CN115507708A - Infrared target simulation plug-in nacelle device - Google Patents
Infrared target simulation plug-in nacelle device Download PDFInfo
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- CN115507708A CN115507708A CN202211451789.3A CN202211451789A CN115507708A CN 115507708 A CN115507708 A CN 115507708A CN 202211451789 A CN202211451789 A CN 202211451789A CN 115507708 A CN115507708 A CN 115507708A
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- battery pack
- infrared
- hung
- heating unit
- fairing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
- F41J9/00—Moving targets, i.e. moving when fired at
- F41J9/08—Airborne targets, e.g. drones, kites, balloons
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- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Radiation Pyrometers (AREA)
Abstract
The application provides an infrared target simulation external hanging nacelle device which comprises an infrared radiation front cabin and a power supply rear cabin, and the infrared target simulation external hanging nacelle device works in a direct-current power supply mode. The pod device is hung at the wing tip position of a high-speed large-sized unmanned aerial vehicle, and has small influence on the flight performance of the unmanned aerial vehicle. The device infrared radiation covers the front hemisphere and the rear hemisphere, the energy is adjustable and stable, the device is not influenced by the external environment, the device can be repeatedly used and is convenient to maintain, small in size and light in weight, and the device is suitable for various different mounting scenes.
Description
Technical Field
The application relates to the technical field of infrared radiation, in particular to an infrared target simulation plug-in nacelle device.
Background
The target drone is an unmanned plane simulating enemy plane and is used for identifying the combat effectiveness of weapon systems such as missiles or airplanes. The drone should have comparable motion characteristics and target display characteristics to the simulated object. In order to simulate the infrared radiation characteristic of the target, an economical, effective and vivid infrared radiation device simulating the target of an airplane or a cruise missile must be installed on the target drone. Various infrared characteristic simulation devices have been developed at home and abroad, and the infrared simulation devices commonly used for various target tests mainly comprise an infrared collimator and an infrared enhancement pod. The infrared enhanced nacelle is provided with a heating hood, and the burning agent heats the stainless steel shell after being burnt and is sprayed out through a reserved hole of the hood. The main advantages of the drag light tube are simple working principle, economical cost, small size, light weight, suitable for target drone installation and stable radiation of the infrared enhancement nacelle.
The infrared characteristic simulation device for the initiating explosive device has the advantages that the infrared characteristic simulation device is obvious in defect, sensitive to use working conditions, used in high-altitude low-air-pressure and high-dynamic environments, unstable combustion of a combustion agent to cause unstable infrared radiation, large difference of ground radiation intensity and aerial radiation intensity, and difficult to evaluate the aerial radiation intensity along with slag falling. And the infrared enhanced pod has the other defects of large volume, limited installation, high requirement on the target drone, great sacrifice of the flight performance of the target drone and limitation of the application range. Both the drag light pipe and the nacelle are initiating explosive devices and are disposable, infrared radiation cannot be adjusted, the requirement on safety is high, and the use and maintenance are complex.
Disclosure of Invention
In order to solve the technical problem, the application aims to provide an infrared target simulation external hanging nacelle device (external hanging nacelle for short). The device is insensitive to the operating mode, and radiation intensity is stable adjustable, used repeatedly, and is safe in utilization to maintain simple and conveniently, small and light in weight do not influence the target drone performance, be applicable to high subsonic speed, big maneuvering type target drone, non-maneuvering type target drone, be applicable to the carry scene of multiple difference. The technical scheme adopted by the application is as follows:
an infrared target simulation external hanging nacelle device comprises a front spherical fairing, an infrared radiator, a heating unit, a temperature sensor, an adapter, a mounting cylinder, a control panel, a battery pack shell, a heat insulation layer, a battery pack, a BMS (battery management system) board, a rear spherical fairing, a transition ring, a central shaft, a front fairing fixing ring and a heating unit mounting seat;
an infrared radiator is arranged in the front spherical fairing, and the front spherical fairing is connected with the adapter through the front fairing fixing ring;
the infrared radiator is cylindrical, a temperature sensor is arranged on the side wall of the infrared radiator, an inverted U-shaped heating unit is arranged inside the infrared radiator, the heating unit is arranged on the heating unit mounting seat positioned at the bottom of the infrared radiator, and the heating unit mounting seat is fixed on the adapter through the central shaft;
the mounting cylinder is connected with the adapter, the mounting cylinder is connected with the battery pack shell through the transition ring arranged inside, and the control panel is fixed at the connection position of the mounting cylinder and the battery pack shell through the transition ring;
the inner side of the battery pack shell is provided with a heat insulation layer, the battery pack shell is connected with the rear spherical fairing through the transition ring arranged in the battery pack shell, the BMS plate is fixed at the inner connection part of the battery pack shell and the rear spherical fairing through the transition ring, and the battery pack is arranged in a cavity of the battery pack shell between the BMS plate and the control plate.
