Aircraft circuit detection device and method

Abstract

The invention relates to an aircraft circuit detection device and method, belongs to the technical field of detection, and solves the problem that the correctness of an aircraft circuit is difficult to determine before an aircraft is launched. The device comprises a signal generation module which is used for storing a preset simulation instruction and a control signal, providing the simulation instruction and the control signal to an aircraft after detection is started to generate an aircraft feedback signal and transmitting the aircraft feedback signal to a signal conditioning detection module; the signal conditioning detection module receives and detects the aircraft feedback signal, and then provides the detected aircraft feedback signal to different indicating lamps to determine whether the feedback signal is qualified; under the condition that the self-checking module is not connected with the aircraft, an equivalent correct signal and a signal exceeding the marked tolerance are sequentially generated and provided for an internal circuit of the aircraft circuit detection device so as to generate a self-checking feedback signal, and the self-checking feedback signal is provided for a self-checking indicator lamp so as to determine whether the internal circuit is qualified or not. And the real-time state of the aircraft is timely mastered to find the fault aircraft.

Description

Technical Field

[0001] The present invention relates to the field of detection technology, and in particular to an aircraft circuit detection device and method. Background Art

[0002] Laser beam-riding guidance is a remote-controlled guidance method with man-in-the-loop and semi-automatic tracking. It can be applied to weapon systems such as anti-tank aircraft and individual air defense aircraft. In this guidance method, when the aircraft is launched, the laser launch device emits a laser beam to illuminate the target. The center line of the laser beam coincides with the aiming line. After the aircraft is launched, it immediately enters the laser beam and keeps flying in the laser beam until it hits the target. In order to achieve the guidance of the aircraft, the laser beam must be spatially frequency encoded to form a laser information field. On the circular cross-section perpendicular to the laser information field and the central axis of the laser, the frequency encoding of different position points is different.

[0003] When the aircraft flies in the laser beam, the laser receiving device at its tail will receive the laser coding information of its location, and then convert the optical signal into an electrical signal, filter and amplify it, and send it to the instruction forming device. The instruction forming device processes the electrical signal to obtain the coordinate deviation of the aircraft's location relative to the laser center axis in the azimuth and height directions, and forms a control instruction based on the deviation. The aircraft servo drives the rudder to deflect according to the control instruction output by the instruction forming device, generates a control torque for the aircraft, and comprehensively controls the yaw and pitch motion of the aircraft, so that the aircraft always flies along the center line of the laser beam until it hits the target.

[0004] Whether the aircraft control command can be formed normally directly determines the aircraft's hit effect, and the formation process of the control command depends on the aircraft circuit. Therefore, how to effectively detect the performance parameters of the aircraft circuit, such as voltage, current, power amplifier, coordinate deviation output signal, etc., has become an important issue in the use of aircraft.

[0005] In the current technical solution, the component detection method is mainly used. That is, before the overall assembly of the aircraft, the parameters of each compartment involved in the aircraft circuit are tested separately to ensure the correctness of the circuit characteristics of each compartment, and then the compartments are connected and assembled.

[0006] The component inspection method has two main deficiencies: first, although the circuit parameters of each compartment of the aircraft have been inspected and guaranteed to be qualified, the overall assembled aircraft has not been inspected; second, the status of the aircraft may change after storage, transportation and service processing, especially the status of the aircraft before launch is difficult to determine. Summary of the invention

[0007] In view of the above analysis, the embodiments of the present invention aim to provide an aircraft circuit detection device and method to solve the problem that it is difficult to determine the correctness of the aircraft circuit before the aircraft is launched.

[0008] On the one hand, an embodiment of the present invention provides an aircraft circuit detection device, comprising: an aircraft circuit detection device, comprising: a signal generating module, which is used to store a predetermined analog command signal and a control signal, and after the aircraft circuit detection starts, the analog command signal and the control signal are provided to the aircraft to generate an aircraft feedback signal and transmit it to a signal conditioning detection module, wherein a control mechanism generates a control signal according to the analog command signal, and the aircraft circuit generates the aircraft feedback signal according to the control signal; the signal conditioning detection module is used to receive the aircraft feedback signal and provide the detected aircraft feedback signal to different indicator lights after detecting the aircraft feedback signal to determine whether the feedback signal is qualified; and a self-test module is used to generate an equivalent correct signal and a signal exceeding the marked tolerance in sequence without connecting to the aircraft, and provide them to the internal circuit of the aircraft circuit detection device to generate a self-test feedback signal, and then provide the self-test feedback signal to the self-test indicator light to determine whether the internal circuit of the aircraft circuit detection device is qualified.

[0009] The beneficial effects of the above technical solution are as follows: by detecting the aircraft at different times such as storage, transportation, service processing and before launch, the real-time status of the aircraft can be grasped in time, and faulty aircraft can be discovered in advance, effectively avoiding the serious consequences caused by launching a faulty aircraft.

[0010] Based on further improvement of the above-mentioned device, the aircraft circuit detection device also includes a cable for connecting the aircraft circuit detection device to a detection interface of an aircraft steering gear cabin, the cable including a detection end interface and an aircraft end plug, wherein the detection end interface is connected to the detection interface on the panel of the aircraft circuit detection device to transmit the analog command signal and the control signal and receive the aircraft feedback signal through the detection interface on the panel of the aircraft circuit detection device; the aircraft end plug is connected to the detection interface of the aircraft steering gear cabin in a plug-in manner and is fastened by a plug nut to detect the aircraft circuit through the detection interface of the aircraft steering gear cabin.

[0011] Based on further improvement of the above-mentioned device, the self-test circuit includes: a self-test control signal generator, which is used to generate an equivalent correct signal or a signal exceeding the marked tolerance range and provide it to the internal circuit of the detection device, so that the output end of the internal circuit outputs a first self-test output signal or a second self-test output signal; a detection circuit switching switch, which is used to switch the first self-test mode to the second self-test mode, wherein in the first self-test mode, the equivalent correct signal is provided to the internal circuit of the aircraft circuit detection device, and in the second self-test mode, the signal exceeding the marked tolerance range is provided to the internal circuit of the aircraft circuit detection device; an out-of-tolerance signal output circuit, which is connected to the output end of the internal circuit via the detection circuit switching switch, and is used to receive and output the second self-test output signal from the output end of the internal circuit; an A / D converter, which is used to output the second self-test output signal from the internal circuit The end receives the first self-test output signal or receives the second self-test output signal from the out-of-tolerance signal output circuit, performs analog-to-digital conversion on the first self-test output signal and the second self-test output signal and provides them to the MCU; the MCU is used to compare the first self-test output signal with a pre-stored reference first self-test signal to determine whether the first self-test output signal meets the requirements or compare the second self-test output signal with a pre-stored reference second self-test signal to determine whether the second self-test output signal meets the requirements; a self-test indicator light includes a green self-test indicator light and a red self-test indicator light, wherein when the first self-test output signal and the second self-test output signal of the MCU meet the requirements, the green self-test indicator light is on; when the first self-test output signal and the second self-test output signal of the MCU do not meet the requirements, the red self-test indicator light is on.

