JP2012255581A - Flying body - Google Patents

Abstract

PROBLEM TO BE SOLVED: To reduce an infrared ray and an ultraviolet ray emitted from a combustion gas generated during combustion of a propellant object without enlarging a flying body, thereby preventing the flying body from being detected by an infrared detector and an ultraviolet detector.SOLUTION: The flying body includes a combustion chamber, an injection nozzle, and a control mechanism of infrared ray and ultraviolet ray emission. The combustion chamber stores the propellant inside, and burns the propellant. The injection nozzle is connected to the combustion chamber and is provided in the rear part of a body, and jets the combustion gas generated by the combustion of the propellant backward. The control mechanism of infrared ray and ultraviolet ray emission is connected to the combustion chamber or the injection nozzle, and emits an agent or member, that absorbs the infrared ray and the ultraviolet ray emitted by the combustion gas, toward the circumference region of the injection region of the combustion gas to cover the outer periphery of the injection region.

Description

  Embodiments of the present invention relate to a flying object that is difficult to detect by an infrared detector or an ultraviolet detector.

  FIG. 20 is a cross-sectional view of a conventional flying object during flight. As shown in the figure, the flying object is produced by burning the propellant 13 (solid propellant or liquid propellant) stored in the combustion chamber 11 and releasing the generated combustion gas from the injection nozzle 15. Fly by thrust. However, since the combustion gas released backward from the injection nozzle 15 emits infrared rays and ultraviolet rays, the flying object is easily detected by using an infrared detector or an ultraviolet detector.

  In addition, in the prior art related to a method for making it difficult to detect an infrared ray or ultraviolet ray by an infrared detector or an ultraviolet ray detector, before the aircraft discharges the combustion gas, separately mixed low-temperature air and the combustion gas are mixed. A method for suppressing the emission of infrared rays and ultraviolet rays by lowering the temperature of the combustion gas is known.

JP 2008-280967 A Japanese Patent Laying-Open No. 2005-280697

  However, in the above-described conventional technology, a structure for taking in air, a method for suppressing emission of infrared rays and ultraviolet rays by mixing low-temperature air and combustion gas and reducing the temperature of the combustion gas, It is necessary to provide a space for mixing the combustion gas and the combustion gas, and there is a problem that the size becomes large when applied to a flying object.

  Therefore, in view of the above-mentioned problems of the prior art, the present invention suppresses infrared rays and ultraviolet rays emitted from the combustion gas generated during combustion of the propellant without requiring an increase in the size of the flying object, and thereby an infrared detector and ultraviolet ray The object is to provide a flying object that is difficult to detect by a detector.

  A flying object according to an embodiment of the present invention includes a combustion chamber, an injection nozzle, and an infrared / ultraviolet emission suppression mechanism.

  A combustion chamber stores a propellant inside and burns this propellant. The injection nozzle is connected to the combustion chamber and provided in the rear part of the airframe, and injects the combustion gas generated by the combustion of the propellant backward. The infrared / ultraviolet emission suppression mechanism is connected to a combustion chamber or an injection nozzle, and discharges an agent or a member that absorbs infrared and ultraviolet rays emitted by combustion gas toward the outer peripheral region of the injection region of the combustion gas. The outer peripheral part of is covered.

Sectional drawing which shows the example of whole structure of the flying body which concerns on Embodiment 1 of this invention. The bottom view which looked at the flying body shown in FIG. 1 from the injection nozzle side. Sectional drawing at the time of flight of the flying body shown in FIG. Sectional drawing which shows the example of whole structure of the flying body which concerns on Embodiment 2 of this invention. The bottom view which looked at the flying body shown in FIG. 4 from the injection nozzle side. Sectional drawing which shows the example of whole structure of the flying body which concerns on Embodiment 3 of this invention. The bottom view which looked at the flying body shown in FIG. 6 from the injection nozzle side. Sectional drawing at the time of flight of the flying body shown in FIG. Sectional drawing which shows the example of whole structure of the flying body which concerns on Embodiment 4 of this invention. The enlarged view of the injection nozzle outer peripheral part of the flying body shown in FIG. Sectional drawing in the AA 'part of the flying body shown in FIG. Sectional drawing which shows the example of whole structure of the flying body which concerns on Embodiment 5 of this invention. Sectional drawing which shows the example of whole structure of the flying body which concerns on Embodiment 6 of this invention. The bottom view which looked at the flying body shown in FIG. 13 from the injection nozzle side. Sectional drawing which shows the example of whole structure of the flying body which concerns on Embodiment 7 of this invention. The bottom view which looked at the flying body shown in FIG. 15 from the injection nozzle side. Sectional drawing at the time of flight of the flying body shown in FIG. The external view at the time of flight of the flying body shown in FIG. The figure which shows the specific example of the separation mechanism of the heat resistant fiber cloth in the flying body shown in FIG. Sectional drawing at the time of the flight of the conventional flying body.

Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings.
<Embodiment 1>
FIG. 1 is a cross-sectional view showing an example of the overall configuration of a flying object according to Embodiment 1 of the present invention. 2 is a bottom view of the flying object shown in FIG. 1 as viewed from the injection nozzle 15 side. As shown in these drawings, the flying body includes a combustion chamber 11 in the front portion, and a ring-shaped propellant 13 is stored in the combustion chamber 11 via a heat insulating member 12 such as ethylene / propylene rubber. Is a flying object. Further, in the space formed in the central portion of the propellant 13 propellant 13, an ignition device 14 that performs ignition is disposed.

  As the propellant 13, for example, a solid propellant such as HTPB (terminal hydroxyl group polybutadiene) is used in consideration of transportability and filling properties.

  Further, an injection nozzle 15 (propulsion device) connected to the combustion chamber 11 is provided in the rear part of the flying body, and the combustion gas generated by the combustion of the propellant 13 is injected backward. On the inner peripheral surface of the injection nozzle 15, as a mechanism for suppressing the emission of infrared rays and ultraviolet rays (hereinafter referred to as “infrared ray / ultraviolet ray emission suppression mechanism”), an infrared reflector, an infrared absorber, an ultraviolet reflector, and an ultraviolet absorber. A layer of a substance (hereinafter collectively referred to as “infrared / ultraviolet emission inhibitor”) 16 in which an agent is appropriately mixed is fixed. Specific examples of the infrared / ultraviolet emission inhibitor 16 include silicon, an infrared absorbing organic compound, titanium oxide, zinc oxide, and a cerium compound.

  In the present embodiment, the layer of the infrared / ultraviolet emission inhibitor 16 is formed by solidification by applying a high pressure. However, the layer is formed at a predetermined time depending on the combustion gas injection pressure from the combustion chamber 11 side to the injection nozzle 15 side. The strength is adjusted so as to be scattered over. For example, a method of kneading into a binder (rubber) or reinforced plastic is suitable. The relationship between the solidified inhibitor and the surrounding flow velocity at the time of scattering varies depending on the speed of the flying object and the design of the nozzle, so it must be designed individually.

  3 is a cross-sectional view of the flying object shown in FIG. 1 when flying. Here, the state in the case of performing the first stage ignition is shown. When combustion gas is generated by combustion on the combustion chamber 11 side, the combustion gas moves in the direction of arrow S and is released from the injection nozzle 15 to the outside. As a result, a propulsive force in the direction of arrow T is generated in the aircraft. Further, at the time of jetting, the layer of the infrared / ultraviolet emission inhibitor 16 formed along the inner peripheral surface of the jet nozzle 15 is scraped off by the jetting pressure. That is, the combustion gas is discharged toward the outer peripheral region of the injection region, and the outer peripheral portion of the injection region is covered with a layer of inhibitor particles (hereinafter, “reflection / absorption layer”) 17. As a result, infrared rays and ultraviolet rays emitted from the combustion gas are diffused and attenuated inside the reflection / absorption layer 17 that reflects and absorbs infrared rays and ultraviolet rays, and are emitted to the outside of the reflection / absorption layer 17. When done, it becomes attenuated infrared and ultraviolet light.

  As described above, according to the present embodiment, since the infrared / ultraviolet emission suppression mechanism is mounted on the inner peripheral surface of the injection nozzle 15 by simple construction, it is not necessary to increase the size of the flying object, and at the time of combustion of the propellant. Infrared rays and ultraviolet rays emitted from the generated combustion gas can be suppressed, and detection from an external sensor or the like can be made difficult.

