CN115507708B - An infrared target simulation external pod device - Google Patents
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- CN115507708B CN115507708BCN202211451789.3ACN202211451789ACN115507708BCN 115507708 BCN115507708 BCN 115507708BCN 202211451789 ACN202211451789 ACN 202211451789ACN 115507708 BCN115507708 BCN 115507708B
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Abstract
Description
Translated fromChinese技术领域technical field
本申请涉及红外辐射技术领域，具体涉及一种红外目标模拟外挂吊舱装置。The present application relates to the technical field of infrared radiation, in particular to an infrared target simulation external pod device.
背景技术Background technique
靶机是一种模拟敌机的无人驾驶飞机，用于鉴定导弹或飞机等武器系统的作战效能。靶机应具有模拟对象相当的运动特性和目标显示特性。为了模拟目标的红外辐射特性，必须在靶机上安装经济、有效、逼真的模拟飞机或巡航导弹目标红外辐射装置。国内外已发展了多种红外特性模拟装置，常用于各种靶试的红外模拟装置主要有红外曳光管和红外增强吊舱，其原理均是采用固体燃料作为燃烧剂，通过点火器点燃固体燃料进行端面燃烧，曳光管燃烧剂燃烧后直接喷入空气中，产生强烈的红外辐射。红外增强吊舱设计有加热头罩，燃烧剂燃烧后加热不锈钢壳体并通过头罩的预留孔进行喷出。曳光管主要优点是工作原理简单、成本经济，尺寸小巧、重量轻，很适合靶机安装，红外增强吊舱主要优点辐射较稳定。A target drone is an unmanned aircraft that simulates an enemy aircraft and is used to identify the combat effectiveness of weapon systems such as missiles or aircraft. The target drone should have the equivalent movement characteristics and target display characteristics of the simulated object. In order to simulate the infrared radiation characteristics of the target, an economical, effective and realistic simulated aircraft or cruise missile target infrared radiation device must be installed on the target aircraft. A variety of infrared characteristic simulation devices have been developed at home and abroad. The infrared simulation devices commonly used in various target tests mainly include infrared tracer tubes and infrared enhanced pods. The fuel is burnt at the end face, and the tracer tube combustion agent is directly sprayed into the air after burning, producing strong infrared radiation. The infrared enhanced pod is designed with a heating hood. After burning, the combustion agent heats the stainless steel shell and sprays it out through the reserved hole of the hood. The main advantages of the tracer tube are simple working principle, low cost, small size and light weight, which is very suitable for target drone installation. The main advantage of the infrared enhanced pod is that the radiation is relatively stable.
火工品类红外特性模拟装置缺点明显，首先对使用工况敏感，在高空低气压、高动态环境下使用，燃烧剂燃烧不稳定，导致红外辐射不稳定，地面与空中辐射强度差异性较大，伴随着掉渣，很难评估空中辐射强度。其次红外增强吊舱另一缺点是体积大，安装受限，对靶机要求很高，极大的牺牲了靶机飞行性能，限制了使用范围。不管是曳光管还是吊舱均为火工品，一次性使用，红外辐射不能调整，对安全性要求高，使用维护复杂。The shortcomings of pyrotechnic infrared characteristic simulators are obvious. First of all, they are sensitive to the working conditions. When used in high-altitude, low-pressure, and high-dynamic environments, the combustion of the combustion agent is unstable, resulting in unstable infrared radiation. There is a large difference in radiation intensity between the ground and the air. With slag falling, it is difficult to assess the radiation intensity in the air. Secondly, another disadvantage of the infrared enhanced pod is that it is large in size, limited in installation, and has high requirements on the target aircraft, which greatly sacrifices the flight performance of the target aircraft and limits the scope of use. Both the tracer tube and the pod are pyrotechnics, which are disposable, and the infrared radiation cannot be adjusted. They have high safety requirements and are complicated to use and maintain.