[0012] Based on further improvements of the above-mentioned device, the internal circuit of the detection device includes a voltage detection circuit, a current detection circuit, an amplifier detection circuit and a command detection circuit, wherein the voltage detection circuit is used to detect the power supply voltage of the aircraft circuit to determine whether the power supply voltage meets the requirements; the current detection circuit is used to detect the power consumption current of the aircraft circuit to determine whether the power consumption current meets the requirements; the amplifier detection circuit is used to detect whether the working state of the aircraft servo amplifier is normal through the analog command signal and the control signal; the command detection circuit is used to input the aircraft position deviation signal into the aircraft command formation device through the analog command signal to detect whether the aircraft control command is normal.

[0013] Based on further improvements of the above-mentioned device, the current detection circuit includes: a measuring resistor, used to detect the power consumption current value from the detection resistor of the power consumption current flowing through the aircraft circuit; an amplifier, used to amplify the power consumption current value; an analog switch, used to provide the amplified power consumption current value to the A / D converter via the analog switch; the A / D converter is used to perform analog-to-digital conversion on the amplified power consumption current value and provide the digital power consumption current value to the MCU; the MCU is used to compare the digital power consumption current value with a pre-stored reference power consumption current value to determine whether the digital power consumption current value meets the requirements; the current indicator light includes a red current indicator light and a green current indicator light, wherein when the power consumption current value of the MCU does not meet the requirements, the red current indicator light is on, and when the power consumption current value of the MCU meets the requirements, the green current indicator light is on.

[0014] Based on the further improvement of the above device, the amplifier detection circuit includes: an amplifier control signal generation submodule, which is used to generate an amplifier control signal and provide the amplifier control signal to the aircraft servo amplifier; an amplifier voltage detection submodule, which is used to detect the amplifier voltage from the aircraft servo amplifier and apply it to both ends of the servo potentiometer; a servo potentiometer detection submodule, which is used to detect the current value flowing through the servo potentiometer or the voltage value at both ends; the A / D converter, which is used to perform analog-to-digital conversion on the current value or voltage value of the servo potentiometer, and provide the analog-to-digital converted current value or voltage value to the MCU; the MCU, which is used to compare the analog-to-digital converted current value or voltage value with a pre-stored reference current value or voltage value to determine whether the analog-to-digital converted current value or voltage value meets the requirements; the amplifier indicator light, including a red amplifier indicator light and a green amplifier indicator light, wherein when the current value of the servo potentiometer of the MCU does not meet the requirements, the red amplifier indicator light is on; and when the current value of the servo potentiometer of the MCU meets the requirements, the green amplifier indicator light is on.

[0015] Based on further improvements of the above-mentioned device, the instruction detection circuit includes: a control signal generation submodule, which is used to generate an analog instruction signal and provide it to an aircraft instruction forming device; a Uz detection submodule, which is used to detect a Uz voltage signal from the output end of the aircraft instruction forming device; a Uy detection submodule, which is used to detect a Uy voltage signal from the output end of the aircraft instruction forming device; the A / D converter, which is used to perform analog-to-digital conversion on the Uz voltage signal and the Uy voltage signal and provide the Uz voltage signal and the Uy voltage signal in digital form to the MCU; the MCU, which is used to compare the Uz voltage signal and the Uy voltage signal in digital form with a pre-stored reference Uz voltage signal and a reference Uy voltage signal to determine whether the Uz voltage signal and the Uy voltage signal values ​​meet the requirements; the instruction indicator light, which includes a red instruction indicator light and a green instruction indicator light, wherein when the Uz voltage signal and the Uy voltage signal of the MCU do not meet the requirements, the red instruction indicator light is on; when the Uz voltage signal and the Uy voltage signal of the MCU meet the requirements, the green instruction indicator light is on.

[0016] On the other hand, an embodiment of the present invention provides an aircraft circuit detection method, comprising: connecting an aircraft circuit detection device to a detection interface of an aircraft steering gear cabin via a cable; initializing an MCU to determine a working mode of the aircraft circuit detection device, wherein the working mode includes a self-test working mode, an aircraft circuit detection working mode, and a calibration working mode; when the aircraft circuit detection device is in the self-test working mode, generating an equivalent correct signal or a signal exceeding a marked tolerance range, providing it to an internal circuit of the aircraft circuit detection device to output a first self-test output signal or a second self-test output signal, and according to whether the first self-test output signal or the second self-test output signal meets the requirements, making a green or red self-test indicator light; after the self-test of the aircraft circuit detection device is qualified, switching the self-test working mode to the aircraft detection working mode through a mode switching switch; detecting the power supply voltage, power consumption current, aircraft steering gear amplifier, and aircraft instruction forming device of the aircraft circuit in sequence, so as to determine whether the power supply voltage, power consumption current, aircraft steering gear amplifier, and aircraft instruction forming device of the aircraft circuit meet the requirements, so that the corresponding green indicator light or red indicator light.

[0017] Based on the further improvement of the above method, when the aircraft circuit detection device is in the self-test working mode, an equivalent correct signal or a signal exceeding the marked tolerance range is generated and provided to the internal circuit of the aircraft circuit detection device to output a first self-test output signal or a second self-test output signal, and according to whether the first self-test output signal or the second self-test output signal meets the requirements, a green or red self-test indicator light is turned on, further comprising: generating an equivalent correct signal or a signal exceeding the marked tolerance range through a self-test control signal generator and providing it to the internal circuit of the aircraft circuit detection device, so that the output end of the internal circuit outputs the first self-test output signal or the second self-test output signal; switching the first self-test mode to the second self-test mode through a detection circuit switching switch, wherein in the first self-test mode, the equivalent correct signal is provided to the internal circuit of the aircraft circuit detection device, and in the second self-test mode, the signal exceeding the marked tolerance range is provided to the internal circuit of the aircraft circuit detection device; exceeding the tolerance The signal output circuit is connected to the output end of the internal circuit via the detection circuit switching switch, and is used to receive and output the second self-test output signal from the output end of the internal circuit; receive the first self-test output signal from the output end of the internal circuit or receive the second self-test output signal from the excess signal output submodule through an A / D converter, perform analog-to-digital conversion on the first self-test output signal and the second self-test output signal and provide them to the MCU; the MCU is used to compare the first self-test output signal or the second self-test output signal with a pre-stored reference first self-test signal and a reference second self-test signal to determine whether the first self-test output signal and the second self-test output signal meet the requirements; when the first self-test output signal and the second self-test output signal of the MCU meet the requirements, the green self-test indicator light is on; when the first self-test output signal and the second self-test output signal of the MCU do not meet the requirements, the red self-test indicator light is on and the self-test working mode is stopped.

