WO2020107844A1 - 辐射功率可控的红外增强器 - Google Patents

辐射功率可控的红外增强器 Download PDF

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Publication number
WO2020107844A1
WO2020107844A1 PCT/CN2019/089285 CN2019089285W WO2020107844A1 WO 2020107844 A1 WO2020107844 A1 WO 2020107844A1 CN 2019089285 W CN2019089285 W CN 2019089285W WO 2020107844 A1 WO2020107844 A1 WO 2020107844A1
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WO
WIPO (PCT)
Prior art keywords
infrared
heating cone
cone
turbojet engine
radiant power
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PCT/CN2019/089285
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English (en)
French (fr)
Inventor
王磊
陈挺飞
孙丽君
Original Assignee
北京金朋达航空科技有限公司
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Publication date
Priority claimed from CN201811421974.1A external-priority patent/CN109372652B/zh
Priority claimed from CN201821958650.7U external-priority patent/CN209100153U/zh
Application filed by 北京金朋达航空科技有限公司 filed Critical 北京金朋达航空科技有限公司
Priority to EP19890323.9A priority Critical patent/EP3754291A4/en
Publication of WO2020107844A1 publication Critical patent/WO2020107844A1/zh
Priority to ZA2020/06502A priority patent/ZA202006502B/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
    • F41J2/00—Reflecting targets, e.g. radar-reflector targets; Active targets transmitting electromagnetic or acoustic waves
    • F41J2/02—Active targets transmitting infrared radiation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/15—UAVs specially adapted for particular uses or applications for conventional or electronic warfare
    • B64U2101/19—UAVs specially adapted for particular uses or applications for conventional or electronic warfare for use as targets or decoys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to the technical field of unmanned aerial vehicles, in particular to an infrared intensifier with controllable radiant power.
  • the target aircraft is mainly used to simulate real flying targets, and provides a realistic simulation target for evaluating the detection, tracking and guidance of various air defense weapons.
  • the target aircraft are generally smaller in size and quality than real flying targets, and their infrared characteristics are far from the real targets.
  • infrared enhancement equipment Since the 1960s, various military powers in the world have been investigating infrared enhancement equipment. At present, there are two main types of infrared enhancement equipment widely used in target aircraft, one is an infrared mop and the other is an infrared wing tip pod.
  • the infrared enhancement equipment currently installed on the target aircraft in China generally adjusts its infrared radiation intensity by burning fuel to enhance the infrared characteristics of the target aircraft, and is close to the real simulated target characteristics to accurately identify the comprehensive performance of various weapon systems.
  • the existing technology has at least the following technical problems: the currently used infrared intensifier generates a high-temperature flame generated by the internal gunpowder combustion and the metal shell heated by the flame as an infrared enhancement source.
  • the gunpowder burns violently but the duration is short.
  • the way of burning fuel is infrared enhancement.
  • the infrared enhancement effect is limited by the combustion radiation characteristics of the fuel, which is difficult to control and adjust.
  • the purpose of the present invention is to provide an infrared enhancer with controllable radiant power, to solve the technical problem that the radiant power of the infrared enhancer in the prior art is difficult to regulate; the preferred technical solution among the many technical solutions provided by the present invention is The many technical effects that can be produced are described in detail below.
  • the present invention provides the following technical solutions:
  • the infrared enhancer with controllable radiant power provided by the present invention includes:
  • An installation adapter is used to connect the product to be installed, which is provided at one end of the support assembly, and is located on the side where the flame is sprayed from the tail nozzle of the turbojet engine;
  • the heating cone is fixed at one end of the mounting adapter and facing the tail nozzle of the turbojet engine.
  • the outside of the heating cone is coated with infrared enhanced paint, and the inside of the heating cone is provided with a heat insulation device.
  • the heat insulation device includes an asbestos layer, and the asbestos layer is attached to the inner side of the heating cone.
