JPH05296700A - Power supply device for missile - Google Patents

Abstract

PURPOSE:To obtain an electric power with a simple mechanism by a method wherein a kinetic energy and the like, generated by accelerating impact and aeronautic resistance received by a weight and the like upon launching or during flying, is changed into the rotary motion of a generator equipped in the fuselage of a missile through connecting materials such as a rope and the like instead of an external power supply. CONSTITUTION:This device is constituted so that a generator 2 is provided in a missile or a projectile 1, a reeling wheel 4 is connected directly to the rotor 3 of the generator and the reeling wheel 4 is rotated through a rope 5 pulled by the kinetic energy of the weight 6 which receives an accelerating impact upon launching the projectile and an aeronautical resistance force during flying whereby electric power is generated by the generator 2.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a power supply device for a flying vehicle such as a projectile or missile when it is being launched or during flight.

[0002]

2. Description of the Related Art Conventional power supply devices for projectiles such as shells and missiles include (1) thermal batteries, (2) wind turbine generators, etc.
Requires an external power source to activate the electrolyte, and is generally expensive, and the volume increases as the amount of power increases. (2) is a missile because it is installed on the head of a flying vehicle. There is a problem such as obstacles to target detection.

In view of the above points, the present invention uses, instead of an external power source, kinetic energy or the like generated by acceleration shock or aerodynamic resistance received by a weight or the like at the time of launching or during flight through a connecting object such as a rope. It is an object of the present invention to provide a power supply device for a flying object that can obtain electric power from the generator by changing the rotational motion of a generator provided inside the flying object.

[0004]

In order to achieve the above object, a power supply device for a flying vehicle of the present invention is provided with a generator inside a flying vehicle such as a cannonball and a missile, and a rotor of the generator. A connecting object such as a rope that is directly connected or connected to the spinning wheel and is pulled by the launch of the flying object, or the rope that is pulled by the kinetic energy of the member that receives the acceleration impact force at the time of launch or the aerodynamic resistance force during flight The spinning wheel is rotated through the connecting object to obtain electric power from the generator.

[0005]

In the power supply device for a flying vehicle of the present invention, the rotor of the generator provided inside the flying vehicle is rotationally driven through a connecting object such as a rope pulled by the launch of the flying vehicle and a spinning wheel. Electromotive force is generated by rotating the kinetic energy of a member such as a weight that receives acceleration impact force or aerodynamic resistance force during or during launch of a flying object through a connecting object such as a rope and a spinning wheel. ing. Further, a blade is attached to the spinning wheel, and the spinning wheel is rotated by the aerodynamic resistance force applied to the blade, whereby electromotive force can be obtained.

Therefore, the power supply device for a flying vehicle according to the present invention has an extremely simple structure and can control the amount of electric power generated by changing the size of the weight.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a power supply device for a flying vehicle according to the present invention will be described below with reference to the drawings.

FIG. 1 shows a first embodiment of the present invention, which is applied to a shell (or a rocket or the like). The rotor of a generator 2 provided inside a shell 1 as a flying body ( As shown in FIG. 2, a spinning wheel 4 that also serves as a flywheel (a so-called flywheel) is directly connected to the armature 3 and a rope 5 is wound around the spinning wheel 4 and the other end of the rope 5 is It is connected and fixed to the weight 6. The weight 6 is movable within a cylinder 7 provided at the rear of the shell 1.

Therefore, when the shell 1 is fired,
The weight 6 receives the acceleration impact force from the inside of the cylinder 7, and
It moves to the outside of the shell 1 like a virtual line. For this reason, the rope 5 is also pulled by the weight 6, so that the spinning wheel 4 rotates, and thus the directly connected rotor 3 also rotates. Thus, the kinetic energy of the weight 6 is converted into electric power, and the generator 2 generates electric power. This electric power can be easily stored in the condenser 8 because the generated voltage can be high.
Further, the electric power is appropriately processed by the power supply circuit 9 and is used as a power supply for the ammunition.

