A stamping type infrared intensifier

Abstract

The present invention discloses a ramjet infrared intensifier, which relates to the field of aviation technology. The ramjet infrared intensifier of the present invention includes an air intake device, a fuel supply device, a combustion chamber, and a control device. Among them, the control device is connected to the air intake device and the fuel supply device, and the air intake device and the fuel supply device are also communicated with the combustion chamber, so that the air intake device can provide combustion-supporting gas for the combustion chamber under the action of the control device, and the fuel supply device can provide liquid fuel and / or gaseous fuel for the combustion chamber under the action of the control device; the control device is also connected to the combustion chamber to control the combustion of the liquid fuel and / or gaseous fuel in the combustion chamber through the control device. The ramjet infrared intensifier of the present invention uses liquid fuel and / or gaseous fuel, so that the combustion speed is controllable and the combustion time is relatively long. When it is used in the head-on and / or tail position of an unmanned aerial vehicle, the working time is long, and it can meet the flight speed range and altitude range required by the unmanned aerial vehicle.

Description

Technical Field

[0001] The present invention relates to the field of aviation technology, and in particular to a ramjet infrared intensifier. Background Art

[0002] As a dynamic simulator that replaces real aircraft, target drones are mainly used to simulate real flight targets, providing dynamic simulation targets with a certain degree of fidelity for evaluating the detection, tracking, and guidance of various air defense weapons. However, except for a few large target drones, the sizes and masses of most target drones are generally smaller than those of real flight targets, and there is a large gap in their infrared characteristics compared with real targets. In order to effectively simulate the infrared radiation characteristics of real flight targets, it is very necessary to carry sufficient infrared enhancement equipment on target drones.

[0003] Since the 1960s, military powers around the world have started investing in research on infrared enhancement equipment. Currently, there are mainly two types of infrared enhancement equipment widely used on target drones. One is the infrared mop, and the other is the infrared wingtip pod. Currently, the infrared enhancement equipment carried on target drones in China generally adjusts its own infrared radiation intensity by burning fuel to enhance the infrared characteristics of the target drone, approaching the characteristics of real simulation targets to accurately evaluate the comprehensive performance of various weapon systems.

[0004] Currently, the commonly used infrared intensifier uses the high-temperature flame generated by internal gunpowder combustion and the metal shell heated by the flame as the infrared enhancement source. The gunpowder combustion is intense but has a short duration. When using the above method of burning fuel for infrared enhancement, the infrared enhancement effect is limited by the combustion radiation characteristics of the fuel, and it is difficult to achieve controllable adjustment. As a result, the working time of the current infrared intensifier for drones in the head-on direction is short, and it cannot meet the flight speed range and altitude range required by drones. Therefore, there is an urgent need to provide a general-purpose infrared intensifier so that target drones can simulate real combat aircraft and be applicable to a larger flight speed range and altitude range. Summary of the Invention

[0005] One of the objectives of the present invention is to propose a ramjet infrared intensifier, which solves the technical problem in the prior art that the infrared intensifier uses gunpowder as fuel, and its combustion duration is short, so that when it is used in the head-on direction, the working time is short and it cannot meet the flight speed range and altitude range required by drones. The many technical effects that can be produced by the preferred technical solution of the present invention are described in detail below.

[0006] To achieve the above objective, the present invention provides the following technical solutions:

[0007] The stamping infrared intensifier of the present invention includes an air intake device, a fuel supply device, a combustion chamber, and a control device. Among them, the control device is connected to the air intake device and the fuel supply device, and the air intake device and the fuel supply device are also communicated with the combustion chamber, so that the air intake device can provide combustion-supporting gas for the combustion chamber under the action of the control device, and the fuel supply device can provide liquid fuel and / or gas fuel for the combustion chamber under the action of the control device; the control device is also connected to the combustion chamber to control the combustion of liquid fuel and / or gas fuel in the combustion chamber through the control device.

[0008] According to a preferred embodiment, the air intake device includes an air intake duct and an air inlet pipe. Among them, the air intake duct is a fixed ram air intake duct, and its outer surface is a conical structure. The air inlet pipe is arranged at the tail of the air intake duct, and the air inlet pipe is communicated with the combustion chamber to provide combustion-supporting gas for the combustion chamber through the air intake duct and the air inlet pipe.

