JPH1123196A - Flying object - Google Patents

Abstract

PROBLEM TO BE SOLVED: To enable attainment to a target by hardly controlling a track along with a smaller size and a lighter weight by a method wherein a penetrator is fired at a given initial velocity by a firing means, accelerated to a superhigh velocity by a flying propulsion generation means and then, separated. SOLUTION: A penetrator 7 shaped in a rocket is housed into a penetrator housing section 8 formed being buried in a solid propulsion powder 3 at the head part of a machine body 2 so as to be movable in the direction of a machine shaft. Firstly, a flying object 1 is loaded into a firing cylinder 21 of a low reaction firing device 20 and a firing powder 22 is ignited to fire it at a given initial velocity by a gas pressure produced by the burning thereof. Thereafter, a solid propellant 3 is ignited by a disposable solid propellant ignitor 11 to accelerate the flying object to a superhigh velocity by a resulting combustion gas. The penetrator 7 is separated from a machine body 2 being integrated with a stable wing 10 by an inertial force generated from a difference between an air resistance the machine body 2 receives and an air resistance the penetrator 7 receives after the end of the burning of the solid propellant 3.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flying object having a penetrator, and more particularly to a flying object having a kinetic energy during an ultra-high-speed flight, which is driven into a target by driving the penetrator.

[0002]

2. Description of the Related Art Conventionally, as the above-mentioned flying object, for example, there has been one shown in FIG.

A flying object 51 shown in FIG. 1 includes a motor section 53 housed over substantially the entire length of a case 52 and a case 52.
The flying object 51 is provided with a small-diameter penetrator 54 housed in a small space partitioned by a partition 52a at the head of the flying object 51. The flying object 51 starts by the operation of the motor unit 53, accelerates to an extremely high speed, and reaches the target. In this case, the total kinetic energy possessed at this time is applied to the small-diameter penetrator 54 so as to strike the target.

The flying object 51 is an INTERA
VIA 3/1986.

[0005]

However, in the above-mentioned conventional flying object 51, the starting and acceleration to a very high speed are performed by the operation of the motor portion 53 which occupies almost the entire length of the case 52. In addition, there is a problem that it is difficult to perform the trajectory control and trajectory control is required in all flight sections.

In addition, since the penetrator 54 is housed in the head of the case 52, it is difficult to keep the total length of the body small in this respect, and it has been a conventional problem to solve these problems. .

[0007]

SUMMARY OF THE INVENTION The present invention has been made in view of the conventional problems, and is capable of achieving a penetrator at a target with almost no need for trajectory control while achieving weight reduction and miniaturization. The purpose is to provide a flying object.

[0008]

According to a first aspect of the present invention, there is provided a flying object having a flying thrust generating means and a penetrator. It is accelerated to high speed, and the penetrator can be separated in the flight direction when the flight thrust generating means has finished operating,
Such a structure of the flying object is used as means for solving the above-mentioned conventional problems.

A flying object according to a second aspect of the present invention is an aircraft pressure receiving section which receives a firing pressure from a firing means, and operates after being fired by receiving a firing pressure from the firing means at the aircraft pressure receiving section to operate at a very high speed. And a penetrator that separates from the airframe and flies along the trajectory when the flight thrust generation means has finished operating. The configuration is a means for solving the conventional problem described above.

In the flying object according to claim 3 of the present invention, the flying thrust generating means has a solid propellant filled in the body, and the penetrator is on the axle and substantially buried in the solid propellant of the flying thrust generating means. In the flying object according to claim 4 of the present invention, the launching means is a low-reaction launching device including a launching tube and a propellant charge, and the launching device is mounted on the launching tube of the low-reaction launching device. The gas pressure generated by the combustion of the medicine is received and fired by the body pressure receiving portion.