  Hereinafter, another embodiment of the invention will be described in detail with reference to FIGS. In addition, since the code | symbol common to the code | symbol attached | subjected to each drawing of the said Embodiment 1 shows the same object, description is abbreviate | omitted and it demonstrates centering on difference.

<Embodiment 2>
FIG. 4 is a cross-sectional view showing an example of the overall configuration of a flying object according to Embodiment 2 of the present invention. FIG. 5 is a bottom view of the flying object shown in FIG. 4 as viewed from the injection nozzle 15 side.

  As shown in these drawings, the flying object according to the present embodiment differs from the flying object of the first embodiment in the formation position of the infrared / ultraviolet emission suppression mechanism, and extends over the outer periphery of the combustion chamber 11 and the injection nozzle 15. Thus, the infrared ray / ultraviolet emission inhibitor 16 is fixed.

  In the case of this embodiment, the layer of the infrared / ultraviolet emission inhibitor 16 scatters backward for a predetermined time due to air resistance during the flight of the aircraft, so that it falls to the touch when touched with a hand like a dirt wall. Is assumed to be solidified. Therefore, basically, a method in which water or an adhesive having a low binding property is used to press and solidify at a high pressure is suitable.

  Thus, according to the present embodiment, as in the first embodiment, the powder of the infrared / ultraviolet emission inhibitor 16 can be scattered on the outer peripheral portion of the injection region of the combustion gas with a simple structure and construction. Become. In addition, since the infrared / ultraviolet suppression mechanism is formed not only on the inner peripheral surface of the injection nozzle 15 but also on the outer peripheral portion of the combustion chamber 11, it is possible to disperse more chemicals than in the first embodiment. There are significant advantages.

<Embodiment 3>
FIG. 6 is a cross-sectional view showing an example of the overall configuration of a flying object according to Embodiment 3 of the present invention. FIG. 7 is a bottom view of the flying object shown in FIG. 6 as viewed from the injection nozzle 15 side.

  As shown in these drawings, in the present embodiment, the infrared / ultraviolet emission suppression mechanism is composed of an infrared / ultraviolet emission inhibitor storage unit 20, a high-pressure gas cylinder 21, a gas pipe 22, and an inhibitor outlet 23. .

  The infrared / ultraviolet emission inhibitor storage unit 20 is a container for storing the powdered infrared / ultraviolet emission inhibitor 16 formed in a ring shape along the outer periphery of the injection nozzle 15.

  The high-pressure gas cylinder 21 is provided by being connected to the infrared / ultraviolet emission inhibitor storage unit 20 by a gas pipe 22, and the infrared / ultraviolet emission inhibitor storage unit 20 is connected to the combustion gas released from the injection nozzle 15. This is a container for storing high-pressure gas that is emitted toward the outside.

  The inhibitor discharge port 23 is connected to the infrared / ultraviolet emission inhibitor storage unit 20 and is provided in a desired number on the outer peripheral portion of the injection port of the injection nozzle 15 to suppress infrared / ultraviolet emission as the high-pressure gas is released. The infrared / ultraviolet emission suppressing agent 16 released from the agent storage unit 20 is released toward the outer peripheral region of the combustion gas injection region.

  FIG. 8 is a cross-sectional view of the flying object shown in FIG. 6 at the time of flight. Here, the state in the case of performing the first stage ignition is shown. When combustion gas is generated by combustion on the combustion chamber 11 side, the combustion gas moves in the direction of arrow S and is released from the injection nozzle 15 to the outside. As a result, a propulsive force in the direction of arrow T is generated in the aircraft. Further, at the time of injection, high-pressure gas is introduced from the high-pressure gas cylinder 21 into the infrared / ultraviolet emission inhibitor storage unit 20 based on a command from a flying body control device (not shown). The powdery infrared / ultraviolet emission inhibitor 16 stored in the infrared / ultraviolet emission inhibitor storage unit 20 is released toward the outer peripheral region of the combustion gas injection region, and covers the outer peripheral portion of the injection region. It becomes a state to do. As a result, infrared rays and ultraviolet rays emitted from the combustion gas are diffused and attenuated inside the reflection / absorption layer 17 that reflects and absorbs infrared rays and ultraviolet rays, and are emitted to the outside of the reflection / absorption layer 17. When this occurs, it becomes attenuated infrared and ultraviolet light.

