Full-automatic airborne hanging test system and method for composite detection device

Abstract

A fully automated airborne flight test system and method for a composite detection device, belonging to the field of equivalent verification of aircraft-borne detection devices, includes a navigation module for acquiring real-time positioning information of the aircraft; a power supply module for connecting to the radar transmitter of the radar detector via a first power supply channel and to all components of the composite detection device except the radar transmitter via a second power supply channel, wherein the power supply of the first power supply channel is greater than that of the second power supply channel; and a control computer for connecting to the radar detection result output port of the radar detector via a high-speed channel and to all other data ports of the composite detection device except the radar detection result output port via a bus channel, wherein the bandwidth of the high-speed channel is greater than that of the bus channel. This application can simultaneously and automatically conduct airborne flight tests of radar and infrared detectors.

Description

Technical Field

[0001] This application relates to the field of equivalent verification of aircraft-borne detection devices, specifically to a fully automated airborne flight test system and method for composite detection devices. Background Technology

[0002] Radar / infrared composite detection technology is an important development direction for detection methods in precision-guided weapons today. Due to the scarcity of resources and limited number of tests available for real-world platform verification, to fully verify the performance indicators of radar / infrared composite detection devices (which consist of a radar detector and an infrared detector), airborne flight testing, simulating the relative position and angle configuration between the detection device and the target under real-world conditions, is typically employed. This simulates the performance verification and data acquisition of the detection device under these conditions, thereby enabling an equivalent analysis of the device's adaptability to real-world scenarios.

[0003] Traditional airborne flight rig systems require a human operator in the loop to manually control the entire system based on flight conditions, which can lead to human error and invalid test data. Furthermore, because radar and infrared detection modes have different power and guidance parameter requirements and different operating sequences, flight rig tests for the two modes are usually conducted separately in practice, resulting in low testing efficiency. Summary of the Invention

[0004] This application provides a fully automated airborne flight test system and method for composite detection devices, which can solve the technical problem in the prior art that it is impossible to conduct airborne flight tests of radar and infrared detectors simultaneously and automatically.

[0005] In a first aspect, embodiments of this application provide a fully automated airborne flight test system for a composite detection device, characterized in that the system includes: a navigation module, which is used to acquire real-time positioning information of the carrier aircraft;

[0006] The power supply module is used to connect the radar transmitter of the radar detector through the first power supply channel and to connect all components in the composite detection device except the radar transmitter through the second power supply channel. The power supply of the first power supply channel is greater than the power supply of the second power supply channel.

[0007] The control computer is used to connect to the radar detection result output port of the radar detector via a high-speed channel, and to connect to all other data ports in the composite detection device except for the radar detection result output port via a bus channel. The bandwidth of the high-speed channel is greater than that of the bus channel.

[0008] The control computer is also used to control the connection of the second power supply channel and the bus channel;

[0009] The control computer is also used to determine whether the flight altitude is greater than a preset specified altitude based on the real-time positioning information of the carrier aircraft. If so, it controls the first power supply channel and the high-speed channel to be connected; if not, it controls the first power supply channel and the high-speed channel to be disconnected.

[0010] The control computer is also used to determine whether the carrier has reached the preset working point based on the carrier's real-time positioning information. If so, it controls the corresponding detector to work according to the preset working mode of the working point; if not, it controls the composite detection device to standby. The working modes include radar working mode and infrared working mode.

[0011] In conjunction with the first aspect, in one embodiment, the real-time positioning information of the carrier aircraft includes the real-time position and real-time heading of the carrier aircraft;

[0012] The control computer determines whether the flight altitude is greater than the preset altitude based on the real-time position of the carrier aircraft; the control computer determines whether the carrier aircraft has reached the preset working point based on the real-time position and real-time heading of the carrier aircraft.

[0013] In conjunction with the first aspect, in one embodiment, the control computer is further configured to, when determining that the current operating mode is radar, send the real-time positioning information of the carrier aircraft, the target area information corresponding to the current operating point, and the operating parameters of the radar detector to the data port of the radar detector; the radar detector operates based on the operating parameters, and completes the detection of the target area based on the real-time positioning information of the carrier aircraft and the target area information, and sends the radar detection results to the control computer through the radar detection result output port;

[0014] The control computer is also used to send the real-time positioning information of the carrier aircraft, the target area information corresponding to the current working point, and the working parameters of the infrared detector to the data port of the infrared detector when it is determined that the current working mode is infrared. The infrared detector operates based on the working parameters, and completes the detection of the target area based on the real-time positioning information of the carrier aircraft and the target area information, and sends the infrared detection results to the control computer through the data port.

[0015] In conjunction with the first aspect, in one embodiment, the power supply module includes:

[0016] A lead-acid battery pack, used to output the first direct current;

[0017] An inverter, connected to a lead-acid battery pack, is used to convert the first direct current into standard alternating current;

[0018] The detection device's DC power supply, connected to the inverter, control computer, and composite detection device, is used to convert standard AC power into a second DC power supply that matches the radar transmitter, and a third DC power supply that matches all components in the composite detection device except the radar transmitter; the voltage and current values ​​of the second DC power supply are both greater than the voltage and current values ​​of the third DC power supply.