A flying object according to a fifth aspect of the present invention has a penetrator storage portion for storing a penetrator movably in the machine axis direction, and an impact load at the time of launching the aircraft side and the penetrator stored in the penetrator storage portion. Claim 6 of the present invention is configured to be fixed by a shear pin sheared by
In the flying object according to the present invention, the penetrator is provided with a stable wing, and in the flying object according to claim 7 of the present invention, the stable wing is provided separately from the penetrator,
When the penetrator is separated, it is integrated with the penetrator and separated from the machine.

[0012]

In the flying object according to the first and second aspects of the present invention, the flying thrust generating means operates and accelerates to an ultra-high speed after being fired at the initial velocity from the firing means. The size of the flight thrust generating means is reduced by the amount not activated at the time of firing, that is, the size of the aircraft is reduced, and in addition, the trajectory is set at the stage of firing from the firing means. Accordingly, the trajectory accuracy is improved as compared with the case where the trajectory control is performed in the flight section from the start to the acceleration to a very high speed.

When the flight thrust generating means has finished operating on the orbit, the penetrator separates from the suddenly decelerated body due to the inertial force generated by the difference in air resistance between the penetrator and the body, and receives little air resistance. The penetrator flies along the orbit while reaching almost the kinetic energy when separated from the airframe, and reaches the target.

The flying object according to the third aspect of the present invention has the above-described configuration, so that the total length of the airframe can be kept short, and the flying object according to the fourth aspect of the present invention has the above-described configuration. Therefore, the impact force at the time of launching is reduced, and, for example, launching from a lightweight vehicle body is performed without problems.

In the flying object according to the fifth aspect of the present invention, since the flying object is configured as described above, it is possible to prevent the penetrator from dropping out of the penetrator housing portion when the flying object is carried or set on the firing means. In the flying object according to claim 6 of the present invention, the flight after the penetrator is separated from the aircraft body becomes stable, and the flying object according to claim 7 of the present invention has the above-described structure, The wing fits well in the fuselage.

[0016]

According to the flying object according to the first and second aspects of the present invention, since the above-mentioned structure is employed, the weight and size can be reduced, and the orbit accuracy can be improved. As a result, a very excellent effect that the penetrator holding the kinetic energy can reliably reach the target is provided.

The flying object according to the third aspect of the present invention has the above-described configuration, so that the total length of the airframe can be kept short. In the flying object according to the fourth aspect of the present invention,
With the above-described configuration, for example, launching from a lightweight vehicle body is possible, and in the flying object according to claim 5 of the present invention,
A very excellent effect that the penetrator can be prevented from dropping out of the penetrator storage portion when being transported or set on the firing means is provided.

The flying object according to the sixth aspect of the present invention can stably fly the penetrator after being separated from the airframe, and the flying object according to the seventh aspect of the present invention has a stable wing in the airframe. This is a very excellent effect that it can be stored in a good manner.

[0019]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below with reference to the drawings.

FIGS. 1 and 2 show an embodiment of a flying object according to the present invention.

As shown in FIG. 1, the flying object 1 is filled into the body 2 substantially over its entire length and fired from a low-reaction launching device (firing means) 20, which will be described later, and burns to accelerate to an extremely high speed. A solid propellant 3 which constitutes a flying thrust generating means, a nozzle 4 which is located at the tail of the body 2 and constitutes a flying thrust generating means together with the solid propellant 3, and a nose cone 5 which covers the head of the body 2; The vehicle includes a fuselage stabilizing wing 6 that is deployed after launch, and a penetrator 7 that separates from the fuselage 2 and flies along an orbit when the solid propellant 3 finishes burning.

The penetrator 7 has a rocket shape, and its diameter is much smaller than the diameter of the fuselage 2. In this case, a penetrator storage portion 8 located on the axis of the body 2 and opening at the head is provided in a state of being buried in the solid propellant 3, and the penetrator 7 is movable in the machine direction in the penetrator storage portion 8. It is stored.