Furthermore, the external hanging nacelle device is designed by a cylindrical rotary body, spherical cowlings are designed axially in the front and at the back, the external hanging nacelle device is hung at the wingtip of the unmanned aerial vehicle and works in a direct-current power supply mode, and a power supply system of the external hanging nacelle device is integrated with a control system and an infrared radiation source.
Furthermore, the externally hung nacelle device is communicated with an unmanned aerial vehicle flight control computer through a control system, the control system finishes starting, stopping and timing of the infrared radiation source according to a control instruction of the flight control computer, controls the temperature of the radiation body in a closed loop mode through a temperature sensor PID, adjusts the infrared radiation intensity, and meanwhile finishes real-time monitoring and protection of a power supply system.
Furthermore, the front spherical fairing is made of a medium-wave infrared transmission window material.
Furthermore, the infrared radiator is made of red copper, the wall thickness of the infrared radiator is 0.2mm, and the infrared radiator is provided with an end face which faces the flying direction.
Furthermore, the heating unit is 3 groups of parallel U-shaped 500W/150V carbon fiber heating tubes.
Furthermore, the control panel comprises an embedded controller, and a temperature detection module, a current detection module, a voltage detection module, a PWM driving module, a communication module and a DC/DC power supply which are respectively connected with the embedded controller, wherein the communication module adopts an RS422 interface.
Further, the temperature sensor is a K-type thermocouple, the maximum measurement temperature is 1024 ℃, the control board collects the temperature of the primary sensor for 100ms, the deviation of the voltage control quantity is solved in real time through a PID algorithm, the PWM driving module is controlled to output voltage, the power of the heating unit is adjusted, the temperature of the infrared radiator is stabilized at a set value of 950 ℃, and the infrared radiation intensity is constant.
Further, the voltage of the battery pack is 150V, the capacity is 2000mAh, and the discharge rate is 10C.
Furthermore, the heat insulation layer is made of an aluminum silicate fiber heat insulation material.
Through the embodiment of the application, the following technical effects can be obtained: the application provides an infrared target simulation nacelle is applicable to high subsonic speed, big motor-driven type and non-motor-driven type slow speed unmanned aerial vehicle and hangs the dress, satisfies fighter, the infrared characteristic simulation of armed helicopter, and is little to unmanned aerial vehicle platform airspeed, mobility ability performance influence. In one embodiment, the sea height is 9km, the speed is 0.82Ma, and the unmanned aerial vehicle can carry out tail positioning maneuvering with the speed not lower than 5 g; the sea height is 5km, the speed is 0.75Ma, the unmanned aerial vehicle can carry out tail placing maneuvering not lower than 7g, and can carry out maneuvering such as barrel rolling, half rolling reversing and the like. The infrared radiation field covers the front and rear semi-spheres, the temperature fluctuation of the infrared radiator is not more than 2%, and the radiation uniformity is not less than 90%.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following descriptions are some embodiments of the present application, and those skilled in the art can obtain other drawings without inventive labor.
FIG. 1 is a schematic diagram of the composition of an external pod device;
FIG. 2 is a schematic sectional view of the external hanging nacelle;
fig. 3 is a schematic diagram of a circuit structure of the control board.
