Testing equipment and method for verifying semi-active guidance loop signal
By verifying the test equipment and methods of semi-active guidance loop signals, the problem of being unable to verify the integrity of the guidance loop of the aircraft weapon system in the existing technology has been solved, and effective verification of the guidance loop signal and interface coordination evaluation have been achieved, ensuring the integrity of the weapon equipment.
Patent Information
- Application Number
- CN202510952955.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-07-10
- Publication Date
- 2025-09-19
AI Technical Summary
Existing technologies are unable to effectively test the complete guidance loop of an aircraft weapon system when it is operating, especially the indicator compliance and interface coordination of the semi-active guidance loop signal, and cannot meet the assessment requirements for the integrity of weapons and equipment.
Provided is a test device and method for verifying the semi-active guidance loop signal, including a follow-up electronic cabin, a data acquisition and processing combination, a control and power supply combination, and a direct wave signal receiving combination. Through cable connection and data acquisition and analysis, the device simulates the attack of enemy targets and verifies the integrity of the aircraft's guidance loop and the coordination of the interface.
It realizes the inspection of the guidance loop integrity and interface coordination when the aircraft weapon system is working, verifies the index compliance of the semi-active guidance loop signal, and provides a reliable evaluation basis for the combat readiness of weapons and equipment.
Smart Images
Figure CN120667977A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the field of measurement and control technology, and in particular, relates to a test device and method for verifying a semi-active guidance loop signal. Background Art
[0002] Semi-active guidance is a common guidance method for aircraft weapon systems. Its characteristic is that target detection and tracking are completed by external equipment, and guidance signals are sent by the external equipment to the aircraft to guide it to hit the target.
[0003] Before executing a major mission, comprehensive testing and evaluation of the weapon system's key tactical and technical performance is necessary to confirm its integrity. Conventional static testing only verifies the illumination system's illumination signal's frequency modulation noise, amplitude modulation noise, and command signal transmission accuracy, but cannot fully verify the complete guidance loop of the aircraft's weapon system during operation. Therefore, new testing methods and equipment are necessary to verify the compliance of the semi-active guidance loop signal indicators, complete the evaluation of the illumination system's guidance power, and provide a basis for equipment integrity. Summary of the Invention
[0004] In view of the defects in the prior art, the object of the present invention is to provide a test device and method for verifying the semi-active guidance loop signal.
[0005] According to the present invention, a test device for verifying a semi-active guidance loop signal comprises: a follow-up electronic cabin, a data acquisition and processing assembly, a control and power supply assembly, and a direct wave signal receiving assembly;
[0006] The following flight electronic cabin is connected to the data acquisition and processing combination via X1, X2, and X3 cables;
[0007] The two sets of primary power supplies in the X1 cable interface provide regulated power to the radio equipment, inertial measurement unit, and onboard computer in the flight electronics compartment. The flight electronics compartment feeds back the bomb motion and aircraft tuning signals to the data recording and analysis equipment of the control and power supply combination via the X2 cable, and feeds back the radio equipment direct wave and echo lock status to the data recording and analysis equipment via the X3 cable.
[0008] The data acquisition and processing assembly is connected to the control device via an X4 cable to receive instructions from the control device;
[0009] The control and power supply combination is connected to the data acquisition and processing combination's data logger via cable X5, and the outputs of the power supplies of groups A and B and the power supply monitoring are connected to the data acquisition and processing combination via cable X6.
[0010] Preferably, the following flight electronic cabin receives the illumination signal through the direct wave antenna and receives the echo signal reflected by the target through the echo antenna; the inertial measurement device in the following flight electronic cabin is used to measure the attitude angle of the following flight electronic cabin; the onboard computer in the following flight electronic cabin communicates with the ground launch and control equipment through the serial port, completes the binding of radio equipment parameters according to the instructions of the launch and control equipment, and reports to the launch and control equipment whether the aircraft is ready.
[0011] Preferably, the data acquisition and processing combination realizes the power-on and power-off control, excitation control, simulation feedback of the control signal and the acquisition of various data of the flight-following electronic cabin; the interface adapter combination in the data acquisition and processing combination is used to receive instructions from the data collector to realize the power-on / off control and signal switching of the flight-following electronic cabin; the data acquisition and processing software in the data acquisition and processing combination includes flight-following detection software, equipment self-test software, report processing software, and data playback software, which realize the guidance head flight-following detection, equipment self-test, flight-following data playback and analysis processing, and report generation functions.