[0019] In conjunction with the first aspect, in one embodiment, the control computer is further configured to control the first power supply channel of the DC power supply of the detection device to be powered on when it is determined that the flight altitude is greater than a specified altitude, and to control the radar detector to enter a standby state after determining that the potential of the first channel is stable.

[0020] The control computer is also used to control the radar detector to enter a low-power mode and then cut off the first power supply channel of the DC power supply of the detection device when it determines that the flight altitude is not greater than the specified altitude.

[0021] In conjunction with the first aspect, in one embodiment, the power supply module further includes:

[0022] The UPS power supply has one end connected to the power supply interface of the carrier aircraft and the other end connected to the control computer and the navigation module. It is used to receive power from the carrier aircraft and to supply power to the control computer and the navigation module.

[0023] In conjunction with the first aspect, in one embodiment, the system further includes:

[0024] A storage module, connected to the composite detection device, is used to store the raw data output by the composite detection device and provide it to the control computer; the storage module includes a radar data storage device for storing the output of the radar detector and an infrared data storage device for storing the output of the infrared detector.

[0025] Secondly, embodiments of this application provide a fully automated airborne flight test method for a composite detection device, based on the aforementioned fully automated airborne flight test system for a composite detection device; the method includes:

[0026] Obtain the real-time location information of the carrier aircraft;

[0027] Based on the real-time positioning information of the carrier aircraft, determine whether the flight altitude is greater than the preset specified altitude. If yes, control the first power supply channel and the high-speed channel to be connected; if no, control the first power supply channel and the high-speed channel to be disconnected.

[0028] The system determines whether the aircraft has reached the preset working point based on the real-time positioning information of the carrier aircraft. If it has, the system controls the corresponding detector to work according to the preset working mode of that working point. If not, the system controls the composite detection device to standby. The working modes include radar working mode and infrared working mode.

[0029] In conjunction with the second aspect, in one embodiment, the method further includes:

[0030] When the radar detector is working, the first power supply channel is used to power the radar transmitter, and the second power supply channel is used to power all components in the composite detection device except the radar transmitter.

[0031] When the infrared detector is working, the second power supply channel is used to power all components in the composite detection device except the radar transmitter.

[0032] In conjunction with the second aspect, in one embodiment, the method further includes:

[0033] When the radar detector is working, a high-speed channel is used to receive the radar detection results output by the radar detector, and a bus channel is used to exchange data between the control computer and the composite detection device.

[0034] When the infrared detector is working, the bus channel is used to receive the infrared detection results output by the infrared detector and to exchange data between the control computer and the composite detection device.

[0035] The beneficial effects of the technical solutions provided in this application include:

[0036] The navigation module collects relevant data to determine whether the aircraft carrying the composite detection device has reached the preset working point. Based on the pre-configured working mode of each working point, the radar / infrared detector is selected to be tested at that working point. This avoids the drawback of the existing technology where the personnel on the aircraft judge the switching of the working status of the radar and infrared detector, thus meeting the requirement of simultaneously conducting aircraft-mounted flight tests on the radar and infrared detector.

[0037] The control computer controls the power supply to the composite detection device through two power supply channels. The first power supply channel is connected to the radar detector, and its power supply is large enough to meet the high power supply requirements of the radar transmitter when the radar detector is working. The second power supply channel is connected to the composite detection device, which can meet the low power supply requirements when the infrared detector is working, as well as the power supply requirements of the composite detection device except for the radar transmitter when it is working, thus meeting the requirement of conducting simultaneous aircraft-borne flight tests on the radar and infrared detectors.

[0038] The control computer communicates with the composite detection device through two channels. The high-speed channel connects to the radar detector, and its large bandwidth can meet the high output requirements of the radar detector when it is working. The bus channel connects to the composite detection device, thus meeting the requirement of conducting simultaneous aircraft-borne flight tests on the radar and infrared detectors. Attached Figure Description

[0039] Figure 1This is a schematic diagram of the architecture of an embodiment of the fully automated airborne flight test system for a composite detection device according to this application;

[0040] Figure 2 This is a schematic diagram illustrating an embodiment of the fully automated airborne flight test system for a composite detection device according to this application.

[0041] Figure 3 This is a flowchart illustrating an embodiment of the fully automated airborne flight test method for a composite detection device according to this application. Detailed Implementation

[0042] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present application.

[0043] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments of this application will be described in further detail below with reference to the accompanying drawings.

[0044] In a first aspect, embodiments of this application provide a fully automated airborne flight test system for a composite detection device.

[0045] In one embodiment, reference is made to Figure 1 and Figure 2 , Figure 1 This is a schematic diagram of the architecture of an embodiment of the fully automated airborne flight test system for a composite detection device according to this application. Figure 1 The direction the top of the triangle in the square frame points indicates the direction of power supply or communication that can be achieved by the port and its connected lines. Figure 2 This is a schematic diagram illustrating an embodiment of the fully automated airborne flight test system for a composite detection device according to this application. Figure 1 and Figure 2 As shown, the fully automated airborne re-launch test system can be installed in the aircraft cabin, with a composite detection device installed below the cabin. The aforementioned fully automated airborne re-launch test system includes:

[0046] The navigation module is used to obtain the real-time positioning information of the carrier aircraft;

[0047] The power supply module is used to connect the radar transmitter of the radar detector through the first power supply channel and to connect all components in the composite detection device except the radar transmitter through the second power supply channel. The power supply of the first power supply channel is greater than the power supply of the second power supply channel.

