Static online test system and test method for acceleration overload switch

Abstract

The invention provides a static online test system and test method for an acceleration overload switch. The system comprises an aircraft control system functional circuit, an aircraft cable, the acceleration overload switch, an overload switch tester and a ground test cable. The method for simulating injection of an overload electric signal into the overload switch is realized, an electric signal equivalent to an overload threshold is injected into an accelerometer in the overload switch, the accelerometer is driven to output a voltage signal, and the voltage signal is compared with a set threshold voltage, so that an output switch of the overload switch is triggered to change. According to the invention, the problem that the overload performance cannot be tested after the overload switch is installed in the cabin of the aircraft is solved, the test of the aircraft and the overload-related time sequence action function under the ground static condition is realized, and the test coverage of the aircraft is improved.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace vehicle control, and particularly relates to an online test system and a test method for an acceleration overload switch under ground static conditions. Background Art

[0002] During the operation of an aircraft, it is often necessary to test the overload value in a specific direction (such as the axial or radial direction of the aircraft), and perform key flight timing actions such as inter-stage separation and attitude adjustment based on the test results. The acceleration overload switch is a small special inertial measurement device developed based on the above requirements. The acceleration overload switch (hereinafter referred to as the "overload switch") generally consists of a power supply module, an accelerometer, a signal conditioning circuit, a relay circuit, etc. The overload switch is installed at a specific position inside the aircraft cabin. During operation, with the accelerometer inside it as the sensitive device, the accelerometer outputs a voltage signal corresponding to the acceleration value it bears, and compares it with the voltage value corresponding to the set acceleration threshold. When the applied acceleration reaches or exceeds the set threshold, it controls the opening or closing of the contacts of an electromagnetic relay or a solid-state relay, causing the switching state of the contacts to change, thereby realizing the functions of acceleration overload measurement and status signal output.

[0003] The overload switch developed based on the above principle has achieved relatively mature applications in engineering. Of course, in response to some pain points in the application process of the overload switch, domestic research institutions have also carried out targeted improvement work. The patent "Acceleration Overload Switch with High and Low Pass Bidirectional Acceleration Signal Output" (Application No. CN200810068904.2) provides a highly reliable acceleration overload switch with high and low pass bidirectional acceleration signal output, which is used to sense the changes in the positive and negative axial accelerations along the sensitive axis of the accelerometer during the flight of the aircraft. Under the specified acceleration overload conditions, it connects the booster control circuit or the inter-stage separation control circuit on the aircraft. The patent "An Acceleration Overload Switch" (Application No. CN202211026424.6) addresses the problem that in the prior art, the electronic switch in the acceleration overload switch maintains the on and off states of the switch by loading a drive signal. When the drive signal is removed, the state of the electronic switch changes and cannot achieve self-locking, and realizes an acceleration overload switch with a self-locking function for the output signal.

[0004] For the test of the overload measurement performance of an overload switch, it is generally achieved through the centrifuge test method, that is, the overload switch is installed on the centrifuge, and a gradually increasing overload is applied to the overload switch through the centrifuge until the applied overload value is equal to or greater than the set threshold, thereby triggering the overload switch to output a switch signal, so as to evaluate the measurement performance of the overload switch. Obviously, this is an offline test method adopted during the production stage of the overload switch. After the acceleration overload switch is delivered from the factory and fixed to a specific installation position inside the aircraft cabin, the centrifuge test method will no longer be applicable. If the overload switch fails to be effectively triggered and output a switch signal during the system-level ground test of the aircraft, key flight timing actions such as inter-stage separation and attitude adjustment of the aircraft will not be able to be executed normally, resulting in the situation that the ground test conditions cannot cover the flight conditions, bringing certain risks to the smooth implementation of the flight test. During the ground static test of the aircraft system, how to effectively stimulate the overload switch to output a switch signal, and then trigger the aircraft control system to execute key flight timing actions such as inter-stage separation and attitude adjustment, so as to achieve a relatively complete test of the aircraft during the ground test stage, is an urgent problem to be solved. Therefore, it is necessary to implement an online test system and its test method for the static condition after the overload switch is installed in the aircraft cabin. Summary of the Invention

[0005] The purpose of the present invention is to solve the above problems, and provide a static online test system and test method for an acceleration overload switch. By using the method of simulating overload injection, the output action of the overload switch under ground static test conditions is triggered, and relevant functional tests are completed in cooperation with the aircraft control system.

