JPH09272496A - Power source for flying body - Google Patents

Abstract

PROBLEM TO BE SOLVED: To solve such a problem that the mounting of a tunnel cable transmitting a control signal and a power from a guidance part to a drive source is difficult because a space in which the internal space of a tunnel cover for protecting a tunnel cable is less in a rear wing steered type flying body which requires the tunnel cable and the tunnel cover. SOLUTION: A flying body comprises an area reduction part 15 having an outer diameter smaller than that of the flying body, a parallel part 16 provided in the reduction part 15, A rudder drive part 9 formed of a shell 14 having an enlarged part 17 which diverges from the parallel part 16 in an enlarging direction and having a surface area equal to that of the reduction part 15, a first metal cylinder 18 internally making contact with the reduction part 15 through the intermediary of an insulator, and a second metal cylinder 20 internally making contact with the enlarged part 17, insulated from the first metal cylinder 18 and having a gap in which gas having a negative pressure or a low pressure is charged are equipped. With this arrangement, it is possible to obtain power from a differential potential produced from a thermal electron effect caused by a temperature difference between the first and second metal cylinders 18, 20 which is caused during flying.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a power supply unit for a rear wing steering flying vehicle that flies at supersonic speed. More specifically, the rear wing steering section includes aerodynamic heating after launch. Is provided with a power generation device for generating power by a temperature difference generated on the surface of the airframe or the rear wing, and thereby predetermined power is obtained.

[0002]

2. Description of the Related Art First, a conventional power supply device for this type of flying object will be described. In FIG. 11, 1 is a guiding part,
Reference numeral 2 is a power load inside the induction unit 1, 3 is a power supply device provided inside the induction unit 1, and supplies power to the power load 2 after launching a flying object.
And a power supply circuit 5 for outputting the output of the battery 4 to the power load 2 by converting the output of the battery 4 into a predetermined voltage. 6 is a front wing provided on the guide unit 1, 7 is a warhead provided behind the guide unit 1, 8 is a projectile propelling device provided behind the warhead 7, and 9 is steering provided behind the propulsion unit 8. The drive units 10a and 10b are rear wings provided on the steering drive unit 9, and 11
Reference characters a and 11b are provided inside the steering drive unit 9 and are drive sources respectively corresponding to the rear wings 10a and 10b. The drive sources 10a and 10b are control signals from the guide unit 1 passing through the tannel cable 12. And the rear wings 10a, 10 by the output power from the power supply device 4 passing through the tannel cable 12.
Drive b. Reference numeral 13 is a tunnel cover for protecting the tunnel cable 12.

[0003]

In the conventional power supply device as described above, the tunnel cable 12 is used for transmitting the control signal and the output power from the induction section 1 to the drive sources 11a and 11b.
Is essential, but because there is a warhead 7 and a propulsion device 8 between the guide unit 1 and the steering drive unit 9, the tunnnel cable 12 cannot be routed through the inside of the projectile, and is only routed outside the projectile. could not. Therefore, the tunnel cable 12 is exposed to the surrounding environment, and the tunnel cover 13 for protecting the tunnel cable 12 from the surrounding environment is indispensable. This tunnel cover 13
Is generally formed to be small in order to reduce the influence on the interface of the flying body with the launcher and the aerodynamic characteristics of the flying body, and the mountable space inside the tunnel cover 13 is small. For this reason, it is difficult to take thermal measures against aerodynamic heating of the tunnel cable 12 passing through the inside of the tunnel cover 13 and to wire the output power from the induction unit 1 to the drive sources 11a and 11b, which requires a large mounting space. There are implementation issues.

The present invention has been made to solve the above problems, and eliminates the output power from the guide section 1 to the drive sources 11a and 11b, and causes the steering drive section 9 to perform steering drive during flight at supersonic speed. The portion 9 or the rear wing 10 generates electric power by using the thermal energy received by the aerodynamic heating, and drives it to generate the drive source 11
It proposes a power supply device for a flying object that is supplied to a and 11b.