[0048] The control computer is used to connect to the radar detection result output port of the radar detector via a high-speed channel, and to connect to all other data ports in the composite detection device except for the radar detection result output port via a bus channel. The bandwidth of the high-speed channel is greater than that of the bus channel.

[0049] The control computer is also used to control the connection of the second power supply channel and the bus channel;

[0050] The control computer is also used to determine whether the flight altitude is greater than a preset specified altitude based on the real-time positioning information of the carrier aircraft. If so, it controls the first power supply channel and the high-speed channel to be connected; if not, it controls the first power supply channel and the high-speed channel to be disconnected.

[0051] The control computer is also used to determine whether the carrier has reached the preset working point based on the carrier's real-time positioning information. If so, it controls the corresponding detector to work according to the preset working mode of the working point; if not, it controls the composite detection device to standby. The working modes include radar working mode and infrared working mode.

[0052] In this embodiment, the power consumption of the radar transmitter is higher than that of other components of the radar detector, and also higher than that of the infrared detector (the power consumption of the infrared detector is not much different when it is working and when it is in standby mode). Therefore, the power consumption of the radar detector during operation needs to be designed separately. In addition, the amount of data of the radar detection results output by the radar detector during operation is also higher than that of the infrared detection results output by the infrared detector during operation. Therefore, the data transmission requirements of the radar detector during operation need to be designed separately.

[0053] The navigation module collects relevant data to determine whether the flight altitude of the aircraft carrying the composite detection device is greater than the preset specified altitude. If so, it indicates that the composite detection device needs to prepare for detection. Therefore, the control computer controls the first power supply channel to be turned on, preparing to supply power to the radar transmitter of the radar detector when the aircraft arrives at the corresponding working point. The control computer also controls the high-speed channel to be turned on, preparing to receive the radar detection data output by the radar detector when the aircraft arrives at the corresponding working point.

[0054] The second power supply channel is always connected, ensuring that both the radar and infrared detectors in the composite detection device are powered. The bus channel is always connected, ensuring that the control computer can communicate with both the radar and infrared detectors. The control computer can send control commands to the radar and infrared detectors via the bus channel, such as controlling the radar detector to enter a certain radar detection mode, the infrared detector to enter a certain infrared detection mode, the radar detector to enter standby mode, or the infrared detector to enter a low-power mode. Entering a radar detection mode or an infrared detector to enter a certain infrared detection mode both indicate that the corresponding detector has entered its operating mode. The standby mode refers to the radar detector preparing to enter its operating mode, while the low-power mode refers to the detector not preparing to enter its operating mode and being idle. During flight, the radar detector generally switches between three phases: low-power phase, standby phase, and operating phase. The infrared detector generally switches between two phases: low-power phase and operating phase.

[0055] In summary, only one port needs to be set on the DC power supply of the detection device to connect to the second power supply channel to power the radar detector and the infrared detector, and only another port needs to be set to connect to the first power supply channel to power the radar transmitter. This reduces the number of required ports and simplifies the circuit structure. On the control computer, only one port needs to be set to connect to the bus channel to control the radar detector and the infrared detector, and only another port needs to be set to connect to the altitude channel to receive the output data of the radar detector. This reduces the number of required ports and simplifies the circuit structure.

[0056] The navigation module collects relevant data to determine whether the aircraft carrying the composite detection device has reached the preset working point. Based on the pre-configured working mode of each working point, the radar / infrared detector is selected to be tested at that working point. This avoids the drawback of the existing technology where the personnel on the aircraft judge the switching of the working status of the radar and infrared detector, thus meeting the requirement of simultaneously conducting aircraft-mounted flight tests on the radar and infrared detector.

[0057] The control computer controls the power supply to the composite detection device through two power supply channels. The first power supply channel is connected to the radar detector, and its power supply is large enough to meet the high power supply requirements of the radar transmitter when the radar detector is working. The second power supply channel is connected to the composite detection device, which can meet the low power supply requirements when the infrared detector is working, as well as the power supply requirements of the composite detection device except for the radar transmitter when it is working, thus meeting the requirement of conducting simultaneous aircraft-borne flight tests on the radar and infrared detectors.

[0058] The control computer communicates with the composite detection device through two channels. The high-speed channel connects to the radar detector, and its large bandwidth can meet the high output requirements of the radar detector during operation. The bus channel connects to the composite detection device, and its bandwidth can meet the requirements of simultaneously exchanging commands with the radar detector and the infrared detector, thereby meeting the requirement of simultaneously conducting aircraft-borne flight tests on the radar and infrared detectors.

[0059] Furthermore, in one embodiment, when the radar detector is working, the control computer uses a first power supply channel to power the radar transmitter, and the control computer uses a second power supply channel to power all components in the composite detection device except the radar transmitter.

[0060] When the infrared detector is working, the control computer uses the second power supply channel to power all components in the composite detection device except for the radar transmitter.