  As described above, according to this embodiment, the scattering of the infrared / ultraviolet emission inhibitor 16 can be controlled by the introduction timing of the high-pressure gas.

<Embodiment 4>
FIG. 9 is a cross-sectional view showing an example of the overall configuration of a flying object according to Embodiment 4 of the present invention. FIG. 10 is an enlarged view of the outer peripheral portion of the spray nozzle 15 of the flying object shown in FIG. 9, and FIG. 11 is a sectional view of the flying object shown in FIG.

  As shown in these drawings, in the present embodiment, the positions of the infrared / ultraviolet emission inhibitor storage unit 20, the high-pressure gas cylinder 21, the gas pipe 22 and the inhibitor discharge port 23 that constitute the infrared / ultraviolet emission suppression mechanism are as described above. Unlike the third embodiment, the infrared / ultraviolet emission inhibitor storage unit 20 is disposed between the high pressure gas cylinder 21 and the outer peripheral surface (side surface) of the injection nozzle 15, and between the inner wall surface and the outer wall surface of the injection nozzle 15. Is provided with an annular inhibitor channel 18 connected to the infrared / ultraviolet emission inhibitor storage unit 20. In addition, an inhibitor discharge port 23 connected to the inhibitor flow path 18 is formed on the outer peripheral surface of the injection nozzle 15.

  Therefore, according to the present embodiment, when a high-pressure gas (for example, nitrogen gas or argon gas) is injected from the high-pressure gas cylinder 21 toward the infrared / ultraviolet emission inhibitor storage unit 20 filled with the infrared / ultraviolet emission inhibitor 16, It can be discharged not only from the bottom surface of the nozzle 15 but also from the side-side inhibitor discharge port 23. As a result, since the medicine released from the side surface stays in the space formed between the rear outer wall surface of the flying object and the injection nozzle 15, when the infrared / ultraviolet emission inhibitor 16 is released as compared with the third embodiment. There is an effect that the density of the can be made uniform.

<Embodiment 5>
FIG. 12 is a cross-sectional view showing an example of the overall configuration of a flying object according to Embodiment 5 of the present invention. As shown in the figure, the infrared / ultraviolet emission suppression mechanism in the present embodiment is formed in an annular shape along the outer peripheral portion of the injection nozzle 15, and stores the infrared / ultraviolet emission suppression agent 16 that has been processed into powder. In addition to the ultraviolet emission inhibitor storage unit 20 and the inhibitor outlet 23, a combustion pressure guide tube 24 and a piston 25 are provided.

  The combustion pressure guide tube 24 is connected to the infrared / ultraviolet emission inhibitor storage unit 20 and the combustion chamber 11, and is a metal tube that guides the combustion pressure from the combustion chamber 11 toward the infrared / ultraviolet emission inhibitor storage unit 20. It is. The combustion pressure guide tube 24 is filled with a desired filler, and the pressure can be transmitted to the piston 25 by pushing the filler with the combustion pressure.

  The piston 25 is provided on the combustion pressure guide tube 24 side in the infrared / ultraviolet emission inhibitor storage unit 20, and the infrared / ultraviolet light stored in the infrared / ultraviolet emission inhibitor storage unit 20 as the combustion pressure is introduced. It is a member that applies a pressing force in the direction of the inhibitor discharge port 23 to the release inhibitor 16.

  As described above, according to the present embodiment, the combustion pressure induction pipe 24 that is a pressure induction path for the combustion gas different from the injection nozzle 15 is provided in the rear part of the flying body. It is possible to push the powder of the infrared / ultraviolet emission suppression agent 16 from the infrared / ultraviolet emission suppression agent storage 20 provided around the injection nozzle 15 to be scattered backward from the injection nozzle 15.

  Therefore, unlike the third and fourth embodiments, the infrared / ultraviolet emission inhibitor 16 can be released and scattered in accordance with the injection timing without using a high-pressure gas cylinder.