[0018] Based on the further improvement of the above method, the power supply voltage, power consumption current, aircraft servo amplifier and aircraft instruction forming device of the aircraft circuit are detected in sequence, so as to determine whether the power supply voltage, power consumption current, aircraft servo amplifier and aircraft instruction forming device of the aircraft circuit meet the requirements, so that the corresponding green indicator light or red indicator light further includes: detecting the power supply voltage of the aircraft circuit, and then determining whether the power supply voltage meets the requirements; when the power supply voltage meets the requirements, the green voltage indicator light is on and the power consumption current of the aircraft circuit is detected, otherwise the red voltage indicator light is on and the aircraft circuit detection working mode is stopped; when it is determined that the power consumption current meets the requirements, the green current indicator light is on and the working state of the aircraft servo amplifier and the feedback potentiometer is detected, otherwise the red current indicator light is on and the aircraft circuit detection working mode is stopped; when the working state of the aircraft servo amplifier meets the requirements, the green amplifier indicator light is on and the aircraft control instruction is detected, otherwise the red amplifier indicator light is on and the aircraft circuit detection working mode is stopped; when the aircraft control instruction is normal, the green instruction indicator light is on, otherwise the red instruction indicator light is on and the aircraft circuit detection working mode is stopped.

[0019] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0020] 1. The aircraft circuit detection device of the present invention can detect the power supply voltage, power consumption current, steering gear amplifier, control instructions and other parameters of the aircraft circuit, thereby solving the problem of functional parameter detection of fixed aircraft.

[0021] 2. The present invention can timely grasp the real-time status of the aircraft by detecting the aircraft at different times such as storage, transportation, service processing and before launch, and can detect faulty aircraft in advance, effectively avoiding the serious consequences caused by launching a faulty aircraft.

[0022] In the present invention, the above-mentioned technical solutions can also be combined with each other to achieve more preferred combination solutions. Other features and advantages of the present invention will be described in the subsequent description, and some advantages can become obvious from the description, or can be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained through the contents particularly pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The drawings are only for the purpose of illustrating particular embodiments and are not to be considered limiting of the present invention. Like reference symbols denote like components throughout the drawings.

[0024] Figure 1 It is a structural diagram of an aircraft circuit detection device according to an embodiment of the present invention;

[0025] Figure 2 It is a composition diagram of an aircraft circuit detection device according to an embodiment of the present invention;

[0026] Figure 3 is a block diagram of current detection according to an embodiment of the present invention;

[0027] Figure 4 is a block diagram of an amplifier detection according to an embodiment of the present invention;

[0028] Figure 5 is a block diagram of instruction detection according to an embodiment of the present invention;

[0029] Figure 6 A block diagram of a self-test circuit according to an embodiment of the present invention;

[0030] Figure 7 A diagram showing the hardware system composition of an aircraft circuit detection device according to an embodiment of the present invention;

[0031] Figure 8 A diagram showing the software functions of an aircraft circuit detection device according to an embodiment of the present invention;

[0032] Fig. 9 A software execution control flow chart of an aircraft circuit detection device according to an embodiment of the present invention;

[0033] Fig.10 A flowchart of a self-checking mode according to an embodiment of the present invention;

[0034] Fig.11 is a flowchart of an aircraft detection mode according to an embodiment of the present invention;

[0035] Fig.12 is a flowchart of a calibration mode according to an embodiment of the present invention;

[0036] Fig.13 4 is a flow chart of an aircraft circuit detection method according to an embodiment of the present invention. DETAILED DESCRIPTION

[0037] The preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not used to limit the scope of the present invention.

[0038] like Figure 1As shown, a specific embodiment of the present invention discloses an aircraft circuit detection device including a host, a cable, a carrying case and accessories. The host may include a power module, a signal generating module, a signal conditioning detection module, a self-test circuit and a housing. The power module, the signal generating module, the signal conditioning detection module and the self-test circuit are all arranged in the housing of the host. The accessories may include a charger, spare parts and a special starter.

[0039] The signal generation module is used to store the predetermined analog command signal and control signal, and after the aircraft circuit detection starts, the analog command signal and control signal are provided to the aircraft circuit. The aircraft circuit is used to generate an aircraft feedback signal according to the control signal, and transmit the aircraft feedback signal to the signal conditioning detection module, that is, the aircraft circuit is the object to be tested. The control mechanism generates a control signal according to the analog command signal, and the aircraft circuit generates an aircraft feedback signal according to the control signal.

[0040] The signal conditioning and detection module is used to receive and detect the aircraft feedback signal, and then provide the detected aircraft feedback signal to different indicator lights to determine whether the feedback signal is qualified.

[0041] The self-test module is used to generate equivalent correct signals and signals exceeding the marked tolerance in sequence without being connected to the aircraft, and provide them to the internal circuit of the aircraft circuit detection device to generate a self-test feedback signal, and then provide the self-test feedback signal to the self-test indicator light to determine whether the internal circuit of the aircraft circuit detection device is qualified.

[0042] The cable is used to connect the aircraft circuit detection device to the detection interface of the aircraft steering gear cabin, and the cable includes a detection end interface and an aircraft end plug. The detection end interface is connected to the detection interface on the panel of the aircraft circuit detection device to transmit analog command signals and control signals through the detection interface on the panel of the aircraft circuit detection device and receive aircraft feedback signals; the aircraft end plug is connected to the detection interface of the aircraft steering gear cabin in a plug-in manner and is fastened by a plug nut to detect the aircraft circuit through the detection interface of the aircraft steering gear cabin.

[0043] Compared with the prior art, the aircraft circuit detection device provided in this embodiment can timely grasp the real-time status of the aircraft by detecting the aircraft at different times such as storage, transportation, service processing and before launch, and can discover faulty aircraft in advance, effectively avoiding the serious consequences caused by launching a faulty aircraft.

[0044] refer to Figure 2The internal circuit of the aircraft circuit detection device includes a power supply component, a current detection circuit, an amplifier detection circuit, a command detection circuit, a voltage detection circuit, a self-detection circuit and a protection circuit. The current detection circuit, the amplifier detection circuit, the command detection circuit, the voltage detection circuit and the self-detection circuit share the same A / D converter.