发明内容Contents of the invention
为了解决上述技术问题，本申请旨在提供一种红外目标模拟外挂吊舱装置（简称外挂吊舱）。该装置对使用工况不敏感，辐射强度稳定可调整，重复使用，使用安全，并且维护简单方便，体积小及重量轻，不影响靶机性能，适用于高亚音速、大机动类靶机，非机动类靶机，适用多种不同的挂载场景。本申请所采用的技术方案如下：In order to solve the above technical problems, the present application aims to provide an infrared target simulation external pod device (abbreviated as external pod). The device is not sensitive to working conditions, the radiation intensity is stable and adjustable, it can be used repeatedly, it is safe to use, and it is simple and convenient to maintain, small in size and light in weight, and does not affect the performance of the target machine. It is suitable for high subsonic speed and large maneuvering target machines. Non-motorized target drones are suitable for many different mounting scenarios. The technical scheme adopted in this application is as follows:
一种红外目标模拟外挂吊舱装置，外挂吊舱包括前球形整流罩、红外辐射体、加热单元、温度传感器、转接座、安装筒、控制板、电池组外壳、隔热层、电池组、BMS板、后球形整流罩、过渡环、中心轴、前整流罩固定环、加热单元安装座；An infrared target simulation external pod device, the external pod includes a front spherical fairing, an infrared radiator, a heating unit, a temperature sensor, an adapter seat, a mounting cylinder, a control panel, a battery pack shell, a heat insulation layer, a battery pack, BMS board, rear spherical fairing, transition ring, central shaft, front fairing fixing ring, heating unit mounting seat;
所述前球形整流罩内设置红外辐射体，所述前球形整流罩通过所述前整流罩固定环与所述转接座相连接；An infrared radiator is arranged in the front spherical fairing, and the front spherical fairing is connected to the adapter seat through the front fairing fixing ring;
所述红外辐射体为筒形，其侧壁上设置有温度传感器，所述红外辐射体的内部设置有倒U形加热单元，所述加热单元安装在位于所述红外辐射体底部的所述加热单元安装座上，所述加热单元安装座通过所述中心轴固定在所述转接座上；The infrared radiator is cylindrical, and a temperature sensor is arranged on its side wall. An inverted U-shaped heating unit is arranged inside the infrared radiator, and the heating unit is installed on the heating unit at the bottom of the infrared radiator. On the unit mounting seat, the heating unit mounting seat is fixed on the adapter seat through the central shaft;
所述安装筒与所述转接座相连接，所述安装筒与所述电池组外壳通过设置在内部的所述过渡环相连接，所述控制板通过所述过渡环固定在所述安装筒与所述电池组外壳的内部连接处；The installation barrel is connected to the adapter seat, the installation barrel is connected to the battery pack casing through the transition ring provided inside, and the control board is fixed to the installation barrel through the transition ring an internal connection to the battery housing;
所述电池组外壳内侧设置隔热层，所述电池组外壳与所述后球形整流罩通过设置在内部的所述过渡环相连接，所述BMS板通过所述过渡环固定在所述电池组外壳与所述后球形整流罩的内部连接处，在所述BMS板与所述控制板之间的所述电池组外壳的空腔内设置有所述电池组。A heat insulation layer is provided inside the battery pack case, and the battery pack case is connected to the rear spherical fairing through the transition ring provided inside, and the BMS board is fixed to the battery pack through the transition ring The battery pack is arranged in the cavity of the battery pack shell between the BMS board and the control board at the internal connection between the shell and the rear spherical fairing.
进一步的，所述外挂吊舱装置采用圆柱形回旋体设计，轴向前后均设计有球形整流罩，挂载在无人机翼尖位置，采用直流电源方式工作，其电源系统与控制系统、红外辐射源一体化集成。Further, the external pod device is designed with a cylindrical gyratory body, and spherical fairings are designed on the front and rear axially, mounted on the wingtip of the UAV, and work in the form of DC power supply. Its power supply system and control system, infrared Integrated radiation source.
进一步的，外挂吊舱装置通过控制系统完成与无人机飞控计算机通讯，所述控制系统根据飞控计算机的控制指令，完成红外辐射源的启停和定时，通过温度传感器PID闭环控制辐射体温度，调整红外辐射强度，同时完成电源系统的实时监控既保护。Further, the external pod device communicates with the UAV flight control computer through the control system, and the control system completes the start-stop and timing of the infrared radiation source according to the control instructions of the flight control computer, and controls the radiation body through the temperature sensor PID closed-loop Temperature, adjust the intensity of infrared radiation, and at the same time complete the real-time monitoring and protection of the power system.
进一步的，所述前球形整流罩采用中波透红外窗口材料。Further, the front spherical fairing adopts medium-wave infrared transparent window material.
进一步的，所述红外辐射体为紫铜，壁厚0.2mm，有一个端面，端面安装朝飞行方向。Further, the infrared radiator is made of red copper with a wall thickness of 0.2 mm and has an end face installed facing the flying direction.
