A point detonation simulation system and method for an adaptive aircraft system

Abstract

The present application discloses a point detonation simulation system and method for an adaptive aircraft system, including: an aircraft identification circuit for identifying the electrical characteristics of a cable connector connected to the aircraft and outputting aircraft identification information; an activation signal receiving circuit for receiving an activation signal, generating activation current information and activation pulse voltage information according to the activation signal, and outputting the activation current information and the activation pulse voltage information; a point detonation simulation circuit for receiving a switch control signal, generating simulated power supply current information and normally open / closed signals according to the switch control signal, and outputting the simulated power supply current information; and a control system for receiving the aircraft identification information, the activation current information, the activation pulse voltage information, and the simulated power supply current information. The problems that it is difficult to generalize the point detonator and it is difficult to ensure the safety and accuracy are solved. The purpose of generalizing the point detonator and improving the safety is achieved.

Description

Technical Field

[0001] This application relates to the field of computer technology, and particularly to a point explosion simulation system and method for an adaptive aircraft system. Background Art

[0002] In the fields of aviation and aerospace, due to the danger and non-repeatability of pyrotechnics, during the docking and debugging process of the aircraft launch control system, a point explosion simulator is widely used to replace some functions of the battery and ejection device on the aircraft, and to simulate the voltage output of various aircraft batteries. Verification by the point explosion simulator is an indispensable link before the aircraft conducts real tests such as point explosion tests, because the point explosion simulator can effectively replace real components to verify the activation ability of the launch control system, thereby verifying and determining the normal working state of the launch control system and the aircraft launch control link technology.

[0003] Since an aircraft is a complex system with high quality requirements, different models of the same series, and even aircraft at different development stages of the same model, have different design requirements and application scenarios in the engineering development stage. Therefore, the hardware functions and index requirements for the point explosion simulator are also different, and the interface definitions and fault criteria for the supporting point explosion simulator are also different. Currently, during the development of domestic aircraft, the development of the point explosion simulator is based on the technical requirements of the aircraft. The developed point explosion simulator can often only meet the development tasks of a certain development stage or model, and cannot be applied to aircraft after the transition stage or other models of the same series. Existing similar general-purpose devices only design multiple external interfaces, and during use, corresponding cables and external pyrotechnic equivalent resistors are manually configured according to needs. The degree of intelligence is low, there is a risk of incorrect operation, and it is difficult to accurately judge whether the activation process meets the timing requirements. Against the background that China is in the stage of vigorous development of the military industry, especially aircraft, there is a need to develop a general-purpose point explosion simulator that can use the same design method and software implementation approach to reduce the development cost of aircraft and avoid technical risks and schedule risks brought about by the development of the point explosion simulator. Summary of the Invention

[0004] The embodiments of this specification provide a point explosion simulation system and method for an adaptive aircraft system, which are used to solve the problems in the prior art that different models of the same series or aircraft at different development stages of the same model have different design requirements and application scenarios, so the hardware functions and index requirements for the supporting point explosion simulator are also different; at the same time, the existing point explosion simulator has a low degree of intelligence and requires a lot of manual participation during use, such as adding external pyrotechnic equivalent resistors and judging the results. There is a risk of incorrect operation during use; as a result, it is difficult to generalize the interface definition and fault criterion of the point explosion simulator, and it is difficult to ensure safety and accuracy.

[0005] In a first aspect, an ignition simulation system for an adaptive aircraft system provided by an embodiment of the present application includes:

[0006] An aircraft identification circuit for identifying the electrical characteristics of a cable connector connected to the aircraft and outputting aircraft identification information, where the electrical characteristics refer to the conduction conditions between several pairs of contacts of the cable connector;

[0007] An activation signal receiving circuit for receiving an activation signal, generating activation current information and activation pulse voltage information according to the activation signal, and outputting the activation current information and the activation pulse voltage information;

[0008] An ignition simulation circuit for receiving a switch control signal, generating simulated power supply current information and normally open / closed signals according to the switch control signal, and outputting the simulated power supply current information;

[0009] A control system electrically connected to the aircraft identification circuit, the activation signal receiving circuit, and the ignition simulation circuit for receiving the aircraft identification information, the activation current information, the activation pulse voltage information, and the simulated power supply current information;

[0010] Wherein,

[0011] The control system obtains working mode information corresponding to the aircraft identification information through the aircraft identification information, and the working mode information includes preset information and activation signal validity criterion information;

[0012] The control system determines whether the ignition simulation circuit receives a valid activation signal according to the working mode information, and if so, sends a switch control signal to the ignition simulation circuit.