  • the heat insulation device includes a heat shield, the heat shield is fixedly disposed on the mounting adapter and extends into the heating cone, the heat shield is coaxially arranged with the heating cone .
  • the heat shield is a cone, and the height of the cone is smaller than the height of the cone of the heating cone.
  • the heating cone is a conical metal piece.
  • a cylindrical collector hood is fixedly arranged at the tail nozzle of the turbojet engine, and the conical end of the heating cone extends into the collector hood.
  • the support assembly includes a support tube, a support rod and a heat insulation tube, the support tube is disposed at one end of the support rod and opposite to the mounting adapter, and the heat insulation tube is disposed at the support On the side of the rod, the pipeline and cable of the turbojet engine pass through the heat insulation pipe and are connected to the product to be installed.
  • the support cylinder, the turbojet engine and the heating cone are arranged coaxially.
  • the support rod includes three, the support cylinder is a cylindrical straight cylinder, and the three support rods are connected to the side of the cylindrical straight cylinder.
  • a rectifying cover is provided at an internal interface between the oil pipe and the cable of the turbojet engine and the product to be installed.
  • the infrared enhancer with controllable radiation power provided by the present invention has the following beneficial effects:
  • the turbojet engine can be operated in different states such as idle, rated, and cart.
  • the engine speed and the flame temperature of the tail nozzle are different for each state; the flame is heated by the turbojet tail nozzle flame.
  • the flame temperature of the tail nozzle can be adjusted by controlling the operating state of the engine.
  • the flame is heated by the tail nozzle flame of the engine during operation.
  • the heating cone is heated to form a stable infrared radiation source to achieve the purpose of enhancing the infrared characteristics of the target; by regulating the engine Adjust the flame temperature of the tail nozzle to achieve the effect of controlling and adjusting the radiant power.
  • the infrared booster with controllable radiant power provided by the present invention can simulate the characteristics of the infrared point source of an aviation jet engine, can be used head-on, can work for a long time, use aviation kerosene, and is suitable for a larger flight speed domain and altitude domain.
  • FIG. 1 is a front view of the overall structure of an infrared enhancer with controllable radiant power of the present invention
  • Fig. 2 is a side view of an infrared intensifier with controllable radiant power of the present invention.
  • FIG. 1 is a front view of the overall structure of the infrared booster with controllable radiant power of the present invention
  • FIG. 2 is the radiant power of the present invention
  • Side view of a controllable infrared intensifier including: a support assembly, a turbojet engine 4, which is fixed inside the support assembly; a mounting adapter 2 for connecting the product to be installed, which is provided at one end of the support assembly, And it is located on the side of the tail nozzle of the turbojet engine 4 that emits flame; the heating cone 1 is fixed to the end of the mounting adapter 2 and faces the tail nozzle of the turbojet engine 4, and the outer surface of the heating cone 1 is coated There is infrared enhanced paint, and a heat insulation device is provided inside the heating cone 1.
  • the above infrared enhancement mainly enhances the mid-infrared (3 ⁇ 5 ⁇ m) and far infrared (8 ⁇ 14 ⁇ m) two bands.
  • the selected infrared enhancement coating is selected according to this, not limited to a specific infrared enhancement coating, this Those skilled in the art can select according to the radiant energy band of the infrared enhanced coating at high temperature, and adjust it according to actual use requirements, which is not specifically limited here.
  • the installation adapter 2 is the docking part of the entire device and the product. Since the infrared enhancer is generally used in conjunction with other products (such as a target machine, etc.), the adapter is a component that installs the infrared enhancer on other products It can be adjusted according to the different products used without special structure and requirements. If the rear part of the installation adapter 2 is matched with the product structure, it can be connected and fixed on the product structure by means of screws or the like.
  • micro-turbojet engine 4 which can be fixed on the support assembly by an engine clamp.