[0006] The present invention consists of the functional circuit of the aircraft control system, the aircraft cable, the acceleration overload switch, the overload switch tester, and the ground test cable. In the flight state, the aircraft control system is connected to one or more overload switches through the aircraft cable respectively, provides power for the overload switch, and receives the switch signal output from the overload switch. In the ground test state, the ground test cable is connected in series between the aircraft cable and the overload switch to connect the overload switch tester to the overload switch in the aircraft: on the one hand, the ground test cable provides a path for the power supply and switch signal transmitted between the aircraft cable and the overload switch; on the other hand, the ground test cable injects the simulated overload signal sent by the overload switch tester into the overload switch, thereby stimulating the overload switch to act.

[0007] The acceleration overload switch includes: a power conversion circuit, a quartz meter head, a servo control circuit, and an overload output circuit; wherein, the power conversion circuit converts the primary power input by the aircraft system into the secondary power required for the operation of each functional circuit inside the overload switch; the quartz meter head includes a quartz pendulum plate, a torque coil, a permanent magnet, a first capacitor plate, and a second capacitor plate; the quartz pendulum plate is located at the gap position between the first capacitor plate and the second capacitor plate; a torque coil is provided on the quartz pendulum plate, and permanent magnets are provided at both ends of the torque coil; the servo control circuit includes a differential capacitance converter, a current integrator, a signal amplifier, an analog overload input signal, and an adder; the overload output circuit is composed of a sampling resistor, a low-pass filter, a voltage comparator, and a relay control circuit.

[0008] The overload switch tester is composed of an AC / DC power module, a resistor R0, a switch S, a resistor R1, and a light-emitting diode V1.

[0009] The beneficial effects of the present invention are as follows:

[0010] 1. The present invention realizes a method of injecting an analog overload electrical signal into the overload switch. By injecting an electrical signal equivalent to the overload threshold into the accelerometer in the overload switch, the accelerometer is driven to output a voltage signal, which is compared with the set threshold voltage, and then the output switch of the overload switch is triggered to change. The solution implemented by the present invention solves the problem that the overload performance test cannot be carried out after the overload switch is installed in the aircraft cabin. Further, the test of the timing action function related to overload of the aircraft under static ground conditions is realized, and the test coverage of the aircraft is improved.

[0011] 2. The present invention realizes an overload switch tester for generating an analog overload electrical signal to provide a signal source for triggering the action of the overload switch. The internal circuit of the overload switch tester is simple and easy to implement. Each analog overload electrical signal is independent of each other and corresponds one-to-one with the overload switch in the aircraft, and the expansion is flexible.

[0012] 3. The present invention realizes a reasonable ground test cable topology configuration, which does not damage the original interface relationship of the cables inside the aircraft and takes into account the reliability of the overload switch working under two working conditions, namely the ground test stage and the flight test implementation stage. Description of the Drawings

[0013] The drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention:

[0014] Figure 1 is a schematic connection diagram of an acceleration overload switch and an aircraft control system according to an embodiment of the present invention;

[0015] Figure 2 is a functional block diagram of a ground online test system with simulated overload injection according to an embodiment of the present invention;

[0016] Figure 3 is a schematic diagram of the simulated overload injection function of a single-channel overload switch according to an embodiment of the present invention;

[0017] Figure 4 is a schematic diagram of the function of a single-channel overload switch tester according to an embodiment of the present invention;

[0018] Figure 5 is the topology configuration of a single-channel ground test cable according to an embodiment of the present invention;

[0019] Figure 6 is a schematic diagram of the connection relationship of the static online test system of the overload switch according to an embodiment of the present invention. Detailed implementation manners

[0020] In order to enable those skilled in the art to better understand the solution of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0021] The overload switch is used to sense the overload in the sensitive flight environment, compare it with the set threshold, and then output a switch signal for the flight vehicle control system to use. The flight vehicle control system performs key flight timing actions such as inter-stage separation and attitude adjustment according to the output result of the acceleration overload switch. In order to improve the reliability of the operation of the flight vehicle system, multiple overload switches with the same technical state are often set at different parts in the flight vehicle cabin, and the overload situation faced by the flight vehicle is finally determined by taking a vote on the output results of these overload switches. The connection relationship diagram between the overload switch and the flight vehicle control system is as shown in Figure 1 shown.