[0012] Preferably, the control and power supply combination controls the data acquisition and processing combination related operations through the display and control unit, and displays the related processing results in real time, while providing two power supply groups A and B, and monitoring the current of the two power supply groups in real time through the power supply monitoring box.
[0013] Preferably, the direct wave receiving combination includes: a direct wave horn antenna and a direct wave adapter, which receive the direct wave irradiation signal emitted by the irradiation system; the direct wave horn antenna in the direct wave receiving combination is used to receive the direct wave irradiation signal emitted by the irradiation system, and transmit the received direct wave signal to the direct wave adapter fixed to the electronic cabin body through a standard radio frequency cable.
[0014] According to a testing method provided by the present invention, the test equipment for verifying the semi-active guidance loop signal is used to perform the test.
[0015] Preferably, it includes:
[0016] S1: Deploy the flight-following electronic cabin, data acquisition and processing assembly, control and power supply assembly, and direct wave signal receiving assembly in sequence;
[0017] S2: The fighter simulates an incoming enemy target. After the weapon system stably tracks the fighter, it issues a power-on command to the aircraft, powering up the tracking electronics compartment. After the compartment is powered up, it reports to the data acquisition and processing unit that the aircraft is powered up normally. The onboard computer communicates with the launch and control equipment, receives the target parameter binding command from the launch and control equipment, and completes the parameter setting of the radio equipment.
[0018] S3: After the fighter enters the interception range of the weapon system, the weapon system issues a launch command to the aircraft. The data acquisition and processing combination sends two bounce signals to the onboard computer through the X2 cable. The radio equipment antenna intercepts the direct wave illumination signal emitted by the illumination system and the echo reflected by the target; the data acquisition and processing combination collects and analyzes various data fed back by the flight-following electronic cabin.
[0019] Preferably, in step S1, one end of the RF cable is connected to the cable interface of the direct-wave horn antenna, and the other end of the RF cable is connected to the direct-wave adapter fixed to the flight-following electronic cabin, thereby completing the cable connection between the flight-following electronic cabin and the data acquisition and processing combination, the data acquisition and processing combination and the control and power supply combination, and the data acquisition and processing combination and the transmission and control equipment.
[0020] Preferably, it also includes:
[0021] S4: After completing an interception mission, the weapon system executes the termination of interception, and the data collection and processing combination automatically generates a follow-up flight test report.
[0022] Preferably, the test values and test index requirements of the semi-active guidance loop signal of the entire follow-up flight test are given in the report to complete the inspection of the correctness of the semi-active guidance loop signal and the coordination of the aircraft's radio frequency, electrical and communication interfaces.
[0023] Compared with the prior art, the present invention has the following beneficial effects:
[0024] The present invention can test the complete guidance loop between ground / ship-surface equipment and the aircraft when the aircraft weapon system is working, test the coordination and correctness of the radio frequency, electrical, communication and other interfaces between the illumination system and the aircraft in the aircraft weapon system adopting a semi-active guidance system, verify the index conformity of the semi-active guidance loop signal, complete the evaluation of the guidance power of the illumination system, and provide a basis for the combat readiness of weapons and equipment. BRIEF DESCRIPTION OF THE DRAWINGS
[0025] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:
[0026] Figure 1 This is a schematic diagram showing the connections for the test equipment used to verify the semi-active guidance loop signal.
[0027] The figure shows:
[0028] Follow-fly electronic cabin 1
[0029] Data Acquisition and Processing Portfolio 2
[0030] Control and power combination 3
[0031] Direct wave signal receiving combination 4
[0032] Weapon system launch and control equipment 5 DETAILED DESCRIPTION
[0033] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.
[0034] The present invention provides a test device for verifying a semi-active guidance loop signal, comprising: a follow-up electronic cabin, a data acquisition and processing assembly, a control and power supply assembly, and a direct wave signal receiving assembly;
[0035] The flight-following electronics compartment is connected to the data acquisition and processing assembly via X1, X2, and X3 cables. Two primary power supplies in the X1 cable interface provide regulated power to the radio equipment, inertial measurement unit, and onboard computer in the flight-following electronics compartment. The flight-following electronics compartment feeds back missile motion and aircraft tuning signals to the data recording and analysis equipment via the X2 cable, and feeds back radio direct wave and echo lock status to the data recording and analysis equipment via the X3 cable. The data acquisition and processing assembly is connected to the launch and control equipment via the X4 cable to receive commands from the launch and control equipment.