[0009] According to a preferred embodiment, the fuel supply device includes a fuel tank for storing propane fuel, and the fuel tank is communicated with the combustion chamber through a first delivery pipe.

[0010] According to a preferred embodiment, the fuel supply device further includes a second delivery pipe. One end of the second delivery pipe is communicated with the fuel tank of the unmanned aerial vehicle, and the other end is communicated with the fuel tank through a solenoid valve and an oil pump, so that the unmanned aerial vehicle can transport aviation kerosene to the combustion chamber through the second delivery pipe.

[0011] According to a preferred embodiment, the stamping infrared intensifier further includes an ignition device connected to the combustion chamber and the control device, so that the ignition device can ignite under the action of the control device and make the fuel in the combustion chamber burn.

[0012] According to a preferred embodiment, the ignition device includes an ignition box and an ignition nozzle. Among them, the ignition box is connected to the control device; the ignition nozzle is arranged on the combustion chamber, and the ignition nozzle is also connected to the ignition box.

[0013] According to a preferred embodiment, the stamping infrared intensifier further includes a nozzle arranged at the tail of the combustion chamber, and the nozzle is also connected to the control device, so that the nozzle can eject the gas after combustion in the combustion chamber under the action of the control device.

[0014] According to a preferred embodiment, the ramjet infrared intensifier further includes a power supply device, which is a battery or a drone power supply, and the power supply device is connected to the control device to supply power to the control device through the power supply device.

[0015] According to a preferred embodiment, the ramjet infrared intensifier further includes a housing, which is located at the end of the air inlet duct, and the fuel supply device, the combustion chamber, the control device, the ignition device and the nozzle are located inside the housing.

[0016] According to a preferred embodiment, an airspeed tube and at least one mounting seat are provided on the housing. Among them, the airspeed tube is arranged on the upper end face of the housing to detect the flight speed of the drone through the airspeed tube; at least one of the mounting seats is arranged on the lower end face of the housing, and the ramjet infrared intensifier is mounted on the drone through at least one of the mounting seats.

[0017] The ramjet infrared intensifier provided by the present invention has at least the following beneficial technical effects:

[0018] The ramjet infrared intensifier of the present invention includes an air intake device, a fuel supply device, a combustion chamber and a control device. The air intake device can provide combustion-supporting gas for the combustion chamber under the action of the control device, and the fuel supply device can provide liquid fuel and / or gas fuel for the combustion chamber under the action of the control device. The control device is also used to control the combustion of the liquid fuel and / or gas fuel in the combustion chamber. Since the ramjet infrared intensifier of the present invention uses liquid fuel and / or gas fuel, the combustion speed can be controlled, and the combustion time is relatively long. When it is used in the head-on and / or tail-rear of the drone, the working time is long, and it can meet the flight speed range and altitude range required by the drone, solving the technical problem in the prior art that the infrared intensifier uses gunpowder as fuel, and its combustion duration is short, so when it is used head-on, the working time is short and it cannot meet the flight speed range and altitude range required by the drone. Description of the Drawings

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0020] Figure 1 It is a schematic diagram of a preferred embodiment module of the ramjet infrared intensifier of the present invention;

[0021] Figure 2It is a schematic structural diagram of a preferred embodiment of the stamping infrared intensifier of the present invention;

[0022] Figure 3 It is a schematic internal structure diagram of a preferred embodiment of the stamping infrared intensifier of the present invention.

[0023] In the figure: 1, combustion chamber; 2, control device; 3, air inlet duct; 4, intake pipe; 5, fuel tank; 6, first conveying pipeline; 7, second conveying pipeline; 8, solenoid valve; 9, oil pump; 10, ignition box; 11, ignition nozzle; 12, nozzle; 13, battery; 14, housing; 15, pitot tube; 16, mounting seat. Specific embodiments

[0024] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the scope protected by the present invention.

[0025] The following combines the description of the attached Figures 1 to 3 A detailed description of the stamping infrared intensifier of this embodiment will be given.

