JPH0594758A - Temperature switch for high speed flying body - Google Patents

Abstract

PURPOSE:To simplify a structure, and also realize the downsizing by carrying out switch operation by volume expansion caused by a temperature rise of an expansion member filled inside a tip shape-forming member. CONSTITUTION:When a high speed flying body 1 is flying, a temperature of a tip shape-forming member 2 in the tip part 1a rises due to aerodynamic heating. Heat is conducted so an expansion member 3 filled in a volume part 2a, and simultaneously when fixation of a driving shaft 4 is released at a point of time when the expansion member 3 is melted up to the rear end surface of a capillary tube part 2b, the driving shaft 4 is driven by internal pressure of the expansion member 3, so that a temperature switch is operated. In this way, by driving the driving shaft 4 by volume expansion caused by melting of the expansion member 3, the downsizing can be realized in a simple structure, and a flying characteristic can be also stabilized by the downsizing.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a temperature switch used for a high speed flying object.

[0002]

2. Description of the Related Art Conventionally, a temperature switch that operates by a temperature rise due to aerodynamic heating has been used as a start switch for allowing a high-speed flying body to perform a predetermined control after a predetermined period from the start of flight. One of such temperature switches is, for example, as shown in FIG.
The tip shape forming member (22) made of a low melting point alloy formed in the tip shape of the high-speed flying body (21) is provided at the tip portion (21a) of 1), and the central portion inside the tip shape forming member (22). The drive shaft (24), which is provided slidably in the front-back direction inside the high-speed flying body (21) and is urged to the rear side of the high-speed flying body (21) by the spring (25), is fixed by screwing. The tip shape forming member (22) made of the low melting point alloy is heated to a predetermined temperature or higher and melted after a predetermined period from the start of flight due to aerodynamic heating when the high-speed flying body (21) flies, and the drive shaft When the fixing of one end of (24) is released, the drive shaft (24) is moved to the rear side of the high-speed flying body (21) by the urging force of the spring (25), so that the temperature switch is activated. I know what I tried to do To have.

[0003]

By the way, in the temperature switch of the high-speed flying object, since the biasing force of the spring (25) is used as the driving force for operating the temperature switch, the driving force should be increased. As a spring (2
If 5) is made larger, the space occupied by the spring (25) becomes larger. Moreover, the spring (2
Since the load generated by 5) also becomes large, the fixed portion of the tip shape forming member (22) that supports the spring (25) and the drive shaft (24) also had to be large. On the other hand, the tip shape forming member (22) is also a temperature sensitive portion, and when it becomes large, a temperature distribution is generated in the fixed portion, and the temperature at which the temperature switch operates varies, and the operating temperature detection accuracy of the temperature switch is high. Would lead to a problem that

The present invention has been made in view of the above points, and an object thereof is to miniaturize the temperature switch and to simplify the structure.

[0005]

In order to achieve the above-mentioned object, the solution means taken by the invention according to claim 1 is to perform a switch operation by utilizing the volume expansion accompanying the temperature rise.

Specifically, as shown in FIG. 1, the solution means taken by the invention according to claim 1 is provided at the tip of a high-speed flying body (1) that flies at high speed, and the temperature rise due to aerodynamic heating. Assuming a temperature switch operating at.

Then, a volume portion (2) fixed to the tip portion (1a) of the high-speed flying body (1) to form the tip shape of the high-speed flying body (1) and having a predetermined volume inside is formed.
a) and a tip shape forming member (2) formed with a thin tubular thin tube portion (2b) which is continuous to the rear side of the volume portion (2a) and extends to the rear end surface and extends, and the tip shape forming member. (2)
Expansion member (3) made of a metal or a polymer solid that is filled up to the middle of the volume part (2a) and the thin tube part (2b) and melts and expands at a predetermined temperature or higher, and the thin tube part (2).
b) is movably fitted in the end face of the thin tube portion (2
The drive shaft (4) fixedly provided to the rear end surface of the expansion member (3) is provided in b).

Further, the solution means taken by the invention according to claim 2 is to perform a switch operation by the high pressure of the high pressure chamber instead of the conventional spring.

Specifically, as shown in FIG. 2, the solution means taken by the invention according to claim 2 is, as shown in FIG. 2, in a tip portion (31a) of a casing (31) of a high-speed flying body (1) flying at high speed. It is premised on a temperature switch which is provided and operates by temperature rise due to aerodynamic heating.