进一步的，所述加热单元为3组并联的U型500W/150V碳纤维发热管。Further, the heating unit is 3 sets of parallel U-shaped 500W/150V carbon fiber heating tubes.
进一步的，所述控制板包括嵌入式控制器及分别与嵌入式控制器连接的温度检测模块、电流检测模块、电压检测模块、PWM驱动模块、通讯模块、DC/DC电源，所述通讯模块采用RS422接口。Further, the control board includes an embedded controller and a temperature detection module, a current detection module, a voltage detection module, a PWM drive module, a communication module, and a DC/DC power supply respectively connected to the embedded controller. The communication module adopts RS422 interface.
进一步的，所述温度传感器为K型热电偶，最大测量温度1024℃，所述控制板100ms采集一次传感器温度，通过PID算法实时解算出电压控制量偏差，控制PWM驱动模块输出电压，对所述加热单元进行功率调整，实现所述红外辐射体温度稳定在设定值950℃，达到红外辐射强度恒定。Further, the temperature sensor is a K-type thermocouple with a maximum measurement temperature of 1024°C. The control board collects the temperature of the sensor once every 100 ms, calculates the deviation of the voltage control amount in real time through the PID algorithm, controls the output voltage of the PWM drive module, and controls the output voltage of the PWM drive module. The power of the heating unit is adjusted to stabilize the temperature of the infrared radiator at a set value of 950° C. and achieve constant infrared radiation intensity.
进一步的，所述电池组的电压150V、容量2000mAh以及放电倍率10C。Further, the battery pack has a voltage of 150V, a capacity of 2000mAh, and a discharge rate of 10C.
进一步的，所述隔热层采用硅酸铝纤维隔热材料。Further, the heat insulation layer adopts aluminum silicate fiber heat insulation material.
通过本申请实施例，可以获得如下技术效果：本申请的一种红外目标模拟吊舱，适用于高亚音速、大机动类和非机动类慢速无人机挂装，满足战斗机、武装直升机红外特性模拟，对无人机平台飞行速度、机动能力性能影响小。在一次实施例中，海高9km，速度0.82Ma，无人机可进行不低于5g置尾机动；海高5km，速度0.75Ma，无人机可进行不低于7g置尾机动，可进行桶滚、半滚倒转等机动。红外辐射视场涵盖前、后半球，红外辐射体温度波动不大于2%，辐射均匀性不低于90%。Through the embodiment of the present application, the following technical effects can be obtained: an infrared target simulation pod of the present application is suitable for mounting high subsonic, large maneuverable and non-motorized slow UAVs, and meets the requirements of fighter jets and armed helicopters. Characteristic simulation, which has little impact on the flight speed and maneuverability of the UAV platform. In an example, when the sea height is 9km and the speed is 0.82Ma, the UAV can perform a tail maneuver of not less than 5g; the sea height is 5km, and the speed is 0.75Ma, the UAV can perform a maneuver of no less than 7g Barrel roll, half roll inversion and other maneuvers. The infrared radiation field of view covers the front and rear hemispheres, the temperature fluctuation of the infrared radiator is not more than 2%, and the radiation uniformity is not less than 90%.
附图说明Description of drawings
为了更清楚地说明本申请实施例中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作一简单地介绍，显而易见地，下面描述中的附图是本申请的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动性的前提下，还可以根据这些附图获得其他的附图。In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following will briefly introduce the drawings that need to be used in the embodiments or the description of the prior art. Obviously, the accompanying drawings in the following description are of the present application For some embodiments, those of ordinary skill in the art can also obtain other drawings based on these drawings without paying creative efforts.
图1 为外挂吊舱装置组成示意图；Figure 1 is a schematic diagram of the composition of the external pod device;
图2 为外挂吊舱剖面结构示意图；Figure 2 is a schematic diagram of the cross-sectional structure of the external pod;
图3为控制板的电路组成结构示意图。Figure 3 is a schematic diagram of the circuit composition structure of the control board.