  • the infrared booster with controllable radiant power provided by the present invention the turbojet engine 4 can be operated in different states such as idle, rated, and cart, and the engine speed and flame temperature of the tail nozzle corresponding to each state are different;
  • the flame of the tail nozzle of the turbojet engine 4 heats the heating cone 1, wherein the flame temperature of the tail nozzle can be adjusted by controlling the operating state of the engine: the flame of the engine nozzle heats the heating cone 1 during operation, and the infrared enhancement outside the heating cone 1
  • the paint is heated to form a stable infrared radiation source to achieve the purpose of enhancing the infrared characteristics of the target; by regulating the operating state of the engine and adjusting the flame temperature of the tail nozzle, the effect of controlling and regulating the radiation power is achieved.
  • Carrying the above-mentioned infrared enhancer on the target aircraft can effectively simulate the infrared radiation characteristics of real flying targets to evaluate the detection, tracking and guidance of various air defense weapons.
  • turbojet engine 4 commonly used in the art is provided with an ECU (engine control unit), which receives control commands and controls the engine to run in different states, such as idle, rated, and cart, and the different states correspond to The radiated power is also different.
  • ECU engine control unit
  • the inside of the heating cone 1 needs to be protected by high temperature to prevent damage to the internal components of the product; in order to protect the internal components of the product, as an optional embodiment, the thermal insulation device includes an asbestos layer, the asbestos layer is attached to the heating cone 1 inside.
  • the heat insulation device further includes a heat shield 5.
  • the heat shield 5 is fixedly installed on the mounting adapter 2 and extends into the heating cone 1,
  • the heat shield 5 is provided coaxially with the heating cone 1 (the broken line indicates that it is provided inside the heating cone 1).
  • the heat shield 5 mainly plays a role of air flow concentration and heat insulation.
  • a preferred solution is that the above-mentioned heat insulation device is used in combination with an asbestos layer and a heat shield 5, the asbestos performs primary heat insulation, and the heat shield 5 in the heating cone 1 performs secondary heat insulation, which can effectively prevent the temperature inside the heating cone 1 from overheating High damage to internal components of the product.
  • the heat shield 5 is a cone, and the height of the cone is smaller than that of the heating cone 1.
  • the heat shield 5 and the heating cone 1 are arranged on the same side of the mounting adapter 2, the heat shield 5 is placed inside the heating cone 1, and the two are the same bottom, which can better isolate the heating cone 1 from the mounting adapter 2 and the high temperature of the target machine to prevent the internal structure from being damaged due to excessive temperature.
  • the heating cone 1 is a conical metal piece.
  • the heating cone 1 is set into a conical shape, which mainly has the following advantages: first, the conical shape is more suitable for the shape of the head of the target machine and other products, and it is adapted to be used head-on on the target machine; second, the turbojet engine 4 The flame at the tail nozzle passes through the tapered end of the heating cone 1 and gradually diffuses to the tapered tail, which can make full use of the flame heat at the tail nozzle and heat more uniformly, preventing the temperature of the tail of the heating cone 1 and the cone head The temperature difference is too large.
  • a cylindrical header 3 is fixedly arranged at the tail nozzle of the turbojet engine 4, and the tapered end of the heating cone 1 extends into the header.
  • the above-mentioned current collecting hood mainly plays the role of air flow concentration and heat insulation; the flame of the tail nozzle of the turbojet engine 4 is ejected through the inside of the current collecting hood to prevent the flame from spreading too much, so that the heat is more concentrated on the heating cone extending into the interior 1 Heat up.
  • the support assembly includes a support cylinder 61, a support rod 62, and a heat insulating tube 63.
  • the support cylinder 61 is disposed at one end of the support rod 62 and is opposite to the mounting adapter 2
  • the heat pipe 63 is disposed on the side of the support rod 62, and the pipeline and cable 7 of the turbojet engine pass through the heat insulation pipe 63 and are connected to the product to be installed.
  • the above heat insulation tube 63 is used to fix and protect the engine pipelines and cables.