[0022] The present invention realizes a ground online test system and a test method under the condition that an overload switch is installed in the flight vehicle cabin. By using the method of simulated overload injection, the output action of the overload switch under the ground static test condition is triggered, and the relevant function tests are completed in cooperation with the flight vehicle control system.

[0023] The present invention is composed of a flight vehicle control system functional circuit, a flight vehicle cable, an overload switch, an overload switch tester, and a ground test cable. For the specific signal flow and interface relationship, please refer to Figure 2As shown in the figure. The aircraft control system is respectively connected to a plurality of overload switches through aircraft cables and ground test cables, provides power for the plurality of overload switches, and receives switch signals output from the plurality of overload switches. In addition, the overload switch tester injects an analog overload signal into the overload switch through the ground test cable to stimulate the action of the overload switch. The specific implementation scheme of the present invention includes the following three core technologies:

[0024] First, the function of injecting an analog overload signal into the overload switch is realized;

[0025] Second, an overload switch tester is realized, which is used to generate an analog overload signal;

[0026] Third, a reasonable topological configuration of the analog overload test cable is realized.

[0027] Embodiment 1

[0028] For the convenience of explanation, taking the ground online test scheme of one-way overload switch as an example, the implementation scheme of the present invention will be described from the above three aspects.

[0029] (1) Injection of analog overload signal for overload switch

[0030] The overload switch described in the present invention is composed of a power conversion circuit, a quartz meter head, a servo circuit, an overload output circuit, etc., as shown in detail Figure 3 as follows. Among them:

[0031] The power conversion circuit is mainly composed of several power modules, which converts the primary power input by the aircraft system into the secondary power required for the operation of each functional circuit inside the overload switch.

[0032] The quartz meter head includes a quartz pendulum sheet, a torque coil, a permanent magnet, a first capacitor plate and a second capacitor plate; the quartz pendulum sheet is located at the gap position between the first capacitor plate and the second capacitor plate; a torque coil is arranged on the quartz pendulum sheet, and permanent magnets are arranged at both ends of the torque coil.

[0033] The servo control circuit includes a differential capacitance converter, a current integrator, a signal amplifier, an analog overload input signal and an adder; the first capacitor plate and the second capacitor plate in the quartz meter head form a differential capacitance sensor, the output end of the differential capacitance sensor is connected to the input end of the differential capacitance converter, the output end of the differential capacitance converter is connected to the input end of the current integrator, the output end of the current integrator and the analog overload signal are jointly connected to the input end of the adder, the output end of the adder is connected to the input end of the signal amplifier, and the output end of the signal amplifier is connected to the input end of the torque coil in the meter head.

[0034] The overload output circuit consists of a sampling resistor, a low-pass filter, a voltage comparator, and a relay control circuit. The sampling resistor is connected to the output terminal of the torquer in the quartz meter head, converting the torque current signal into a voltage signal. This voltage signal is connected to the input terminal of the low-pass filter, the output terminal of the low-pass filter is connected to the input terminal of the voltage comparator, the output terminal of the voltage comparator is connected to the input terminal of the relay control circuit, and the output terminal of the relay control circuit outputs a switch signal for use by the aircraft control system.

[0035] When the aircraft is in the flight phase, with the changes in flight trajectory and flight attitude, if the quartz meter head in the overload switch senses the acceleration of the aircraft, the quartz pendulum will deflect, and the differential capacitance sensor composed of the first capacitor plate and the second capacitor plate generates a differential capacitance. This capacitance is converted into a current signal through a differential capacitance converter. Subsequently, the current signal is converted into a voltage signal through a current integrator, and after being conditioned by a signal amplifier, it is input to the input terminal of the torquer coil. The torquer coil generates an electromagnetic torque under the combined action of the torque current and the permanent magnet, driving the quartz pendulum to move to counteract the deflection of the pendulum caused by the external acceleration of the external input. At the same time, the output terminal of the torquer coil generates an induced current representing the change in external acceleration. This induced current passes through the sampling resistor, converting the above-mentioned current change process representing acceleration into a voltage signal. The voltage signal is filtered by the low-pass filter to remove high-frequency noise and compared with the set voltage threshold in the voltage comparator. If it reaches or is greater than the set voltage threshold, the output terminal of the voltage comparator will generate a voltage signal to drive the relay control circuit, causing the switch contacts of the relay to change, and the change signal of the contacts is the output signal of the entire overload switch.