[0045] Specifically, the self-test circuit includes a self-test control signal generator, which is used to generate an equivalent correct signal or a signal exceeding the marked tolerance range and provide it to the internal circuit of the aircraft circuit detection device, so that the output end of the internal circuit outputs a first self-test output signal or a second self-test output signal; a detection circuit switching switch, which is used to switch the first self-test mode to the second self-test mode, wherein in the first self-test mode, the equivalent correct signal is provided to the internal circuit of the aircraft circuit detection device, and in the second self-test mode, the signal exceeding the marked tolerance range is provided to the internal circuit of the aircraft circuit detection device; an out-of-tolerance signal output circuit, which is connected to the output end of the internal circuit via the detection circuit switching switch, and is used to receive and output the second self-test output signal from the output end of the internal circuit; an A / D converter, which is used to output the second self-test output signal from the internal circuit The end receives the first self-test output signal or receives the second self-test output signal from the out-of-tolerance signal output circuit, performs analog-to-digital conversion on the first self-test output signal and the second self-test output signal and provides them to the MCU; the MCU is used to compare the first self-test output signal with a pre-stored reference first self-test signal to determine whether the first self-test output signal meets the requirements or compare the second self-test output signal with a pre-stored reference second self-test signal to determine whether the second self-test output signal meets the requirements; a self-test indicator light, including a green self-test indicator light and a red self-test indicator light, wherein when the first self-test output signal and the second self-test output signal of the MCU meet the requirements, the green self-test indicator light is on; when the first self-test output signal and the second self-test output signal of the MCU do not meet the requirements, the red self-test indicator light is on.

[0046] The voltage detection circuit is used to detect the power supply voltage of the aircraft circuit to determine whether the power supply voltage meets the requirements. For example, when the detected power supply voltage is greater than U(1+5%)V or less than U(1-5%)V, it does not meet the requirements.

[0047] The current detection circuit is used to detect the power consumption current of the aircraft circuit to determine whether the power consumption current meets the requirements. Specifically, the current detection circuit includes: a measuring resistor, which is used to detect the power consumption current value from the detection resistor of the power consumption current flowing through the aircraft circuit; an amplifier, which is used to amplify the power consumption current value; an analog switch, which is used to provide the amplified power consumption current value to the A / D converter via the analog switch; the A / D converter, which is used to perform analog-to-digital conversion on the amplified power consumption current value and provide the digital power consumption current value to the MCU; the MCU, which is used to compare the digital power consumption current value with the pre-stored reference power consumption current value to determine whether the digital power consumption current value meets the requirements; the current indicator light includes a red current indicator light and a green current indicator light, wherein when the power consumption current value of the MCU does not meet the requirements, the red current indicator light is on, and when the power consumption current value of the MCU meets the requirements, the green current indicator light is on. For example, when the power consumption current value is greater than I (1+5%) or less than I (1-5%), the power consumption current value does not meet the requirements.

[0048] The amplifier detection circuit is used to detect whether the working state of the aircraft servo amplifier is normal through analog command signals and control signals.

[0049] Specifically, the amplifier detection circuit includes: an amplifier control signal generating submodule, which is used to generate an amplifier control signal and provide the amplifier control signal to the aircraft servo amplifier; an amplifier voltage detecting submodule, which is used to detect the amplifier voltage from the aircraft servo amplifier and apply it to both ends of the servo potentiometer; a servo potentiometer detecting submodule, which is used to detect the current value flowing through the servo potentiometer or the voltage value at both ends; an A / D converter, which is used to perform analog-to-digital conversion on the current value or voltage value of the servo potentiometer and provide the analog-to-digital converted current value or voltage value to the MCU; the MCU, which is used to compare the analog-to-digital converted current value or voltage value with a pre-stored reference current value or voltage value to determine whether the analog-to-digital converted current value or voltage value meets the requirements; the amplifier indicator light includes a red amplifier indicator light and a green amplifier indicator light, wherein when the current value of the servo potentiometer of the MCU does not meet the requirements, the red amplifier indicator light is on; and when the current value of the servo potentiometer of the MCU meets the requirements, the green amplifier indicator light is on.

[0050] The command detection circuit is used to input the aircraft position deviation signal into the aircraft command forming device through simulating the command signal and the control signal to detect whether the aircraft control command is normal.

[0051] Specifically, the instruction detection circuit includes: a control signal generation submodule, which is used to generate an analog instruction signal and provide it to an aircraft instruction forming device; a Uz detection submodule, which is used to detect a Uz voltage signal from the output end of the aircraft instruction forming device; a Uy detection submodule, which is used to detect a Uy voltage signal from the output end of the aircraft instruction forming device; an A / D converter, which is used to perform analog-to-digital conversion on the Uz voltage signal and the Uy voltage signal and provide the Uz voltage signal and the Uy voltage signal in digital form to the MCU; the MCU, which is used to compare the digital Uz voltage signal and the Uy voltage signal with a pre-stored reference Uz voltage signal and a reference Uy voltage signal to determine whether the Uz voltage signal and the Uy voltage signal values ​​meet the requirements; and an instruction indicator light, which includes a red instruction indicator light and a green instruction indicator light, wherein when the Uz voltage signal and the Uy voltage signal of the MCU do not meet the requirements, the red instruction indicator light is on; when the Uz voltage signal and the Uy voltage signal of the MCU meet the requirements, the green instruction indicator light is on.

[0052] Another specific embodiment of the present invention discloses an aircraft circuit detection method, including: in step S1301, connecting an aircraft circuit detection device to a detection interface of an aircraft steering gear cabin via a cable; in step S1302, initializing an MCU to determine a working mode of the aircraft circuit detection device, wherein the working mode includes a self-test working mode, an aircraft circuit detection working mode, and a calibration working mode; in step S1303, when the aircraft circuit detection device is in the self-test working mode, generating an equivalent correct signal or a signal exceeding the marked tolerance range, and providing it to an internal circuit of the aircraft circuit detection device to output a first self-test output signal or a first calibration output signal. In step S1304, after the self-test of the aircraft circuit detection device is qualified, the self-test working mode is switched to the aircraft detection working mode through the mode switching switch; in step S1305, the power supply voltage, power consumption current, aircraft servo amplifier and aircraft instruction forming device of the aircraft circuit are detected in sequence to determine whether the power supply voltage, power consumption current, aircraft servo amplifier and aircraft instruction forming device of the aircraft circuit meet the requirements, so that the corresponding green indicator light or red indicator light is on.

