JP2000046494A - Jet channel and airframe launcher - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an airframe launcher by providing a jet channel for passing a rapid, high temperature and high pressure jet. SOLUTION: A truncated conical ejector 11 disposed concentrically with a rapid, high temperature and high pressure jet 14 and disposed at its one end at a gap from an upstream side outer peripheral edge of the jet 14 and radially enlarged from the one end side toward the other end side to surround the outer peripheral edge of the jet 14 is provided at a jet channel for passing the jet 14. Thus external cold air is sucked from a gap formed between one end of the ejector 11 and the upstream side outer peripheral edge of the jet 14 by means of an adjoint flow effect of the jet flowing at a high speed at the jet channel, fed into the ejector 11 mixed with the high temperature and high pressure jet, and expanded. Thus, the jet is lowered at its temperature and pressure, thereby reducing an energy of the jet 14.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a high-speed, high-temperature, high-pressure jet flowing through a jet flow path, and more particularly, to effectively deflected the jet direction and discharges the energy of the jet to the outside. A jet flow path that can be reduced and discharged at low speed, low temperature and low pressure, and such a jet flow path is provided inside, and when a flying object contained therein is launched, the jet direction is changed. Deflection by 180 degrees, the abrasion generated in the jet flow path by the jet discharged to the outside,
Alternatively, the present invention relates to a flying object launching device that prevents damage due to melting or the like.

[0002]

2. Description of the Related Art Conventionally, high-speed, high-temperature, high-pressure jets passing through a jet flow path are diffused to effectively reduce the energy of the jets, to reduce the energy of the jets, and to discharge them to the outside. Is being done.

For example, when performing a combustion test on an aircraft engine, a high-speed, high-temperature, high-pressure jet injected from the aircraft engine parked in a test cell is used to reduce the volume of roaring sound generated during the injection, or In order to damage the silencing tower provided to muffle the roar, or the duct provided to introduce the jet injected from the engine into the silencing tower, the energy of the jet is reduced as much as possible, A low jet is introduced into a duct, silenced in a silencing tower, and then discharged to the outside.

Further, in a flying object launching apparatus in which a flying object accommodated inside is launched directly from the accommodation section to the outside, a high speed rocket motor provided at the rear end of the flying object is usually used. Often, the high-temperature and high-pressure jets jetted by the jet cause damage to a launching device or the like that accommodates and transports the flying object inside.

[0005] In order to prevent such damage by the jet of the launching device or the like, it is necessary to reduce the energy of the jet injected from the rocket motor in a short section of the jet flow path.

FIG. 3 is a longitudinal sectional view of a projectile launching tube 10 conventionally mounted on a ship and used to directly launch a projectile housed in a launching device. In the figure, 1 accommodates the flying object 5 inside, facilitates the transfer, and, if necessary, directs the accommodated flying object 5 directly to the outside through an opening provided at the upper end that can be opened and closed. This is a launching device in which a plurality of storage chambers 2 are provided so that they can be fired vertically.

[0007] In the center of the plurality of storage chambers 2, when the projectile 5 is fired, the projectile 5
A high-pressure, high-pressure jet 7 jetted at high speed from a nozzle 9 of a flying object motor 6 provided at the rear end of the projectile 1 is deflected by 180 degrees and discharged from the front end of the launching device 1 to the outside. 4 are provided.

That is, it is mounted on a vehicle or the like and transported,
In a projectile launching device used on the ground, the nozzle 9
A high-temperature and high-pressure jet 7 jetted at high speed from the nozzle 9
Even if you spray toward the ground which is the opening direction of
In addition to causing minor damage to the launching device 1 and the like due to pebbles, sand, and the like that are rolled up when the high-temperature and high-pressure jet 7 collides with the ground, there is a problem that noise problems of an allowable size are generated. On the other hand, in the projectile launching tube 10 which is mounted on a ship as shown in the figure and used on the deck and fires the projectile 5 in the vertical direction, If the high-temperature and high-pressure jet 7 is jetted perpendicularly from the nozzle 9 onto the deck, serious problems such as serious damage to the deck or the equipment mounted on the deck will occur, and the launch personnel Of the high-temperature and high-pressure jet 7 ejected from the nozzle 9 due to the safety problem of the nozzle and the problem of noise exceeding the allowable limit due to the restriction of the diffusion of the noise generated at the time of launch.
By deflecting by 80 degrees and discharging from the distal end of the launching device 1 to an external space above, the occurrence of these problems is avoided.