Reference numerals are as follows:
1. the solar battery pack comprises a front spherical fairing, 2 infrared radiators, 3 heating units, 4 temperature sensors, 5 adapter seats, 6 mounting cylinders, 7 control panels, 8 battery pack shells, 9 heat insulation layers, 10 battery packs, 11 BMS boards, 12 rear spherical fairings, 13 transition rings, 14 central shafts, 15 front fairing fixing rings and 16 heating unit mounting seats.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The infrared target simulation external hanging pod (called the external hanging pod for short) can be hung on a high maneuvering target and a non-high maneuvering target according to different target simulation requirements.
Fig. 1 is a schematic diagram of the external hanging nacelle device. The external hanging nacelle device is hung at the wing tip of the unmanned aerial vehicle and works in a direct-current power supply mode, and a power supply system, a control system and an infrared radiation source are integrally designed. The externally hung pod device is communicated with the unmanned aerial vehicle flight control computer through a control system. The control system completes the start, stop and timing of the infrared radiation source according to the control instruction of the flight control computer, controls the temperature of the radiation body in a closed loop mode through the temperature sensor PID, adjusts the infrared radiation intensity, and simultaneously completes the real-time monitoring and protection of the power supply system.
Fig. 2 is a sectional structure schematic diagram of the externally hung nacelle. The external hanging nacelle device is suitable for hanging high subsonic speed, large maneuvering targets and non-maneuvering targets, has small influence on the flying speed and maneuvering capability of an unmanned aerial vehicle platform, and is not limited in use height and speed. The externally-hung pod is used for meeting the infrared characteristic simulation of fighters and armed helicopters, such as targets F-16, apache and the like, the externally-hung pod is symmetrically hung at wing tips on two sides of a hypersonic large maneuvering unmanned aerial vehicle, and meanwhile, the infrared radiation intensity of front and rear semi-spheres is equivalent to that of the simulation target, so that the influence on the flying speed and maneuvering capability performance of an unmanned aerial vehicle platform is small.
The externally hung nacelle is designed by adopting a cylindrical revolution body, and hemispherical cowlings are axially arranged in front and at the back of the externally hung nacelle, so that the aerodynamic appearance requirement of the high-speed aircraft is met. The external hanging nacelle comprises a front spherical fairing, an infrared radiator, a heating unit, a temperature sensor, an adapter, a mounting cylinder, a control panel, a battery pack shell, a heat insulation layer, a battery pack, a BMS (battery management system) board, a rear spherical fairing, a transition ring, a central shaft, a front fairing fixing ring and a heating unit mounting seat;
an infrared radiator 2 is arranged in the front spherical fairing 1, and the front spherical fairing is connected with the adapter 5 through the front fairing fixing ring 15;
the infrared radiator is cylindrical, a temperature sensor 4 is arranged on the side wall of the infrared radiator, an inverted U-shaped heating unit 3 is arranged inside the infrared radiator, the heating unit is mounted on a heating unit mounting seat 16 located at the bottom of the infrared radiator, and the heating unit mounting seat 16 is fixed on the adapter 5 through the central shaft 14;
the mounting cylinder 6 is connected with the adapter, the mounting cylinder 6 is connected with the battery pack shell 8 through the transition ring arranged inside, and the control panel is fixed at the connection position of the connection cylinder and the battery pack shell through the transition ring 13;
the inner side of the battery pack shell is provided with a heat insulation layer 9, the battery pack shell is connected with the rear spherical fairing 12 through the transition ring arranged inside, the BMS board 11 is fixed at the inner connection part of the battery pack shell and the rear spherical fairing through the transition ring 13, and the battery pack is arranged in a cavity of the battery pack shell between the BMS board 11 and the control board.
The front spherical fairing is made of a material with high medium wave infrared transmittance, is high-temperature resistant and is preferably made of sapphire.
The infrared radiator is made of red copper, the wall thickness of the infrared radiator is 0.2mm, and the infrared radiator is provided with an end face which faces to the flight direction.