[0053] Specifically, when the aircraft circuit detection device is in the self-test working mode, an equivalent correct signal or a signal exceeding the marked tolerance range is generated and provided to the internal circuit of the aircraft circuit detection device to output a first self-test output signal or a second self-test output signal, and a green or red self-test indicator light is turned on according to whether the first self-test output signal or the second self-test output signal meets the requirements. The method further includes: generating an equivalent correct signal or a signal exceeding the marked tolerance range through a self-test control signal generator and providing it to the internal circuit of the aircraft circuit detection device, so that the output end of the internal circuit outputs the first self-test output signal or the second self-test output signal; switching the first self-test mode to the second self-test mode through a detection circuit switching switch, wherein in the first self-test mode, the equivalent correct signal is provided to the internal circuit of the aircraft circuit detection device, and in the second self-test mode, the signal exceeding the marked tolerance range is provided to the internal circuit of the aircraft circuit detection device. Internal circuit; the out-of-tolerance signal output circuit is connected to the output end of the internal circuit via the detection circuit switching switch, and is used to receive and output the second self-test output signal from the output end of the internal circuit; the first self-test output signal is received from the output end of the internal circuit or the second self-test output signal is received from the out-of-tolerance signal output submodule through an A / D converter, and the first self-test output signal and the second self-test output signal are analog-to-digital converted and provided to the MCU; the MCU is used to compare the first self-test output signal or the second self-test output signal with the pre-stored reference first self-test signal and the reference second self-test signal to determine whether the first self-test output signal and the second self-test output signal meet the requirements; when the first self-test output signal and the second self-test output signal of the MCU meet the requirements, the green self-test indicator light is on; when the first self-test output signal and the second self-test output signal of the MCU do not meet the requirements, the red self-test indicator light is on and the self-test working mode is stopped.

[0054] Specifically, the power supply voltage, power consumption current, aircraft servo amplifier and aircraft instruction forming device of the aircraft circuit are detected in sequence to determine whether the power supply voltage, power consumption current, aircraft servo amplifier and aircraft instruction forming device of the aircraft circuit meet the requirements, so that the corresponding green indicator light or red indicator light further includes: detecting the power supply voltage of the aircraft circuit, and then determining whether the power supply voltage meets the requirements; when the power supply voltage meets the requirements, the green voltage indicator light is on and the power consumption current of the aircraft circuit is detected, otherwise the red voltage indicator light is on and the aircraft circuit detection working mode is stopped; when it is determined that the power consumption current meets the requirements, the green current indicator light is on and the working state of the aircraft servo amplifier is detected, otherwise the red current indicator light is on and the aircraft circuit detection working mode is stopped; when the working states of the aircraft servo amplifier and the feedback potentiometer meet the requirements, the green amplifier indicator light is on and the aircraft control instruction is detected, otherwise the red amplifier indicator light is on and the aircraft circuit detection working mode is stopped; when the aircraft control instruction is normal, the green instruction indicator light is on, otherwise the red instruction indicator light is on and the aircraft circuit detection working mode is stopped.

[0055] In the following, reference Figures 1 to 12 , an aircraft circuit detection device according to an embodiment of the present invention is described in detail by way of specific examples.

[0056] 1. System composition

[0057] refer to Figure 1 The aircraft circuit detection device is mainly composed of a main unit, cables, a carrying case and accessories. The main unit is mainly composed of a power module, a signal generation module, a signal conditioning detection module, a self-calibration module, a shell, etc. The accessories are composed of a charger, spare parts, a special starter, etc.

[0058] In the aircraft circuit detection device, the signal generation module is used to store the pre-set simulation command information and control signals. When the detection starts, the simulation command information and control signals are sent to the aircraft according to the prescribed detection procedure. During the detection process, after the aircraft receives the control signal, it will transmit the feedback signal to the signal conditioning detection module in the aircraft circuit detection device. After the signal conditioning detection module detects the feedback signal of the aircraft circuit, it will display whether the feedback signal is qualified with different indicator lights. The self-test of the aircraft circuit detection device refers to the self-test circuit generating equivalent correct information and information exceeding the marked tolerance in sequence without connecting to the aircraft, and displaying whether the internal circuit of the aircraft circuit detection device is qualified through the corresponding indicator lights.

[0059] 2. Working Principle

[0060] The aircraft circuit detection device uses the detection interface of the aircraft steering cabin, connects the detection device to this interface through a cable, and outputs analog command information and control signals to the aircraft through the signal generation module according to the detection program, and detects the feedback signal of the aircraft circuit through the signal conditioning detection module. The detection data and results are sent to the display screen of the detection device through the serial port for status display and data storage.

[0061] The aircraft circuit detection device is a semi-automatic detection instrument that realizes the self-test function through the self-test circuit and is used to check the circuit integrity of the aircraft circuit detection device. The aircraft circuit detection device generates control instructions for controlling the aircraft (the control instructions are set in advance and stored in the aircraft circuit detection device. After the detection starts, they can be sent to the aircraft according to the detection program) and transmits them to the aircraft. Then, the corresponding output components of the aircraft are tested for marked tolerances, and the test results are automatically distinguished as "normal" and "faulty", and the results are displayed with indicator lights. The self-test function of the aircraft circuit detection device is divided into two types: the first is to send out equivalent correct information, and the second is to send out information that exceeds the marked tolerance. Within the tolerance range, the green lights of "self-test 1" and "self-test 2" are on; if it is not within the tolerance range, the red light of "faulty" is on.

[0062] The aircraft circuit detection device automatically detects the component parameters of the aircraft in the following order: when the aircraft circuit detection device is in the "aircraft detection" position when the knob switch is in the "aircraft detection" position, it first detects the power supply voltage of the aircraft circuit, then detects the power consumption current of the aircraft circuit, and then checks whether the aircraft servo amplifier and feedback potentiometer are working normally, and finally inputs the aircraft position deviation signal to the aircraft command formation device to detect whether the control command formation is normal.

[0063] According to the above detection process, the indicator lights on the panel of the aircraft circuit detection device display the detection results in two situations: If the aircraft circuit is normal, the five green indicator lights on the panel reflecting the power consumption current, amplifier circuit, zero command, azimuth command, and high and low command will light up in sequence. If a certain item is detected to be faulty, then starting from this item, the subsequent green lights will not light up, and the "fault" red light will light up. If the voltage of the power module of the aircraft circuit detection device is lower than the specified value, the "battery" red light will light up, and the power module must be charged in time using the charger in the accessories.

[0064] As long as one of the two red indicator lights "Fault" and "Battery" of the aircraft circuit detection device is lit, the aircraft circuit detection device stops detection.

[0065] 3. Workflow

[0066] 1. Take out the aircraft circuit detection device host and cable from the carrying case and place them on an open and level ground outdoors; take out the aircraft to be tested from the packaging box and place it in the arc-shaped groove on the packaging box cover, with the detection interface on the aircraft servo cabin facing upward; the head and tail of the aircraft face the direction without obstruction, and the horizontal distance between the aircraft and the aircraft circuit detection device is about 2 meters.