[0013] Further, the aircraft identification circuit includes an optocoupler, one end of which is used to obtain the contact conduction condition, and the other end is electrically connected to the control system.

[0014] Further, the activation signal receiving circuit includes:

[0015] An activation loop equivalent resistance module capable of being multiplexed with multiple activation signal input channels;

[0016] A voltage sensor connected between the activation loop equivalent resistance module and the activation signal input channel for detecting the voltage of each activation signal input channel;

[0017] A first controllable switch connected between the activation loop equivalent resistance module and the activation signal input channel for changing the situation of the activation loop equivalent resistance module accessing the positive and negative input ends of the activation channel.

[0018] Further, the equivalent resistance module of the activation circuit includes a parallel circuit capable of changing the resistance connection condition and a current sensor capable of collecting the current flowing through the equivalent resistance module of the activation circuit; the parallel circuit includes at least one branch, and each branch includes at least one resistor and a second controllable switch connected in series with the resistor.

[0019] Further, a voltage sensor is provided for each activation signal input channel, and the input and output terminals of each voltage sensor are correspondingly connected to the input and output terminals of the equivalent resistance module of the activation circuit.

[0020] Further, the detonation simulation circuit includes a normally open signal quantity generation circuit, a normally closed signal quantity generation circuit, and an analog power supply channel control circuit provided correspondingly for each activation channel;

[0021] Among them, the normally open signal quantity generation circuit is in a non-conducting high-resistance state before the input of a valid activation signal and can become a conducting low-resistance state after the input;

[0022] The normally closed signal quantity generation circuit is in a conducting low-resistance state before the input of a valid activation signal and becomes a non-conducting high-resistance state after the input;

[0023] The analog power supply channel control circuit can be controlled by a computer control circuit to change the conduction state of a group of power input terminals and corresponding power output terminals. Before the input of a valid activation signal, the power input and output terminals are in a disconnected state and become in a conducting state after the activation signal is input;

[0024] Each of the analog power supply channel control circuits further includes a current sensor capable of obtaining the analog power supply current information of the analog power supply channel control circuit.

[0025] Further, the detonation simulation circuit further includes a relay, the input end of the relay is electrically connected to the control system, and the output end is connected to the normally open signal quantity generation circuit, the normally closed signal quantity generation circuit, and the analog power supply channel control circuit.

[0026] Further, the control system further includes a human-computer interaction interface.

[0027] In a second aspect, an embodiment of the present specification provides a detonation simulation method for an adaptive aircraft system, which is used for the detonation simulation system of any one of the adaptive aircraft systems in the first aspect, including:

[0028] Obtain aircraft identification information;

[0029] Obtain the working mode information corresponding to the aircraft identification information according to the aircraft identification information. The working mode information includes preset information and activation signal valid criterion information. The preset information includes the activation pulse voltage timing sequence of each channel, activation current information, the acquisition sequence of the current output information of the analog battery power supply, the control of the access activation channel and the equivalent resistance combination, and determining the upper and lower limits of the normal ranges for acquiring the activation current information, activation pulse voltage information, and analog power supply current information of each channel. The activation pulse voltage timing sequence includes the relative time and holding time of the generation moment of the activation voltage of each channel;

[0030] The activation signal receiving circuit obtains the activation signal, generates activation current information and activation pulse voltage information according to the activation signal, and outputs the activation current information and activation pulse voltage information to the control system;

[0031] The control system determines whether the activation current information and activation pulse voltage information meet the requirements according to the working mode information;

[0032] The control system determines whether the detonation simulation circuit receives a valid activation signal according to the working mode information. If so, it sends a switch control signal to the detonation simulation circuit;

[0033] The detonation simulation circuit generates analog power supply current information and normally open / closed signals according to the switch control signal, and outputs the analog power supply current information to the control system;

[0034] The control system determines whether the analog power supply current information meets the requirements according to the working mode information.