  • the two ends of the support rod 62 are respectively fixed by the support cylinder 61 and the mounting adapter 2 to facilitate the turbojet engine 4 to be fixed to the support rod 62 by the engine clamp on.
  • the support tube 61, the turbojet engine 4 and the heating cone 1 are arranged coaxially.
  • the support rod 62 includes three, the support cylinder 61 is a cylindrical straight cylinder, and the three support rods 62 are connected to the sides of the cylindrical straight cylinder. Three supporting rods 62 are connected to the cylindrical straight cylinder to determine the concentricity of the whole part.
  • a rectifying cover is provided at the internal interface of the oil pipe and cable of the turbojet engine 4 and the product to be installed.
  • the above rectifying cover is used to protect the oil pipes and cables, and to rectify the airflow on the fuselage of the product.
  • the invention simulates the characteristics of the infrared point source of an aviation jet engine, uses the flame of the nozzle of the turbojet engine to heat the infrared enhanced coating outside the heating cone, and the heating cone is heated to form a stable infrared radiator to achieve the purpose of enhancing the infrared characteristic of the target;
  • the running state of the engine is used to adjust the flame temperature of the tail nozzle to achieve the effect of adjusting the radiant power.
  • the above-mentioned device is used head-on and can work for a long time. It uses aviation kerosene. It is suitable for larger flight speed and altitude fields. It is a head-on universal infrared power intensifier with controllable radiant power.

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Abstract