For this reason, a high-temperature / high-pressure jet 7 jetted from a nozzle 9 at a high speed is provided below a launching device 1 of a projectile launching tube 10 mounted and used on a ship.
To deflect the jet flow direction, a bottom material 3 having a heat-resistant material made of glass fiber or a carbon-based material (not shown) stretched on its surface is provided, and the flying object 5 stored in each storage chamber 2 is provided. A section 8 communicating the opening of the nozzle 9 of the flying object motor 6 with the flue 4 is formed inside the bottom member 3 to form a jet flow path.

The high-temperature / high-pressure jet 7 jetted at a high speed from the nozzle 9 is deflected by 180 degrees in this section 8 and discharged to the outside from the flue 4 having an opening at the upper end of the firing device 1. The high-pressure jet 7 prevents damage on the deck or on-board equipment installed on the deck, and at the same time reduces noise by efficiently dispersing the noise at the time of launch above the launch device 1. To ensure the safety of

However, in such a conventional projectile launching tube 10, the projectile 5
When high-speed high-temperature
Since the high-pressure jet 7 directly collides with the bottom material 3, the bottom material 3 and the heat-resistant material stretched on the surface of the bottom material 3 are burned by the high-temperature and high-pressure jet 7 at this high speed,
In some cases, significant wear 3 'may occur, which not only shortens the life of the bottom material 3 provided on the deck or the like, but also causes a through hole in the bottom material 3 or the like due to the wear 3', so that the high temperature and high pressure jet 7 May flow at high speed to the outside such as on the deck.

As described above, the high-temperature and high-pressure jet 7 flows out of the bottom material 3 through the through-hole in the direction orthogonal to the deck surface. It is predicted that damage will occur, and there will be a problem in the safety of the firing personnel and the like, and there will be a problem that a loud noise exceeding an allowable limit is generated.

[0013] Such a defect occurs not only in the above-mentioned projectile launcher 10 which is conventionally mounted and used on a ship, but also in the above-described aircraft engine combustion test apparatus. In such a test apparatus, a noise is generated, so that a time period for performing the test is restricted, or a noise-suppressing tower or a duct for introducing a jet into the noise-suppressing tower is provided to reduce the noise. The noise-muffling material is greatly worn away, which may cause a serious problem in noise control.

[0014]

SUMMARY OF THE INVENTION The present invention relates to a problem that occurs when a high-speed, high-temperature, high-pressure jet passing therethrough is discharged to the outside, or burns out or occurs due to remarkable wear.
Or, in order to solve the problem of the conventional jet flow path, which causes a problem in terms of safety, noise generation, or the life of the device, the energy of the high-speed, high-temperature, high-pressure jet that passes when discharging to the outside is efficiently used. It is an object of the present invention to provide a jet flow path provided with an energy reducing means capable of reducing the energy and discharging the same to the outside.

The present invention also provides a jet flow path for discharging a high-temperature, high-pressure jet ejected from a flying object at the time of launch to the outside of the launch cylinder in order to solve the above-mentioned disadvantages of the conventional projectile launch cylinder. By using the jet flow path provided with the above-mentioned energy reducing means, the high energy that the high-temperature and high-pressure jet possesses can be efficiently reduced to a low-energy jet and released to the outside. It is an object to provide a launch device.

[0016]

For this reason, the jet flow channel of the present invention is as follows.

(1) Concentric with the shape of the flow of the jet flowing through the jet flow path through which the high-speed, high-temperature, high-pressure jet passes, ie, concentric with the axis of the nozzle that jets the jet. The jet is ejected from the nozzle and is installed in a jet flow path that allows the jet to pass therethrough. One end is arranged with a gap from the upstream outer peripheral edge of the jet, and is arranged from one end to the downstream of the jet. A frusto-conical ejector is provided which has a shape that increases in diameter substantially linearly toward the other end side, surrounds the outer peripheral edge of the jet, and allows the jet to flow inside.