[0036] The flight control electronics cabin includes radio equipment, an onboard computer, an inertial measurement unit (IMU), a radome, and a cabin. It receives illumination signals via a direct wave antenna and echo signals reflected from the target via an echo antenna. The IMU in the cabin measures the cabin's attitude angle. The onboard computer communicates with ground-based launch and control equipment via a serial port, sets radio equipment parameters based on instructions from the launch and control equipment, and reports to the launch and control equipment whether the aircraft is ready.
[0037] The data acquisition and processing assembly includes a data collector, an interface adapter assembly, a self-test assembly, a chassis, and data acquisition and processing software. This enables power-on and power-off control, excitation control, simulated feedback of control signals, and data acquisition of various channels for the flight-following electronic compartment. The interface adapter assembly in the data acquisition and processing assembly receives instructions from the data collector to enable power-on and power-off control and signal switching for the flight-following electronic compartment. The data acquisition and processing software includes flight-following detection software, equipment self-test software, report processing software, and data playback software. This software enables seeker flight-following detection, equipment self-test, flight-following data playback and analysis, and report generation.
[0038] The control and power supply assembly includes a display and control unit, a DC regulated power supply group A, a DC regulated power supply group B, and a primary power supply monitoring device. The display and control unit controls operations related to the data acquisition and processing assembly and displays relevant processing results in real time. It also provides two power supply groups, A and B, and monitors the current of both power supply groups in real time via a power monitoring plug-in box. The control and power supply assembly has an adjustable output voltage of 0 to 40V, with a ripple voltage no greater than 10mV; the maximum output protection current is 38A; and the current detection module automatically shuts off the power supply when the output current exceeds 20A for group A and 10A for group B, respectively. The control and power supply assembly is connected to the data acquisition unit of the data acquisition and processing assembly via an X5 cable. The outputs of the power supply groups A and B and the power monitoring device are connected to the data acquisition and processing assembly via an X6 cable.
[0039] The direct wave receiving assembly includes a direct wave horn antenna and a direct wave adapter, which receives the direct wave illumination signal emitted by the illumination system. The direct wave horn antenna in the direct wave receiving assembly is used to receive the direct wave illumination signal emitted by the illumination system and transmit the received direct wave signal to the direct wave adapter fixed to the electronic compartment body via a standard radio frequency cable.
[0040] The present invention will be described in more detail below.
[0041] like Figure 1 As shown, when the present invention is in use, the flight-following electronic cabin 1, the data acquisition and processing combination 2, the control and power supply combination 3 and the direct wave signal receiving combination 4 are unfolded in sequence, one end of the radio frequency cable is connected to the cable interface of the horn antenna of the direct wave signal receiving combination 4, and the other end of the radio frequency cable is connected to the direct wave adapter fixed to the flight-following electronic cabin 1, completing the cable connection between the flight-following electronic cabin 1 and the data acquisition and processing combination 2, the cable connection between the data acquisition and processing combination 2 and the control and power supply combination 3, and the cable connection between the data acquisition and processing combination 2 and the transmission and control equipment 5.
[0042] The fighter simulates an incoming enemy attack. After the weapon system stably tracks the fighter, it issues an "aircraft power-on" command to power up the following electronic cabin 1. After the following electronic cabin 1 is powered up, it reports "aircraft power-on is normal" to the data acquisition and processing assembly 2. The onboard computer communicates with the launch and control equipment 5, receives the target parameter binding instruction from the launch and control equipment 5, and completes the radio equipment parameter setting.
[0043] After the fighter enters the weapon system's interception range, the weapon system issues an "aircraft launch" command. The data acquisition and processing unit 2 sends two bounce signals to the onboard computer via the X2 cable. The radio equipment antenna then intercepts the direct wave illumination signal emitted by the illumination system and the echo reflected by the target. The data acquisition and processing unit 2 collects and analyzes the various data fed back by the flight tracking electronic cabin 1.
[0044] After completing the interception mission, the weapon system terminates the interception, and the data acquisition and processing combination 2 automatically generates a flight-following test report. During the flight-following test, the semi-active guidance loop signal test values and test index requirements are given in the report. The results show that the irradiation frequency coordination, irradiation power and predetermined error are all qualified.
[0045] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.
[0046] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.