[0035] Furthermore,

[0036] Compare and analyze the activation current information, activation pulse voltage information, and analog power supply current information with the working mode information to obtain a quality report. The quality report includes the analysis results displayed in the form of a timing diagram.

[0037] The above at least one technical solution adopted in the embodiments of the present application can achieve the following beneficial effects: It can identify aircraft information, and through flexible control of the activation signal receiving circuit and the detonation simulation circuit, it can meet the interface requirements of different aircraft. Moreover, it realizes automatic setting of the working mode after connecting the matching cable to meet the test requirements of the flight control docking test of different aircraft, minimizes manual operation during use to avoid the risk of misoperation, and can display and judge the test results, accurately judge whether the activation process meets the timing requirements, and improves safety and accuracy. The general detonation simulator described in the present invention can be used for different stages of aircraft or other models of the same series of aircraft, improves the versatility and utilization rate of the detonation simulator, and reduces the test cost of the aircraft by using the same design method and software implementation approach, avoiding technical risks and schedule risks brought by the development of the detonation simulator. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The drawings described herein are used to provide a further understanding of the present application, form a part of the present application, and the illustrative embodiments and descriptions thereof are used to explain the present application, and do not constitute an improper limitation of the present application. In the drawings:

[0039] Figure 1 It is a schematic diagram of the system structure provided for the embodiments of the specification;

[0040] Figure 2 It is the aircraft identification circuit provided for the embodiments of this specification;

[0041] Figure 3 It is a schematic diagram of the activation signal receiving circuit provided for the embodiments of this specification;

[0042] Figure 4 It is the detonation simulation circuit provided for the embodiments of this specification;

[0043] Figure 5 It is a schematic diagram of the method flow provided for the embodiments of the specification. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0044] To make the objectives, technical solutions, and advantages of the present application clearer, the technical solutions of the present application will be clearly and completely described below in conjunction with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0045] The following will detail the technical solutions provided by the embodiments of the present application with reference to the drawings.

[0046] This embodiment of the specification provides a point detonation simulation system for an adaptive aircraft system. Please refer to Figure 1 as shown, including:

[0047] An aircraft identification circuit 001, configured to identify the electrical characteristics of a cable connector connected to the aircraft, and output aircraft identification information. The electrical characteristics refer to the conduction conditions between several pairs of contacts of the cable connector;

[0048] In a specific implementation, the aircraft identification circuit includes, but is not limited to, an optocoupler 011. One end of the optocoupler is used to obtain the contact conduction condition, and the other end is electrically connected to the control system. Specifically, the input end of the optocoupler 011s is electrically connected to the contacts of the cable connector to obtain the contact conduction condition; the output end is electrically connected to the input end of the control system; the power supply pin and the ground pin of the optocoupler are connected to the corresponding pins of the circuit board in the traditional way, and the relevant pins here and below are not described. The aircraft identification circuit can output different aircraft identification information M according to the electrical characteristics of different aircraft cable connectors.

[0049] In a possible application, such as Figure 2 as shown, the electrical characteristics are the conduction conditions between 4 pairs of contacts on the cable connector, which can represent a total of 16 situations. Except for the situation where all 4 pairs of contacts are not conducting, which represents invalid input, it can represent at most 15 electrical characteristics of the aircraft.

[0050] An activation signal receiving circuit 002, configured to receive an activation signal, generate activation current information and activation pulse voltage information according to the activation signal, and output the activation current information and the activation pulse voltage information;

[0051] In a specific implementation, the activation signal receiving circuit includes:

[0052] An activation loop equivalent resistance module 021, which can be multiplexed with multiple activation signal input channels;

[0053] A voltage sensor 022, connected between the activation loop equivalent resistance module and the activation signal input channel, for detecting the voltage of each activation signal input channel;

[0054] A first controllable switch 023, connected between the activation loop equivalent resistance module and the activation signal input channel, for changing the situation where the activation loop equivalent resistance module is connected to the positive and negative input ends of the activation channel.