[0061] When the radar detector is working, the control computer uses a high-speed channel to receive the radar detection results output by the radar detector, and uses a bus signal to exchange data between the control computer and the composite detection device.

[0062] When the infrared detector is working, the control computer uses the bus channel to receive the infrared detection results output by the infrared detector and performs data interaction between the control computer and the composite detection device.

[0063] In this embodiment, the first power supply channel can remain connected during the working and standby phases of the radar detector to ensure the power requirements of the radar transmitter, and remain disconnected during the low-power idle phase.

[0064] During the low-power idle phase, standby phase, and working phase of the radar detector, the control computer can control the power supply module to supply power to all components in the composite detection device except the radar transmitter through the second power supply channel, ensuring that the composite detection device can maintain basic operation. The computer can also adjust the on / off state of the second power supply channel according to the actual test scenario or actual test requirements.

[0065] The high-speed channel can remain connected during the working and standby phases of the radar detector to ensure the output of radar detection data, and remain disconnected during the low-power idle phase.

[0066] In summary, the second power supply channel and bus channel ensure communication and power needs when the radar and infrared detectors are not in operation. The first power supply channel and high-speed channel ensure communication and power needs when the radar detector is operating alone. The flexible switching between the two power supply channels and the two channels ensures that the aircraft can simultaneously conduct load tests on the radar and infrared detectors during a single flight. This ensures that power and communication needs are met while improving the targeting of high power and high communication needs and low power and low communication needs, thus saving energy and improving efficiency.

[0067] Furthermore, in one embodiment, the control computer is also used to send the real-time positioning information of the carrier aircraft, the target area information corresponding to the current working point, and the working parameters of the radar detector to the data port of the radar detector when it is determined that the current working mode is radar. The radar detector operates based on the working parameters, and completes the detection of the target area based on the real-time positioning information of the carrier aircraft and the target area information, and sends the radar detection results to the control computer through the radar detection result output port.

[0068] The control computer is also used to send the real-time positioning information of the carrier aircraft, the target area information corresponding to the current working point, and the working parameters of the infrared detector to the data port of the infrared detector when it is determined that the current working mode is infrared. The infrared detector operates based on the working parameters, and completes the detection of the target area based on the real-time positioning information of the carrier aircraft and the target area information, and sends the infrared detection results to the control computer through the data port.

[0069] In this embodiment, the fully automated airborne flight test system performs configuration parameter setting on the ground. The setting parameters include the number of working points (WrokNum) and the predetermined position of the carrier aircraft (Pos). set Aircraft's planned heading FltAng set The settings include WorkMode, WorkPara, and Tar.

[0070] For a work point WrokCnt, the carrier's predetermined position Pos set Including the predetermined latitude PosB set Pre-determined longitude PosL set and the planned altitude PosH set Aircraft's planned heading: FltAng setDefined as the angle between the ground projection of the flight speed and true north. Working modes include RadarHeight, RadarAngle, RadarSAR, and InfraredImage. Working parameters include the RadarPara parameter package and the InfraredRPara parameter package. Target area Tar includes the latitude of the area center (TarB), the longitude of the area center (TarL), and the altitude of the area center (TarH).

[0071] After the carrier aircraft enters the designated operating area, the system control module puts the composite detection device into standby mode while the navigation calculation module calculates the carrier aircraft's current latitude (PosB) in real time. real Current longitude of the carrier aircraft (PosL) real Current altitude of the carrier aircraft (PosH) real and the aircraft's current heading FltAng real The calculation results are sent to the system control module. After obtaining the real-time position and heading of the carrier aircraft, the control computer performs the following operation (1) to calculate the position error and heading error between the carrier aircraft and each binding point:

[0072]

[0073] Among them, FltAng seti FltAngErr represents the planned heading of the aircraft at the i-th work point. i PosB represents the heading error of the aircraft at the i-th operating point. seti PosL represents the predetermined dimension of the carrier at the i-th working point. seti PosH represents the planned longitude of the aircraft at the i-th working point. seti DisErr represents the planned altitude of the aircraft at the i-th working point. i This represents the carrier position error at the i-th working point.

[0074] If all position and heading errors exceed the position error threshold DisErrTH or the heading error threshold FltAngErrTH, the control computer keeps the composite detection device in standby mode. When the Nth position and heading error satisfies the following formula (2):

[0075] FltAngErr N ≤FltAngErrTH & DisErr N ≤DisErrTH (2)

[0076] The control computer automatically controls the corresponding detector to enter the mode corresponding to the working point (WrokCntN). Simultaneously, it performs navigation calculations on the working mode (WorkModeN), working parameters (WorkParaN), and target area (TarN) information corresponding to that working point and sends them to the corresponding detector so that it can perform detection work on the designated target area, thereby achieving automatic control of the composite detection device. The method for controlling the composite detection device to exit the working mode in the fully automatic airborne flight test system is the same as the method for entering the working mode described above.

[0077] Furthermore, in one embodiment, the power supply module includes:

[0078] A lead-acid battery pack, used to output the first direct current;

[0079] An inverter, connected to a lead-acid battery pack, is used to convert the first direct current into standard alternating current;

[0080] The detection device's DC power supply, connected to the inverter, control computer, and composite detection device, is used to convert standard AC power into a second DC power supply that matches the radar transmitter, and a third DC power supply that matches all components in the composite detection device except the radar transmitter; the voltage and current values ​​of the second DC power supply are both greater than the voltage and current values ​​of the third DC power supply.