<Embodiment 6>
FIG. 13: is sectional drawing which shows the example of whole structure of the flying body which concerns on Embodiment 6 of this invention. FIG. 14 is a bottom view of the flying object shown in FIG. 13 as viewed from the injection nozzle 15 side.

As shown in these drawings, the infrared / ultraviolet emission suppression mechanism according to the present embodiment includes a push spring 26, a vibration device 27, and an inhibitor release mesh 28 in addition to the infrared / ultraviolet emission suppression agent storage unit 20. It is a configuration. It is assumed that the infrared / ultraviolet emission inhibitor 16 stored in the infrared / ultraviolet emission inhibitor storage unit 20 is solidified by applying a binder (rubber) or high pressure.

  The push spring 26 is provided on the combustion chamber 11 side adjacent to the infrared / ultraviolet emission inhibitor storage unit 20, and injects the infrared / ultraviolet emission inhibitor 16 in the infrared / ultraviolet emission inhibitor storage unit 20 from the injection nozzle 15. It is a spring that is pressed in parallel to the direction toward the inhibitor release mesh 28 side.

  The vibration device 27 is a device that is provided adjacent to the push spring 26 and applies vibration to the push spring 26 at a desired timing based on a command from a flying body control device (not shown).

  The inhibitor release mesh 28 is a file member formed in a mesh shape along the outer peripheral portion of the injection port of the injection nozzle 15 at one end of the infrared / ultraviolet emission suppression storage unit 20. The infrared / ultraviolet emission inhibitor 16 abutted on the basis of the pressing force from the pressing spring 26 is scraped off and released toward the outer peripheral region of the combustion gas injection region.

  As described above, according to the present embodiment, vibration is generated from the vibration device 27 based on a command from the control device (not shown) of the flying object, and the powder of the infrared / ultraviolet emission inhibitor 16 is generated by filing. Because of the configuration, the effect of facilitating the scattering control is achieved compared to the case where it is previously powdered.

<Embodiment 7>
FIG. 15: is sectional drawing which shows the example of whole structure of the flying body which concerns on Embodiment 7 of this invention. 16 is a bottom view of the flying object shown in FIG. 15 as viewed from the injection nozzle 15 side, and FIG. 17 is a cross-sectional view of the flying object shown in FIG. 15 at the time of flight.

As shown in these figures, the infrared / ultraviolet emission suppression mechanism in this embodiment reflects or reflects infrared or ultraviolet rays generated from a flying object using a heat-resistant fiber cloth 29 instead of the infrared / ultraviolet emission inhibitor 16. It absorbs and attenuates, and includes a cross storage portion 30 and a cross unfolding portion 31. As a specific example of the heat resistant fiber cloth 29. Examples include those in which heat-resistant rubber is processed on a sheet of woven reinforcing fibers such as aramid fibers (which can withstand temperatures of 2000 ° C. to 3000 ° C. by spraying or pasting the fibers). .

  The cloth storage unit 30 is a container that is formed in an annular shape along the outer periphery of the injection nozzle 15 and stores the heat-resistant fiber cloth 29. The cloth unfolding section 31 unfolds the heat resistant fiber cloth 29 stored in the cloth storing section 30 by pushing it toward the outer peripheral area of the combustion gas injection region, and the outer periphery of the combustion gas injection area is expanded to the heat resistant fiber cloth. 29. In the present embodiment, a firing tube system is used, and the heat-resistant fiber cloth 29 is folded and stored inside the cloth storage portion 30 that is a firing tube, and the bellows is developed by pushing out the cloth unfolding portion 31 at the time of firing. It is configured as follows. In addition, although it is thought that air resistance becomes large compared with the case where there is no heat-resistant fiber cloth 29, a big influence is suppressed by controlling a flying body according to the characteristic when a cloth is developed.