[0055] Preferably, please refer to Figure 3As shown, the equivalent resistance module 021 of the activation circuit includes a parallel circuit capable of changing the resistance connection situation and a current sensor capable of collecting the current flowing through the equivalent resistance module of the activation circuit; the parallel circuit includes at least one branch, and each branch includes at least one resistor and a second controllable switch 024 connected in series with the resistor.

[0056] Specifically, please continue to refer to Figure 1 As shown, a parallel circuit of a group of branches whose resistance connection situation can be controlled by the control signal CRn, and a current sensor capable of collecting the sum in of the currents flowing through all branches. The CRn is the control signal of the computer system for the nth activation signal receiving circuit, and n is a natural number greater than 1. The In is the current value collected by the current sensor of the current flowing through the equivalent resistance module of the activation circuit in the nth activation signal receiving circuit, and n is a natural number greater than 1. The parallel circuit controllable by the control signal CRn includes the series connection of at least one second controllable switch and at least one resistor. The second controllable switch is controlled by the signal CRn, that is, the resistance of the parallel circuit can be controlled by the signal CRn to be the resistance value of the resistor in any one branch, or the resistance value after the parallel connection of the resistors in any number of branches.

[0057] Further preferably, please continue to refer to Figure 3 As shown, a voltage sensor is set for each activation signal input channel, and the input and output ends of each voltage sensor are correspondingly connected to the input and output ends of the equivalent resistance module of the activation circuit.

[0058] Specifically, it is composed of a first controllable switch device capable of changing the multiplexing access situation of the equivalent resistance module of the activation circuit, and can be controlled by the control signal CRn.

[0059] The detonation simulation circuit 003 is used to receive the switch control signal, generate analog power supply current information and normally open / normally closed signals according to the switch control signal, and output the analog power supply current information;

[0060] In a specific implementation, the detonation simulation circuit includes a normally open signal quantity generation circuit, a normally closed signal quantity generation circuit, and an analog power supply channel control circuit provided correspondingly for each activation channel;

[0061] Among them, the normally open signal quantity generation circuit is in a non-conducting high-resistance state before the input of an effective activation signal, and can become a conducting low-resistance state after the input;

[0062] The normally closed signal quantity generation circuit is in a conducting low-resistance state before the input of an effective activation signal, and becomes a non-conducting high-resistance state after the input;

[0063] The analog power supply channel control circuit can be controlled by a computer control circuit to change the conduction state between a set of power input terminals and corresponding power output terminals. Before the input of a valid activation signal, the power input and output terminals are in a disconnected state, and they become conductive after the activation signal is input.

[0064] Each of the analog power supply channel control circuits further includes a current sensor capable of obtaining the analog power supply current information of the analog power supply channel control circuit.

[0065] Preferably, the detonation simulation circuit further includes a relay. The input terminal of the relay is electrically connected to the control system, and the output terminal is connected to the normally open signal quantity generation circuit, the normally closed signal quantity generation circuit, and the analog power supply channel control circuit.

[0066] In a possible application, as Figure 4 shown, the normally open signal quantity generation circuit includes a controllable switch device that can be controlled by a computer system control signal COn. The controllable switch device has at least two ports as the detection ports of the normally open signal quantity. The impedance between the detection ports is not affected by the measurement polarity and can be controlled by the control signal COn to be in two states: low resistance or high resistance. When there is no drive from the control signal COn, it is in the high-resistance state. Preferably, the low-resistance state is less than 1Ω, and the high-resistance state is greater than 10MΩ.

[0067] The normally closed signal quantity generation circuit includes a controllable switch device that can be controlled by a control signal COn. The controllable switch device has at least two ports as the detection ports of the normally closed signal quantity. The impedance between the detection ports is not affected by the measurement polarity and can be controlled by the control signal COn to be in two states: low resistance or high resistance. When there is no drive from the control signal COn, it is in the low-resistance state. Preferably, the low-resistance state indicates an impedance less than 1Ω, and the high-resistance state indicates an impedance greater than 10MΩ.

