Flight management system sensor simulation test method based on RT real-time environment

Abstract

The invention belongs to the technical field, and relates to a flight management system sensor simulation test method based on an RT real-time environment. Real-time fault simulation of a bus signal output by a sensor is realized by a flight management system semi-physical test method verification platform through a software programming technology and a programmable software interface technology; comprising the steps of single-byte setting, fault data simulation, normal data simulation, switching between a sensor bus signal simulation interface and a real object interface, bus signal transmission path fault simulation and flight management system sensor simulation test. The semi-physical simulation test method is high in real-time performance, small in size, strong in function, high in precision and capable of achieving the functions of fault simulation, data interaction, object / simulation interface switching and the like of bus signals, and has the advantages of being high in speed, comprehensive in function, capable of achieving fault simulation and the like.

Description

Technical Field

[0001] The invention belongs to the technical field and is a flight tube system sensor simulation test method based on RT real-time environment. Background Art

[0002] There are few real-time semi-physical simulation test methods for data interaction and bus signal simulation of sensors such as intelligent probes, inertial navigation and gyro components in the flight control system, while ensuring the consistency of simulation interfaces with physical interfaces. There are uncontrollable time risks in the development cycle of flight control system tests, which greatly increases the development cost. Traditional test methods are mainly manual tests and semi-automatic tests. The equipment used in the tests is basically a simulation test system built with discrete instruments, meters or equipment, which has the disadvantages of no real-time performance, complex system, poor operability, poor maintainability, high labor costs, and long test cycles. Summary of the invention

[0003] Purpose of the Invention

[0004] The purpose of the present invention is to provide a semi-physical simulation test method for the test of flight control system sensors, which has high real-time performance, small size, strong functions, high precision, and can realize bus signal fault simulation, data interaction and physical / simulation interface switching. It has many advantages such as fast speed, comprehensive functions and fault simulation.

[0005] Technical Solution

[0006] A flight control system sensor simulation test method based on RT real-time environment includes the following:

[0007] Through software programming technology and programmable software interface technology, the flight control system semi-physical test method verification platform is used to realize real-time fault simulation of bus signals output by sensors, including single-byte setting, fault data simulation, normal data simulation, switching between sensor bus signal simulation interface and physical interface, and bus signal transmission path fault simulation, to carry out flight control system sensor simulation test.

[0008] Further, the specific steps are:

[0009] Step 1: Composition of the sensor test method verification platform: The test method verification platform is mainly composed of a high-speed switch, a power supply, a bus interface and software. The high-speed switch is used for signal switching and disconnection. The software is used to implement the logic instructions of each simulation experiment. The bus interface is used for signal transmission. The power supply provides power for the module.

[0010] Step 2 Sensor test method verification platform working principle: The sensor test method verification platform is connected to the sensor port of the signal adapter. There is a network-controlled SPDT switch module inside the function box. The SPDT switch module realizes the simulation and physical switching of the RS422 signal of the sensor and external device. The simulation signal is simulated by the RS422 board of the lower computer and connected to the signal adapter box through the adapter board in the function box. The effective data signal of each sensor and external device is simulated according to the interface protocol.

[0011] Furthermore, it also includes the form of the test method verification platform in step 3: the sensor test method verification platform adopts a cabinet form, and other functional modules and lower and upper computers are placed in the semi-physical test electrical equipment cabinet of the flight control system.

[0012] Furthermore, the sensor bus signal fault simulation includes a physical layer and a protocol layer.

[0013] Furthermore, the physical layer includes hardware physical disconnection, and the disconnection includes multiple simulation modes such as single disconnection, partial disconnection and complete disconnection.

[0014] Furthermore, the protocol layer includes bus communication frame count stop updating, checksum exception, data error and communication cycle change failure modes.

[0015] Furthermore, the test method verification is specifically polarity transmission ratio test, redundancy management test, time domain test, and flight-in-the-loop test.

[0016] Furthermore, the collected signals of the sensor include left L, right L, inertial navigation, and gyroscope signals.

[0017] Furthermore, the external equipment includes a communication identification terminal, a task management computer, an altimeter, a radar transponder, a remote interface device, an anti-skid brake control box, and a power supply control device.

[0018] The beneficial effects of this application are:

[0019] The present invention realizes semi-physical simulation of flight control system sensors based on RT real-time system verification platform through universal software programming technology and programmable interface software technology, and determines the test method of semi-physical simulation of flight control system sensors, which includes interface simulation, fault simulation, test item simulation, etc.

[0020] a) Other similar sensor bus signal simulation faults and simulation / physical switching solutions;

[0021] b) Other simulated faults and simulation / real switching solutions for similar analog signals. Other simulated faults and simulation / real switching solutions for similar analog signals. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is the working principle diagram of the test method verification platform;

[0023] Figure 2 A schematic diagram of the method flow chart. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical scheme and advantages of the implementation of the present invention clearer, the technical scheme in the embodiment of the present invention will be described in more detail in combination with the embodiment of the present invention. In the example, the same or similar reference numerals throughout represent the same or similar originals or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, not all of them. The embodiments described below by reference are exemplary and intended to be used to explain the present invention, and should not be construed as limitations on the present invention. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present invention. The following is a detailed description in combination with the embodiments of the present invention.

[0025] 1. The sensor test method verification platform consists of the following parts: The test method verification platform mainly consists of high-speed switches, power supplies, bus interfaces and software.