Claims
1. A test device for verifying a semi-active guidance loop signal, characterized in that: include: Flight-following electronic cabin, data acquisition and processing combination, control and power supply combination, direct wave signal receiving combination; The following flight electronic cabin is connected to the data acquisition and processing combination via X1, X2, and X3 cables; The two sets of primary power supplies in the X1 cable interface provide regulated power to the radio equipment, inertial measurement unit, and onboard computer in the flight electronics compartment. The flight electronics compartment feeds back the bomb motion and aircraft tuning signals to the data recording and analysis equipment of the control and power supply combination via the X2 cable, and feeds back the radio equipment direct wave and echo lock status to the data recording and analysis equipment via the X3 cable. The data acquisition and processing assembly is connected to the control device via an X4 cable to receive instructions from the control device; The control and power supply combination is connected to the data acquisition and processing combination's data logger via cable X5, and the outputs of the power supplies of groups A and B and the power supply monitoring are connected to the data acquisition and processing combination via cable X6.
2. The test equipment for verifying the semi-active guidance loop signal according to claim 1, characterized in that: The following flight electronic cabin receives the illumination signal through the direct wave antenna and receives the echo signal reflected by the target through the echo antenna; the inertial measurement device in the following flight electronic cabin is used to measure the attitude angle of the following flight electronic cabin; the on-board computer in the following flight electronic cabin communicates with the ground launch and control equipment through the serial port, completes the binding of radio equipment parameters according to the instructions of the launch and control equipment, and reports to the launch and control equipment whether the aircraft is ready.
3. The test equipment for verifying the semi-active guidance loop signal according to claim 1, characterized in that: The data acquisition and processing combination realizes the power-on and power-off control, excitation control, control signal simulation feedback and various data acquisition of the flight-following electronic cabin; the interface adapter combination in the data acquisition and processing combination is used to receive instructions from the data collector to realize the power-on / off control and signal switching of the flight-following electronic cabin; the data acquisition and processing software in the data acquisition and processing combination includes flight-following detection software, equipment self-test software, report processing software, and data playback software, which realize the guidance head flight-following detection, equipment self-test, flight-following data playback and analysis processing, and report generation functions.
4. The test equipment for verifying the semi-active guidance loop signal according to claim 1, characterized in that: The control and power supply combination controls the data acquisition and processing combination related operations through the display and control unit, and displays the related processing results in real time. At the same time, it provides two power supply groups A and B, and monitors the current of the two power supply groups in real time through the power supply monitoring box.
5. The test equipment for verifying the semi-active guidance loop signal according to claim 1, characterized in that: The direct wave receiving combination includes: a direct wave horn antenna and a direct wave adapter, which receive the direct wave illumination signal emitted by the illumination system; the direct wave horn antenna in the direct wave receiving combination is used to receive the direct wave illumination signal emitted by the illumination system, and transmit the received direct wave signal to the direct wave adapter fixed on the electronic cabin body through a standard radio frequency cable.
6. A testing method, characterized in that: The test is performed using the test equipment for verifying the semi-active guidance loop signal according to any one of claims 1 to 5.
7. The testing method according to claim 6, characterized in that: include: S1: Deploy the flight-following electronic cabin, data acquisition and processing assembly, control and power supply assembly, and direct wave signal receiving assembly in sequence; S2: The fighter simulates an incoming enemy target. After the weapon system stably tracks the fighter, it issues a power-on command to the aircraft, powering up the tracking electronics compartment. After the compartment is powered up, it reports to the data acquisition and processing unit that the aircraft is powered up normally. The onboard computer communicates with the launch and control equipment, receives the target parameter binding command from the launch and control equipment, and completes the parameter setting of the radio equipment. S3: After the fighter enters the interception range of the weapon system, the weapon system issues a launch command to the aircraft. The data acquisition and processing combination sends two bounce signals to the onboard computer through the X2 cable. The radio equipment antenna intercepts the direct wave illumination signal emitted by the illumination system and the echo reflected by the target; the data acquisition and processing combination collects and analyzes various data fed back by the flight-following electronic cabin.
8. The testing method according to claim 7, characterized in that: In step S1, one end of the RF cable is connected to the cable interface of the direct-wave horn antenna, and the other end of the RF cable is connected to the direct-wave adapter fixed to the flight-following electronic cabin, thereby completing the cable connection between the flight-following electronic cabin and the data acquisition and processing combination, the data acquisition and processing combination and the control and power supply combination, and the data acquisition and processing combination and the transmission and control equipment.
9. The testing method according to claim 7, characterized in that: Also includes: S4: After completing an interception mission, the weapon system executes the termination of the interception, and the data collection and processing combination automatically generates a follow-up flight test report.
10. The testing method according to claim 9, characterized in that: The test values and test index requirements of the semi-active guidance loop signal of the entire flight test are given in the report, completing the inspection of the correctness of the semi-active guidance loop signal and the coordination of the aircraft's radio frequency, electrical and communication interfaces.