[0081] The UPS power supply has one end connected to the power supply interface of the carrier aircraft and the other end connected to the aforementioned control computer and navigation module. It is used to receive power from the carrier aircraft and to supply power to the control computer and navigation module.

[0082] The control computer is also used to control the first power supply channel of the DC power supply of the detection device to be powered on when it is determined that the flight altitude is greater than the specified altitude, and to control the detector to enter the standby state after determining that the potential of the first channel is stable (in addition, the detector also enters the standby state after completing the corresponding working mode exit).

[0083] The control computer is also used to control the radar detector to enter a low-power mode and cut off the power to the first power supply channel of the DC power supply of the detection device when it is determined that the flight altitude is not greater than the specified altitude.

[0084] In this embodiment, the UPS power supply provides 220V / 50Hz power to the navigation module and control computer during the preparation phase before aircraft engine startup. After the aircraft engine starts and stabilizes, the power supply switches to aircraft power (the aircraft's 220V / 50Hz power output is connected to the UPS power supply), thus providing 220V / 50Hz power to the navigation module and control computer. It also serves as a backup power supply for use during fluctuations in the aircraft's power supply. The UPS power supply model with appropriate load capacity is selected based on the actual power consumption of the navigation module and control computer.

[0085] Lead-acid battery packs are used to provide power to the composite detection device under test (hereinafter referred to as the test product). The series and parallel configuration of the battery packs are selected according to the power consumption of the actual test product and the test duration.

[0086] Inverters are used to convert the DC output of lead-acid batteries into standard AC power of 220V / 50Hz. The inverter model with the appropriate load capacity should be selected according to the power consumption of the actual test product.

[0087] The 24V / DC power output of the lead-acid battery pack is connected to the inverter. The inverter converts the DC input to 220V / 50Hz and outputs it to the DC power supply of the detection device. The DC power supply of the detection device supplies power to the composite detection device under the control of the control computer.

[0088] Furthermore, in one embodiment, the system further includes:

[0089] A storage module, connected to the composite detection device, is used to store the raw data output by the composite detection device and provide it to the control computer. The storage module includes a radar data storage device for storing raw radar data and an infrared data storage device for storing raw infrared data. When the system is offline, the raw data from the radar and infrared data storage devices can be downloaded to the control computer.

[0090] In this embodiment, the control computer acquires and analyzes the data output by the composite detection device. Specifically, based on the raw navigation information output by the small inertial / satellite integrated navigation system, the data is analyzed according to the navigation requirements of various operating modes of the composite detection device, and the calculated navigation data is then transmitted.

[0091] Furthermore, in one embodiment, the navigation module includes a small inertial / satellite integrated navigation system connected to a satellite navigation antenna, used to provide real-time navigation information for the airborne flight system.

[0092] Small inertial / satellite integrated navigation systems are used to simulate integrated navigation systems on aircraft. They output time-stamped information, aircraft position information (including latitude, longitude, altitude coordinates and velocity and acceleration information in the north, sky, and east directions), and aircraft attitude information (including heading angle, pitch angle, roll angle, and three-axis angular rates in the carrier coordinate system). The output information is provided to the control computer for navigation information calculation.

[0093] In one specific embodiment, the fully automated airborne flight test system is centered on a control computer and integrates a variety of commonly used devices. It can simultaneously realize the verification requirements of composite detection devices and fully automated flight tests, and has the characteristics of low cost and high versatility.

[0094] The test products of the fully automated airborne flight test system include aircraft-borne composite detection devices, aircraft radar antenna radomes, and aircraft infrared optical windows.

[0095] The fully automated airborne flight test system also includes a structural subsystem, which comprises a test product mounting fixture (equipped with pitch angle adjustment function) and a navigation module mounting fixture. The test product mounting fixture is used to fix the test product under the fuselage of the aircraft, while ensuring that the mechanical axes of the test product and the aircraft meet the test requirements. The navigation module mounting fixture is used to strapdown the navigation module to the aircraft, while ensuring that the coordinate axes of the inertial measurement unit in the navigation module coincide with the coordinate axes of the aircraft body.

[0096] The control computer is the core of the entire flight system, responsible for controlling various devices, calculating navigation information, and storing test data. The control computer uses configuration files to schedule the entire system, perform navigation calculations, and store navigation data. The DC power supply for the composite detection device, under the control computer's management, powers and de-energizes the test product.

[0097] The software subsystem in the control computer includes a system control module, a data storage module, and a navigation calculation module. The system control module is responsible for managing system tasks and configuration files, as well as controlling and coordinating the various sub-modules to achieve fully automated implementation of the airborne take-off system process.

[0098] The accessories for the fully automated airborne flight test system include cables and connectors for connecting various devices within the system to the test products.

[0099] This invention realizes fully automated airborne flight verification conditions for an aircraft-borne radar / infrared composite detection device. By integrating power supply, control, navigation calculation, and data storage for both radar and infrared modes, it can meet the requirement of simultaneous flight verification of both operating modes, reducing testing costs and improving testing efficiency. Furthermore, the system integrates automatic control functions in its control module, enabling full system automation and avoiding the risks of human error in the loop.