[0068] The analog power supply channel control circuit includes a set of power input terminals (including at least positive and negative two ports), a set of power output terminals (including at least positive and negative two ports), a current sensor that can measure the current ion flowing through the power supply channel, and a controllable switch device that can be controlled by a control signal COn.

[0069] The power input terminals are connected to the output ports of an external analog power supply. The power output terminals are connected to the input ports of a load that requires analog power supply. The controllable switch device can be controlled by the signal COn to disconnect or conduct the electrical relationship between the power input terminals and the power output terminals, and when there is no drive from the control signal COn, the controllable switch device is in the disconnected state. The Ion is the current value of the current flowing through the nth power supply channel collected by the current sensor, where n is a natural number greater than 1.

[0070] The control system 004 is electrically connected to the aircraft identification circuit, the activation signal receiving circuit, and the detonation simulation circuit, and is used to receive the aircraft identification information, the activation current information, the activation pulse voltage information, and the simulated power supply current information;

[0071] In a specific implementation, it includes a data acquisition interface circuit that can receive the above-mentioned aircraft identification information, the activation signal voltage collected by the voltage sensor, the activation current collected by the current sensor, and the power supply channel current signal; a drive circuit that can output all the above control signals; a computer hardware circuit that can store and execute the general detonation simulator software program; and a human-computer interaction interface, preferably including a display screen interface, a keyboard, a mouse, and a network interface.

[0072] Preferably, the above computer control circuit is a computer system with the PC104 bus as the core, and the implementation of functional circuits such as data acquisition and switch control preferably uses compact modular boards.

[0073] In a possible application, please refer to Figure 1 , the computer control circuit includes: a data acquisition interface circuit that can receive the above-mentioned aircraft identification information M, the activation signal voltage Un collected by the voltage sensor, the activation current In collected by the current sensor, and the power supply channel current Ion signal; a drive circuit that can output the above CRn and COn control signals.

[0074] Among them, the control system obtains the working mode information corresponding to the aircraft identification information through the aircraft identification information, and the working mode information includes preset information and activation signal validity criterion information;

[0075] The control system judges whether the detonation simulation circuit receives a valid activation signal according to the working mode information. If so, it sends a switch control signal to the detonation simulation circuit.

[0076] This embodiment can be compatible with the interface requirements of different aircraft through the multi-channel multiplexing of the activation loop equivalent resistance module and the flexible control of the resistance value. It is equipped with special software, which realizes the automatic setting of the working mode after connecting the matching cable to meet the test requirements of different aircraft launch control docking tests. During the use process, manual operations are minimized to avoid the risk of misoperations, and the test results can be displayed and judged. It can accurately judge whether the activation process meets the timing requirements, improving safety and accuracy. The general detonation simulator described in the present invention can be used for different stages of aircraft or other models of the same series, improving the versatility and utilization rate of the detonation simulator, and using the same design method and software implementation approach to reduce the test cost of the aircraft and avoid the technical risks and schedule risks brought by the development of the detonation simulator.

[0077] This embodiment also provides a method for simulating the point detonation of an adaptive aircraft system, which is used for the point detonation simulation system of any one of the adaptive aircraft systems in the first aspect. Please refer to Figure 5 as shown, including:

[0078] 100. Obtain aircraft identification information;

[0079] In a specific implementation, whether the general point detonation simulator is connected to an effective adapter cable, that is, whether the input aircraft identification information M is valid. When the detection is invalid, it has to be continuously executed until valid aircraft identification information is obtained.