Then, in the tip portion (31a) of the casing (31), a sliding space (3) having an opening on the tip surface side is formed.
2) is formed, and the drive shaft (4) is formed in the sliding space (32).
On the other hand, the tip shape forming member (2) that closes the sliding space (32) is connected to the tip surface of the casing (31).

Further, the tip shape forming member (2) includes
The distal end portion (4b) of the drive shaft (4) is fitted through a support member (35) that reduces a predetermined supporting force capable of supporting the drive shaft (4) at a predetermined temperature.

In addition, the drive shaft (4) has a flange portion (40) for partitioning the sliding space (32) into a front chamber (41) on the front end side and a rear chamber (42) on the rear end side. However, the inner surface (31b) of the casing (31) is slidably connected.

Furthermore, the front room (41) is
The rear chamber (42) is configured to have a higher pressure and a higher pressure.

[0014]

With the above structure, according to the invention of claim 1, when the high-speed flying body (1) flies, the tip shape forming member (2) provided at the tip portion (1a) of the flying body (1) is aerodynamically heated. The temperature rises. Then, heat is transferred from the tip shape forming member (2) to the expansion member (3) filled in the internal volume (2a), and the heat transfer causes the expansion member (3) to reach a predetermined temperature or higher. Begins to thaw. In this case, since the tip portion of the tip shape forming member (2) is heated by aerodynamic heating, heat is transferred to the expansion member (3) from the tip side, and accordingly, the expansion member (3). Of the expansion member (3) filled in the thin tube portion (2b) continuous from the front side to the rear side and continuing to the rear side.
Melts to the tip side of. In this case, the expansion member (3) tries to expand with the melting due to the temperature rise, but since the expansion member (3) of the thin tube portion (2b) is completely melted, While the volume remains the same, the volume expansion is converted into pressure and the internal pressure increases. Then, at the time when the expansion member (3) of the thin tube portion (2b) has melted to the rear end surface, the fixation of the drive shaft (4) is released, and at the same time, the internal pressure of the expansion member (3) causes the drive shaft (4) to move. 4) is pushed backwards, which causes
Switch works. At this time, all the volume expansion in the volume section (2a) is pushed out into the narrow tube section (2b), so that the movement amount of the drive shaft (4) can be effectively increased.
Moreover, the driving force is sufficiently secured.

According to the second aspect of the invention, at the start of flight, the temperature switch has the drive shaft (4) supported by the support member (35), whereby the front chamber (4)
The drive shaft (4) is supported by the tip shape forming member (2) against the load due to the pressure and the large acceleration of 1) and is kept in the state before the switch operation. In actuality, the load due to the acceleration is only due to the mass of the drive shaft (4) since the force exerted by the high pressure atmosphere in the front chamber (41) on the drive shaft (4) can be ignored.

On the other hand, when subjected to aerodynamic heating during high speed flight,
The support member (35) is heated directly or the support member (3
5) It is indirectly heated by heat conduction from around. When the support force of the support member (35) becomes lower than a predetermined support force capable of supporting the drive shaft (4) due to aerodynamic heating, the support of the drive shaft (4) is released. Therefore, the drive shaft (4)
Will be pushed into the casing (31) by the high-pressure atmosphere of the front chamber (41) and switch operation will be performed.

[0017]

Embodiments of the present invention will be described below with reference to the drawings.

FIG. 1 shows a first embodiment of the invention according to claim 1. In this embodiment, the present invention is applied to a training tank shell. In the figure, (1) is a bullet for a training tank shell as a high-speed projectile, and (2) is a hemisphere whose bottom is fixed to the tip (1a) of the bullet (1). It is a warhead as a conical tip shape forming member formed in a shape of a circle. The warhead (2) is made of a non-low melting point metal, and a columnar volume portion (2a) having a predetermined volume is provided near the tip side inside the warhead portion (2a). A thin tubular thin tube portion (2b) is provided, one end of which is open at the rear end surface, extends rearward, and the other end of which is opened at the bottom surface of the warhead (2). An expansion member (3) made of a low melting point alloy that melts and expands at a temperature equal to or higher than a predetermined temperature is filled up to an intermediate portion between the volume portion (2a) and the thin tube portion (2b).