[0005]

A power supply device according to a first aspect of the present invention comprises a narrowed portion which is behind a flying body and is narrowed down to be smaller than an outer diameter of the flying body, and a parallel portion which is provided in the narrowed portion. A steering drive unit that includes a shell that extends from the parallel portion in an expansion direction and has an expansion portion that has the same surface area as the throttle portion,
A first cylindrical body made of metal, which is inscribed with the throttle portion and the insulator interposed therebetween, and a gap which is inscribed with the expansion portion, is insulated from the first cylindrical body, and is filled with a vacuum or low-pressure gas. A second cylindrical body made of metal having, and transmitting a difference in surface temperature between the narrowed portion and the expanded portion caused by aerodynamic heating in flight to the first cylindrical body and the second cylindrical body by heat conduction,
The electric power is obtained from a potential difference caused by a thermoelectron effect between the first cylindrical body and the second cylindrical body.

Further, the power supply device according to the second aspect of the present invention is, behind the flying body, a narrowed portion which is narrower than the outer diameter of the flying body, a parallel portion provided in the narrowed portion, and the parallel portion. From the steering drive unit including a shell having an expansion portion having the same surface area as the narrowed portion, and a metal first member that is insulated from the shell and is provided at an arbitrary position inside the steering drive unit. A cylindrical body, a second cylindrical body made of metal, which is insulated from the first cylindrical body and has a gap in which a vacuum or low-pressure gas is sealed, and is inscribed with the narrowed portion sandwiching an insulating body, and A first heat pipe that contacts the first cylindrical body, and a second heat pipe that is inscribed in the expansion portion and that contacts the second cylindrical body, and the throttle that is generated by aerodynamic heating in flight Difference between the surface temperature of the expansion part and the surface temperature of the expansion part And a second heat pipe to transfer the electric power to the first and second cylindrical bodies and obtain electric power from a potential difference caused by a thermoelectron effect between the first and second cylindrical bodies. Configured.

The power supply device according to the third aspect of the present invention is provided at the front edge portion of the rear wedge-shaped rear wing and has a convex heating portion insulated from the surroundings, and is insulated from the front edge portion, and Provided at the trailing edge of the rear blade having the same outside air contact area as the leading edge, facing the heating section, and having a concave cooling section having a gap filled with vacuum or low-pressure gas, Due to the difference in surface temperature between the leading edge portion and the trailing edge portion caused by aerodynamic heating in flight, a temperature difference occurs between the heating portion and the cooling portion, and due to a thermoelectron effect between the heating portion and the cooling portion. Configured to obtain electric power from the resulting potential difference.

The power supply device according to the fourth aspect of the invention is provided with a plurality of convex heating portions provided on the front edge of the twin wedge-shaped rear wing and insulated from the surroundings, and insulated from the front edge. A plurality of concave cooling sections provided at the trailing edge section of the rear blade having the same outside air contact area as the leading edge section, facing the heating section and having gaps filled with vacuum or low-pressure gas. The temperature difference between the heating portion and the cooling portion is caused by the difference in surface temperature between the leading edge portion and the trailing edge portion caused by aerodynamic heating during flight. It is configured to obtain electric power from the potential difference caused by the thermionic effect between them.

In the power supply device according to the fifth aspect of the present invention, a convex heating portion insulated from the surroundings is provided in the parallel portion provided at the leading edge portion of the rear wedge-shaped rear wing, and the parallel portion is insulated from the parallel heating portion. Is
And a concave cooling section provided at the trailing edge of the rear blade having the same outside air contact area as the leading edge, facing the heating section and having a gap filled with vacuum or low-pressure gas,
Due to the difference in surface temperature between the leading edge portion and the trailing edge portion caused by aerodynamic heating in flight, a temperature difference will occur between the heating portion and the cooling portion, and the heat between the heating portion and the cooling portion will be increased. It is configured to obtain electric power from the potential difference caused by the electronic effect.