[0067] 2. Carry out the self-test process of the aircraft circuit detection device. The specific steps are: ① Turn on the power switch on the main panel of the aircraft circuit detection device; ② Set the knob switch to the "Self-test 1" position, and observe that the "Self-test 1" green light should be on; ③ Set the knob switch to the "Self-test 2" position, and observe that the "Self-test 2" green light should be on; ④ Set the knob switch to the "off" position. If the "fault" light is on during the "Self-test 1" and "Self-test 2" processes, stop the test.

[0068] 3. After the self-test process of the aircraft circuit detection device is completed and confirmed to be normal, prepare for the aircraft detection. The specific steps are: ① Confirm that the knob switch is in the "off" position; ② Reliably connect the detection end interface of the cable to the "detection interface" on the aircraft circuit detection device panel; ③ Use a special opener to unscrew and remove the switch on the aircraft detection interface, and place the switch facing up next to the aircraft; ④ Plug the aircraft end plug of the cable into the aircraft detection interface and tighten the plug nut.

[0069] 4. Carry out the aircraft detection process. The specific steps are as follows: ① Put the knob switch to the "aircraft detection" position, and the aircraft circuit detection device will automatically start the aircraft function detection; ② Observe that the five green indicator lights of "current", "amplifier circuit", "zero instruction", "azimuth instruction", and "high and low instruction" on the panel of the aircraft circuit detection device should light up in sequence; ③ After the detection is completed, put the knob switch to the "off" position. If the "fault" red light is on during the detection process, stop the detection immediately.

[0070] 5. Carry out aircraft inspection and collection. The specific steps are: ① Unscrew the plug nut of the aircraft end of the cable and unplug the cable plug connected to the aircraft detection interface; ② Place the switch on the aircraft detection interface and tighten it with a special opener; ③ Put the aircraft into the packaging box; ④ Remove the detection end interface of the cable from the "detection interface" on the aircraft circuit detection device panel; ⑤ Turn off the power switch on the aircraft circuit detection device host panel; ⑥ Put the aircraft circuit detection device host and cable into the carrying box.

[0071] 4. Circuit Design

[0072] refer to Figure 2The circuit design of the aircraft circuit detection device can be divided into six parts: power supply component, input component, signal generator, display component, detection control component, and self-test component.

[0073] 1. Power supply components: The working voltage of the detector circuit is ±5V, and the reference voltage of AD conversion is 2V. The ±5V voltage is generated by the DC-DC module, which is mainly used for MCU and peripheral chips, analog conversion switches and AD conversion. The reference voltage of AD conversion is generated by the reference power supply, and the output reference voltage of 2V is adjusted by the potentiometer.

[0074] 2. Current measurement: The current measurement circuit consists of a measuring resistor, an operational amplifier, an analog switch, an A / D acquisition and a result display module (reference Figure 3 ). The current detection error is required to be no greater than ±5%.

[0075] 3. Amplifier detection: After completing the current detection and confirming that it is qualified, the aircraft circuit detection device begins to detect the amplifier circuit. Figure 4 ,The amplifier detection circuit is mainly composed of control signal generation, amplifier voltage detection, servo potentiometer detection, A / D acquisition and result display module.

[0076] The aircraft servo amplifier is a key component in the aircraft control system. It is responsible for amplifying the rudder control voltage sent by the guidance computer and sending it to the servo. The amplifier usually needs to have high stability and fast response capabilities to ensure accurate control of the aircraft. The feedback potentiometer is a position sensor that is usually manufactured to maintain its original characteristics and maintain performance even after long-term use. The working principle of the feedback potentiometer is to change the terminal voltage through an adjustable resistor, generally using a sliding rheostat, and output a voltage value that is proportional to the position of the sliding contact. In the aircraft servo system, the feedback potentiometer converts the displacement of the rudder surface into a DC voltage signal output, which is then used by the control unit for position feedback.

[0077] The servo amplifier and feedback potentiometer work together to achieve precise control of the rudder surface. The servo amplifier receives the signal from the guidance system and amplifies it to drive the servo, while the feedback potentiometer provides the actual position information of the rudder surface so that the system can perform closed-loop control to ensure that the rudder surface reaches the predetermined position.

[0078] 4. Command detection: After completing the amplifier detection and confirming that it is qualified, the aircraft circuit detection device begins to perform command detection. Figure 5 ,The command detection circuit is mainly composed of control signal generation, Uz detection, Uy detection, A / D acquisition and result display modules.

[0079] The aircraft command formation device is a key part of the aircraft guidance system. It is responsible for forming guidance commands based on the comparison and calculation of the motion parameters of the target and the aircraft. These command signals will be used to control the flight direction of the aircraft to ensure that the aircraft can accurately hit the target. The main function of the aircraft command formation device is to compare and calculate the motion parameters of the target and the aircraft to form command signals.

[0080] The laser receiving component includes a laser receiver and a coordinate solving circuit, wherein the laser receiver is used to receive the modulated light signal of the laser information field and convert the light signals of different frequencies into electrical pulse signals of corresponding frequencies; the coordinate solving circuit is used to convert the electrical pulse signals into command voltage signals Uy and Uz.

[0081] 5. Voltage detection: Since the internal power source of the aircraft circuit detection device is a battery, before starting to detect the aircraft each time, you must first check whether the battery voltage meets the requirements. The power supply voltage consists of two paths, which are divided by a voltage divider and sent to the input end of the analog switch. After A / D conversion, it is compared with the marked tolerance value. If it is normal, the aircraft circuit detection device starts to detect the aircraft. If one path is lower than the rated output voltage of the battery, the red "battery" indicator light is on, indicating that the battery capacity is insufficient and the aircraft can no longer be detected. The battery must be charged.

[0082] 6. Self-test circuit: The self-test function of the aircraft circuit detection device is divided into two parts: self-test 1 and self-test 2. Self-test 1 sends the data within the qualified judgment criteria to test the internal circuit of the aircraft circuit detection device, and self-test 2 sends out-of-tolerance signals for detection. Figure 6 ,The self-test circuit is mainly composed of control signal generation, ,detection circuit switching, out-of-tolerance signal output, A / D acquisition and result display ,module.

[0083] During self-check 1, the aircraft circuit detection device will compare the collected values ​​with the marked tolerances in turn. If the green light of "self-check 1" is on, it means that the detector program and circuit are working normally. During self-check 2, if all the information sent in exceeds the tolerance range, the self-check result should be that the red indicator light of "self-check 2" is on, which can verify the correctness of the aircraft circuit detection device program and circuit from another perspective.

[0084] 7. Protection circuit: The protection circuit is set to prevent the detection circuit from being damaged by overvoltage of the external power supply. When the positive power supply is greater than 14V or the negative power supply is less than -14V, the "overvoltage" indicator light will light up and the aircraft circuit detection device will stop working.