The gap provided between one end of the ejector and the outer peripheral edge on the upstream side of the jet is formed between one end of the ejector and the nozzle skirt in which the jet flows inside and accelerates the jet. Preferably, the size of the gap should be such that the amount of inflow from the outside flowing through the gap from the outside generated by the flow velocity of the jet becomes largest, and the size of the wake effect can be maximized. Is preferred.

Thus, in the jet flow path of the present invention, external cooling air flows through the jet flow path at a high speed from the gap formed between one end of the truncated conical ejector and the outer peripheral edge on the upstream side of the jet. The jet is sucked by the wake effect of the flowing jet, flows into the ejector, mixes with the high-temperature and high-pressure jet, expands, lowers the jet, and lowers the pressure per collision area to reduce the collision energy of the jet. Can be reduced.

The jet flow channel of the present invention employs the following means. (2) On the surface of the jet flow channel at the position where the jet of the jet flow channel configured to pass the high-speed, high-temperature, high-pressure jet flows impinges,
An ablator that melts and sublimates due to the high temperature possessed by the impinging jet, disturbs the flow of the jet, and generates a shock wave is provided.

The ablator is made of a heat-resistant FRP (FRP using glass fiber or carbon fiber and phenolic resin).
iber Reinforced Plastics)
It is preferable to use a material having a substantially conical shape in which the center portion of the jet colliding with the surface of the jet flow path with which the jet collides protrudes from the surface of the jet flow path.

Thus, in the jet flow path of the present invention, the ablator provided on the surface of the jet flow path at the position where the jet collides melts and sublimes due to the high temperature of the jet, and the endothermic of the ablator during melting By reducing the temperature of the jet and lowering the temperature of the jet by the action, and by providing the ablator protruding from the surface of the jet flow path, a shock wave is generated in the high-speed jet immediately before colliding with the ablator, and this shock wave is generated. When the jet flows, the pressure of the jet is reduced, the pressure of the jet is reduced, and the energy of the jet can be reduced.

The flying object launcher of the present invention employs the following means. (3) Generates propulsion of the flying object when the projectile is fired from a projectile launching device that accommodates the projectile inside and launches the projectile directly from the accommodation section In order to discharge the jet injected from the nozzle of the rocket motor to the outside of the launching device, a frustoconical ejector of the above-mentioned means (1) is provided as a jet flow channel provided in the projectile launching device. A jet flow provided with a jet flow path or an ablator that reduces the temperature of the jet by absorbing heat during melting and sublimation by means of the above (2) and generates a shock wave to reduce the pressure of the jet. One or both of the roads are provided.

Thus, in the flying object launching apparatus of the present invention, the rocket motor is injected from the nozzle of
The energy of the high-temperature, high-pressure jet, which is deflected and discharged to the outside, can be reduced and discharged to the outside. What is generated when the flying object is launched by the passage of the high-temperature, high-pressure jet Prevents damage to the projectile launching device due to depletion or melting of the jet flow path, especially damage to the bottom plate that forms a part of the jet flow path, where high-temperature, high-pressure jets collide in an orthogonal state Can prevent the flow of high-temperature, high-pressure jets that may have flowed out onto the deck through the bottom plate, preventing damage to the deck or equipment on the deck, as well as launch personnel. Can be secured, and furthermore, generation of a loud noise exceeding an allowable range can be prevented.

[0025]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a jet flow channel and a projectile launching device according to the present invention will be described below with reference to the drawings. In the drawings showing the embodiments, members that are the same as or similar to those shown in FIG. 3 are given the same reference numerals, and descriptions thereof are omitted as much as possible. FIG. 1 is a view showing a first embodiment of a flying object launching device having a jet flow channel according to the present invention, and FIG. 1 (a) is a cross section showing the lower end and the inside of a bottom member of the launching device shown in FIG. FIG. 1B is a view taken in the direction of arrow A- shown in FIG.
It is a bottom view in A.