[0026] The stamping infrared intensifier of this embodiment includes an air intake device, a fuel supply device, a combustion chamber 1 and a control device 2, as Figure 1 shown. Among them, the control device 2 is connected to the air intake device and the fuel supply device, and the air intake device and the fuel supply device are also communicated with the combustion chamber 1, so that the air intake device can provide combustion-supporting gas for the combustion chamber 1 under the action of the control device 2, and the fuel supply device can provide liquid fuel and / or gas fuel for the combustion chamber 1 under the action of the control device 2. The control device 2 is also connected to the combustion chamber 1 to control the combustion of the liquid fuel and / or gas fuel in the combustion chamber 1 through the control device 2. Preferably, the combustion chamber 1 includes a pre-mixing part and a combustion part, wherein the pre-mixing part is used for mixing the combustion-supporting gas with the liquid fuel and / or gas fuel; the combustion part is used for the combustion of the fuel.

[0027] Preferably, the control device 2 includes a combustion control component and an integrated control component. Among them, the combustion control component includes an oncoming flow sensor (including an air temperature sensor and / or a barometric pressure sensor), an exhaust gas temperature sensor, a flow valve, etc., for controlling the combustion of the fuel in the combustion chamber 1. The integrated control component is used for self-checking of the infrared intensifier, normal operation control (including starting, automatically adjusting the air-fuel mixture ratio according to the air flow, shutting down), shutting down and alarming in case of emergency, and exchanging working information through an interface, etc.

[0028] The ramjet infrared intensifier of this embodiment includes an air intake device, a fuel supply device, a combustion chamber 1, and a control device 2. The air intake device can supply combustion-supporting gas to the combustion chamber 1 under the action of the control device 2. The fuel supply device can supply liquid fuel and / or gaseous fuel to the combustion chamber 1 under the action of the control device 2. The control device 2 is further used to control the combustion of the liquid fuel and / or gaseous fuel in the combustion chamber 1. Since the ramjet infrared intensifier of this embodiment uses liquid fuel and / or gaseous fuel, the combustion speed is controllable and the combustion time is relatively long. When it is used at the front or rear of the unmanned aerial vehicle, the working time is long, which can meet the flight speed range and altitude range required by the unmanned aerial vehicle, and solves the technical problem in the prior art that the infrared intensifier uses gunpowder as fuel, and its combustion duration is short, so when it is used at the front, the working time is short and it cannot meet the flight speed range and altitude range required by the unmanned aerial vehicle.

[0029] According to a preferred embodiment, the air intake device includes an air intake duct 3 and an air inlet pipe 4. Among them, the air intake duct 3 is a fixed ram air intake duct, and its outer surface is a conical structure, as Figure 2 shown in FIG. 3. The air inlet pipe 4 is arranged at the tail of the air intake duct 3, and the air inlet pipe 4 is communicated with the combustion chamber 1 to supply combustion-supporting gas to the combustion chamber 1 through the air intake duct 3 and the air inlet pipe 4, as Figure 3 shown. Preferably, the combustion-supporting gas supplied by the air intake device to the combustion chamber 1 is air. The air intake device of the preferred technical solution of this embodiment includes an air intake duct 3 and an air inlet pipe 4. Among them, the air intake duct 3 adopts a fixed and non-adjustable ram air intake duct to supply the required air flow rate and pressure to the combustion chamber 1, and it is applicable to a relatively large flight speed range and altitude range. Preferably, the required air flow rate and pressure of the combustion chamber 1 can be determined based on the fuel flow rate, the required temperature, the altitude range and / or the speed range of the unmanned aerial vehicle flight in the combustion chamber 1.

[0030] According to a preferred embodiment, the fuel supply device includes a fuel tank 5. The fuel tank 5 is used to store propane fuel, and the fuel tank 5 is communicated with the combustion chamber 1 through a first conveying pipeline 6, as Figure 3 shown. Preferably, the fuel tank 5 is in a cylindrical or cylindrical ring structure, and the middle part or the lower end surface of the fuel tank 5 has an arc-shaped groove matching the outer surface of the air inlet pipe 4 to clamp and arrange the fuel tank 5 on the outer surface of the air inlet pipe 4. The fuel tank 5 of the preferred technical solution of this embodiment is clamped and arranged on the outer surface of the air inlet pipe 4, which can not only provide enough space for the fuel tank 5 to store gaseous fuel, but also make the structure of the infrared intensifier compact, will not affect the flight of the unmanned aerial vehicle, and can also ensure the stability of the installation of the fuel tank 5, so that the fuel can burn stably.