The heating unit is 3 groups of parallel 500W/150V U-shaped carbon fiber heating tubes.
The control panel comprises an embedded controller, and a temperature detection module, a current detection module, a voltage detection module, a PWM (pulse-width modulation) driving module, a communication module and a DC/DC power supply which are respectively connected with the embedded controller, wherein the communication module adopts an RS422 interface, as shown in figure 3.
The temperature sensor is a K-type thermocouple, the maximum measured temperature is 1024 ℃, the control panel collects the temperature of the primary sensor for 100ms, the deviation of voltage control quantity is solved in real time through a PID algorithm, the PWM driving module is controlled to output voltage, the power of the heating unit is adjusted, the temperature of the infrared radiator is stabilized at a set value of 950 ℃, and the infrared radiation intensity is constant.
The battery pack has the voltage of 150V, the capacity of 2000mAh and the discharge multiplying power of 10C.
And an aluminum silicate fiber heat insulating material with the thickness of 5mm is arranged between the battery pack and the outer shell.
The control panel is used for controlling the work of the infrared radiator and adjusting the work voltage of the infrared radiator.
The BMS board is used for carrying out charge and discharge, thermal runaway and balanced management on the battery pack.
The rear spherical fairing is designed for shape keeping and is made of aluminum alloy materials.
While specific embodiments of the present application have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the present application is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and principles of this application, and these changes and modifications are intended to be included within the scope of this application.
Claims (10)
1. The infrared target simulation externally-hung nacelle device is characterized by comprising a front spherical fairing, an infrared radiator, a heating unit, a temperature sensor, a switching seat, a mounting cylinder, a control panel, a battery pack shell, a heat insulation layer, a battery pack, a BMS (battery management system) board, a rear spherical fairing, a transition ring, a central shaft, a front fairing fixing ring and a heating unit mounting seat;
an infrared radiator is arranged in the front spherical fairing, and the front spherical fairing is connected with the adapter through the front fairing fixing ring;
the infrared radiator is cylindrical, a temperature sensor is arranged on the side wall of the infrared radiator, an inverted U-shaped heating unit is arranged inside the infrared radiator, the heating unit is arranged on the heating unit mounting seat positioned at the bottom of the infrared radiator, and the heating unit mounting seat is fixed on the adapter through the central shaft;
the mounting cylinder is connected with the adapter, the mounting cylinder is connected with the battery pack shell through the transition ring arranged inside, and the control panel is fixed at the connection position of the mounting cylinder and the battery pack shell through the transition ring;
the inner side of the battery pack shell is provided with a heat insulation layer, the battery pack shell is connected with the rear spherical fairing through the transition ring arranged in the battery pack shell, the BMS board is fixed at the inner connection part of the battery pack shell and the rear spherical fairing through the transition ring, and the battery pack is arranged in a cavity of the battery pack shell between the BMS board and the control board.
2. The externally-hung nacelle device according to claim 1, wherein the externally-hung nacelle device is designed by a cylindrical rotating body, spherical fairings are designed in the axial direction in the front and back directions, the externally-hung nacelle device is mounted at the wing tips of the unmanned aerial vehicle and works in a direct-current power supply mode, and a power supply system of the externally-hung nacelle device is integrated with a control system and an infrared radiation source.
3. The externally-hung nacelle device according to claim 1 or 2, wherein the externally-hung nacelle device is in communication with an unmanned aerial vehicle flight control computer through a control system, the control system completes start-stop and timing of an infrared radiation source according to a control instruction of the flight control computer, adjusts infrared radiation intensity through closed-loop control of a temperature sensor PID (proportion integration differentiation) on a radiator temperature, and simultaneously completes real-time monitoring and protection of a power supply system.
4. The external hanging pod device of claim 3 wherein the front spherical fairing is a medium wave infrared transparent window material.
5. The device of claim 3, wherein the infrared radiator is copper with a wall thickness of 0.2mm and has an end surface mounted in the direction of flight.
6. The pendant pod device of claim 3 wherein said heating units are 3 sets of parallel U-shaped 500W/150V carbon fiber heating tubes.