As shown in the figure, a flying object 5 which is accommodated in the accommodation room 2 and is directly fired from an opening provided above the accommodation room 2 has a flying object. A motor 6 is provided, and an ejector 11 having an upper end diameter somewhat larger than an outlet diameter of the nozzle 9 is attached to a support 12 outside the nozzle 9 of the flying object motor 6.

As described above, the diameter of the ejector 11 at the upper end is slightly larger than the outlet diameter of the nozzle 9, but the inner diameter is increased toward the lower end, and the other end at the lower end. Is formed in a frusto-conical shape having a size close to the inner diameter of the storage chamber 2 in the firing device 1.

Further, a support 12 for supporting the ejector 11 has a cross-shaped central portion in the axial direction of the ejector 11 having one end fixed to the ejector 11 and the other end connected to the lower end of the storage chamber 2. I try to support. Thus, the ejector 11 and the support 12
When the launching device 1 integrated with the launching device 1 and containing the flying object 5 in the accommodation room 2 is transferred and installed on the bottom member 3 provided on the hull side, at the same time, these ejectors 11 and a support 12 are also attached so that after the projectile 5 is fired, it is removed from the bottom material 3 at the same time as the launching device 1 is removed.

As described above, by installing the frusto-conical ejector 11 around the nozzle 9 of the flying object motor 6, a high-speed, high-temperature, high-pressure jet 7 is opened from the opening of the nozzle 9 when the flying object 5 is fired. Is ejected from the outer peripheral surface of the nozzle 9, that is, the gap formed between the upstream outer peripheral edge of the jet 7 and the upper end opening of the ejector 11, due to the accompanying flow effect of the jet 7. The air in the storage chamber 2 is dragged by the jet and flows into the ejector 11, and the air flowing into the ejector 11 is mixed with the jet 7 to increase the outer diameter of the jet 7. It flows downward and is discharged from the other lower end of the ejector 11.

That is, the pressure is reduced in the ejector 11 by the high-speed flow of the jet 7, and a negative pressure region 13 is generated in the ejector 11. Due to the generation of the negative pressure region 13, when the ejector 11 is not provided and the ejector 11 is not provided, the jet 7 flowing into the section 8 in the shape shown by the dotted line is forcibly expanded and ejected. Spreads along the inner peripheral surface of the ejector 11 and flows toward the lower end side of the ejector 11 while the outer diameter shape increases as shown by the solid line,
It is discharged downward from the lower end of the ejector 11 and flows into the section 8.

As described above, the inside of the jet flow injected from the nozzle 9 opening changes from the conventional jet flow 7 shown by the dotted line to the jet flow 14 shown by the solid line while flowing through the ejector 11, so that the jet 14 is formed. Jet 1 on the floor of the colliding bottom material 3
4, the collision area of the bottom member 3 is reduced, and the jet 7 is locally concentrated as shown in FIG. The increase in the maximum wear depth of the bottom member 3 that has been increased can be reduced. Furthermore, the temperature of the jet 14 can be expected to decrease due to the mixing of air sucked from the gap between the outer peripheral surface of the nozzle 9 and the upper end opening of the ejector 11 by the accompanying effect of the jet 7.

As described above, the flying object launcher 15 of the present embodiment is installed behind the nozzle 9 and
The jet 14 formed by providing the ejector 11 having a truncated cone shape so as to surround the jet 14 injected from the opening
Due to the forced diffusion effect of
It is possible to efficiently reduce the flow rate, and it is possible to prevent a through hole from being formed in the bottom material 3 by the jet 14, and
4 can be completely prevented from leaking onto the deck, preventing damage to the deck or equipment on the deck, ensuring the safety of launch personnel, and generating loud noise that exceeds the allowable range. Can be prevented.

Since the high-temperature and high-speed jet 14 does not directly collide with the ejector 11 and becomes a relatively parallel flow along the inner peripheral surface of the ejector 11, the ejector 11 itself The possibility of loss of the effect due to damage is reduced, and the launching device 1 provided with the ejector 11
Can be used repeatedly.