一种辐射功率可控的红外增强器，涉及无人飞行器领域，解决了红外增强器的辐射功率难以调控的问题。该红外增强器包括：支撑组件；涡喷发动机（4），其固定于支撑组件的内部；安装转接件（2），用于连接待安装产品，其设置于支撑组件的一端，且其位于涡喷发动机的尾喷管喷出火焰一侧；加热锥（1），其固定于安装转接件的一端并朝向涡喷发动机的尾喷管处，加热锥的外部涂覆有红外增强涂料，加热锥的内部设置有隔热装置。该红外增强器利用涡喷发动机尾喷口火焰对加热锥进行加热，可以通过控制发动机的运行状态大小来调控尾喷口火焰温度，加热锥受热形成稳定的红外辐射源，以增强目标红外特性；可模拟航空喷气发动机红外点源特性，并适用于较大飞行速度域和高度域。

Description

辐射功率可控的红外增强器
本申请要求于2018年11月26日提交中国国家知识产权局、申请号为201811421974.1、发明专利名称为“辐射功率可控的红外增强器”的中国专利申请的优先权，其全部内容通过引用结合在本申请中。
本申请要求于2018年11月26日提交中国国家知识产权局、申请号为201821958650.7、实用新型名称为“辐射功率可控的红外增强器”的中国专利申请的优先权，其全部内容通过引用结合在本申请中。
技术领域
本发明涉及无人飞行器技术领域，尤其是涉及一种辐射功率可控的红外增强器。
背景技术
靶机作为一种替代真实飞行器的动态模拟器，主要用来模拟真实飞行目标，为评估各类防空兵器探测、跟踪与制导提供有一定逼真度的动态仿真目标。但除个别大型靶机外，多数靶机尺寸、质量均普遍小于真实飞行目标，其红外特征与真实目标相比差距较大。为了有效模拟真实飞行目标的红外辐射特征，在靶机上搭载足够的红外增强设备是十分必要的。
世界各军事强国自20世纪60年代开始，均对红外增强设备开始投入研究。目前广泛应用于靶机的红外增强设备主要由两种，一种是红外拖把，另一种是红外翼尖吊舱。国内目前在靶机上搭载的红外增强设备，普遍以通过燃烧燃料来调整自身的红外辐射强度来增强靶机的红外特性，接近真实的模拟目标特性以准确鉴定各类武器系统的综合性能。
本申请人发现现有技术至少存在以下技术问题：目前常用的红外增强器通过内部火药燃烧产生的高温火焰和被火焰加热的金属壳体作为红外增强源，火 药燃烧剧烈但是持续时间短，以上述燃烧燃料的方式进行红外增强，红外增强效果受限于燃料的燃烧辐射特性，很难做到可控可调。
发明内容
本发明的目的在于提供一种辐射功率可控的红外增强器，以解决现有技术中存在的红外增强器的辐射功率难以调控的技术问题；本发明提供的诸多技术方案中的优选技术方案所能产生的诸多技术效果详见下文阐述。
为实现上述目的，本发明提供了以下技术方案：
本发明提供的辐射功率可控的红外增强器，包括：
支撑组件，
涡喷发动机，其固定于所述支撑组件的内部；
安装转接件，用于连接待安装产品，其设置于所述支撑组件的一端，且其位于所述涡喷发动机的尾喷管喷出火焰一侧；
加热锥，其固定于安装转接件的一端并朝向所述涡喷发动机的尾喷管处，所述加热锥的外部涂覆有红外增强涂料，所述加热锥的内部设置有隔热装置。
优选的，所述隔热装置包括石棉层，所述石棉层贴附于所述加热锥的内侧。
优选的，所述隔热装置包括隔热罩，所述隔热罩固定设置于所述安装转接件上并延伸至所述加热锥内部，所述隔热罩与所述加热锥同轴设置。
优选的，所述隔热罩为圆锥体，且其圆锥体的高度小于所述加热锥的锥体高度。
优选的，所述加热锥为圆锥形金属件。
优选的，所述涡喷发动机的尾喷管处固定设置有圆柱形集流罩，所述加热锥的锥形端部延伸至所述集流罩内。
优选的，所述支撑组件包括支筒、支杆和隔热管，所述支筒设置于所述支杆的一端并与所述安装转接件相对，所述隔热管设置于所述支杆的边侧，所述 涡喷发动机的管路及线缆穿过所述隔热管与待安装产品连接。
优选的，所述支筒、所述涡喷发动机和所述加热锥同轴设置。
优选的，所述支杆包括三根，所述支筒为圆柱形直筒，三根所述支杆连接于所述圆柱形直筒的边侧。
优选的，所述涡喷发动机的油管及线缆与待安装产品的内部接口处设置有整流盖。
本发明提供的辐射功率可控的红外增强器，与现有技术相比，具有如下有益效果：
1、涡喷发动机可在慢车、额定、大车等不同的状态下运行，每一个状态对应的发动机转速和尾喷口火焰温度均不相同；利用涡喷发动机尾喷口火焰对加热锥进行加热，其中可以通过控制发动机的运行状态大小来调控尾喷口火焰温度，工作时由发动机尾喷口火焰对加热锥进行加热，加热锥受热形成一个稳定的红外辐射源，达到增强目标红外特性的目的；通过调控发动机的运行状态，调节尾喷口火焰温度，实现控制调节辐射功率的效果。
2、本发明提供的辐射功率可控的红外增强器，可模拟航空喷气发动机红外点源特性、迎头使用、能长时间工作、使用航空煤油、并适用于较大飞行速度域和高度域。
附图说明