[0036] Similarly, when the aircraft is in a static state on the ground and there is no acceleration in a specific sensitive direction, the overload switch will not be able to output a switch signal. At this time, the overload switch tester generates an analog overload electrical signal equivalent to the external acceleration input and injects it into the overload switch. This signal will be superimposed and input to the signal amplifier through the adder in the servo circuit. After being amplified by the signal amplifier, it is input to the input terminal of the torquer in the meter head. Under the combined action of the input signal of the torquer and the permanent magnet, it drives the quartz pendulum to deflect. At the same time, the output terminal of the torquer coil generates an induced current representing the change in external acceleration. This induced current passes through the sampling resistor, converting the current change process into a voltage signal. The voltage signal is filtered by the low-pass filter to remove high-frequency noise and compared with the set voltage threshold in the voltage comparator. If it reaches or is greater than the set voltage threshold, the output terminal of the voltage comparator will generate a voltage signal to drive the relay control circuit, causing the switch contacts of the relay to change. This change signal is the output signal of the overload switch generated by being excited by the analog overload signal for use by the aircraft control system. In this way, the in-system test of the overload switch under static conditions is realized.

[0037] In summary, by utilizing the operating characteristics of the quartz meter head and its servo circuit in the overload switch, an analog overload electrical signal is injected into the servo circuit to drive the quartz meter head to generate an additional electrical signal representing the acceleration change. This electrical signal is processed step by step through each functional circuit, and then the overload switch outputs a switch signal, realizing the output of the overload switch under static conditions.

[0038] (2) Generate an analog overload signal

[0039] In order to generate an analog overload electrical signal, the present invention realizes an overload switch tester. The overload switch tester uses components such as a power supply module, resistors, and switches to form a simple signal generation circuit to generate an analog overload electrical signal equivalent to the acceleration threshold voltage. Its composition block diagram is as Figure 4 shown.

[0040] The overload switch tester consists of an AC / DC power supply module, resistor R0, switch S, resistor R1, and light-emitting diode V1. Among them:

[0041] The AC / DC power supply converts the externally input AC power into DC power (the positive pole is labeled as VCC and the negative pole is labeled as GND) for use by the subsequent circuit.

[0042] In the subsequent circuit, resistor R0 and switch S form branch 1, and resistor R0, switch S, light-emitting diode V1, and resistor R1 form branch 2.

[0043] Branch 1 is used to generate an analog overload electrical signal. In branch 1: the output positive terminal VCC of the AC / DC power supply module is connected to one end of resistor R0, the other end of resistor R0 is connected to one end of switch S, and the other end of switch S is used to externally output the analog overload + signal; the output negative terminal GND of the AC / DC power supply module is connected to the analog overload - signal. Resistor R0 serves as the current-limiting resistor of branch 1 and plays a decisive role in the magnitude of the analog overload signal. Its value is jointly determined by the output voltage of the AC / DC power supply module, the electrical parameters inside the overload switch, and the cable resistance value between the overload switch tester and the overload switch.

[0044] Branch 2 is used to monitor the on / off state of switch S. When S is on, the light-emitting diode V1 is on, otherwise it is off. In branch 2: the output positive terminal GND of the AC / DC power supply module is connected to one end of resistor R0, the other end of resistor R0 is connected to one end of switch S, the other end of switch S is connected to the positive terminal of the light-emitting diode, the negative terminal of the light-emitting diode is connected to one end of resistor R1, and the other end of resistor R1 is connected to the negative terminal GND of the AC / DC power supply module. Resistors R0 and R1 serve as the current-limiting resistors of branch 2. The value of resistor R0 is determined by branch 1, and the value of resistor R1 is jointly determined by the output voltage of the AC / DC power supply module, resistor R0, and the electrical parameters of the light-emitting diode V1.

[0045] When the switch S is closed, branch 1 and branch 2 of the overload switch tester are connected simultaneously. Branch 1 outputs an analog overload electrical signal externally, and the light-emitting diode V1 in branch 2 lights up, indicating that the switch S is connected and the analog overload signal has been sent. Conversely, when the switch S is opened, the analog overload signal is no longer output and the light-emitting diode V1 goes out.