Further, (4) is a drive shaft which is provided inside the bullet (1) so as to extend in the front-rear direction of the bullet (1) and be movable in the front-rear direction. Is formed so as to extend from the tip portion (1a) of the bullet (1) so as to be slidably fitted in the thin tube portion (2b), and the end surface of the end portion (4a). Is the expansion member (3)
The drive shaft (4) is fixed to the rear end face of the vehicle.
In this case, the end surface of the end portion (4a) and the rear end surface of the expansion member (3) may be welded or bonded.

A temperature switch is constituted by the bullet head (2), the expansion member (3) and the drive shaft (4), and executes a predetermined operation provided on the rear side inside the bullet body (1). It functions as a switch that activates a mechanism or control.

Next, the operation of the temperature switch will be described. First, when a training tank shell is fired from the barrel, the bullet (1) starts to fly at high speed. At this time,
Bullet head (2) fixed to the tip (1a) of the bullet (1)
The tip portion of is heated by aerodynamic heating to a high temperature.
Since the warhead (2) is made of a non-low melting point metal, it does not melt immediately and the flight is continued while maintaining the tip shape.

At this time, the above-mentioned high temperature warhead (2)
From the above, heat is conducted to the expansion member (3) made of a low melting point alloy filled in the internal volume (2a), and due to this heat conduction, the expansion member (3) begins to melt when reaching a predetermined temperature or higher. .. In this case, since the tip portion of the warhead (2) is heated by aerodynamic heating, heat conduction to the expansion member (3) is from the tip side, and accordingly,
The melting of the expansion member (3) also starts in order from the front end side to the rear side, and melts toward the front end side of the expansion member (3) filled in the rearward continuous thin tube portion (2b).

At this time, the expansion member (3) tries to expand with melting, but since the expansion member (3) in the thin tube portion (2b) is completely sealed until it melts, the volume is As it is, the volume expansion is converted into pressure, and the internal pressure increases.

Then, when the expansion member (3) in the thin tube portion (2b) has melted to the rear end surface of the expansion member (3), the expansion member (3), which is in a hermetically sealed state and has an increased internal pressure, is attached to the drive shaft (4). The fixation is released and one end is released, and at the same time, the expansion member (3) pushes the drive shaft (4) rearward due to its internal pressure. As a result, a mechanism or control provided on the rear side inside the bullet (1) for executing a predetermined operation is activated to perform a switch operation.

Therefore, in the above embodiment, since the volume expansion due to the temperature rise of the expansion member (3) is utilized as the driving force for driving the drive shaft (4), a spring or the like having a separate driving force is provided. No need. for that reason,
The temperature switch can have a simple structure and a small size, and the miniaturization can stabilize the flight characteristics.

Further, a volume portion (2a) having a predetermined volume
Since the volume expansion of the expansion member (3) is pushed out into the thin tubular portion (2b), the drive shaft (4).
Can be effectively increased and the driving force can be made sufficient. Further, since the rear end surface of the expansion member (3) in the thin tube portion (2b) that fixes the drive shaft (4) is small corresponding to the cross-sectional area of the thin tube portion (2b), There is less variation in the temperature when the fixed portion melts, and the temperature detection accuracy during switch operation can be improved.

FIG. 2 shows a second embodiment of the invention according to claim 2. In this embodiment, instead of the low melting point alloy of the previous embodiment, the drive shaft (4) is driven by the pressure of gas.

Specifically, a sliding space (32) having an opening on the front end side is formed in the front end (31a) of the casing (31) of the bullet (1) as a high-speed projectile.
A drive shaft (4) is arranged in the sliding space (32), and a warhead (2) as a tip shape forming member of a temperature switch for driving the drive shaft (4) is continuously provided on the tip surface. ing.

In this warhead (2), while the main body (34) closes the sliding space (32), the drive shaft (in the axial direction) is formed in the central portion of the rear surface (34a) of the main body (34). The mounting hole (37) of the supporting member (35) of 4) is formed, and the supporting member (35) is fitted in the supporting member mounting hole (37).

The main body (34) is made of a material such as aluminum alloy whose strength is not easily reduced by aerodynamic heating.