  FIG. 18 is an external view of the flying object shown in FIG. 15 at the time of flight. As shown in the figure, a desired number of slits 32 are formed in the heat resistant fiber cloth 29, and the internal pressure and the atmospheric pressure of the heat resistant fiber cloth 29 are reduced as the pressure decreases due to the expansion of the combustion gas. It is configured to adjust the pressure difference. This is because the injection nozzle 15 needs to be designed so that the combustion gas is always in the optimum expansion to the underexpansion (the gas pressure at the nozzle outlet is the same as or higher than the atmosphere). In the event of overexpansion (in the worst case, the combustion gas flow is separated from the nozzle inner surface), a shock wave is generated from the nozzle inner surface, or the combustion gas is heat resistant fiber cloth. This is because an indefinite movement is caused inside 29, causing flapping and the like, which adversely affects the movement of the flying object. Therefore, the pressure in the vicinity of the injection port of the injection nozzle 15 is set to atmospheric pressure or higher.

  Further, during combustion, since the pressure is received from the inside by the combustion gas, the heat-resistant fiber cloth 29 swells, but the cloth development part 31 is based on a command from a control device (not shown) according to the combustion end time. It has a function of separating the heat-resistant fiber cloth 29 developed in step 1 from the airframe and does not affect the subsequent flight operation.

  Various methods can be considered as the separation method. For example, as shown in FIG. 19 below, there is a mechanical method in which the flying object is separated by causing the flying object to perform a predetermined motion (for example, a motion such as swinging the neck to the left or right, or rotating the roll). Here, the groove in the airframe is formed, and the groove is sequentially formed by the action of the roll G from the position at the time of launch of the joint of the heat-resistant fiber cloth 29 (FIG. 19A) by the movement of the flying object. It moves (FIGS. 19B and 19C), and the pin of the joint portion of the heat-resistant fiber cloth 29 is finally dropped from the groove by repeating a plurality of movements (FIG. 19D). Has been. In this embodiment, this groove is formed in the cross development part 31.

  Note that other methods may be used as a method of separating the heat resistant fiber cloth 29. For example, as an electrical method, there is a method in which a hook is moved with a solenoid or the like in accordance with a combustion time and separated, or a magnet is applied to a cross joint portion and electromagnetically separated. As for the mechanical method, using the fact that the aircraft decelerates due to air resistance when combustion is completed, it can be separated by a spring that operates by deceleration acceleration, or the cross joint can be forcibly destroyed by an explosion bolt or the like. It is possible to separate them.

  As described above, according to the present embodiment, the heat-resistant fiber cloth 29 is deployed instead of scattering the infrared / ultraviolet emission inhibitor 16, so that it is reliably released from the combustion gas as compared with the above embodiments. The infrared ray and ultraviolet ray are absorbed or reflected and attenuated to produce an effect that makes it difficult to detect the flying object by the infrared ray detector and the ultraviolet ray detector.

  As mentioned above, although several embodiment of this invention was described, these embodiment is shown as an example and is not intending limiting the range of invention. These novel embodiments can be implemented in various other forms, and various omissions, replacements, and changes can be made without departing from the spirit of the invention. These embodiments and modifications thereof are included in the scope and gist of the invention, and are included in the invention described in the claims and the equivalents thereof.

DESCRIPTION OF SYMBOLS 11 ... Combustion chamber 12 ... Thermal insulation member 13 ... Propellant 14 ... Ignition device 15 ... Injection nozzle 16 ... Infrared ray / ultraviolet emission inhibitor 20 ... Infrared ray / ultraviolet emission inhibitor storage part 21 ... High pressure gas cylinder 22 ... Gas pipe 23 ... Inhibitor Release port 24 ... Combustion pressure induction tube 25 ... Piston 26 ... Push spring 27 ... Vibration device 28 ... Inhibitor release mesh 29 ... Heat-resistant fiber cloth 30 ... Cross storage part 31 ... Cross unfolding part 32 ... Slit

Claims (8)