In the power supply device according to the sixth aspect of the present invention, a plurality of convex heating portions insulated from the surroundings are provided in the parallel portion provided at the leading edge portion of the rear wedge-shaped rear wing, and the parallel portion is provided. A plurality of concave shapes that are insulated from each other and that are provided at the trailing edge of the rear blade that has the same outside air contact area as the leading edge, face the heating section, and that have a gap filled with a vacuum or low-pressure gas. The cooling portion, the difference in surface temperature between the leading edge portion and the trailing edge portion caused by aerodynamic heating during flight, a temperature difference occurs between the heating portion and the cooling portion, the heating portion and It is configured to obtain electric power from the potential difference caused by the thermoelectron effect between the cooling parts.

[0011]

BEST MODE FOR CARRYING OUT THE INVENTION

Embodiment 1. 1 is a configuration diagram showing a first embodiment of the present invention. In the figure, 1 is a guide portion, 6 is a front wing provided on the guide portion 1, 7 is a warhead provided behind the guide portion 1, and 8 is a warhead 7. , 9 is a steering drive unit provided behind the propulsion device 8, 10a and 10b are rear wings provided on the steering drive unit 9, and 11a and 11b are provided inside the steering drive unit 9.
The drive sources 11a and 11b are drive sources corresponding to the rear wings 10a and 10b, respectively.
The rear wings 10a, 10 by the control signal from the guiding section 1 passing through
Control b. Reference numeral 13 is a tannel cover for protecting the tannel cable 12, 14 is a steering drive portion, and a throttle portion 15 that is narrowed to a smaller diameter than the outer diameter of the flying body, a parallel portion 16 provided in the throttle portion 15, and a parallel portion. A shell provided with an expansion portion 17 that expands from 16 in the direction of expansion and has the same surface area as the throttle portion 15, 18 is a first metal cylindrical body inscribed between the throttle portion 15 and the insulator 19, and 20 is an expansion portion. Inscribed in 20,
A second metal cylinder 5, which is insulated from the first cylinder 18 and has a gap filled with a vacuum or low-pressure gas, is formed between the first cylinder 18 and the second cylinder 20. By converting the potential difference into a predetermined voltage, the drive sources 11a, 1
It is a power supply circuit for outputting to 1b.

In the power supply device for a flying vehicle constructed as described above, if the pressure on the surface of the throttle portion 15 flying at supersonic speed is P1 and the pressure on the surface of the expansion portion 17 is P2, P1, The relationship of P2 is as shown in "Equation 1".

[0013]

[Equation 1]

Here, if the heat transfer coefficient from the surface of the throttle portion 15 to the outside air is h1, and the heat transfer coefficient from the surface of the expansion portion 17 to the outside air is h2, the relationship between the pressure and the heat transfer coefficient is "Equation 2". ”
become that way.

[0015]

[Equation 2]

However, n is a constant determined by the flow state, n = 0.5 for laminar flow and n = 0.
3. Here, from "Equation 1" and "Equation 2", h1, h2
The relationship is as in "Equation 3".

[0017]

(Equation 3)

Assuming that the heat insulating wall temperature is T0, the surface temperature of the narrowed portion 15 is T1, the surface temperature of the expanded portion 17 is T2, the surface area of the narrowed portion 15 is A1, and the surface area of the expanded portion 17 is A2, The surface temperatures of the portion 15 and the extension portion 17 are as shown in "Equation 4" and "Equation 5", respectively.

[0019]

(Equation 4)

[0020]

(Equation 5)

Here, in the first embodiment, since the surface areas of the narrowed portion 15 and the expanded portion 17 are the same, "Equation 3" and "Equation 4"
And from "Equation 5", the surface temperature T1 of the narrowed portion 15 and the expanded portion 1
The relationship of the surface temperature T2 of No. 7 is as shown in "Equation 6".

[0022]

(Equation 6)

From the relation of "Equation 6", aerodynamic heating during flight causes a difference in surface temperature between the throttle portion 15 and the expansion portion 17.