The support member (35) has a drive shaft fitting hole (38) in which a female screw is formed. As the supporting member (35), a low melting point alloy is used, and the drive shaft (4) is supported against the load due to the acceleration acting on the drive shaft (4) during flight and the pressure of the front chamber (41) described later. While having a predetermined supporting force that can be supported, it is configured to be lower than the predetermined supporting force at a predetermined temperature.

The drive shaft (4) has a male screw threaded tip portion (4b) in which the drive shaft fitting hole (3) of the support member (35) is inserted.
8) is screwed and supported by the warhead (2), while the rear end (4c) has a flange (40) on the casing (3).
It is slidably connected to the inner surface (31b) of 1). This flange portion (40) allows the front chamber (4
1), a rear chamber (42) is formed on the rear end side.

Further, O is formed on the outer peripheral surface of the flange portion (40).
The ring (43) is buried, and the O-ring (43) is
The front chamber (41) and the rear chamber (42) are configured to hold the pressure in the front chamber (41) in close contact with the inner surface (31b) of the casing (31) so that air cannot flow.

Then, high pressure air is introduced into the front chamber (41) through an air hole (44) formed in the tip portion (31a) of the casing (31), and then closed by a plug (46). To form a high-pressure atmosphere, and the high-pressure atmosphere is maintained at a pressure higher than the pressure in the rear chamber (42).

The high pressure atmosphere in the front chamber (41) is applied to the drive shaft (4) whose tip (4b) is fixed to the warhead (2) and whose flange (40) is slidable. On the other hand, it is configured to act as a driving force for pushing the casing (31). Then, the driving force of the drive shaft (4) is appropriately set by setting the sealing pressure of the front chamber (41).

Further, from the inner surface (31b) side of the casing (31) forming the front chamber (41) to the main body portion (3).
4) A heat insulating material (47) is stretched over the rear surface (34a) side, and the heat insulating material (47) on the rear surface (34a) side reaches the side wall of the drive shaft (4). This heat insulating material (47) suppresses the influence of heat transfer from the casing (31) and the main body (34), so that the pressure in the front chamber (41)
That is, the driving force is kept constant.

Next, the operation of the temperature switch of the high-speed flying object will be described. At the start of flight, in the temperature switch, since the drive shaft (4) is supported by the support member (35), the drive shaft (4) resists the load due to the pressure and acceleration of the front chamber (41). It is supported by (2) and is kept in the state before the switch operation. The load due to acceleration includes the mass of the air in the front chamber (41) and the mass of the drive shaft (4), but the former is extremely small and can be ignored.
Only the latter need be considered.

On the other hand, when subjected to aerodynamic heating during high speed flight,
The support member (35) is heated by heat conduction from the main body (34). When the support force of the drive shaft fitting hole (38) becomes lower than a predetermined support force capable of supporting the drive shaft (4) due to aerodynamic heating, the female screw is broken and the support of the drive shaft (4) is released. For this reason, the drive shaft (4) is
It is pushed into the casing (31) by the high pressure atmosphere of 1), and the switch operation is performed.

Therefore, in the above embodiment, the drive mechanism of the drive shaft (4) is simplified by the front chamber (41). Further, since the driving force can be increased only by changing the pressure condition without changing the volume of the front chamber (41), the space required for the driving mechanism can be reduced. Moreover, since the load acting on the drive shaft (4) at the start of flight is actually only due to the mass of the drive shaft (4), the supporting member (35) can be made small. As a result, it is possible to achieve simplification and miniaturization of the same structure as the invention according to claim 1.

Moreover, by making the supporting member (35) smaller, the supporting force of the supporting member (35) can be promptly and surely reduced in response to aerodynamic heating, and the operating accuracy can be improved. it can.

In the second embodiment, the warhead (2)
The whole may be configured as a support member (35).

The gas sealed in the front chamber (41) of the second embodiment may be other than air.

Further, the air hole (44) of the second embodiment is always opened to introduce a high-speed atmosphere flow into the front chamber (41) to obtain the driving force of the drive shaft (4). May be configured as a pressure introduction hole for The air hole (44) as a pressure introducing hole is preferably formed with an open end to the outside on the tip side of the front chamber (41) so that the atmosphere can easily flow in.