[0100] In one embodiment, reference is made to Figure 3 , Figure 3 This is a flowchart illustrating an embodiment of the fully automated airborne flight test method for a composite detection device according to this application. Figure 3 As shown, the fully automated airborne takeoff test method includes:

[0101] Obtain the real-time location information of the carrier aircraft;

[0102] Based on the real-time positioning information of the carrier aircraft, determine whether the flight altitude is greater than the preset specified altitude. If yes, control the first power supply channel and the high-speed channel to be connected; if no, control the first power supply channel and the high-speed channel to be disconnected.

[0103] The system determines whether the aircraft has reached the preset working point based on the real-time positioning information of the carrier aircraft. If it has, the system controls the corresponding detector to work according to the preset working mode of that working point. If not, the system controls the composite detection device to standby. The working modes include radar working mode and infrared working mode.

[0104] In one specific embodiment, the raw data from the radar section of the composite detection device is transmitted to the radar data storage device via a gigabit Ethernet interface. The raw data from the infrared section of the composite detection device is transmitted to the infrared data storage device via a CameraLink interface. The navigation module is connected to the control computer via an RS422 serial port, sending raw navigation data to the control computer. The DC power supply of the detection device is connected to the control computer via an RS232 serial port, responding to the control computer's commands for power-on and power-off operations. The control computer is connected to each part of the flight system via communication and control interfaces, achieving master control of the entire system. Communication with the radar section of the composite detection device is achieved through a CAN bus interface and an LVDS interface. The CAN bus interface controls the radar's power-on / off, mode setting, parameter setting, and operating status, while providing navigation data to the radar during operation. The LVDS interface receives guidance information output by the radar. Simultaneously, communication with the infrared section of the composite detection device is achieved through the CAN bus interface, controlling the infrared's power-on / off, parameter setting, and operating status, while providing navigation data to the infrared section during operation.

[0105] The system computer comprises three parts: configuration loading, mode control, and interface control. The configuration loading section loads configuration files on the ground. The mode control section compares the loaded configuration parameters with the navigation calculation output results in real time in the air, automatically entering the predetermined operating mode and initiating control of each subsystem when the conditions are met. The interface control section specifically implements control over different interfaces and protocols of each device. The data storage module mainly stores radar output guidance information, navigation data output by the navigation calculation module, and input / output commands from the system control module. Based on the raw navigation data output by the integrated navigation system, the navigation calculation module performs time alignment and coordinate transformation calculations in real time according to the requirements of different operating modes of the composite detection device, and outputs the navigation calculation results according to the protocol.

[0106] The specific workflow of the airborne sling-on system is as follows:

[0107] Mission planning. Based on the requirements of the test mission, plan the aircraft flight path, target area, operating mode, and operating parameters, and generate configuration files.

[0108] System installation. Install the fully automatic airborne flight test system onto the carrier aircraft, and complete the fastening of all equipment and cable connections.

[0109] System self-test. Check and confirm that the system is installed correctly, and use ground power to complete the self-test of the entire system and the power supply system's power level.

[0110] Configuration file loading. After the fully automated airborne flight test system passes its self-test, the configuration file generated by the mission plan is loaded onto the control computer.

[0111] Ground preparation for the fully automated airborne flight test system. Initial north-finding and leveling of the navigation module are completed. Ground power is disconnected and withdrawn, switching to UPS power and lead-acid battery packs to power the airborne flight test system. The aircraft's engines are started, and once the aircraft's power supply is stable, the UPS power supply switches to the aircraft's power supply. Ground personnel disembark.

[0112] When the carrier aircraft takes off and its flight altitude exceeds a certain threshold HeightTH1, the control computer controls the DC power supply of the detection device to be turned on. After the voltage stabilizes, the control computer controls the composite detection device to be turned on and switch to standby mode.

[0113] The fully automated airborne flight test system synchronizes time. When the aircraft enters or returns to the predetermined altitude of HeightTH2 for level flight, the control computer controls the composite detection device to perform time synchronization of the entire system.

[0114] The fully automated airborne flight test system enters working mode. After the aircraft reaches level flight and completes system time synchronization, the control computer continuously determines the transition to a new working mode. When the conditions for entering a specific working mode are met, the control computer activates the corresponding detectors and simultaneously initiates data acquisition from the control computer and data storage devices.

[0115] The fully automated airborne flight test system exits its operating mode. Upon entering a specific operating mode, the control computer continuously checks for exiting that mode. When the conditions for exiting the operating mode are met, the control computer puts the corresponding detectors into standby mode and simultaneously stops data acquisition from the computer and data storage devices.

[0116] After completing one working mode, the fully automatic airborne flight test system repeats the working mode judgment until all working modes are completed, at which point the mission ends.

[0117] The fully automatic airborne flight test system is powered off. When the aircraft returns to base after completing its mission and its flight altitude is below the threshold HeightTH1, the control computer switches the composite detection device to a low-power mode and then cuts off the DC power supply to the detection device.

[0118] The aircraft landed.

[0119] Data analysis. Complete the download and analysis of experimental data.