FIG. 2 is a view showing a second embodiment of a flying object launching device having a jet flow channel according to the present invention.
2A is a cross-sectional view showing the lower end and the inside of the bottom member of the launching device shown in FIG. 3, and FIG. 2B is a view taken along the line BB shown in FIG.
FIG.

As shown in the figure, a flying object motor 6 is provided at the rear end of the flying object 5 which is accommodated in the accommodation room 2 and is directly fired from an opening provided above the accommodation room 2. The high-speed, high-temperature, high-pressure jet 7 jetted from the opening of the nozzle 9 of the flying object motor 6 is perpendicular to the vertical direction, that is, on the bottom surface of the bottom member 3 facing the opening of the nozzle 9, itself. Conical ablator 1 made of ablation material that consumes heat by melting and sublimating
6 are arranged.

The ablator 16 is made of a heat-resistant FRP using glass fiber or carbon fiber and phenolic resin.
(Fiber Reinforced Plastie
s) as a material, so that it does not move due to the collision of the jet 7 and can be replaced when the firing device 1 is replaced, on the bottom surface facing the opening of the nozzle 9 of the bottom material 3. The lateral support 17a, which is formed in a conical shape in which the apex is disposed at the center position of the jet flow 7, and the lateral supports 17a disposed on both sides of the conical ablator 16, the ends of the lateral supports 17a, and the accommodation chamber 2 The U-shaped support 18 composed of a vertical support 17b connecting the lower end portion is fixed to the launching device 1.

As described above, the conical ablator 16 disposed on the bottom member 3 immediately below the nozzle 9 causes the ablator 16 itself to wear due to the melting and sublimation of the ablator 16 due to the collision of the jet 7 as described above. In the jet 7 having a high temperature, the heat quantity (energy) is consumed by the endothermic action due to the melting and sublimation of the ablator 16, the temperature is reduced, and the load on the bottom member 3 is reduced.

Further, by providing the conical ablator 16 on the bottom member 3, a shock wave 19 is generated in the jet 7 colliding with the ablator 16, and the total pressure loss of the jet 7 passing through the shock wave 19 is reduced. At the same time, the jet flow 7 that has passed through the shock wave 19 flows substantially along the cone angle of the ablator 16 and reaches the bottom member 3, and flows as it is parallel to the bottom surface. The pressure of the jet 7 can be reduced by the frictional force, and the load on the bottom member 3 is reduced.

The collision of the jet flow 7 causes the ablator 16
Although itself is worn away, the shape of the shock wave 19 is also deformed, so that a shock wave close to a strong vertical shock wave that causes a larger total pressure loss is formed in the jet 7, and the passage of the shock wave 19 causes a complete shock wave. The pressure is further reduced, and the load on the bottom member 3 can be further reduced.

As described above, in the flying object launching apparatus 20 of the present embodiment, the temperature of the jet 7 jetted from the nozzle 9 provided on the bottom member 3 facing the opening of the nozzle 9 In addition to consuming heat in sublimation and reducing it,
By providing an ablator 16 that generates a shock wave to cause a total pressure loss of the jet 7 and lowers the pressure of the jet 7, the temperature and pressure of the jet 7 colliding with the bottom member 3 are particularly efficiently reduced. And the through-hole 14 is not formed in the bottom material 3 by the jet 14, and the jet 1
4 can be completely prevented from flowing onto the deck,

[0041]

As described above, according to the jet flow path of the present invention, the jet flow is made substantially concentric with the axis of the shape of the jet flowing through the jet flow path through which the jet flows. A shape that is installed in a path, one end of which is arranged with a gap with the upstream outer peripheral edge of the jet, and whose diameter increases substantially linearly from one end to the other end arranged downstream of the jet. A frustoconical ejector is provided to surround the outer peripheral edge of the jet and allow the jet to flow inside.

Thus, in the jet flow path of the present invention, external cooling air flows through the jet flow path at high speed from the gap formed between one end of the frustoconical ejector and the outer peripheral edge on the upstream side of the jet. It is sucked by the wake effect of the flowing jet, flows into the ejector, mixes with the high-temperature, high-pressure jet,
The inside of the ejector expands to lower the temperature and the pressure of the jet, thereby reducing the energy of the jet.