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。
图1是本发明辐射功率可控的红外增强器的整体结构主视图；
图2是本发明辐射功率可控的红外增强器的的侧视图。
图中1、加热锥；2、安装转接件；3、圆柱形集流罩；4、涡喷发动机；5、 隔热罩；61、支筒；62、支杆；63、隔热管；7、涡喷发动机的管路及线缆。
具体实施方式
为使本发明的目的、技术方案和优点更加清楚，下面将对本发明的技术方案进行详细的描述。显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动的前提下所得到的所有其它实施方式，都属于本发明所保护的范围。
在本发明的描述中，需要理解的是，术语“中心”、“长度”、“宽度”、“高度”、“上”、“下”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”、“内”、“外”、“侧”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的设备或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。在本发明的描述中，除非另有说明，“多个”的含义是两个或两个以上。
本发明提供了一种辐射功率可控的红外增强器，如图1和图2所示，图1是本发明辐射功率可控的红外增强器的整体结构主视图，图2是本发明辐射功率可控的红外增强器的的侧视图；包括：支撑组件，涡喷发动机4，其固定于支撑组件的内部；安装转接件2，用于连接待安装产品，其设置于支撑组件的一端，且其位于涡喷发动机4的尾喷管喷出火焰一侧；加热锥1，其固定于安装转接件2的一端并朝向涡喷发动机4的尾喷管处，加热锥1的外部涂覆有红外增强涂料，加热锥1的内部设置有隔热装置。
其中，上述红外增强主要增强的是中红外(3～5μm)和远红外(8～14μm)两个波段，所选用的红外增强涂料根据此来选取，不限定为某一特定红外增强涂料，本领域技术人员均可根据红外增强涂料在高温时的辐射能量波段进行选择，并根据实际使用需求进行调整，在此不做具体限定。
其中，上述安装转接件2是整个装置与产品的对接部分，由于红外增强器一般是配合其他产品使用(如靶机等)，转接件是将此红外增强器安装到其他 产品上的部件，可根据所配合使用产品的不同进行调整，无特殊结构与要求。如安装转接件2后部与产品结构相配合，可通过螺钉等方式连接固定在产品结构件上。
为了减轻上述装置的自重、便于安装固定，优选的，选用微型涡喷发动机4，涡喷发动机4可通过发动机卡箍固定在支撑组件上。
本发明提供的辐射功率可控的红外增强器，其涡喷发动机4可在慢车、额定、大车等不同的状态下运行，每一个状态对应的发动机转速和尾喷口火焰温度均不相同；利用涡喷发动机4尾喷口火焰对加热锥1进行加热，其中可以通过控制发动机的运行状态大小来调控尾喷口火焰温度：工作时由发动机喷口火焰对加热锥1进行加热，加热锥1外部的红外增强涂料受热形成一个稳定的红外辐射源，达到增强目标红外特性的目的；通过调控发动机的运行状态，调节尾喷口火焰温度，实现控制调节辐射功率的效果。在靶机上搭载上述红外增强器能够有效模拟真实飞行目标的红外辐射特征，以此来评估各类防空兵器探测、跟踪与制导。
应当理解的是，本领域常用的涡喷发动机4设置有ECU(发动机控制单元)，其接收控制指令，控制发动机在不同状态下运行，如慢车、额定、大车等状态，其不同状态对应的可辐射功率也不相同。
其中，加热锥1的内部需要通过隔热装置防止内部温度过高损坏产品内部元件；为了保护产品的内部元件，作为可选的实施方式，隔热装置包括石棉层，石棉层贴附于加热锥1的内侧。
为了增强隔热效果，作为可选的实施方式，隔热装置还包括隔热罩5，如图1所示，隔热罩5固定设置于安装转接件2上并延伸至加热锥1内部，隔热罩5与加热锥1同轴设置(虚线表示设置于加热锥1内部)。其中，隔热罩5主要起到气流集中、隔热作用。
优选的方案是，上述隔热装置通过石棉层和隔热罩5结合使用，石棉进行一次隔热，加热锥1中的隔热罩5进行二次隔热，能够有效防止加热锥1内部 温度过高损坏产品内部元件。
作为可选的实施方式，如图1，隔热罩5为圆锥体，且其圆锥体的高度小于加热锥1的锥体高度。隔热罩5和加热锥1设置于安装转接件2的同侧，隔热罩5置于加热锥1的内部，且两者同底，能够更好地隔绝加热锥1对安装转接件2及靶机的高温，防止温度过高内部结构受损。