[0031] Preferably, the fuel supply device further includes a second delivery pipe 7. One end of the second delivery pipe 7 communicates with the fuel tank of the UAV, and the other end communicates with the fuel tank 5 via a solenoid valve 8 and an oil pump 9, enabling the UAV to supply aviation kerosene to the combustion chamber 1 through the second delivery pipe 7, as Figure 3 shown. More preferably, the oil pump 9 is used to pump the aviation kerosene in the UAV fuel tank into the fuel tank 5, and the solenoid valve 8 is used to control parameters such as the speed and flow rate of the oil pump 9 for pumping aviation kerosene. The solenoid valve 8 and the oil pump 9 are structures in the prior art and will not be elaborated here. Specifically, the aviation kerosene enters the fuel tank 5 through the second delivery pipe 7 and then enters the combustion chamber 1 through the first delivery pipe 6.

[0032] Preferably, the fuel supply device further includes structures such as a pressure regulator, a safety controller (including a safety valve and / or a flame arrester), and a heater. Specifically, structures such as the pressure regulator, the safety controller, and the heater are structures in the prior art and will not be elaborated here. The preferred technical solution of this embodiment can, through the fuel supply device, supply fuel that meets the requirements in terms of flow rate, pressure, temperature, etc. to the combustion chamber 1 based on the requirements for combustion in terms of radiation power and radiation temperature; according to the time of the flight mission, the fuel supply device can also supply oil from the UAV to the fuel tank 5 to ensure the operation of the infrared intensifier.

[0033] The fuel supply device of this embodiment can supply gaseous fuel and liquid fuel to the combustion chamber 1. Preferably, the gaseous fuel is propane and the liquid fuel is aviation kerosene. However, it is not limited thereto, and other gaseous fuels and liquid fuels can also be used. The fuel supply device of the preferred technical solution of this embodiment includes a fuel tank 5, in which a certain amount of propane fuel is pre-stored, which can meet the operation of the infrared intensifier for a period of time. If the flight mission time is relatively long, after the pre-stored propane fuel in the fuel tank 5 is burned out, part of the aviation kerosene in the UAV fuel tank can be provided to the combustion chamber 1 through the second delivery pipe 7 and the oil pump 9 to ensure the normal operation of the infrared intensifier and meet the requirements of the flight mission time.

[0034] According to a preferred embodiment, the ramjet infrared intensifier further includes an ignition device, which is connected to the combustion chamber 1 and the control device 2, enabling the ignition device to ignite under the action of the control device 2 and cause the fuel in the combustion chamber 1 to burn. Preferably, the ignition device includes an ignition box 10 and an ignition nozzle 11. Among them, the ignition box 10 is connected to the control device 2; the ignition nozzle 11 is arranged on the combustion chamber 1 and is also connected to the ignition box 10, as Figure 3 shown. The preferred technical solution of this embodiment can control the ignition time of the ignition device through the control device 2.

[0035] According to a preferred embodiment, the ramjet infrared intensifier further includes a nozzle 12. Preferably, the nozzle 12 is arranged at the tail of the combustion chamber 1, and the nozzle 12 is also connected to the control device 2, so that the nozzle 12 can eject the gas after combustion in the combustion chamber 1 under the action of the control device 2, as Figure 3 shown. The nozzle 12 is a structure in the prior art. Specifically, the nozzle 12 includes a rectifying device, a stabilizing screen, a nozzle, etc. Through the action of the nozzle 12, the gas after combustion in the combustion chamber 1 can be ejected at a certain temperature and speed.

[0036] According to a preferred embodiment, the ramjet infrared intensifier further includes a power supply device. Preferably, the power supply device is a battery 13 or a UAV power supply, and the power supply device is connected to the control device 2 to supply power to the control device 2 through the power supply device, as Figure 3 shown. In the preferred technical solution of this embodiment, the power supply device of the infrared intensifier is the built-in battery 13 of the infrared intensifier or the UAV power supply. Through the action of the power supply device, the components that require electricity of the infrared intensifier can be powered to ensure the normal operation of the infrared intensifier.