[0120] In one specific embodiment, the power-on and power-off altitude (HeightTH1) of the fully automated airborne flight test system is 2000m. The timing altitude (HeightTH2) for the fully automated airborne flight test is 6000m. The binding work points are shown in Table 1.

[0121] Table 1 Working Point Configuration Parameters

[0122]

[0123] The specific workflow of the above fully automated airborne flight test method is as follows:

[0124] Generate the "Hang Flight Example.txt" configuration file according to the task in Table 1.

[0125] according to Figure 1 Install the fully automated airborne flight test system on the carrier aircraft and complete the fastening of all equipment and cable connections.

[0126] Check and confirm that the system is installed in place, and use ground power to complete the single-unit self-test of the entire system and the power supply system power check.

[0127] After the system self-test passes, install the "Hang Flight Example.txt" configuration file on the control computer.

[0128] Complete the initial north-finding and leveling of the navigation module. Disconnect and withdraw ground power, switching to UPS power and lead-acid battery packs to power the airborne flight system. Start the aircraft's engines, and once the aircraft's power supply is stable, switch from UPS power to aircraft power. Ground personnel disembark.

[0129] The aircraft takes off.

[0130] When the aircraft flies at an altitude greater than 2000m, the control computer powers on the DC power supply of the detection device, and 10 seconds later, it powers on the composite detection device and switches it to standby mode.

[0131] When the aircraft reaches a level flight altitude of 6000m, the control computer synchronizes the entire system in time.

[0132] The aircraft enters the operational area and flies westward, first approaching work point 1. Upon meeting the entry conditions for work point 1, the control computer activates the radar section of the composite detection device to enter imaging mode and begin data acquisition. Upon meeting the exit conditions for work point 1, the control computer deactivates the radar section of the composite detection device to exit imaging mode and terminates data acquisition.

[0133] The aircraft continued westward, entering work point 2. Upon meeting the entry conditions for work point 2, the control computer activated the infrared component of the composite detection device to enter imaging mode and begin data acquisition. Upon meeting the exit conditions for work point 2, the control computer deactivated the infrared component of the composite detection device to exit imaging mode and terminate data acquisition.

[0134] The aircraft continued westward, entering operational point 3. Upon meeting the entry conditions for point 3, the control computer initiated the altimeter mode for the radar section of the composite detection device and began data acquisition. Upon meeting the exit conditions for point 3, the control computer initiated the exit mode for the radar section of the composite detection device and terminated data acquisition.

[0135] The aircraft continued westward, entering operational point 4. Upon meeting the entry conditions for point 4, the control computer initiated the radar section of the composite detection device into angle measurement mode and began data acquisition. Upon meeting the exit conditions for point 4, the control computer initiated the radar section of the composite detection device out of angle measurement mode and terminated data acquisition.

[0136] When the aircraft returns to base after completing its mission, and the flight altitude is less than 2000m, the control computer switches the composite detection device to low power consumption, and after 10 seconds, the DC power supply of the detection device is cut off.

[0137] The aircraft landed.

[0138] Complete the download and analysis of experimental data.

[0139] The functions of each module in the above-mentioned fully automatic airborne flight test system correspond to the steps in the above-mentioned fully automatic airborne flight test method embodiment, and their functions and implementation processes will not be described in detail here.

[0140] The terms "comprising" and "having," and any variations thereof, in the specification, claims, and accompanying drawings of this application are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that includes a series of steps or units is not limited to the listed steps or units, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to such process, method, product, or apparatus. The terms "first," "second," and "third," etc., are used to distinguish different objects, etc., and do not indicate a sequence, nor do they limit "first," "second," and "third" to different types.

[0141] In the description of the embodiments of this application, terms such as "exemplary," "for example," or "for instance" are used to indicate examples, illustrations, or explanations. Any embodiment or design described as "exemplary," "for example," or "for instance" in the embodiments of this application should not be construed as being more preferred or advantageous than other embodiments or designs. Specifically, the use of terms such as "exemplary," "for example," or "for instance" is intended to present the relevant concepts in a concrete manner.

[0142] In the description of the embodiments of this application, unless otherwise stated, " / " means "or". For example, A / B can mean A or B. The "and / or" in the text is merely a description of the relationship between related objects, indicating that there can be three relationships. For example, A and / or B can mean: A exists alone, A and B exist simultaneously, and B exists alone. In addition, in the description of the embodiments of this application, "multiple" means two or more.

[0143] In some processes described in the embodiments of this application, multiple operations or steps are included in a specific order. However, it should be understood that these operations or steps may not be executed in the order they appear in the embodiments of this application, or they may be executed in parallel. The sequence number of the operation is only used to distinguish different operations, and the sequence number itself does not represent any execution order. In addition, these processes may include more or fewer operations, and these operations or steps may be executed sequentially or in parallel, and these operations or steps may be combined.