Therefore, the first cylindrical body 18 and the second cylindrical body 20 which are in contact with the narrowed portion 15 and the expanded portion 17, respectively.
A temperature difference occurs between the drive sources 11a, 1 and the potential difference generated by the thermoelectron effect between the first cylindrical body 18 and the second cylindrical body 20 is converted into a predetermined voltage by the power supply circuit 5.
It becomes possible to output to 1b.

Embodiment 2 2 is a block diagram showing a second embodiment of the present invention. In the figure, 1 and 5 to 17 are exactly the same as those of the first embodiment. 18 is provided inside the parallel portion 16 and is made of a metal first cylindrical body that is insulated from the shell 14, and 20 is insulated from the first cylindrical body 18,
The second heat source 21 is made of metal and has a gap in which a vacuum or low-pressure gas is sealed. The first heat source 21 is inscribed in the narrowed portion 15 with the insulator 17 in between and is in contact with the first heat source 18. The pipe, 22 is a second heat pipe that is inscribed in the expanded portion 17 and is in contact with the second cylindrical body 20.

In the power supply device configured as described above, the throttle unit 15 is caused by the relationship of "Equation 6" while flying at supersonic speed.
And the surface temperature of the expanded portion 17 is different. This temperature difference is transmitted to the first cylindrical body 18 and the second cylindrical body 20 by the first heat pipe 21 and the second heat pipe 22, respectively, and between the first cylindrical body 18 and the second cylindrical body 20. A difference in temperature occurs in the first cylindrical body 18 and the second cylindrical body 20 and the potential difference caused by the thermoelectron effect is converted into a predetermined voltage by the power supply circuit 5, and output to the drive sources 11a and 11b. It will be possible.

Embodiment 3 3 and 4 are configuration diagrams showing a third embodiment of the present invention. In these figures, 1
5 to 9 and 12 and 13 are exactly the same as those in the first embodiment. Reference numerals 10a and 10b are twin wedge-shaped rear wings provided in the steering drive unit 9, and 23 is provided in a front edge portion 24 of the rear wings 10a and 10b, and is a convex heating unit that is insulated from the surroundings.
Reference numeral 5 is fixed to the front edge portion 24 and the insulator 18 and is provided at the rear edge portion 26 having the same outside air contact area as that of the front edge portion 24 so as to face the heating portion 23 and generate a vacuum or low pressure gas. It is a concave cooling unit with a sealed gap.

If the pressure on the surface of the leading edge portion 24 during flight at supersonic speed is P2 and the pressure on the surface of the trailing edge portion 26 is P1, "
The relation of the equation 1 is obtained. When the surface temperature of the leading edge portion 24 is T2 and the surface temperature of the trailing edge portion 26 is T1, the above-described first embodiment is performed.
According to the principle explained in Section 1, the relation of "Equation 6" is established, and the leading edge 2
4 and the surface temperature of the trailing edge portion 26 are different from each other.

Therefore, a temperature difference occurs between the heating section 23 and the cooling section 25, and the potential difference caused by the thermoelectron effect between the heating section 23 and the cooling section 25 is converted into a predetermined voltage by the power supply circuit 5. Then, it becomes possible to output to the drive sources 11a and 11b.

Fourth Embodiment 5 and 6 are block diagrams showing a fourth embodiment of the present invention. In these figures, 1
5 to 9 and 12 and 13 are exactly the same as those in the first embodiment. Reference numerals 10a and 10b are twin wedge-shaped rear wings provided in the steering drive unit 9, 23 is a front edge portion 24 of the rear wings 10a and 10b, and a plurality of convex heating units insulated from the surroundings. It is fixed by sandwiching the edge 24 and the insulator 18,
A plurality of concave cooling sections are provided on the rear edge section 26 having the same outside air contact area as the front edge section 24, face the heating section 23, and have a gap filled with vacuum or low-pressure gas.

Also in the case of the fourth embodiment, similarly to the third embodiment, from the difference in surface temperature between the leading edge portion 24 and the trailing edge portion 26 caused by aerodynamic heating during flight at supersonic speed, A temperature difference occurs between the heating unit 23 and the cooling unit 27, and a potential difference caused by the thermoelectron effect between the heating unit 23 and the cooling unit 27 is converted into a predetermined voltage by the power supply circuit 5, and the driving source 11a, It becomes possible to output to 11b.