7. The hanging pod device as claimed in claim 3, wherein the control board comprises an embedded controller and a temperature detection module, a current detection module, a voltage detection module, a PWM driving module, a communication module, and a DC/DC power supply connected to the embedded controller respectively, wherein the communication module employs an RS422 interface.
8. The external hanging nacelle device according to claim 3, wherein the temperature sensor is a K-type thermocouple, the maximum measured temperature is 1024 ℃, the control board collects the temperature of the sensor once in 100ms, the deviation of the voltage control quantity is solved in real time through a PID algorithm, the PWM driving module is controlled to output voltage, the power of the heating unit is adjusted, the temperature of the infrared radiator is stabilized at a set value of 950 ℃, and the infrared radiation intensity is constant.
9. The hanging pod device of claim 3 wherein the battery pack has a voltage of 150V, a capacity of 2000mAh, and a discharge rate of 10C.
10. The pendant pod device of claim 9 wherein said insulation layer is an aluminum silicate fiber insulation material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211451789.3A CN115507708B (en) | 2022-11-21 | 2022-11-21 | Infrared target simulation plug-in nacelle device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211451789.3A CN115507708B (en) | 2022-11-21 | 2022-11-21 | Infrared target simulation plug-in nacelle device |
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| CN115507708A true CN115507708A (en) | 2022-12-23 |
| CN115507708B CN115507708B (en) | 2023-01-31 |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5102145A (en) * | 1991-04-16 | 1992-04-07 | Teledyne Industries, Inc. | Aerial gunnery target system |
| JPH05133697A (en) * | 1991-11-08 | 1993-05-28 | Nec Corp | Temperature sensitive towed body |
| EP0911601A2 (en) * | 1997-10-22 | 1999-04-28 | Global Target Systems Limited | Aerial target system |
| US20070234922A1 (en) * | 2006-04-11 | 2007-10-11 | Van Laar Kurt D | Countermeasures radiation source for missile decoys |
| US20170341749A1 (en) * | 2014-12-15 | 2017-11-30 | Alfred-Wegener-Institut | Aerodynamically shaped, active towed body |
| RU2651457C1 (en) * | 2017-04-27 | 2018-04-19 | Открытое акционерное общество "Завод им. В.А. Дегтярева" | Air target simulator |
| CN109372652A (en) * | 2018-11-26 | 2019-02-22 | 北京金朋达航空科技有限公司 | The controllable Infrared Intensifier of radiant power |
| CN110989728A (en) * | 2019-10-12 | 2020-04-10 | 北京安达维尔航空设备有限公司 | Method for simulating infrared characteristics and target drone |
-
2022
- 2022-11-21 CN CN202211451789.3A patent/CN115507708B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5102145A (en) * | 1991-04-16 | 1992-04-07 | Teledyne Industries, Inc. | Aerial gunnery target system |
| JPH05133697A (en) * | 1991-11-08 | 1993-05-28 | Nec Corp | Temperature sensitive towed body |
| EP0911601A2 (en) * | 1997-10-22 | 1999-04-28 | Global Target Systems Limited | Aerial target system |
| US20070234922A1 (en) * | 2006-04-11 | 2007-10-11 | Van Laar Kurt D | Countermeasures radiation source for missile decoys |
| US20170341749A1 (en) * | 2014-12-15 | 2017-11-30 | Alfred-Wegener-Institut | Aerodynamically shaped, active towed body |
| RU2651457C1 (en) * | 2017-04-27 | 2018-04-19 | Открытое акционерное общество "Завод им. В.А. Дегтярева" | Air target simulator |
| CN109372652A (en) * | 2018-11-26 | 2019-02-22 | 北京金朋达航空科技有限公司 | The controllable Infrared Intensifier of radiant power |
| CN110989728A (en) * | 2019-10-12 | 2020-04-10 | 北京安达维尔航空设备有限公司 | Method for simulating infrared characteristics and target drone |
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| CN115507708B (en) | 2023-01-31 |
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