[0037] According to a preferred embodiment, the ramjet infrared intensifier further includes a housing 14. Preferably, the housing 14 is located at the end of the air intake duct, and the fuel supply device, the combustion chamber 1, the control device 2, the ignition device and the nozzle 12 are located inside the housing 14, as Figure 2 shown. As Figure 2 and Figure 3 can be seen, the control device 2, the ignition box 10, the solenoid valve 8, the oil pump 9 and the battery 13 are located on both sides of the intake pipe 4. The housing 14 can integrate all parts. Preferably, the housing 14 is provided with spaces for installing other equipment and interfaces for machinery, electricity, information, etc.

[0038] According to a preferred embodiment, an airspeed tube 15 and at least one mounting seat 16 are arranged on the housing 14, as Figure 2 shown. Among them, the airspeed tube 15 is arranged on the upper end face of the housing 14, and the flight speed of the UAV is detected through the airspeed tube 15. At least one mounting seat 16 is arranged on the lower end face of the housing 14, and the ramjet infrared intensifier is mounted on the UAV through at least one mounting seat 16. In the preferred technical solution of this embodiment, the airspeed tube 15 arranged on the housing 14 can detect the flight speed of the UAV. Preferably, the airspeed tube 15 is connected to the control device 2 so that the control device 2 can control the working states of the other components based on the flight speed of the UAV. As Figure 2 shown, two mounting seats 16 are arranged on the lower end face of the housing 14, and the infrared intensifier can be hung on the UAV through the mounting seats 16.

[0039] The infrared intensifier of this embodiment can simulate the far-field infrared point source characteristics of the nozzle of an aviation jet engine, such as wavelength, radiation power, temperature, flame length, etc.; it can be used in the head-on and tail positions of an unmanned aerial vehicle; due to the use of liquid fuel (aviation kerosene) and / or gaseous fuel (propane), it has a long working time and is a general-purpose infrared intensifier applicable to a relatively large flight speed range and altitude range. The infrared intensifier of this embodiment also has the advantages of simple structure, safe, convenient, reliable use, easy maintenance, and can be hung on multiple types of carrier aircraft. The infrared intensifier of this embodiment has the code name "HZ1", and can also be called the HZ1 ramjet infrared intensifier.

[0040] The infrared intensifier of this embodiment can achieve intermittent or continuous operation in the air and work in a programmed control or ground command control mode. It does not generate thrust during the flight of the unmanned aerial vehicle; it can be reused; through the control device 2, functions such as self-checking and safety control can also be achieved, such as automatic alarm and shutdown when the temperature is too high, there is a leak, or the system is working abnormally, or alarm and not allowing startup, etc.; the infrared intensifier of this embodiment can also be equipped with a miss distance indicator, a telemetry engine, a transponder, etc.

[0041] It can be understood that the same or similar parts in this embodiment can be referred to each other, and the content not detailed in some embodiments can be referred to the same or similar content in other embodiments.

[0042] It should be noted that in the description of this application, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. In addition, in the description of this application, unless otherwise specified, the meaning of "a plurality" refers to at least two.

[0043] The "connection" described in this application can be one or more forms of connection such as data connection, communication connection, wired connection, wireless connection, connection through physical connectors, etc. The specific connection method is well-known to those skilled in the technical field to which the embodiments of this application belong.

[0044] Any process or method description shown in the flowchart or described in other ways herein can be understood as representing a module, segment, or part of executable instructions including one or more steps for implementing a specific logical function or process, and the scope of the preferred embodiments of this application includes additional implementations, where the functions can be executed in a manner that is not shown or discussed in sequence, including in a substantially simultaneous manner or in the reverse order according to the functions involved, which should be understood by those skilled in the technical field to which the embodiments of this application belong.

[0045] It should be understood that each part of the present application can be implemented by hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented by software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented by hardware, as in another embodiment, any one or a combination of the following techniques well known in the art can be used: discrete logic circuits with logic gate circuits for implementing logical functions on data signals, application specific integrated circuits with appropriate combinational logic gate circuits, programmable gate arrays (PGAs), field programmable gate arrays (FPGAs), etc. Such as the control device 2 in the present application.