In this embodiment, the nose cone 5 and the penetrator 7 are fixed via shear pins 9, 9. These shear pins 9, 9 are sheared by the penetrator 7, which has received an impact load at the time of firing, moving in the direction of the space S provided between the tail of the penetrator 7 and the penetrator storage portion 8. Therefore, when the flying object 1 is fired, the fixed state of the penetrator 7 to the body 2 by the shear pins 9, 9 is released.

The flying object 1 has a nose cone 5 provided with a penetrator stabilizing wing 10. The penetrator stabilizing blade 10 includes a cylindrical portion 10a and a plurality of stabilizers 10b arranged around the cylindrical portion 10a at appropriate intervals.
Consists of And this penetrator stable wing 10
Is a penetrator 7 projecting from the penetrator storage portion 8.
A cylindrical portion 10a is slidably and non-rotatably fitted on a portion near the head of the penetrator 7. When the penetrator 7 separates from the penetrator storage portion 8, a projection (not shown) provided on the tail portion of the penetrator 7 is provided. Is locked to the cylindrical portion 10a so that it is separated from the nose cone 5 integrally with the penetrator 7 as shown in FIG.

That is, the penetrator 7 is in a free state with respect to the body 2 immediately after the projectile 1 is fired,
At the stage where the combustion of the solid propellant 3 is completed and the body 2 is decelerated by the air resistance, the penetrator 7 and the penetrator stabilizing wing 10 are moved from the penetrator storage unit 8 to the penetrator stabilizing wing 10 by the inertial force generated by the difference in the air resistance received by the penetrator 7 and the body 2. They are separated as one and fly to the target while maintaining the kinetic energy at this time.

A low-reaction launching device 20 as a launching means for launching the flying object 1 comprises a firing cylinder 21 and a firing charge 22.
The flying object 1 is provided with the low reaction launching device 20.
, And is fired by receiving the gas pressure generated by the combustion of the propellant charge 22 at the base (airframe pressure receiving portion) 11 a of the disposable solid propellant igniter 11 provided at the tail of the airframe 2. It has become something.

Next, the operation of the flying object 1 will be described.

First, when the projectile 1 is loaded into the launching tube 21 of the low reaction launching device 20 and ignites the propellant 22, the gas pressure generated by the combustion of the propellant 22 is discharged to a solid propellant igniter. Since the base 11a receives the flying object 1, the flying object 1 obtains the initial velocity and is launched from the launching cylinder 21 and starts flying along the set trajectory.

During this time, the shear pins 9, 9 are sheared by the movement of the penetrator 7 in the space S direction due to the impact load, and the fixed state of the penetrator 7 to the body 2 is released.

Thereafter, when the solid propellant 3 is ignited by the solid propellant igniter 11 to start combustion,
Combustion gas generated by the combustion of the solid propellant 3 is ejected from the nozzle 4 from which the throwaway solid propellant igniter 11 has been removed,
Acceleration to ultra-high speed will be made.

Next, when the combustion of the solid propellant 3 is completed during the flight, the fuselage 2 falls into a sharp deceleration state due to air resistance. At this time, the difference occurs between the penetrator 7 and the air resistance received by the fuselage 2. Due to the inertial force, as shown by a dashed line in FIG.
From the penetrator storage section 8 in the machine axis direction (flying direction).

At the time of this separation, a projection (not shown) provided at the tail of the penetrator 7 is engaged with the cylindrical portion 10a of the penetrator stabilizing wing 10 located inside the nose cone 5, so that it is indicated by a two-dot chain line in FIG. Further, the penetrator 7 is separated from the fuselage 2 side integrally with the penetrator stabilizing wings 10, and the penetrator 7 integrated with the penetrator stabilizing wings 10 stably flies toward the target.

During this flight, since the air resistance received by the penetrator 7 is not large, the penetrator 7
Flies along the orbit while almost retaining the kinetic energy when separated from the airframe 2, and reaches the target.