[0044]

As described above, according to the invention of claim 1, during high speed flight, the expansion member (3) provided inside the tip shape forming member (2) melts at a predetermined temperature or higher. In addition, since the drive shaft (4) is expanded and driven by the volume expansion, a spring or the like is not required as a driving force, the structure is simple, and the size can be reduced. It is also possible to stabilize the flight characteristics.

Moreover, since the tip shape forming member (2), the expansion member (3) and the drive shaft (4) constituting the temperature switch can be downsized, the expansion member (3) can be swiftly responded to aerodynamic heating. In addition, it is possible to surely inflate and improve the operation accuracy.

Further, in the narrow tube portion (2b), the expansion member (3)
The portion where the rear end face is fixed to the end of the drive shaft (4) becomes small, and the temperature detection accuracy during switch operation can be improved.

According to the second aspect of the invention, the drive mechanism for the drive shaft (4) is simplified by the front chamber (41). Further, since the driving force can be increased only by changing the pressure condition without changing the volume of the front chamber (41), the space required for the driving mechanism can be reduced. Moreover, since the load acting on the drive shaft (4) at the start of flight is actually only due to the mass of the drive shaft (4), the supporting member (35) can be made small. As a result, the same structure as the invention according to claim 1 can be simplified, the size can be reduced, and the flight characteristics can be stabilized.

Moreover, by making the supporting member (35) smaller, the supporting force of the supporting member (35) can be promptly and surely reduced in response to aerodynamic heating, and the operating accuracy can be improved. ..

[Brief description of drawings]

FIG. 1 is a sectional view showing a temperature switch for a high-speed flying object according to a first embodiment of the present invention.

FIG. 2 is a sectional view showing a temperature switch for a high-speed flying object according to a second embodiment of the present invention.

FIG. 3 is a cross-sectional view showing a conventional temperature switch for a high-speed flying object.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 bullet (high-speed projectile) 2 bullet head (tip shape forming member) 2a volume part 2b thin tube part 3 expansion member 4 drive shaft 4b drive shaft tip 31 casing 31a casing tip 31b casing inner surface 32 sliding space 35 Support Member 40 Flange Part 41 Front Room 42 Rear Room

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Naoshi Goto 1-1, Nishiichitsuya, Settsu-shi, Osaka Daikin Industries, Ltd. Yodogawa Works (72) Inventor Yasuto Takaoka 1-1, Nishiichitsuya, Settsu-shi, Osaka Daikin Yodogawa Manufacturing Co., Ltd.

Claims (2)

[Claims] 1. A temperature switch which is provided at a tip portion (1a) of a high-speed flying body (1) flying at a high speed and which operates by a temperature rise due to aerodynamic heating. 1a), which forms the tip shape of the high-speed projectile (1) and has a volume part (2a) having a predetermined volume inside and a rear end face which is continuous to the rear side of the volume part (2a). Tip shape forming member (2) having a thin tubular portion (2b) extending in parallel
And an expansion member (3) made of a metal or a polymer solid that is filled up to the middle of the volume portion (2a) and the narrow tube portion (2b) of the tip shape forming member (2) and melts and expands at a predetermined temperature or higher. And a drive shaft (4) movably fitted in the thin tube portion (2b) and having an end surface fixedly attached to the rear end surface of the expansion member (3) in the thin tube portion (2b). A temperature switch for high-speed flying vehicles, which is equipped with 2. A temperature switch which is provided at a tip portion (31a) of a casing (31) of a high-speed flying body (1) flying at high speed, and which operates by a temperature rise due to aerodynamic heating. A sliding space (32) having an opening on the distal end surface side is formed in the distal end portion (31a), and a drive shaft (4) is arranged in the sliding space (32), while the casing (31) The sliding space (3
The tip shape forming member (2) that closes 2) is provided in a row, and the tip portion (4b) of the drive shaft (4) is attached to the tip shape forming member (2) at a predetermined temperature. Is fitted through a supporting member (35) having a reduced supporting force, and the drive shaft (4) is provided with the sliding space (32) and a front chamber (41) on the front end side and a rear side. The flange portion (40) which is divided into the rear chamber (42) on the end side is the casing (31).
Is slidably connected to the inner surface (31b) of the rear chamber (41), and the front chamber (41) is configured to have a higher pressure atmosphere than the rear chamber (42). Temperature switch.