[0046] (3) Ground test cable topology

[0047] After the overload switch is installed at a specific location inside the aircraft cabin, it is connected to the aircraft control system through the cables inside the aircraft. The aircraft control system supplies power to the overload switch and receives the switch signal output by the overload switch. During the ground test of the aircraft, in order to stimulate the output of the overload switch and utilize the overload switch tester to output an analog overload excitation signal, it is necessary to achieve the injection requirement of the analog overload signal through a reasonable design of the ground test cable without changing the cable interface state during the flight mission phase of the aircraft. After demonstrating several design schemes, the present invention has achieved the ground test cable topology as Figure 5 shown.

[0048] As Figure 5 shown, during the flight phase of the aircraft, the plug of the cable connector C1 inside the aircraft is directly docked with the socket of the connector C2 of the overload switch to achieve the power supply and the transmission and interaction of the switch signal between the aircraft control system and the overload switch. During the ground test phase of the aircraft, the ground test cable is connected in series between the aircraft control system cable and the overload switch in a Y-shaped topology: the socket of the ground test cable connector C1 is connected to the plug of the aircraft cable connector C1, and the plug of the ground test cable connector C2 is connected to the socket of the overload switch connector C2 to provide a power supply and a switch output signal path between the aircraft control system and the overload switch; the plug of the ground test cable connector C3 is connected to the socket of the overload switch tester C3, and a signal path for injecting an analog overload signal into the overload switch is provided through the cable between the connector C3 and the connector C2.

[0049] The ground test cable topology achieved by the present invention has the following advantages:

[0050] 1) The analog overload signal, the power supply signal, and the switch output signal are integrated on the same connector C2, without the need to additionally increase connectors, and thus the external dimension envelope of the overload switch is not changed;

[0051] 2) The original cable topology configuration in the aircraft flight state is not changed. In the aircraft flight state, the aircraft cable is directly connected to the overload switch, the power supply and switch output signals between the aircraft control system and the overload switch can be transmitted normally, and the analog overload injection signal interface of the overload switch is enclosed inside the overload switch connector C2, without generating additional "blind cables", thus minimizing the risk of introducing external interference signals.

[0052] Embodiment 2

[0053] Based on the one-way overload switch ground online test solution, the present invention realizes a multi-way overload switch ground online test system, see Figure 6 As shown. Among them:

[0054] The multi-channel overload switches installed in the aircraft cabin are independent of each other and are connected to the overload switch tester and the aircraft control system through ground test cables and aircraft cables respectively.

[0055] The aircraft control system provides power to the multi-way overload switch and receives switch output signals from the multi-way overload switch.

[0056] The overload switch tester is equipped with a corresponding number of independent analog overload signal generating circuits according to the number of overload switches in the aircraft cabin. By operating the switches of each analog overload signal generating circuit separately, multiple analog overload electrical signals can be sent out simultaneously or in different time periods.

[0057] After the ground test is completed, the ground test cable and the overload switch tester are withdrawn, and the aircraft cable is used to connect each overload switch to the aircraft control system to complete the cable state conversion of the aircraft flight state.

[0058] Embodiment 3

[0059] The present invention provides a testing method for a static online testing system of an acceleration overload switch, taking a ground static online test of an overload switch as an example.

[0060] When the aircraft is in flight, the overload switch is connected to the aircraft control system through an aircraft cable. The aircraft control system supplies power to the overload switch and receives a switch signal output by the overload switch. Under the static ground test conditions of the aircraft, since there is no overload condition, the overload switch cannot trigger the output signal for use by the aircraft control system, and thus the aircraft control system cannot perform flight timing actions such as interstage separation and attitude adjustment. Therefore, the present invention implements a set of ground static online test system for overload switches. An overload switch tester sends a simulated overload electrical signal to the overload switch, which stimulates the overload switch to output a corresponding switch signal for use by the aircraft control system.

[0061] likeFigure 5 As shown, the ground test cable is connected in series between the aircraft control system and the overload switch in a Y-shaped topological configuration: the socket of the ground test cable connector C1 is connected to the plug C1 of the aircraft cable connector, and the plug of the ground test cable connector C2 is connected to the socket of the overload switch connector C2, providing a power supply and a switch output signal path between the aircraft and the overload switch; the plug of the ground test cable connector C3 is connected to the overload switch tester, and a signal path for injecting an analog overload signal into the overload switch is provided through the cable between the connector C3 and the connector C2.