Therefore, in the flying object 1, the solid propellant 3 is burned and accelerated to a very high speed after being fired by the low reaction launcher 20, so that the solid propellant 3 is not burned from the time of firing. Therefore, the amount of the solid propellant 3 to be charged is small, that is, the size of the airframe 2 is reduced, and in addition, the trajectory of the flying object 1 is set at the time of firing by the low reaction launching device 20. Therefore, as compared with the case where the trajectory control is performed from the start stage, the trajectory accuracy is improved.

In the flying object 1 of this embodiment,
Penetrator storage section 8 provided in a state buried in solid propellant 3
Since the penetrator 7 is housed in the aircraft 1, the total length of the airframe 2 can be kept short.
Since it is fired by the low recoil firing device 20, the impact force at the time of firing becomes small, and for example, it becomes possible to fire from a lightweight vehicle body.

Further, in the above-described embodiment, the nose cone 5 of the airframe 2 and the penetrator 7 are fixed via the shear pins 9, 9, so that the flying object 1 can be transported.
This prevents the penetrator 7 from dropping out of the penetrator housing portion 8 when the penetrator 7 is loaded into the launching cylinder 21 of the low reaction launching device 20.
In this configuration, since the penetrator 7 is detached from the penetrator storage section 8 and the penetrator stabilizing wings 10 are mounted at the same time, the flight after the penetrator 7 is separated from the airframe 2 becomes stable. The stable wing 10 can be settled well in the fuselage 2.

The detailed structure of the flying object according to the present invention is not limited to the above embodiment.

[Brief description of the drawings]

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective sectional view (a) showing a flying object according to an embodiment of the present invention immediately after being launched from a low reaction launching device, and a portion of the low reaction launching device with the flying object loaded therein. It is a crushing perspective explanatory view (b).

FIG. 2 is an operation explanatory diagram showing a situation in which a penetrator separates from the airframe of the flying object of FIG. 1 integrally with a penetrator stabilizing wing.

FIG. 3 is a partially broken side explanatory view showing a flying object provided with a conventional penetrator.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Flying object 2 Aircraft body 3 Solid propellant (flying thrust generating means) 4 Nozzle (flying thrust generating means) 7 Penetrator 8 Penetrator storage part 9 Sharpin 10 Penetrator stabilizing wing 11a Base of solid disposable solid propellant igniter (body receiving part) 20) Low reaction launching device (launching means) 21 Launch cylinder 22 Launch charge

Claims (7)

[Claims] The present invention has a flying thrust generating means and a penetrator, and after being fired at an initial velocity from a firing means, is accelerated to an ultra-high speed by the operation of the flying thrust generating means, and the flying thrust generating means ends its operation. A flying object characterized in that a penetrator can be separated in a flight direction at a time. 2. An airframe pressure receiving section receiving a firing pressure from the firing means, a flying thrust generating means operating after receiving the firing pressure from the firing means at the airframe pressure receiving section and operating to accelerate to an ultra-high speed; A flying object, comprising: a penetrator that separates from the aircraft and flies along a trajectory when the thrust generating means has finished operating. 3. The flying thrust generating means includes a solid propellant charged in an airframe, and the penetrator is provided on the axle and substantially buried in the solid propellant of the flying thrust generating means. The flying object described in. 4. The launching means is a low-reaction launching device provided with a launch cylinder and a launch charge, and a gas pressure generated by combustion of the launch charge loaded in the launching tube of the low-reaction launching device is received by an airframe pressure receiving portion. The flying object according to claim 1, wherein the flying object is fired. 5. A penetrator accommodating portion for accommodating the penetrator movably in the machine axis direction, wherein the fuselage side and the penetrator accommodated in the penetrator accommodating portion are fixed by a shear pin sheared by an impact load at the time of firing. 1
A flying object according to claim 4. 6. The flying object according to claim 1, wherein the penetrator has a stable wing. 7. The flying object according to claim 6, wherein the stabilizer wing is provided separately from the penetrator, and is integrated with the penetrator and separated from the airframe when the penetrator is separated.