为了使得加热锥1快速升温增强其对红外增强涂料的热传导，作为可选的实施方式，加热锥1为圆锥形金属件。
其中，加热锥1设置成圆锥形，主要有以下优点：其一，圆锥形更加适于靶机等产品的头部形状，与其适配，在靶机上迎头使用；其二，涡喷发动机4的尾喷管处火焰经过加热锥1的锥形端部，逐渐扩散至锥形尾部，能够更加充分的利用尾喷管处的火焰热量，受热更加均匀，防止加热锥1的尾部温度与锥头处温差过大。
作为可选的实施方式，参照图1，涡喷发动机4的尾喷管处固定设置有圆柱形集流罩3，加热锥1的锥形端部延伸至集流罩内。
上述集流罩主要起到气流集中、隔热作用；涡喷发动机4尾喷管的火焰喷射出经过集流罩内部，防止火焰过多扩散，使得热量更加集中地对延伸至其内部的加热锥1进行加热。
作为可选的实施方式，参照图1和图2，支撑组件包括支筒61、支杆62和隔热管63，支筒61设置于支杆62的一端并与安装转接件2相对，隔热管63设置于支杆62的边侧，涡喷发动机的管路及线缆7穿过隔热管63与待安装产品连接。上述隔热管63用来固定、保护发动机管路和线缆，支杆62的两端分别通过支筒61和安装转接件2固定，便于涡喷发动机4通过发动机卡箍固定在支杆62上。
作为可选的实施方式，参照图2，支筒61、涡喷发动机4和加热锥1同轴设置。
为了便于上述装置同轴设置，作为可选的实施方式，参照图1，支杆62包括三根，支筒61为圆柱形直筒，三根支杆62连接于圆柱形直筒的边侧。三根支杆62连接到圆柱形直筒上，用以确定整体部件同心度。
作为可选的实施方式，涡喷发动机4的油管及线缆与待安装产品的内部接口处设置有整流盖。
上述整流盖用来保护油管、线缆，并且对产品上机身气流起整流作用。
本发明模拟航空喷气发动机红外点源特性，利用涡喷发动机喷口火焰对加热锥外部的红外增强涂料进行加热，加热锥受热形成一个稳定的红外辐射体，达到增强目标红外特性的目的；并通过调控发动机的运行状态来调节尾喷口火焰温度，从而达到调节辐射功率的效果。上述装置迎头使用、能长时间工作，其使用航空煤油，适用于较大飞行速度域和高度域，是一种迎头通用型辐射功率可控的红外增强器。
在本说明书的描述，具体特征、结构或者特点可以在任何的一个或多个实施例或示例中以合适的方式结合。
以上所述，仅为本发明的具体实施方式，但本发明的保护范围并不局限于此，任何熟悉本技术领域的技术人员在本发明揭露的技术范围内，可轻易想到变化或替换，都应涵盖在本发明的保护范围之内。因此，本发明的保护范围应以所述权利要求的保护范围为准。

Claims (10)

  1. 一种辐射功率可控的红外增强器，其特征在于，包括：
    支撑组件，
    涡喷发动机，其固定于所述支撑组件的内部；
    安装转接件，用于连接待安装产品，其设置于所述支撑组件的一端，且其位于所述涡喷发动机的尾喷管喷出火焰一侧；
    加热锥，其固定于安装转接件的一端并朝向所述涡喷发动机的尾喷管处，所述加热锥的外部涂覆有红外增强涂料，所述加热锥的内部设置有隔热装置。
  2. 根据权利要求1所述的辐射功率可控的红外增强器，其特征在于，所述隔热装置包括石棉层，所述石棉层贴附于所述加热锥的内侧。
  3. 根据权利要求1或2所述的辐射功率可控的红外增强器，其特征在于，所述隔热装置包括隔热罩，所述隔热罩固定设置于所述安装转接件上并延伸至所述加热锥内部，所述隔热罩与所述加热锥同轴设置。
  4. 根据权利要求3所述的辐射功率可控的红外增强器，其特征在于，所述隔热罩为圆锥体，且其圆锥体的高度小于所述加热锥的锥体高度。
  5. 根据权利要求1所述的辐射功率可控的红外增强器，其特征在于，所述加热锥为圆锥形金属件。
  6. 根据权利要求1所述的辐射功率可控的红外增强器，其特征在于，所述涡喷发动机的尾喷管处固定设置有圆柱形集流罩，所述加热锥的锥形端部延伸至所述集流罩内。
  7. 根据权利要求1所述的辐射功率可控的红外增强器，其特征在于，所述支撑组件包括支筒、支杆和隔热管，所述支筒设置于所述支杆的一端并与所述安装转接件相对，所述隔热管设置于所述支杆的边侧，所述涡喷发动机的管路及线缆穿过所述隔热管与待安装产品连接。
  8. 根据权利要求7所述的辐射功率可控的红外增强器，其特征在于，所述支筒、所述涡喷发动机和所述加热锥同轴设置。
  9. 根据权利要求7或8所述的辐射功率可控的红外增强器，其特征在于，所述支杆包括三根，所述支筒为圆柱形直筒，三根所述支杆连接于所述圆柱形直筒的边侧。