It should be noted that the weight 6 exerts a force to pull the rope 5 immediately after the cannonball 1 is fired while the acceleration impact force due to the firing is applied, but thereafter, an aerodynamic resistance force is exclusively applied to the weight 6 to cause the rope 5 to move. Will be the force to pull. Then, the rope 5 continues to rotate the spinning wheel 4 for an appropriate time, and then leaves the spinning wheel 4 and is discharged together with the weight 6 to the outside of the shell 1.

Needless to say, power can be supplied for the required time due to the flywheel effect.

FIG. 3 shows a second embodiment of the present invention. In this case, a weight 6 is installed outside the missile 1A as a flying object. That is, the weight 6 is installed on the guide rail 10 provided on the missile 1A. The rope 5 is connected to the weight 6 and the spinning wheel 4 via the pulley 11.
The relationship between the rotor 3 and the spinning wheel 4 of the generator 2 provided inside the missile 1A, the configuration in which the rope 5 is wound around the spinning wheel 4, and the like are as shown in FIG.

Also in the case of the second embodiment, the kinetic energy of the weight 6 generated by the missile launch is converted into electric power as described in the first embodiment.

FIG. 4 shows a third embodiment of the present invention. In this case, the weight 6 used in the first and second embodiments described above is eliminated, and the other end of the rope 5 wound around the spinning wheel 4 on the missile 1A side is fixed to a fixed structure on the ground, such as a launcher (launcher). ) 1
It is connected and fixed to point A of 2. The relationship between the rotor 3 and the spinning wheel 4 of the generator 2 provided inside the missile 1A, and the spinning wheel 4
The structure in which the rope 5 is wound around is as shown in FIG.

In the case of the third embodiment, the movement of the missile 1A causes the rope 5 to be immediately pulled and the spinning wheel 4 to rotate, so that the rotor 3 directly connected to the rope 5 is rotationally driven. Power is obtained as well.

FIGS. 5 and 6 show a fourth embodiment of the present invention, in which the present invention is applied when flying at high speed like a shell. In these figures, a gear wheel 13 having a smooth curve and also serving as a flywheel is provided integrally with the spinning wheel 4, and a rack mechanism 14 meshing with the gear wheel 13 is combined. The spinning wheel 4 and the gear 13 are directly connected to the rotor 3 of the generator 2 in the shell 1, and one end of the rack mechanism 14 is provided with a spring 15 having an appropriate strength fixed to the shell 1 at the other end. Try to reduce the high-acceleration impact force that is received by the etc. At the same time, on the other hand, the rope 5 whose one end is connected to the rack mechanism 14 is connected and wound around the spinning wheel 4. The spring 15 is set to an initial state in which the rack mechanism 14 is engaged with the gear 13 as shown by the solid line in FIG.

Now, when the shell 1 is fired and a predetermined acceleration impact force is applied, the spring 15 is released (disengaged from the shell) and together with the rack mechanism 14, the rope 5 of the spinning wheel 4 as shown by the phantom line in FIG.
Is released outside the flying body while pulling. In this way, the spinning wheel 4 rotates and power is generated. The rope 5
After continuing to rotate the spinning wheel 4 for a suitable time, the spinning wheel is disengaged from the spinning wheel 4 and separated from the shell 1 together with the rack mechanism 14 and the spring 15.

FIGS. 7 to 9 show a fifth embodiment of the present invention, in order to drive the generator 2 in the missile 1A to rotate,
Instead of the rack mechanism 14 of FIG. 5, a small-diameter gear 16 that directly connects (or integrates) the spinning wheel 4 is provided so as to mesh with a gear 13 that is directly connected to the rotor 3 of the generator 2. And
The rope 5 is wound around the spinning wheel 4, and the weight 6 is passed through the rope 5.
Are connected.

In this case, there is a feature that the speed of pulling the rope 5, and thus the length of power generation time, can be adjusted by the gear mechanism.