[0085] 5. Software Design

[0086] refer to Figure 7The aircraft circuit detection device software includes two configuration items: the main control software and the display board software. The main control software runs on the main control circuit board of the detector, and is mainly used to complete the detection of the aircraft and the self-test and calibration of the aircraft circuit detection device, and send the results to the display board for display; the display board software runs on the display system of the aircraft circuit detection device, receives the data sent by the main control circuit board, and can store, query, delete and other operations on the data.

[0087] The aircraft circuit detection device software includes four functional states, namely initialization settings, detection device self-test, aircraft detection and parameter calibration.

[0088] Beneficial effects: 1. The present invention adopts a circuit detection method for fixed aircraft before launch. Through the aircraft circuit detection device in the present invention, the power supply voltage, power consumption current, steering gear amplifier, control instructions and other parameters of the aircraft circuit can be detected, solving the problem of functional parameter detection of fixed aircraft. 2. The present invention can timely grasp the real-time status of the aircraft by detecting the aircraft at different times such as storage, transportation, service processing and before launch, and can detect faulty aircraft in advance, effectively avoiding the serious consequences caused by launching faulty aircraft.

[0089] refer to Figure 8 The detector software can be divided into 4 functional states, namely initialization settings, product self-test, product testing, and calibration mode.

[0090] The execution control process of the detector software is as follows: Fig. 9 shown.

[0091] (1) Initialization settings

[0092] The software initialization setting is to initialize the setting parameters of the MCU.

[0093] The initialization unit completes the initialization function of the timer and IO port by configuring the registers.

[0094] (2) Self-test (reference Fig.10 )

[0095] (3) Product testing (reference Fig.11 )

[0096] (4) Calibration mode (reference Fig.12 ): There are 11 calibration commands in total in the calibration mode. The software functions corresponding to the calibration commands are shown in Table 1.

[0097] Table 1: Calibration mode calibration command software execution operation mapping table

[0098] Serial number Software Features 1 Power supply detection 2 Positive current detection 3 Negative current detection 4 0 instruction Uz detection 5 0 instruction Uy detection 6 -1 Command Uz detection 7 -1 command Uy detection 8 +1 Command Uz Detection 9 +1 Command Uy Detection 10 Positive amplifier detection 11 Negative Amplifier Detection

[0099] Those skilled in the art will appreciate that all or part of the processes of the above-mentioned embodiments can be implemented by instructing related hardware through a computer program, and the program can be stored in a computer-readable storage medium, wherein the computer-readable storage medium is a disk, an optical disk, a read-only storage memory, or a random access memory, etc.

[0100] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. An aircraft circuit detection device, characterized in that: include: a signal generating module, used for storing a predetermined analog command signal and a control signal, and providing the analog command signal and the control signal to the aircraft after the aircraft circuit detection starts, so as to generate an aircraft feedback signal and transmit it to the signal conditioning detection module, wherein the control mechanism generates the control signal according to the analog command signal, and the aircraft circuit generates the aircraft feedback signal according to the control signal; The signal conditioning and detection module is used to receive the aircraft feedback signal, detect the aircraft feedback signal, and then provide the detected aircraft feedback signal to different indicator lights to determine whether the feedback signal is qualified; as well as The self-test module is used to generate equivalent correct signals and signals exceeding the marked tolerance in sequence without being connected to the aircraft, and provide them to the internal circuit of the aircraft circuit detection device to generate a self-test feedback signal, and then provide the self-test feedback signal to the self-test indicator light to determine whether the internal circuit of the aircraft circuit detection device is qualified.

2. The aircraft circuit detection device according to claim 1, characterized in that: It also includes a cable for connecting the aircraft circuit detection device to a detection interface of an aircraft steering engine cabin, wherein the cable includes a detection end interface and an aircraft end plug, wherein: The detection end interface is connected to the detection interface on the panel of the aircraft circuit detection device to transmit the analog command signal and the control signal through the detection interface on the panel of the aircraft circuit detection device and receive the aircraft feedback signal; The aircraft end plug is connected to the detection interface of the aircraft steering gear cabin in a plug-in manner and is fastened through a plug nut, so as to detect the aircraft circuit through the detection interface of the aircraft steering gear cabin.

3. The aircraft circuit detection device according to claim 2, characterized in that: The self-test circuit comprises: A self-test control signal generator, used to generate an equivalent correct signal or a signal exceeding a marked tolerance range and provide it to an internal circuit of the detection device, so that an output end of the internal circuit outputs a first self-test output signal or a second self-test output signal; a detection circuit switching switch, used to switch a first self-test mode to a second self-test mode, wherein in the first self-test mode an equivalent correct signal is provided to an internal circuit of the aircraft circuit detection device, and in the second self-test mode an out-of-marked tolerance range signal is provided to an internal circuit of the aircraft circuit detection device; An out-of-tolerance signal output circuit, connected to the output end of the internal circuit via the detection circuit switching switch, and used for receiving and outputting the second self-test output signal from the output end of the internal circuit; An A / D converter, configured to receive the first self-test output signal from the internal circuit output terminal or the second self-test output signal from the out-of-tolerance signal output circuit, perform analog-to-digital conversion on the first self-test output signal and the second self-test output signal, and provide the signals to the MCU; The MCU is used to compare the first self-test output signal with a pre-stored reference first self-test signal to determine whether the first self-test output signal meets the requirements or compare the second self-test output signal with a pre-stored reference second self-test signal to determine whether the second self-test output signal meets the requirements; A self-test indicator light, comprising a green self-test indicator light and a red self-test indicator light, wherein when the first self-test output signal and the second self-test output signal of the MCU meet the requirements, the green self-test indicator light is on; when the first self-test output signal and the second self-test output signal of the MCU do not meet the requirements, the red self-test indicator light is on.

4. The aircraft circuit detection device according to claim 3, characterized in that: The internal circuit of the detection device includes a voltage detection circuit, a current detection circuit, an amplifier detection circuit and an instruction detection circuit, wherein The voltage detection circuit is used to detect the power supply voltage of the aircraft circuit to determine whether the power supply voltage meets the requirements; The current detection circuit is used to detect the power consumption current of the aircraft circuit to determine whether the power consumption current meets the requirements; The amplifier detection circuit is used to detect whether the working state of the aircraft servo amplifier is normal through the analog command signal and the control signal; The command detection circuit is used to input the aircraft position deviation signal into the aircraft command forming device through the analog command signal to detect whether the aircraft control command is normal.

5. The aircraft circuit detection device according to claim 4, characterized in that: The current detection circuit comprises: a measuring resistor for detecting a consumption current value from a detection resistor of the consumption current flowing through the aircraft circuit; An amplifier, used for amplifying the power consumption current value; an analog switch for providing the amplified consumption current value to the A / D converter via the analog switch; The A / D converter is used to perform analog-to-digital conversion on the amplified power consumption current value and provide the digital power consumption current value to the MCU; The MCU is used to compare the digital power consumption current value with a pre-stored reference power consumption current value to determine whether the digital power consumption current value meets the requirement; The current indicator light comprises a red current indicator light and a green current indicator light, wherein when the power consumption current value of the MCU does not meet the requirements, the red current indicator light is on, and when the power consumption current value of the MCU meets the requirements, the green current indicator light is on.