Further, according to the jet flow path of the present invention, the impinging jet is held on the surface of the jet flow path at the position where the jet of the jet flow path adapted to pass the high-speed, high-temperature, high-pressure jet flows. An ablator that melts and sublimes due to the high temperature and generates a shock wave in the flow of the jet is provided.

Thus, in the jet flow channel of the present invention, the ablator provided on the surface of the jet flow channel at the position where the jet collides melts and sublimates due to the high temperature of the jet, and the ablator during melting and sublimation The heat absorption effect of the jet reduces the temperature of the jet to lower the temperature of the jet, and the protruding ablator from the surface of the jet flow path generates a shock wave in the high-speed jet that collides with the ablator. , The pressure of the jet is reduced, the pressure of the jet is reduced, and the energy of the jet can be reduced.

Further, according to the projectile launcher of the present invention, when the projectile launched from the projectile launcher is launched, the jet stream injected from the nozzle of the rocket motor is discharged to the outside of the launcher. Therefore, as the jet flow path provided in the projectile launching device, the jet flow path provided with the above-mentioned frustoconical ejector, or the above-described melting, the temperature of the jet is reduced by the heat absorbing action during sublimation, In addition, at least one of a jet flow path provided with an ablator for generating a shock wave to reduce the pressure of the jet and to make the direction of the jet flow along the bottom surface is provided.

As a result, in the flying object launching apparatus of the present invention, the rocket motor is injected from the nozzle,
The energy of the high-temperature and high-pressure jet, which is deflected and discharged to the outside, can be reduced and discharged to the outside. The projectile launcher can be prevented from being damaged due to wear or melting, and in particular, high-temperature, high-pressure jets that may have penetrated the bottom plate and flowed onto the deck can be reliably prevented. In addition to preventing damage to the equipment on the deck or on the deck, it is also possible to ensure the safety of launch personnel and prevent the generation of loud noises that exceed the allowable range.

[Brief description of the drawings]

FIG. 1 is a view showing a first embodiment of a flying object launching device having a jet flow channel according to the present invention, and FIG. 1 (a) is a cross section showing the lower end and the inside of a bottom member of the launching device shown in FIG. Figure, Figure 1
FIG. 1B is a bottom view taken along the line AA shown in FIG.

FIG. 2 is a view showing a second embodiment of a flying object launching device having a jet flow channel according to the present invention, and FIG. 2 (a) is a cross section showing the lower end and the inside of a bottom member of the launching device shown in FIG. FIG. 2
FIG. 2B is a bottom view taken along the line BB shown in FIG.

FIG. 3 is a longitudinal sectional view of a flying object launching device conventionally mounted and used on a ship.

[Explanation of symbols]

 REFERENCE SIGNS LIST 1 launching device 2 accommodation room 3 bottom material 3 ′ wear of bottom material 4 flue 5 projectile 6 projectile motor 7 jet 7 ′ exhaust 8 section 9 nozzle 10 projectile launcher 11 ejector 12 support 13 negative Pressure area 14 Jet 15 Projectile launcher 16 Ablator 17a Horizontal support 17b Vertical support 18 Support 19 Shock wave 20 Projectile launcher

Claims (3)

[Claims] 1. A jet flow path through which a high-speed, high-temperature, high-pressure jet is passed. The jet flow path is arranged concentrically with a nozzle axis for jetting the jet, and one end is provided with a gap with an upstream outer peripheral edge of the jet. And a frusto-conical ejector having a diameter that expands from one end to the other end and that surrounds an outer peripheral edge of the jet. 2. A jet flow path through which a high-speed, high-temperature, high-pressure jet is passed. The surface of the jet flow path at a position where the jet impinges is melted by the temperature of the jet, and the jet flow is directed upstream. A jet flow path provided with an ablator for generating a shock wave. 3. A flying object is accommodated in the interior,
In a projectile launching device configured to directly launch the projectile from a storage compartment, a jet flow path for discharging the jet jetted from the projectile at the time of launch to the outside of the launching device is claimed. A flying object launching device, wherein at least one of the jet flow path according to claim 1 and the jet flow path according to claim 2 is provided.