[0080] 200. Execute operations according to the aircraft identification information;

[0081] Specifically, according to the aircraft identification information, obtain the working mode information corresponding to the aircraft identification information. The working mode information includes preset information and activation signal validity criterion information. The preset information includes the activation pulse voltage timing sequence of each channel, activation current information, the acquisition sequence of the current output information of the simulated battery power supply, the control of the access activation channel and the equivalent resistance combination, and the determination of the upper and lower limits of the normal range for collecting the activation current information, activation pulse voltage information, and simulated power supply current information of each channel. The activation pulse voltage timing sequence includes the relative time and holding time of the activation voltage generation moment of each channel;

[0082] 300. The activation signal receiving circuit obtains the activation signal, generates activation current information and activation pulse voltage information according to the activation signal, and outputs the activation current information and activation pulse voltage information to the control system;

[0083] 400. The control system determines whether the activation current information and activation pulse voltage information meet the requirements according to the working mode information;

[0084] 500. The control system determines whether the point detonation simulation circuit receives a valid activation signal according to the working mode information. If so, it sends a switch control signal to the point detonation simulation circuit;

[0085] 600. The point detonation simulation circuit generates simulated power supply current information and normally open / closed signals according to the switch control signal, and outputs the simulated power supply current information to the control system;

[0086] 700. The control system determines whether the simulated power supply current information meets the requirements according to the working mode information.

[0087] In a specific implementation, the activation signal input information obtained is Un and In. According to the working mode information, it is possible to detect whether a valid activation signal is input to the general ignition simulator. After detecting the input of a valid activation signal, the COn signal is output to generate normally open and normally closed signals simulating the actions of the real system and to control the closing of the power supply channel.

[0088] Furthermore, the activation current information, activation pulse voltage information, and simulated supply current information are obtained.

[0089] In a specific implementation, obtaining the activation current information, activation pulse voltage information, and simulated supply current information can be understood as obtaining the activation pulse voltage timings of each channel, activation current information, and the current output information of the simulated battery power supply.

[0090] The activation current information, activation pulse voltage information, and simulated supply current information are compared and analyzed with the working mode information to obtain a quality report. The quality report includes the analysis results displayed in the form of a timing diagram. The working mode information includes the activation current information, activation pulse voltage information, and simulated supply current information corresponding to the aircraft identification information.

[0091] In a specific implementation, it can be understood that the activation pulse voltage timings of each channel, activation current information, and the current output information of the simulated battery power supply obtained are compared and analyzed with the acquisition sequences of the activation pulse voltage timings of each channel, activation current information, and the current output information of the simulated battery power supply in the working mode information, and the analysis results are displayed on the display.

[0092] It should also be noted that the term "including", "comprising", or any other variant thereof is intended to cover non-exclusive inclusion, such that a process, method, commodity, or device including a series of elements not only includes those elements but also includes other elements not explicitly listed, or further includes elements inherent to such process, method, commodity, or device. Without further limitations, an element defined by the statement "including one..." does not exclude the existence of additional identical elements in the process, method, commodity, or device including the said element.

[0093] The above are only the embodiments of the present application and are not used to limit the present application. For those skilled in the art, various changes and modifications can be made to the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included within the scope of the claims of the present application.

Claims

1. A point detonation simulation system for an adaptive aircraft system, characterized in that, it includes: An aircraft identification circuit for identifying the electrical characteristics of a cable connector connected to the aircraft and outputting aircraft identification information, where the electrical characteristics refer to the conduction conditions between several pairs of contacts of the cable connector; An activation signal receiving circuit for receiving an activation signal, generating activation current information and activation pulse voltage information according to the activation signal, and outputting the activation current information and the activation pulse voltage information; A point detonation simulation circuit for receiving a switch control signal, generating simulated power supply current information and normally open / closed signal according to the switch control signal, and outputting the simulated power supply current information; A control system electrically connected to the aircraft identification circuit, the activation signal receiving circuit and the point detonation simulation circuit for receiving the aircraft identification information, the activation current information, the activation pulse voltage information, and the simulated power supply current information; wherein, The control system obtains working mode information corresponding to the aircraft identification information through the aircraft identification information, and the working mode information includes preset information and activation signal validity criterion information; The control system judges whether the point detonation simulation circuit receives a valid activation signal according to the working mode information. If so, it sends a switch control signal to the point detonation simulation circuit.

2. A point detonation simulation system for an adaptive aircraft system according to claim 1, characterized in that, The aircraft identification circuit includes an optocoupler, one end of which is used to obtain the contact conduction condition, and the other end is electrically connected to the control system.