[0062] As Figure 4 Shown in the schematic diagram of the internal circuit of the overload switch tester, when the switch S is closed, branch 1 and branch 2 of the overload switch tester are simultaneously connected. Branch 1 outputs an analog overload signal externally, and the light-emitting diode V1 in branch 2 lights up, indicating that the switch S is connected and the analog overload signal has been sent. Conversely, when the switch S is opened, no analog overload signal is sent, and the light-emitting diode V1 goes out.

[0063] On the premise that the aircraft control system supplies power to the overload switch, the overload switch tester sends an analog overload electrical signal to the overload switch. This signal will be superimposed and input into the signal amplifier through the adder in the Figure 3 shown servo circuit, and after being amplified by the signal amplifier, it is input to the input end of the torque motor in the quartz meter head. Under the combined action of the input signal of the torque motor and the permanent magnet, the quartz pendulum is driven to deflect. At the same time, an induced current representing the change of the external acceleration is generated at the output end of the torque coil. This induced current passes through the sampling resistor, converting the current signal representing the acceleration into a voltage signal. The voltage signal is filtered by a low-pass filter to remove high-frequency noise and compared with a set voltage threshold in a voltage comparator. If it reaches or exceeds the set voltage threshold, a voltage signal will be generated at the output end of the voltage comparator to drive the relay control circuit, causing the switch contacts of the relay to change. This switch change signal is the overload switch output signal generated by being excited by the analog overload electrical signal. After receiving this overload output signal, the aircraft control system issues corresponding timing actions, thus realizing the on-line test of the overload switch under static conditions.

[0064] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be obvious to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the scope of the present invention. Therefore, the present invention will not be limited to these embodiments shown herein, but will be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A static online test system for accelerating overload switches, characterized in that: Including aircraft control system functional circuit, aircraft cable, acceleration overload switch, overload switch tester, ground test cable; In the flight state, the aircraft control system is connected to the acceleration overload switch through the aircraft cable, provides power to the acceleration overload switch, and receives the switch signal output from the acceleration overload switch; In the ground test state, the ground test cable is connected in series between the aircraft cable and the acceleration overload switch to connect the overload switch tester to the acceleration overload switch in the aircraft: on the one hand, the ground test cable provides a path for the power supply and switch signal transmitted between the aircraft cable and the acceleration overload switch; on the other hand, the ground test cable injects the simulated overload signal sent by the overload switch tester into the acceleration overload switch, thereby stimulating the acceleration overload switch to operate; Wherein, there are one or more acceleration overload switches.

2. A static online test system for an acceleration overload switch according to claim 1, characterized in that: The acceleration overload switch includes: a power conversion circuit, a quartz meter, a servo control circuit, and an overload output circuit; wherein the power conversion circuit converts the primary power input from the aircraft system into the secondary power required for the operation of each functional circuit inside the overload switch; The servo control circuit includes an adder, which can superimpose the analog overload input signal and the voltage signal output by the current integrator and input them into the signal amplifier. After that, the electrical signal is processed step by step by each functional circuit, so that the acceleration overload switch outputs a switching signal, realizing the output of the overload switch under static conditions.

3. A static online test system for an acceleration overload switch according to claim 2, characterized in that: The servo control circuit also includes a differential capacitor converter, a current integrator, a signal amplifier, and an analog overload input signal; the quartz meter head includes a quartz pendulum, a torquer coil, a permanent magnet, a first capacitor plate, and a second capacitor plate; the quartz pendulum is located in the gap between the first capacitor plate and the second capacitor plate; a torquer coil is arranged on the quartz pendulum, and permanent magnets are arranged at both ends of the torquer coil.

4. The static online test system for an acceleration overload switch according to claim 2, characterized in that: The overload output circuit is composed of a sampling resistor, a low-pass filter, a voltage comparator, and a relay control circuit.

5. The static online testing system for an acceleration overload switch according to claim 1, characterized in that: The overload switch tester is composed of an AC / DC power supply module, a resistor R0, a switch S, a resistor R1 and a light emitting diode V1.