6. The aircraft circuit detection device according to claim 4, characterized in that: The amplifier detection circuit comprises: an amplifier control signal generating submodule, for generating an amplifier control signal and providing the amplifier control signal to an aircraft servo amplifier; An amplifier voltage detection submodule, used to detect the amplifier voltage from the aircraft servo amplifier and apply it to both ends of the servo potentiometer; A servo potentiometer detection submodule, used to detect the current value flowing through the servo potentiometer or the voltage value at both ends thereof; The A / D converter is used to perform analog-to-digital conversion on the current value or voltage value of the servo potentiometer, and provide the analog-to-digital converted current value or voltage value to the MCU; The MCU is used to compare the current value or voltage value after the analog-to-digital conversion with a pre-stored reference current value or voltage value to determine whether the current value or voltage value after the analog-to-digital conversion meets the requirements; The amplifier indicator light comprises a red amplifier indicator light and a green amplifier indicator light, wherein when the current value of the servo potentiometer of the MCU does not meet the requirements, the red amplifier indicator light is on; and when the current value of the servo potentiometer of the MCU meets the requirements, the green amplifier indicator light is on.

7. The aircraft circuit detection device according to claim 4, characterized in that: The instruction detection circuit comprises: A control signal generation submodule, used to generate a simulated command signal and provide it to an aircraft command forming device; A Uz detection submodule, used to detect a Uz voltage signal from the output end of the aircraft command forming device; A Uy detection submodule, used to detect a Uy voltage signal from the output end of the aircraft instruction forming device; The A / D converter is used to perform analog-to-digital conversion on the Uz voltage signal and the Uy voltage signal and provide the Uz voltage signal and the Uy voltage signal in digital form to the MCU; The MCU is used to compare the digital Uz voltage signal and Uy voltage signal with a pre-stored reference Uz voltage signal and a pre-stored reference Uy voltage signal to determine whether the Uz voltage signal and the Uy voltage signal values ​​meet the requirements; The command indicator light comprises a red command indicator light and a green command indicator light, wherein when the Uz voltage signal and the Uy voltage signal of the MCU do not meet the requirements, the red command indicator light is on; when the Uz voltage signal and the Uy voltage signal of the MCU meet the requirements, the green command indicator light is on.

8. An aircraft circuit detection method, characterized in that: include: Connecting the aircraft circuit detection device to the detection interface of the aircraft steering engine cabin via a cable; Initialize the MCU to determine the working mode of the aircraft circuit detection device, wherein the working mode includes a self-test working mode, an aircraft circuit detection working mode, and a calibration working mode; When the aircraft circuit detection device is in a self-test working mode, an equivalent correct signal or a signal exceeding the marked tolerance range is generated and provided to an internal circuit of the aircraft circuit detection device to output a first self-test output signal or a second self-test output signal, and a green or red self-test indicator light is turned on according to whether the first self-test output signal or the second self-test output signal meets the requirements; After the self-test of the aircraft circuit detection device is qualified, the self-test working mode is switched to the aircraft detection working mode through the mode switching switch; The power supply voltage, current consumption, aircraft servo amplifier and aircraft command forming device of the aircraft circuit are tested in sequence to determine whether the power supply voltage, current consumption, aircraft servo amplifier and aircraft command forming device of the aircraft circuit meet the requirements, so that the corresponding green indicator light or red indicator light is on.

9. The aircraft circuit detection method according to claim 8, characterized in that: When the aircraft circuit detection device is in a self-test working mode, an equivalent correct signal or a signal exceeding the marked tolerance range is generated and provided to an internal circuit of the aircraft circuit detection device to output a first self-test output signal or a second self-test output signal, and a green or red self-test indicator light is turned on according to whether the first self-test output signal or the second self-test output signal meets the requirements. The method further includes: Generate an equivalent correct signal or a signal exceeding the marked tolerance range through a self-test control signal generator and provide it to an internal circuit of the aircraft circuit detection device, so that the output end of the internal circuit outputs a first self-test output signal or a second self-test output signal; Switching the first self-test mode to the second self-test mode through the detection circuit switching switch, wherein in the first self-test mode an equivalent correct signal is provided to the internal circuit of the aircraft circuit detection device, and in the second self-test mode an out-of-standard tolerance range signal is provided to the internal circuit of the aircraft circuit detection device; The out-of-tolerance signal output circuit is connected to the output end of the internal circuit via the detection circuit switching switch, and is used to receive and output the second self-test output signal from the output end of the internal circuit; receiving the first self-test output signal from the internal circuit output terminal or receiving the second self-test output signal from the excess signal output submodule through an A / D converter, performing analog-to-digital conversion on the first self-test output signal and the second self-test output signal and providing them to the MCU; The MCU is used to compare the first self-test output signal or the second self-test output signal with a pre-stored reference first self-test signal and a pre-stored reference second self-test signal to determine whether the first self-test output signal and the second self-test output signal meet the requirements; When the first self-test output signal and the second self-test output signal of the MCU meet the requirements, the green self-test indicator light turns on; when the first self-test output signal and the second self-test output signal of the MCU do not meet the requirements, the red self-test indicator light turns on and stops the self-test working mode.

10. The aircraft circuit detection method according to claim 9, characterized in that: Testing the power supply voltage, power consumption current, aircraft steering gear amplifier and aircraft command forming device of the aircraft circuit in sequence to determine whether the power supply voltage, power consumption current, aircraft steering gear amplifier and aircraft command forming device of the aircraft circuit meet the requirements, so that the corresponding green indicator light or red indicator light further includes: detecting the power supply voltage of the aircraft circuit, and then determining whether the power supply voltage meets the requirements; When the power supply voltage meets the requirements, the green voltage indicator light is on and the power consumption current of the aircraft circuit is detected, otherwise the red voltage indicator light is on and the aircraft circuit detection working mode is stopped; When it is determined that the power consumption current meets the requirements, the green current indicator light is on and the working status of the aircraft servo amplifier and the feedback potentiometer is detected, otherwise the red current indicator light is on and the aircraft circuit detection working mode is stopped; When the working state of the aircraft servo amplifier meets the requirements, the green amplifier indicator light is on and the aircraft control command is detected, otherwise the red amplifier indicator light is on and the aircraft circuit detection working mode is stopped; When the aircraft control command is normal, the green command indicator light is on, otherwise the red command indicator light is on and the aircraft circuit detection working mode is stopped.

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