Embodiment 5 7 and 8 are configuration diagrams showing a fifth embodiment of the present invention. In these figures, 1
5 to 9 and 12 and 13 are exactly the same as those in the first embodiment. Reference numerals 10a and 10b are twin wedge-shaped rear wings provided in the steering drive unit 9, and 23 is a parallel section 16 provided at the front edges of the rear wings 10a and 10b, and is a convex heating unit that is insulated from the surroundings. Is fixed by sandwiching the front edge portion 24 and the insulator 18, and has the same outside air contact area as the front edge portion 24.
6 is a concave cooling unit which is provided in 6 and faces the heating unit 23 and has a gap filled with a vacuum or low-pressure gas.

Also in the case of the fifth embodiment, as in the case of the third embodiment, from the difference in surface temperature between the leading edge portion 24 and the trailing edge portion 26 caused by aerodynamic heating during flight at supersonic speed, A temperature difference occurs between the heating unit 23 and the cooling unit 27, and a potential difference caused by the thermoelectron effect between the heating unit 23 and the cooling unit 27 is converted into a predetermined voltage by the power supply circuit 5, and the driving source 11a, It becomes possible to output to 11b.

Embodiment 6 FIG. 9 and 10 are configuration diagrams showing a sixth embodiment of the present invention. In these figures,
1 and 5 to 9 and 12 and 13 are exactly the same as those in the first embodiment. Reference numerals 10a and 10b are twin wedge-shaped rear wings provided in the steering drive unit 9, and 23 is a parallel section 16 provided at the front edges of the rear wings 10a and 10b. , 25 are fixed on both sides of the insulator 18 and the front edge 24, and are provided on the rear edge 26 having the same outside air contact area as the front edge 24, and are opposed to the heating section 23, and are in a vacuum or low pressure gas. It is a plurality of concave cooling units with a gap enclosing them.

Also in the case of the sixth embodiment, as in the case of the third embodiment, from the difference in surface temperature between the front edge portion 24 and the rear edge portion 26 caused by aerodynamic heating during flight at supersonic speed, A temperature difference occurs between the heating unit 23 and the cooling unit 27, and a potential difference caused by a thermoelectron effect between the heating unit 23 and the cooling unit 27 is converted into a predetermined voltage by the power supply circuit 5, and the drive sources 11a and 11b. Can be output to.

By the way, in the above description, the present invention has been described as being applied to a flying vehicle for steering a rear wing that flies at supersonic speed. It goes without saying that you can do it.

[0037]

As described above, according to the present invention, the steering drive unit of the flying vehicle for steering the rear wing receives the thermal energy received by the aerodynamic heating of the steering drive unit or the rear wing during flight at supersonic speed. By using a power supply device that can generate power and output it to the drive source, wiring of output power from the induction part to the drive source is not required, and it is easy to mount the tunnel cable inside the tunnel cover. There is an effect.

In addition, the steering drive unit and the power supply device provided on the rear wing according to the present invention can be applied to any rear wing steering flying body that can fly at supersonic speed regardless of its type because of its operating principle. The components are also extremely simple parts such as metal cylinders and heat pipes, and the number of parts can be reduced. Therefore, there is no need for maintenance and inspection, and there is no need for an external power source. There is an effect that electric power can be obtained regardless of the posture of the body, the generated voltage can be easily taken high, and the safety is also extremely excellent.

[Brief description of drawings]

FIG. 1 is a configuration diagram showing a first embodiment of the present invention.

FIG. 2 is a configuration diagram showing a second embodiment of the present invention.

FIG. 3 is a configuration diagram showing a third embodiment of the present invention.

FIG. 4 is a configuration diagram showing a cross-sectional shape of a rear wing according to a third embodiment of the present invention.

FIG. 5 is a configuration diagram showing a fourth embodiment of the present invention.