[0046] Those of ordinary skill in the art can understand that all or part of the steps carried by the method of implementing the above embodiments can be completed by instructing relevant hardware through a program. The said program can be stored in a computer-readable storage medium. When the program is executed, it includes one or a combination of the steps of the method embodiments.

[0047] In addition, in each embodiment of the present application, each functional unit can be integrated into a processing module, or each unit can exist physically alone, or two or more units can be integrated into one module. The above integrated module can be implemented in the form of hardware or in the form of a software functional module. When the above integrated module is implemented in the form of a software functional module and sold or used as an independent product, it can also be stored in a computer-readable storage medium.

[0048] The above-mentioned storage medium can be a read-only memory, a magnetic disk, an optical disk, etc.

[0049] In the description of this specification, the descriptions referring to terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0050] The above is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the said claims.

Claims

1. A stamping infrared intensifier, characterized in that, it includes an air intake device, a fuel supply device, a combustion chamber (1) and a control device (2), wherein, the control device (2) is connected to the air intake device and the fuel supply device, and the air intake device and the fuel supply device are also communicated with the combustion chamber (1), so that the air intake device can provide combustion-supporting gas for the combustion chamber (1) under the action of the control device (2), and the fuel supply device can provide liquid fuel and / or gaseous fuel for the combustion chamber (1) under the action of the control device (2); the control device (2) is also connected to the combustion chamber (1) to control the combustion of liquid fuel and / or gaseous fuel in the combustion chamber (1) through the control device (2); the fuel supply device includes a fuel tank (5), the fuel tank (5) is used for storing propane fuel, and the fuel tank (5) is communicated with the combustion chamber (1) through a first delivery pipeline (6); the fuel supply device further includes a second delivery pipeline (7), one end of the second delivery pipeline (7) is communicated with the fuel tank of the unmanned aerial vehicle, and the other end is communicated with the fuel tank (5) through a solenoid valve (8) and an oil pump (9), so that the unmanned aerial vehicle can deliver aviation kerosene to the combustion chamber (1) through the second delivery pipeline (7); the air intake device includes an air intake duct (3) and an air inlet pipe (4), wherein, the air intake duct (3) is a fixed stamping air intake duct, and its outer surface is a conical structure, the air inlet pipe (4) is arranged at the tail of the air intake duct (3), and the air inlet pipe (4) is communicated with the combustion chamber (1) to provide combustion-supporting gas for the combustion chamber (1) through the air intake duct (3) and the air inlet pipe (4); it further includes an ignition device, the ignition device is connected to the combustion chamber (1) and the control device (2), so that the ignition device can ignite under the action of the control device (2) and make the fuel in the combustion chamber (1) burn; the ignition device includes an ignition box (10) and an ignition nozzle (11), wherein, the ignition box (10) is connected to the control device (2); the ignition nozzle (11) is arranged on the combustion chamber (1), and the ignition nozzle (11) is also connected to the ignition box (10); it further includes a housing (14), the housing (14) is located at the end of the air intake duct (3), and the fuel supply device, the combustion chamber (1), the control device (2), the ignition device and a nozzle (12) are located inside the housing (14).

2. The stamping infrared intensifier according to claim 1, characterized in that, it further includes a nozzle (12), the nozzle (12) is arranged at the tail of the combustion chamber (1), and the nozzle (12) is also connected to the control device (2), so that the nozzle (12) can eject the gas after combustion in the combustion chamber (1) under the action of the control device (2).

3. The stamping infrared intensifier according to claim 1, characterized in that, It further includes a power supply device, which is a battery (13) or a drone power supply, and the power supply device is connected to the control device (2) to supply power to the control device (2) through the power supply device.

4. The ramjet infrared intensifier according to claim 1, characterized in that a pitot tube (15) and at least one mounting seat (16) are provided on the housing (14), wherein the pitot tube (15) is arranged on the upper end face of the housing (14), and the flight speed of the drone is detected through the pitot tube (15); at least one of the mounting seats (16) is arranged on the lower end face of the housing (14), and the ramjet infrared intensifier is mounted on the drone through at least one of the mounting seats (16).

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