FIGS. 10 and 11 show a sixth embodiment of the present invention, in which a spinning wheel with blades receiving aerodynamic resistance is used to rotationally drive the generator 2 in the missile 1A. In these figures, the spinning wheel 4 is rotatably supported by the missile 1A around the AA 'axis, and has blades 18 attached to the periphery of the spinning wheel 4 to receive wind pressure due to the flow of wind in flight. As can be obtained, the blade 18 is partially out of the missile 1A. A transmission wheel 20 is integrated with the spinning wheel 4 with blades. A transmission wheel 22 is directly connected to the rotor 3 of the generator 2 in the missile.
The belt 21 is wound around 22. Therefore,
The rotation of the spinning wheel 4 is caused by the transmission wheel 20, the belt 21, and the transmission wheel 2.
It is transmitted to the rotor 3 of the generator 2 via 2. A spool 19 is integrally attached to the other side of the spinning wheel 4, around which the rope 5 is wound, and the end of the rope 5 is fixed to a ground fixture 23 such as a launcher.

Therefore, when the missile 1A is launched,
The rope 5 is pulled, the spinning wheel 4 is rotated, and preliminary rotation is performed until an aerodynamic load is applied. In this case, the rope 5 moves away from the spinning wheel 4 after some preliminary rotational movement has taken place. Therefore, the spinning wheel 4 with blades will continue to rotate due to the aerodynamic load thereafter. The rotation of the spinning wheel 4 is transmitted to the generator 2 by the belt 21 to generate electricity.

[0022]

As described above, the power supply device for a flying vehicle of the present invention is applicable irrespective of the type of flying vehicle due to its operating principle, and the main components are the generator, It is an extremely simple part such as a weight and rope, and the number of parts can be reduced, so there is no need for maintenance and inspection and no external power supply, and it is possible to obtain electric power regardless of the attitude of the flying body, The generated voltage can be easily taken to be high and the safety is extremely excellent.

[Brief description of drawings]

FIG. 1 is a configuration diagram showing a first embodiment of a power supply device for a flying vehicle according to the present invention, which is applied to a shell.

FIG. 2 is a side sectional view showing details of the inside of the generator and the spinning wheel.

FIG. 3 is a configuration diagram showing a second embodiment of the present invention, in which a weight is provided outside the missile.

FIG. 4 is a configuration diagram showing a third embodiment of the present invention in which the weight is abolished.

FIG. 5 is a configuration diagram showing a fourth embodiment of the present invention, which is applied to a high-acceleration projectile such as a shell.

FIG. 6 is a side sectional view showing a generator, a spinning wheel and a rack mechanism portion in the case of a fourth embodiment.

FIG. 7 is a configuration diagram of a fifth embodiment of the present invention in which a gear mechanism is provided in a spinning wheel.

FIG. 8 is a side sectional view showing a generator and a gear mechanism portion in a fifth embodiment.

FIG. 9 is a front view of the same.

FIG. 10 is a sixth embodiment of the present invention, and is a configuration diagram of a spinning wheel provided with blades.

FIG. 11 is a configuration diagram showing a connection relationship between a generator and a spinning wheel with blades according to a sixth embodiment.

[Explanation of symbols]

 1 Cannonball 1A Missile 2 Generator 3 Rotor 4 Spinning Wheel 5 Rope 6 Weight 10 Guide Rail 12 Launch Pad (Launcher) 13, 16 Gear 14 Rack Mechanism 18 Blades 20, 22 Transmission Wheel 21 Belt

Claims (2)

[Claims] 1. A generator provided inside a flying body such as a shell or a missile, a spinning wheel directly connected to or connected to a rotor of the generator, and a connecting object such as a rope pulled by the firing of the flying body, or The flywheel characterized in that electric power is obtained from the generator by rotating the spinning wheel through a connecting object such as the rope that is pulled by the kinetic energy of a member that receives acceleration impact force at launch or aerodynamic resistance force during flight. Power supply for shovel. 2. The power supply device for a flying object according to claim 1, wherein the spinning wheel is provided with blades for receiving aerodynamic resistance.