6. The static online test system for an acceleration overload switch according to claim 1, characterized in that: The resistor R0 and the switch S form a branch 1, which is used to generate a simulated overload electrical signal; the resistor R0, the switch S, the light-emitting diode V1, and the resistor R1 form a branch 2, which is used to monitor the on / off state of the switch S.

7. The static online test system for an acceleration overload switch according to claim 5, characterized in that: In the branch 2: the output positive terminal GND of the AC / DC power module is connected to one end of the resistor R0, the other end of the resistor R0 is connected to one end of the switch S, the other end of the switch S is connected to the positive end of the light-emitting diode, the negative end of the light-emitting diode is connected to one end of the resistor R1, and the other end of the resistor R1 is connected to the negative end GND of the AC / DC power module; the resistor R0 and the resistor R1 serve as the current limiting resistors of the branch 2, the value of the resistor R0 is determined by the branch 1, and the value of the resistor R1 is determined according to the output voltage of the AC / DC power module, the resistor R0, and the electrical parameters of the light-emitting diode V1.

8. The static online test system for an acceleration overload switch according to claim 1, characterized in that: During the flight phase of the aircraft, the cable connector C1 plug inside the aircraft is directly connected to the connector C2 socket of the overload switch to realize the transmission and interaction of power supply and switch signals between the aircraft control system and the overload switch; during the ground test phase of the aircraft, the ground test cable is connected in series between the aircraft cable and the overload switch in a Y-shaped topology configuration: the ground test cable connector C1 socket is connected to the aircraft cable connector C1 plug, and the ground test cable connector C2 plug is connected to the overload switch connector C2 socket, providing power supply and switch output signal path between the aircraft and the overload switch; The ground test cable connector C3 plug is connected to the overload switch tester connector C3 socket, and a signal path for simulating overload signal injection is provided to the overload switch through the cable between connector C3 and connector C2.

9. The static online testing system for an acceleration overload switch according to claim 1, characterized in that: When there are multiple acceleration overload switches, the multiple overload switches are independent of each other and are connected to the overload switch tester and the aircraft control system through ground test cables and aircraft cables respectively; the overload switch tester is internally provided with a corresponding number of independent analog overload signal generating circuits according to the number of overload switches in the aircraft cabin. By operating the switches of each analog overload signal generating circuit separately, multiple analog overload electrical signals can be sent out simultaneously or in different times.

10. A method for testing a static online testing system of an acceleration overload switch according to any one of claims 1 to 9, characterized in that: The ground test cable connector C1 socket is connected to the aircraft cable connector plug C1, and the ground test cable connector C2 plug is connected to the overload switch connector C2 socket, providing power supply and switch output signal path between the aircraft and the overload switch; The ground test cable connector C3 plug is connected to the overload switch tester C3 socket, and a signal path for simulating overload signal injection is provided for the overload switch through the cable between connector C3 and connector C2; When switch S is closed, branch 1 and branch 2 of the overload switch tester are connected at the same time, branch 1 outputs a simulated overload signal, and the light-emitting diode V1 in branch 2 is on, indicating that switch S is connected and the simulated overload signal has been issued; conversely, when switch S is disconnected, the simulated overload signal is no longer issued, and the light-emitting diode V1 is off; Under the premise that the aircraft control system supplies power to the overload switch, the overload switch tester sends a simulated overload electrical signal to the overload switch. The signal is superimposed and input into the signal amplifier through the adder in the servo circuit, and then amplified by the signal amplifier and input into the input end of the torquer in the quartz meter head. Under the joint action of the torquer input signal and the permanent magnet, the quartz pendulum is driven to deflect. At the same time, the output end of the torque coil generates an induced current representing the change of external acceleration. The induced current passes through the sampling resistor to convert the above current signal representing the acceleration into a voltage signal. The voltage signal passes through a low-pass filter to filter out high-frequency noise and is compared with the set voltage threshold in the voltage comparator. If it reaches or exceeds the set voltage threshold, the output end of the voltage comparator will generate a voltage signal to drive the relay control circuit, so that the switch contact state of the relay changes. This switch change signal is the overload switch output signal generated by the stimulation of the simulated overload electrical signal. After receiving the overload output signal, the aircraft control system sends a corresponding timing action, thereby realizing the online test of the overload switch under static conditions.

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