附图标记：Reference signs:
1 前球形整流罩、2 红外辐射体、3加热单元、4温度传感器、5 转接座、6 安装筒、7控制板、8 电池组外壳、9隔热层、10 电池组、11 BMS板、12后球形整流罩、13过渡环、14 中心轴、15 前整流罩固定环、16 加热单元安装座。1. Front spherical fairing, 2. Infrared radiator, 3. Heating unit, 4. Temperature sensor, 5. Adapter seat, 6. Installation cylinder, 7. Control board, 8. Battery pack shell, 9. Heat insulation layer, 10. Battery pack, 11. BMS board, 12 Rear spherical fairing, 13 Transition ring, 14 Central shaft, 15 Front fairing fixing ring, 16 Heating unit mounting seat.
具体实施方式Detailed ways
为使本申请实施例的目的、技术方案和优点更加清楚，下面将结合本申请实施例中的附图，对本申请实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例是本申请一部分实施例，而不是全部的实施例。基于本申请中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的全部其他实施例，都属于本申请保护的范围。In order to make the purposes, 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 in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments It is a part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application.
红外目标模拟外挂吊舱（简称：外挂吊舱）根据不同的目标模拟需求可挂装在高机动目标和非高机动目标类。The infrared target simulation external pod (abbreviation: external pod) can be mounted on high maneuvering targets and non-high maneuvering targets according to different target simulation requirements.
图1为外挂吊舱装置组成示意图。外挂吊舱装置挂在无人机翼尖位置，采用直流电源方式工作，其电源系统与控制系统、红外辐射源一体化集成设计。外挂吊舱装置通过控制系统完成与无人机飞控计算机通讯。控制系统根据飞控计算机的控制指令，完成红外辐射源的启停和定时，通过温度传感器PID闭环控制辐射体温度，调整红外辐射强度，同时完成电源系统的实时监控及保护。Figure 1 is a schematic diagram of the composition of the external pod device. The external hanging pod device is hung on the wingtip of the UAV, and it works in the form of DC power supply. Its power supply system, control system, and infrared radiation source are integrated and integrated. The external pod device communicates with the UAV flight control computer through the control system. According to the control instructions of the flight control computer, the control system completes the start-stop and timing of the infrared radiation source, controls the temperature of the radiation body through the PID closed-loop of the temperature sensor, adjusts the infrared radiation intensity, and completes the real-time monitoring and protection of the power system at the same time.
图2为外挂吊舱剖面结构示意图。该外挂吊舱装置适用于高亚音速、大机动目标类和非机动目标类挂装，对无人机平台飞行速度、机动能力影响小，使用高度、速度不受限制。该类型的外挂吊舱用于满足战斗机和武装直升机的红外特性模拟，比如F-16、阿帕奇等目标，外挂吊舱对称挂装在高亚音速大机动无人机两侧翼尖位置，同时前、后半球红外辐射强度与模拟目标相当，对无人机平台飞行速度、机动能力性能影响小。Figure 2 is a schematic cross-sectional structure diagram of the external pod. The external pod device is suitable for high subsonic speed, large maneuvering targets and non-maneuvering targets, and has little impact on the flight speed and maneuverability of the UAV platform, and the use height and speed are not limited. This type of external pod is used to meet the infrared characteristics simulation of fighter jets and armed helicopters, such as F-16, Apache and other targets. The infrared radiation intensity of the front and rear hemispheres is equivalent to that of the simulated target, and has little effect on the flight speed and maneuverability of the UAV platform.
