form the fuselage body together with the rocket motor, and also contains a payload such as a torpedo. A capsule that is housed in a rocket and is separated from the rocket motor after being given rocket propulsion and then released into the air, and a capsule that is installed in the capsule and activated at the same time as or after the capsule is separated from the rocket motor. The capsule is equipped with a deceleration device that decelerates the vehicle and is separated from the capsule before the capsule lands on water, and a release device that is provided on the capsule and releases the payload from the capsule after the capsule lands on the water.

Function According to the above structure, after being launched from a ship, aircraft, etc. by rocket propulsion and flying through the air, by the time the capsule touches down on water, the rocket motor and decelerator are separated in that order, and payloads such as torpedoes are stored in the capsule. It suddenly enters the water, and once underwater it is ejected from the capsule and begins its payload activities, such as torpedo activities.

Embodiment FIG. 1 is a configuration explanatory diagram showing a first embodiment of the present invention. At the tip of a rocket motor 1 as a propulsion device, a deceleration device 2 and a capsule 3 are installed in order from the rocket motor 1 side with an explosive bolt or separation nut. Separation mechanism 30.
33 (see FIG. 4), and a nose cap 4 is attached to the tip of the capsule 3. These elements constitute a flying object 5.

The capsule 3 has a double cylindrical structure consisting of an inner capsule 6 and an outer capsule 7, each having a cylindrical shape with a bottom. Together with the rocket motor 1, the capsule 3 constitutes the fuselage body of the flying object 5, and the inside of the capsule 3 carries a payload. as torpedo 8
is accommodated.

The torpedo 8, together with the inner capsule 6, is supported by an outer capsule 7 via a reinforcing member 9, and the outer capsule 7 protects the torpedo 8 from thermal and mechanical loads during flight.

Inside the nose cap 4, there is housed a sequencer 10 that controls sequence processing such as deceleration 1 water landing and torpedo release, as will be described later, as well as a buffer material 11 that cushions the impact upon water landing. It is fitted onto the tip of the capsule 3 and is coupled with a shear pin, for example. Due to this shear pin connection, when a force exceeding a predetermined value is applied in the direction in which the nose cap 4 comes off from the capsule 3, the shear pin inserted between the capsule 3 and the nose cap 4 is sheared and destroyed, and the 7- Zukinopu 4
(For sherbin, the 10th
(see figure).

A piston 12 for pushing out the torpedo 8 from the inner capsule 6 and a folded air bag 13 are housed at the bottom of the inner capsule 6, and the space between the inner capsule 6 and the outer capsule 7 is A gas generator 14 for the airbag 13 is housed therein.

The gas generator 14 constitutes the release device 15 of the torpedo 8 together with the airbag 13 and piston 12 described above, and when the gas generator 14 is activated in response to an ignition signal, the third
As shown in FIGS. (A) to (D), the gas generated by the gas generator 14 is sent to the airbag 13, and the inflation pressure of the airbag 13 separates the nose canope 4. At the same time, the gas is sent to the torpedo via the piston 12. 8 from the capsule.

The speed reducer 2 includes a main body 16 as shown in FIGS. 4 to 6.
A plurality of stabilizing wings 17 are connected to each other so as to be radially deployable via hinge pins 21, and a parasitic airbag 18 is stretched between the stabilizing wings 17 and the main body 16.
and an actuator (
When the function of the device consisting of the cylinder) 19 and the gas generator 20 for supplying a predetermined gas to the actuator 19 is not required, the stabilizing blade 17 and the airbag l8 are folded as shown in Fig. 4. It is stored in the main body part 16.

A flapper 22 having a substantially U-shaped cross section and forming a part of the stabilizing blade ml7 is hinged to each stabilizing blade l7 so as to be openable and closable, and as shown in FIG. At the same time as the stabilizing wing 1 is deployed against the section 16
7 to form an air intake port 23 in the stable '&l7.

That is, in the above-mentioned deceleration device 2, when the gas generator 20 is ignited and activated by a predetermined deceleration command during flight, the gas generated by the gas generator 20 is sent to the actuator 19, so that the stable ffl7 is developed. At the same time, the flapper 22 is expanded and the air intake port is opened. While maintaining the aerodynamic stability of the aircraft by deploying the stabilizing wings 17, the ram pressure associated with flight inflates and deploys the airbag 18 from the air intake port 23, and the air resistance of the airbag 18 causes the aircraft to stabilize. It serves to slow down.