FIG. 6 is a configuration diagram showing a cross-sectional shape of a rear wing according to a fourth embodiment of the present invention.

FIG. 7 is a configuration diagram showing a fifth embodiment of the present invention.

FIG. 8 is a configuration diagram showing a cross-sectional shape of a rear wing according to a fifth embodiment of the present invention.

FIG. 9 is a configuration diagram showing a sixth embodiment of the present invention.

FIG. 10 is a configuration diagram showing a cross-sectional shape of a rear wing according to a sixth embodiment of the present invention.

FIG. 11 is a configuration diagram of a conventional rear-wing steering flying body.

[Explanation of symbols]

1 induction part, 2 power load, 3 power supply device, 4 batteries,
5 power circuits, 6 front wings, 7 warheads, 8 propulsion devices, 9
Steering drive section, 10 rear wing, 11 drive source, 12 tunnel cable, 13 tunnel cover, 14 shell,
15 narrowed portion, 16 parallel portion, 17 extended portion, 18 first cylindrical body, 19 insulator, 20 second cylindrical body, 21
First heat pipe, 22 second heat pipe, 2
3 heating part, 24 front edge part, 25 cooling part, 26 rear edge part.

Claims (6)

[Claims] 1. A narrowed portion that is located behind the flying body and has a diameter smaller than the outer diameter of the flying body, a parallel portion provided on the narrowed portion, and a widened portion from the parallel portion in an expanding direction. A steering drive unit including a shell having an expanded portion having the same surface area as the above, a first cylindrical body made of metal inscribed between the throttle unit and an insulator, and an inscribed portion of the expanded unit. A power supply device for a flying object, characterized in that it is provided with a second metal cylinder that is insulated from the cylinder and has a gap filled with a vacuum or low-pressure gas. 2. A narrowed portion which is behind the flying body and is narrowed to be smaller than the outer diameter of the flying body, a parallel portion provided on the narrowed portion, and a narrowed portion which spreads in an expanding direction from the parallel portion. A steering drive unit including a shell having an expanded portion having the same surface area as the above; a first cylindrical body made of metal, which is insulated from the shell and is provided at an arbitrary position inside the steering drive unit; A second cylindrical body made of metal, which is insulated from the body and has a gap in which a vacuum or low-pressure gas is sealed, and is inscribed in the narrowed portion with an insulator interposed between the second cylindrical body and the first cylindrical body. A power supply device for a flying object, comprising: a heat pipe No. 1; and a second heat pipe inscribed in the expansion portion and in contact with the second cylindrical body. 3. A convex heating portion provided at a front edge portion of a twin wedge-shaped rear wing and insulated from the surroundings, and an outside air contact area which is insulated from the front edge portion and is the same as the front edge portion. The flying body is characterized in that it is provided at the trailing edge of the rear blade and has a concave cooling section facing the heating section and having a gap filled with a vacuum or low-pressure gas. Power supply. 4. A plurality of convex heating portions provided on the front edge of a twin wedge-shaped rear wing and insulated from the surroundings, and the same outside air contact with the front edge and the same with the front edge. An air-conditioning device provided with a plurality of concave cooling portions which are provided at a trailing edge portion of the rear blade having an area and which face the heating portion and have a gap filled with a vacuum or low-pressure gas. The power supply for the body. 5. A convex heating part, which is provided in a front edge portion of a twin wedge-shaped rear wing, is insulated from the surroundings, and is the same as the front edge portion and is insulated from the parallel portion. An air-cooling unit provided at the trailing edge of the rear blade having an outside air contact area, facing the heating unit, and having a concave cooling unit having a gap filled with vacuum or low-pressure gas. The power supply for the body. 6. A plurality of convex heating portions in a parallel portion provided on a front edge portion of a twin wedge-shaped rear wing, and a plurality of convex heating portions insulated from the surroundings, and the front edge portion insulated from the parallel portions. And a plurality of concave cooling sections provided at the trailing edge of the rear blade having the same outside air contact area, facing the heating section, and having a gap filled with vacuum or low-pressure gas. Characteristic flying power supply unit.