外挂吊舱采用圆柱形回旋体设计，轴向前后均设计有半球形整流罩，满足高速飞行器气动外形要求。外挂吊舱包括前球形整流罩、红外辐射体、加热单元、温度传感器、转接座、安装筒、控制板、电池组外壳、隔热层、电池组、BMS板、后球形整流罩、过渡环、中心轴、前整流罩固定环、加热单元安装座；The external pod adopts a cylindrical gyratory design, and hemispherical fairings are designed on the front and rear axially, which meet the aerodynamic shape requirements of high-speed aircraft. The external pod includes the front spherical fairing, infrared radiator, heating unit, temperature sensor, adapter seat, mounting cylinder, control board, battery pack shell, heat insulation layer, battery pack, BMS board, rear spherical fairing, transition ring , central shaft, front fairing fixing ring, heating unit mounting seat;
所述前球形整流罩1内设置红外辐射体2，所述前球形整流罩通过所述前整流罩固定环15与所述转接座5相连接；An infrared radiator 2 is arranged in the front spherical fairing 1, and the front spherical fairing is connected with the adapter seat 5 through the front
所述红外辐射体为筒形，其侧壁上设置有温度传感器4，所述红外辐射体的内部设置有倒U形加热单元3，所述加热单元安装在位于所述红外辐射体底部的所述加热单元安装座16上，所述加热单元安装座16通过所述中心轴14固定在所述转接座5上；The infrared radiator is cylindrical, its side wall is provided with a temperature sensor 4, the inside of the infrared radiator is provided with an inverted U-shaped heating unit 3, and the heating unit is installed on the bottom of the infrared radiator. On the heating
所述安装筒6与所述转接座相连接，所述安装筒6与所述电池组外壳8通过设置在内部的所述过渡环相连接，所述控制板通过所述过渡环13固定在所述连接筒与所述电池组外壳的内部连接处；The installation cylinder 6 is connected with the adapter seat, the installation cylinder 6 is connected with the battery pack casing 8 through the transition ring provided inside, and the control board is fixed on the
所述电池组外壳内侧设置隔热层9，所述电池组外壳与所述后球形整流罩12通过设置在内部的所述过渡环相连接，所述BMS板11通过所述过渡环13固定在所述电池组外壳与所述后球形整流罩的内部连接处，在所述BMS板11与所述控制板之间的所述电池组外壳的空腔内设置有所述电池组。A heat insulating layer 9 is provided inside the battery pack casing, and the battery pack casing and the rear
所述前球形整流罩采用中波红外透过率比较高的材料，同时耐高温，优选蓝宝石。The front spherical fairing is made of a material with relatively high mid-wave infrared transmittance and high temperature resistance, preferably sapphire.
所述红外辐射体为紫铜，壁厚0.2mm，有一个端面，端面安装朝飞行方向。The infrared radiator is made of red copper with a wall thickness of 0.2mm and has an end face installed facing the flying direction.
所述加热单元为3组并联的500W/150V U型碳纤维发热管。The heating unit is 3 sets of 500W/150V U-shaped carbon fiber heating tubes connected in parallel.
所述控制板包括嵌入式控制器及分别与嵌入式控制器连接的温度检测模块、电流检测模块、电压检测模块、PWM驱动模块、通讯模块、DC/DC电源，所述通讯模块采用RS422接口，如图3所示。The control board includes an embedded controller and a temperature detection module, a current detection module, a voltage detection module, a PWM drive module, a communication module, and a DC/DC power supply respectively connected to the embedded controller. The communication module adopts an RS422 interface, As shown in Figure 3.
所述温度传感器为K型热电偶，最大测量温度1024℃，所述控制板100ms采集一次传感器温度，通过PID算法实时解算出电压控制量偏差，控制PWM驱动模块输出电压，对所述加热单元进行功率调整，实现所述红外辐射体温度稳定在设定值950℃，达到红外辐射强度恒定。The temperature sensor is a K-type thermocouple with a maximum measurement temperature of 1024°C. The control board collects the temperature of the sensor once every 100 ms, calculates the deviation of the voltage control amount in real time through the PID algorithm, controls the output voltage of the PWM drive module, and controls the temperature of the heating unit. The power is adjusted to stabilize the temperature of the infrared radiator at a set value of 950° C. and achieve constant infrared radiation intensity.
所述电池组为电压为150V，容量2000mAh，放电倍率10C。The battery pack has a voltage of 150V, a capacity of 2000mAh, and a discharge rate of 10C.
所述电池组与外壳之间有5mm厚度硅酸铝纤维隔热材料。There is a 5mm thick aluminum silicate fiber heat insulating material between the battery pack and the casing.
所述控制板用于控制红外辐射体工作，调整红外辐射体工作电压。The control board is used to control the work of the infrared radiator and adjust the working voltage of the infrared radiator.
所述BMS板用于对电池组进行充放电、热失控、均衡管理。The BMS board is used for charge and discharge, thermal runaway, and balance management of the battery pack.
所述后球形整流罩为保型设计，采用铝合金材料。The rear spherical fairing is a conformal design and is made of aluminum alloy.
虽然以上描述了本申请的具体实施方式，但是本领域的技术人员应当理解，这些仅是举例说明，本申请的保护范围是由所附权利要求书限定的。本领域的技术人员在不背离本申请的原理和实质的前提下，可以对这些实施方式做出多种变更或修改，但这些变更和修改均落入本申请的保护范围。Although the specific embodiments of the present application have been described above, those skilled in the art should understand that these are only examples, and the protection scope of the present application is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principle and essence of the present application, but these changes and modifications all fall within the protection scope of the present application.
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