3. A point detonation simulation system for an adaptive aircraft system according to claim 1, characterized in that, The activation signal receiving circuit includes: An activation loop equivalent resistance module capable of being multiplexed with multiple activation signal input channels; A voltage sensor connected between the activation loop equivalent resistance module and the activation signal input channel for detecting the voltage of each activation signal input channel; A first controllable switch connected between the activation loop equivalent resistance module and the activation signal input channel for changing the situation of the activation loop equivalent resistance module accessing the positive and negative input ends of the activation channel.

4. A point detonation simulation system for an adaptive aircraft system according to claim 3, characterized in that, The activation loop equivalent resistance module includes a parallel circuit capable of changing the resistance access situation and a current sensor capable of collecting the current flowing through the activation loop equivalent resistance module; the parallel circuit includes at least one branch, and each branch includes at least one resistor and a second controllable switch connected in series with the resistor.

5. A point detonation simulation system for an adaptive aircraft system according to claim 3, characterized in that, A voltage sensor is provided for each activation signal input channel, and the input and output ends of each voltage sensor are correspondingly connected to the input and output ends of the activation loop equivalent resistance module.

6. A point detonation simulation system for an adaptive aircraft system according to claim 1, characterized in that, The point detonation simulation circuit includes a normally open signal quantity generation circuit, a normally closed signal quantity generation circuit, and a simulated power supply channel control circuit provided for each activation channel correspondingly; Among them, the normally open signal quantity generation circuit is in a non-conductive high-impedance state before the input of an effective activation signal, and can become a conductive low-impedance state after the input; The normally closed signal quantity generation circuit is in a conductive low-impedance state before the input of an effective activation signal, and becomes a non-conductive high-impedance state after the input; The analog power supply channel control circuit can be controlled by the computer control circuit to change the conduction state of a group of power input terminals and corresponding power output terminals. Before the input of an effective activation signal, the power input and output terminals are in a disconnected state, and become conductive after the activation signal is input; Each of the analog power supply channel control circuits further includes a current sensor capable of obtaining the analog power supply current information of the analog power supply channel control circuit.

7. A detonation simulation system of an adaptive aircraft system as described in claim 6, characterized in that the detonation simulation circuit further includes a relay, the input end of the relay is electrically connected to the control system, and the output end is connected to the normally open signal quantity generation circuit, the normally closed signal quantity generation circuit and the analog power supply channel control circuit.

8. A detonation simulation system of an adaptive aircraft system as described in claim 1, characterized in that the control system further includes a human-computer interaction interface.

9. A detonation simulation method for an adaptive aircraft system, used for the detonation simulation system of any one of claims 1-8 of the adaptive aircraft system, characterized in that it includes: obtaining aircraft identification information; According to the aircraft identification information, obtaining the corresponding working mode information, the working mode information includes preset information and activation signal validity criterion information, the preset information includes the activation pulse voltage timing of each channel, activation current information, the acquisition sequence of the current output information of the analog battery power supply, the control of the access activation channel and equivalent resistance combination, and determining the upper and lower limits of the normal range of collecting the activation current information, activation pulse voltage information and analog power supply current information of each channel. The activation pulse voltage timing includes the relative time and holding time of the activation voltage generation moment of each channel; The activation signal receiving circuit obtains the activation signal, generates activation current information and activation pulse voltage information according to the activation signal, and outputs the activation current information and activation pulse voltage information to the control system; The control system judges whether the activation current information and activation pulse voltage information meet the requirements according to the working mode information; The control system judges whether the detonation simulation circuit receives an effective activation signal according to the working mode information. If so, it sends a switch control signal to the detonation simulation circuit; The detonation simulation circuit generates analog power supply current information and normally open / closed signals according to the switch control signal, and outputs the analog power supply current information to the control system; The control system judges whether the analog power supply current information meets the requirements according to the working mode information.

10. The method as described in claim 9, characterized in that comparing and analyzing the activation current information, activation pulse voltage information and analog power supply current information with the working mode information to obtain a quality report, and the quality report includes the analysis result displayed in the form of a timing diagram.

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