A combustion chamber for storing the propellant inside and burning the propellant;
An injection nozzle that is connected to this combustion chamber and is provided in the rear part of the fuselage, and injects the combustion gas generated by the combustion of the propellant backward,
A chemical agent or member that is provided in connection with the combustion chamber or the injection nozzle and absorbs infrared rays and ultraviolet rays emitted from the combustion gas is discharged toward the outer peripheral region of the injection region of the combustion gas, and the outer peripheral portion of the injection region Infrared / ultraviolet emission suppression mechanism that coats
A flying object characterized by comprising:   The infrared / ultraviolet emission suppression mechanism is an infrared / ultraviolet emission inhibitor that is fixedly formed along the inner peripheral surface of the injection nozzle of the injection nozzle and scatters over a predetermined time by the injection pressure of the combustion gas. The flying object according to claim 1.   The infrared / ultraviolet emission suppression mechanism is an infrared / ultraviolet emission inhibitor that is formed to be fixed to the outer peripheral portion of the combustion chamber or the injection nozzle and scatters over a predetermined time due to air resistance during the flight of the aircraft. The flying object according to claim 1. The infrared / ultraviolet emission suppression mechanism is
An infrared / ultraviolet emission inhibitor storage unit that stores an infrared / ultraviolet emission inhibitor that is formed in a ring shape along the outer periphery of the injection nozzle and that is processed into powder; and
A high-pressure gas cylinder that is connected to the infrared / ultraviolet emission inhibitor storage unit and stores a high-pressure gas that is released toward the infrared / ultraviolet emission inhibitor storage unit;
It is connected to the infrared / ultraviolet emission inhibitor storage part, provided in a desired number on the outer peripheral part of the injection nozzle, and is released from the infrared / ultraviolet emission inhibitor storage part as the high-pressure gas is released. An inhibitor discharge port for releasing the infrared / ultraviolet emission inhibitor toward the outer peripheral region of the injection region of the combustion gas;
The flying object according to claim 1, comprising: The infrared / ultraviolet emission suppression mechanism is
An infrared / ultraviolet emission inhibitor storage unit that stores an infrared / ultraviolet emission inhibitor that is formed in a ring shape along the outer periphery of the injection nozzle and that is processed into powder; and
A combustion pressure induction tube that is connected to the infrared / ultraviolet emission inhibitor storage unit and the combustion chamber, and induces the combustion pressure of the combustion gas toward the infrared / ultraviolet emission inhibitor storage unit;
A piston that is provided on the combustion pressure induction tube side in the infrared / ultraviolet emission inhibitor storage unit and applies pressure to the infrared / ultraviolet emission inhibitor with the introduction of the combustion pressure;
Connected to the infrared / ultraviolet emission suppressing agent storage part, a desired number of outer peripheral parts of the injection nozzle of the injection nozzle are provided, and the infrared rays from the infrared / ultraviolet emission suppression inhibitor storage part are accompanied by pressure from the piston. An inhibitor discharge port for releasing the ultraviolet emission inhibitor toward the outer peripheral region of the combustion gas injection region;
The flying object according to claim 1, comprising: The infrared / ultraviolet emission suppression mechanism is
An infrared / ultraviolet emission inhibitor storage part that is formed annularly along the outer periphery of the injection nozzle and stores an infrared / ultraviolet emission inhibitor,
A pressing spring provided on the combustion chamber side adjacent to the infrared / ultraviolet emission inhibitor storage unit and pressing the infrared / ultraviolet emission inhibitor in the infrared / ultraviolet emission inhibitor storage unit in the injection direction of the injection nozzle; ,
A vibration device that is provided adjacent to the push spring and applies vibration to the push spring at a desired timing;
A file member formed in a mesh shape along the outer periphery of the injection port of the injection nozzle at one end of the infrared / ultraviolet emission inhibitor storage unit, the vibration from the vibration device and the pressing force from the pressing spring Scraping the infrared / ultraviolet emission inhibitor that has been abutted on the basis of, and an inhibitor release mesh that releases toward the outer peripheral region of the injection region of the combustion gas,
The flying object according to claim 1, comprising: A cloth storage part that is formed in an annular shape along the outer periphery of the injection nozzle and stores a heat-resistant fiber cloth,
A cross deploying portion that unfolds the heat-resistant fiber cloth stored in the cloth storing portion toward an outer peripheral region of the injection region of the combustion gas, and covers an outer peripheral portion of the injection region;
The flying object according to claim 1, comprising:   The heat-resistant fiber cloth is formed with a desired number of slits for adjusting the pressure in the vicinity of the injection port of the injection nozzle when the combustion gas is released to a value equal to or higher than the atmospheric pressure. Item 7. A flying object according to item 7.