  10. 根据权利要求1所述的辐射功率可控的红外增强器，其特征在于，所述涡喷发动机的油管及线缆与待安装产品的内部接口处设置有整流盖。
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113049257A (zh) * 2021-03-23 2021-06-29 中国空气动力研究与发展中心空天技术研究所 一种出口高度可调的声速喷管

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030197332A1 (en) * 2002-03-09 2003-10-23 Bernt Obkircher Flying device for IR flying target representation
CN201421294Y (zh) * 2008-11-14 2010-03-10 北京航天长征飞行器研究所 一种红外特征增强装置
CN103470376A (zh) * 2013-09-23 2013-12-25 蔡肃民 红外线发生器
CN104266552A (zh) * 2014-08-07 2015-01-07 河北环航科技股份有限公司 空放拖曳式航炮红外激光靶标
CN106438106A (zh) * 2016-05-18 2017-02-22 上海空天微型航空航天发动机有限公司 红外线发生器
CN206387315U (zh) * 2017-01-13 2017-08-08 河北环航科技股份有限公司 一种航空外挂靶标短舱
CN109372652A (zh) * 2018-11-26 2019-02-22 北京金朋达航空科技有限公司 辐射功率可控的红外增强器

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4605232A (en) * 1984-04-24 1986-08-12 Hundstad Richard L Infrared radiation responsive target
US4607849A (en) * 1985-03-07 1986-08-26 Southwest Aerospace Corporation Jet exhaust simulator
US6571714B1 (en) * 2001-12-26 2003-06-03 Meggitt Defense Systems Silicon window infrared augmenter

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030197332A1 (en) * 2002-03-09 2003-10-23 Bernt Obkircher Flying device for IR flying target representation
CN201421294Y (zh) * 2008-11-14 2010-03-10 北京航天长征飞行器研究所 一种红外特征增强装置
CN103470376A (zh) * 2013-09-23 2013-12-25 蔡肃民 红外线发生器
CN104266552A (zh) * 2014-08-07 2015-01-07 河北环航科技股份有限公司 空放拖曳式航炮红外激光靶标
CN106438106A (zh) * 2016-05-18 2017-02-22 上海空天微型航空航天发动机有限公司 红外线发生器
CN206387315U (zh) * 2017-01-13 2017-08-08 河北环航科技股份有限公司 一种航空外挂靶标短舱
CN109372652A (zh) * 2018-11-26 2019-02-22 北京金朋达航空科技有限公司 辐射功率可控的红外增强器

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP3754291A4

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113049257A (zh) * 2021-03-23 2021-06-29 中国空气动力研究与发展中心空天技术研究所 一种出口高度可调的声速喷管

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