Next, a specific method of operating the flying object configured as described above will be explained with reference to the Bronnock diagram of the sequencer 10 shown in FIG. 7 as well as FIG. 2.

The sequencer 10 has a flight computer 24 mounted inside the aircraft that controls the guidance and control of the entire flying object 5, and a fire control device 25 inside the ship 29, while the sequencer 10 itself has a calculation device 26 and a timer 27. Alternatively, it has an acceleration sensor 28, etc., and can determine when the rocket motor 1 is separated from the capsule 3, when the deceleration device 2 is activated, when the deceleration device 2 is separated from the capsule 3, and when the torpedo 8 is released from the capsule 3. It directly controls the timing.

As shown in FIGS. 2 and 7, the flying object 5 launched from the launcher on the ship 29 is accelerated by the propulsive force of the rocket motor 1, and even after the rocket motor 1 is completely burned out, the flying object 5 reaches the water landing point. Perform a high-speed trajectory toward the target. During this trajectory, the aircraft may make a turn or change its trajectory as necessary.

When approaching the water landing point, the sequencer 10 outputs a separation command signal for the rocket motor 1. In response to this separation command signal, the separation mechanism 30 shown in FIGS. 4 and 5 provided at the joint between the rocket motor 1 and the speed reducer 2 is operated, and the rocket motor 1 is separated from the capsule 3.

Simultaneously with or immediately after separation of the rocket motor 1, the sequencer 10 outputs a deceleration command signal, that is, an activation signal for the deceleration device 2, and upon receiving this deceleration command signal, the deceleration device is activated as shown in FIGS. 5 and 6. 2 works. That is, the stabilizing blades 17, which had been in the retracted state until then, are deployed, and air is further blown from the air intake port 23 to deploy the airbag 18, which causes the capsule 3 to collapse due to the air resistance.
starts decelerating.

At this point, at the same time as the rocket motor 1 is separated, the wings 31 (see Figure 1) attached to the rocket motor 1 are lost, so the stabilizing wings 17 are replaced in place of the wings 31.
By deploying, the aerodynamic stability of the flying body 5 is maintained.

When the flying object 5 continues to fly while being decelerated by the deceleration device 2 and is about to land on the sea surface 32, the sequencer 10 outputs a separation command signal for the deceleration device 2. In response to this separation command signal, the separation mechanism 33 shown in FIGS. 3 and 4 provided at the joint between the speed reducer 2 and the capsule 3 is operated, and the speed reducer 2 is separated from the capsule 3. As a result, the capsule 3 lands on the sea surface 32 at a relatively high speed.

On the other hand, the fire control device 25 shown in FIG. The delay time) is calculated and the sequencer 10
The above release time command is input manually via the flight computer 24.

Then, when the capsule 3 lands on the sea surface 32 and plunges below the sea surface 32, the acceleration sensor 28 in the sequencer 10 detects the impact at the time of landing on the water as acceleration, and the information is taken into the arithmetic unit 26 of the sequencer 10. The arithmetic unit 26 monitors the time using a timer 27 and outputs an ignition signal to the gas generator 14 after delaying the water landing detection time by the amount of the above-mentioned release time command.

In response to this ignition signal, the gas generator 14 is activated, and the gas generated by the gas generator 14 is delivered to the airbag 1 inside the capsule 3.
3, the air nozzle/knob 13 gradually expands as shown in FIGS. 3(A) to 3(D). This expansion pressure causes the torpedo 8 to press the nose cap 4, and this pressing force causes the nose cap 4 to be connected until then.

The shear pin will be sheared if the tolerance limit of the shear pin is exceeded. As a result, the nose cap 4 is removed from the capsule 3 and the torpedo 8 is released from the capsule 3. In this way, the torpedo 8 released into the sea starts torpedo activity toward the target 34 by, for example, homing guidance.

8(A) and 8(B) show a second embodiment of the present invention. In this embodiment, a gas generator 43 and a piston 44 constituting a discharge device 42 on the 7-z side of a capsule 41 are shown.
An air bag 45 is housed therein, and when releasing the torpedo 8 from the capsule 41, a rear cap 46 at the rear of the capsule 41 is removed and the torpedo 8 is released to the rear of the capsule 41.