[0144] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. A fully automated airborne flight test system for a composite detection device, characterized in that, The system includes: The navigation module is used to obtain the real-time positioning information of the carrier aircraft; The power supply module is used to connect the radar transmitter of the radar detector through the first power supply channel and to connect all components in the composite detection device except the radar transmitter through the second power supply channel. The power supply of the first power supply channel is greater than the power supply of the second power supply channel. The control computer is used to connect to the radar detection result output port of the radar detector via a high-speed channel, and to connect to all other data ports in the composite detection device except for the radar detection result output port via a bus channel. The bandwidth of the high-speed channel is greater than that of the bus channel. The control computer is also used to control the connection of the second power supply channel and the bus channel; The control computer is also used to determine whether the flight altitude is greater than the preset altitude based on the real-time positioning information of the carrier aircraft. If so, it controls the first power supply channel and the high-speed channel to be connected; if not, it controls the first power supply channel and the high-speed channel to be disconnected. The control computer is also used to determine whether the carrier has reached the preset working point based on the carrier's real-time positioning information. If so, it controls the corresponding detector to work according to the preset working mode of the working point; if not, it controls the composite detection device to standby. The working mode includes radar working mode and infrared working mode.

2. The fully automated airborne flight test system for composite detection devices as described in claim 1, characterized in that, The real-time positioning information of the carrier aircraft includes the real-time position and real-time heading of the carrier aircraft. The control computer determines whether the flight altitude is greater than the preset altitude based on the real-time position of the carrier aircraft; the control computer determines whether the carrier aircraft has reached the preset working point based on the real-time position and real-time heading of the carrier aircraft.

3. The fully automated airborne flight test system for composite detection devices as described in claim 1, characterized in that, The control computer is also used to send the real-time positioning information of the carrier aircraft, the target area information corresponding to the current working point, and the working parameters of the radar detector to the data port of the radar detector when it is determined that the current working mode is radar. The radar detector operates based on the aforementioned operating parameters, and completes the detection of the target area based on the real-time positioning information of the carrier aircraft and the target area information. The radar detection results are then sent to the control computer through the radar detection result output port. The control computer is also used to send the real-time positioning information of the carrier aircraft, the target area information corresponding to the current working point, and the working parameters of the infrared detector to the data port of the infrared detector when it is determined that the current working mode is infrared. The infrared detector operates based on the working parameters, and completes the detection of the target area based on the real-time positioning information of the carrier aircraft and the target area information, and sends the infrared detection results to the control computer through the data port.

4. The fully automated airborne flight test system for composite detection devices as described in claim 1, characterized in that, The power supply module includes: A lead-acid battery pack, used to output the first direct current; An inverter, connected to a lead-acid battery pack, is used to convert the first direct current into standard alternating current; The detection device's DC power supply, connected to the inverter, control computer, and composite detection device, is used to convert standard AC power into a second DC power supply that matches the radar transmitter, and a third DC power supply that matches all components in the composite detection device except the radar transmitter; the voltage and current values ​​of the second DC power supply are both greater than the voltage and current values ​​of the third DC power supply.

5. The fully automated airborne flight test system for composite detection devices as described in claim 1, characterized in that, The control computer is also used to control the first power supply channel to be powered on when it is determined that the flight altitude is greater than the preset altitude, and to control the radar detector to enter the standby state after it is determined that the potential of the first power supply channel is stable. The control computer is also used to control the radar detector to enter a low-power mode and then control the first power supply channel to cut off power when it determines that the flight altitude is not greater than a preset altitude.

6. The fully automated airborne flight test system for composite detection devices as described in claim 1, characterized in that, The power supply module also includes: The UPS power supply has one end connected to the power supply interface of the carrier aircraft and the other end connected to the control computer and the navigation module. It is used to receive power from the carrier aircraft and to supply power to the control computer and the navigation module.

7. The fully automated airborne flight test system for composite detection devices as described in claim 1, characterized in that, The system also includes: A storage module, connected to the composite detection device, is used to store the raw data output by the composite detection device and provide it to the control computer; the storage module includes a radar data storage device for storing the output of the radar detector and an infrared data storage device for storing the output of the infrared detector.

8. A fully automated airborne flight test method for a composite detection device, characterized in that, The fully automated airborne flight test system for composite detection devices according to any one of claims 1-7; the method includes: Obtain the real-time location information of the carrier aircraft; Based on the real-time positioning information of the carrier aircraft, determine whether the flight altitude is greater than the preset altitude. If so, control the first power supply channel and the high-speed channel to be connected; if not, control the first power supply channel and the high-speed channel to be disconnected. The system determines whether the aircraft has reached the preset working point based on the real-time positioning information of the carrier aircraft. If it has, the system controls the corresponding detector to work according to the preset working mode of that working point. If not, the system controls the composite detection device to standby. The working modes include radar working mode and infrared working mode.

9. The fully automated airborne flight test method for a composite detection device as described in claim 8, characterized in that, The method further includes: When the radar detector is working, the first power supply channel is used to power the radar transmitter, and the second power supply channel is used to power all components in the composite detection device except the radar transmitter. When the infrared detector is working, the second power supply channel is used to power all components in the composite detection device except the radar transmitter.

10. The fully automated airborne flight test method for a composite detection device as described in claim 8, characterized in that, The method further includes: When the radar detector is working, a high-speed channel is used to receive the radar detection results output by the radar detector, and a bus channel is used to exchange data between the control computer and the composite detection device. When the infrared detector is working, the bus channel is used to receive the infrared detection results output by the infrared detector and to exchange data between the control computer and the composite detection device.

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