The capsule 41 and rear gear tube 46 are shown in Figures 9 and 1.
As shown in Figures 0 (A) and (B), they are connected by a shear pin 47, and when a destructive shearing force larger than the allowable limit is applied to the shear pin 47 due to the expansion of the air knob 45, the yarn pin 47 is sheared and the rear part cap 46
will come off from the capsule 41.

FIGS. 11(A) and 11(B) are diagrams showing a third embodiment of the present invention. In this embodiment, a torpedo 8 is housed in a capsule 48 of a two-part craniotomy method, and when released, a separation nut or an explosive bolt is used. The separation mechanism 49 is actuated to open the capsule 48 by the action of the compression coil spring 50, and the capsule 48 is ejected by the propulsive force of the torpedo 8.

These second. In the third embodiment, the same effects as in the first embodiment can be obtained, and in the case of the embodiment shown in FIG. 8, the gas generator 43, air bag 45, etc. are stored in the tapered space of the nose part This is advantageous in terms of space efficiency, and in the case of the embodiment shown in FIG. 11, since the capsule 48 itself is divided, torpedo release can be carried out more reliably and with high reliability.

Note that the speed reduction device according to the present invention is not limited to the one illustrated in each embodiment, and for example, a parachute may be used as in the conventional case.

Furthermore, the objects to be carried by the flying vehicle of the present invention are not limited to torpedoes, but may also be payloads such as mines or bombs that are relatively susceptible to impact.

Additionally, the projectile itself may be launched from an aircraft.

Effects of the Invention As described above, according to the present invention, a payload such as a torpedo is stored in a capsule until it lands on water, and the payload is released from the capsule in the water after landing. This makes it easier to protect the payload from thermal or mechanical loads during flight and water landing, allowing for faster flight speeds.
In order to have high turning ability, the speed limit when landing on water is relaxed, and there is no need to increase the deceleration rate so much. As a result, it is possible to extend the firing range and shorten the flight time, and at the same time, it is possible to reduce the size of the deceleration device, and it is possible to reduce the dispersion of the landing points due to the influence of wind and the like.

[Brief explanation of drawings]

FIG. 1 is a configuration explanatory diagram showing the first embodiment of the present invention;
The figures are explanatory diagrams showing the specific operating method of the flying object in the above embodiment, and Figures 3 (A), (B), (C), and (D)
is an explanatory diagram of the release of a torpedo from the capsule, and Figure 4 is the first
Cross-sectional explanatory diagram along line A-A in the figure, Figures 5 and 6 (
A) and (B) are diagrams explaining the operation of the reduction gear in Figure 4, Figure 7 is a block diagram of the signal processing system of the above-mentioned flying object,
Figure 8(A). (B) is an operation explanatory diagram showing the second embodiment of the present invention;
The figure is an enlarged view of the main part of Figure 8 (A), Figure 10 (A), (B
) is an explanatory diagram of the operation of the structure in Figure 9, Figure 11 (A),
(B) is an operation explanatory diagram showing the third embodiment of the present invention;
Figure 2 is a configuration explanatory diagram showing an example of a conventional flying object.
FIG. 3 is an explanatory diagram showing a specific method of operating the flying object shown in FIG. 12. 1...Rocket motor, 2...Reduction gear, 3.41
48 ・Capsule, 4... Nose cap, 5...
Projectile object, 6... Inner capsule, 7... Outer capsule, 8... Torpedo as payload, 10
...Sequencer, 15.42...Emission device, 32.
...Sea level, 34...Target. 587-3(5) Figure 7

Claims (1)

[Claims] (1) A rocket motor for rocket propulsion, which is attached to the tip of the rocket motor and forms the body of the aircraft together with the rocket motor, and a payload such as a torpedo is stored inside, and after providing rocket propulsion force, it lands on the water. A capsule that is detached from the rocket motor before the capsule is separated from the rocket motor, and a device that is installed in the capsule and operates at the same time as the capsule is detached from the rocket motor, or after the capsule is detached, to decelerate the capsule and detach the capsule from the rocket motor before the capsule lands on the water. 1. A payload carrying spacecraft, such as a torpedo, comprising: a deceleration device that is detachable; and a release device that is provided on a capsule and releases the payload from the capsule after the capsule lands on water.