[0026] 2. The working principle of the sensor test method verification platform is as follows: The sensor test method verification platform is connected to the sensor port of the signal adapter. There is a network-controlled SPDT switch module inside the function box. The SPDT switch module realizes the simulation and physical switching of RS422 signals of sensors (left L, right L, inertial navigation, gyroscope) and external devices (communication identification terminal, task management computer, altimeter, radar transponder, remote interface device, anti-skid brake control box, power supply control device). The simulation signal is simulated by the RS422 board of the lower computer and connected to the signal adapter box through the adapter board in the function box. The effective data signals of each sensor and external device are simulated according to the interface protocol.

[0027] 3. The sensor test method verification platform adopts a cabinet form, in which other functional modules and lower and upper computers are placed in the semi-physical test electrical equipment cabinet of the flight control system.

[0028] 4. The test method verification platform can achieve the following functions:

[0029] a) Realize real-time fault simulation of bus signals output by sensors, including single-byte setting, fault data simulation, and normal data simulation;

[0030] b) Realize the switching between the sensor bus signal simulation interface and the physical interface, and the bus signal transmission path fault simulation;

[0031] c) Transfer physical signals of inertial navigation components, heading and attitude components, intelligent probes, etc.

[0032] First, the bus interface of the inertial navigation, gyroscope, and multi-function probe is simulated and tested to verify the correctness of the bus interface and the integrity of the function. If the interface is not implemented properly, it is easy to cause system failures and functional defects. Therefore, it is very important to test the interface to ensure that the interface is implemented correctly, the data interaction between the interfaces is correct, and the fault tolerance of the interface is sufficient.

[0033] Secondly, the sensor bus signal fault simulation of the flight control system is mainly reflected in the physical layer and protocol layer. The physical layer includes hardware physical disconnection, and the disconnection includes multiple simulation modes such as single disconnection, partial disconnection and complete disconnection. The protocol layer mainly includes failure modes such as bus communication frame count stop updating, checksum anomaly, data error and communication cycle change. The bus fault simulation verifies the reliability and stability of the flight control system sensor bus transmission from different methods.

[0034] Finally, according to the different test requirements of the flight control system, the sensor simulation technology is fully tested and verified. The test items mainly include polarity transmission ratio test (including normal and fault conditions), redundancy management test, time domain test (including normal and fault conditions) and flight-in-the-loop test. The purpose of the test is mainly to verify whether the flight control logic of the flight control system meets the design requirements, and to conduct sufficient test verification in the ground test environment to improve the flight safety of the aircraft.

[0035] Through the verification of the simulation method of the flight control system sensor mentioned above, a semi-physical simulation test method with high real-time performance, small size, strong function, high precision and the ability to realize bus signal fault simulation, data interaction and physical / simulation interface switching can be provided for the test of the flight control system sensor. It has many advantages such as fast speed, comprehensive functions and fault simulation.

[0036] It is understood by those skilled in the art that, unless otherwise defined, all terms (including technical terms and scientific terms) used herein have the same meaning as the general understanding of ordinary technicians in the field to which the present invention belongs. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and unless defined as here, will not be interpreted with idealized or overly formal meanings. The specific implementation methods described above further describe the purpose, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the present invention. Within the spirit and principle of the present invention, any technician familiar with the profession may use the above disclosed technical content to change or modify it into an equivalent embodiment of equivalent changes for application in other fields, but any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the technical solution content of the present invention, any modification, equivalent replacement, improvement, etc., made according to the technical essence of the present invention, should be included in the protection scope of the present invention.

Claims

1. A flight control system sensor simulation test method based on RT real-time environment, characterized in that: These include: Through software programming technology and programmable software interface technology, the flight control system semi-physical test method verification platform is used to realize real-time fault simulation of bus signals output by sensors, including single-byte setting, fault data simulation, normal data simulation, switching between sensor bus signal simulation interface and physical interface, and bus signal transmission path fault simulation, to carry out flight control system sensor simulation test.

2. The method according to claim 1, characterized in that The specific steps are: Step 1: Composition of the sensor test method verification platform: The test method verification platform is mainly composed of a high-speed switch, a power supply, a bus interface and software. The high-speed switch is used for signal switching and disconnection. The software is used to implement the logic instructions of each simulation experiment. The bus interface is used for signal transmission. The power supply provides power for the module. Step 2 Working principle of the sensor test method verification platform: The sensor test method verification platform is connected to the sensor port of the signal adapter. There is a network-controlled SPDT switch module inside the function box. The SPDT switch module realizes the simulation and physical switching of RS422 signals of sensors and external devices; the simulation signal is simulated by the RS422 board of the lower computer and connected to the signal adapter box through the adapter board inside the function box; the valid data signals of each sensor and external device are simulated according to the interface protocol.

3. The method according to claim 2, characterized in that It also includes step 3 test method verification platform form: the sensor test method verification platform adopts a cabinet form, and other functional modules and lower and upper computers are placed in the flight control system semi-physical test electrical equipment cabinet.

4. The method according to claim 3, characterized in that Sensor bus signal fault simulation includes physical layer and protocol layer.

5. The method according to claim 4, characterized in that The physical layer includes hardware physical disconnection, and the disconnection includes multiple simulation modes such as single disconnection, partial disconnection and complete disconnection.

6. The method according to claim 5, characterized in that The protocol layer includes bus communication frame count stop updating, checksum exception, data error and communication cycle change failure modes.

7. The method according to claim 6, characterized in that The test method verification includes polarity transmission ratio test, redundancy management test, time domain test and flight-in-the-loop test.

8. The method according to claim 7, characterized in that The collected signals of the sensor include left L, right L, inertial navigation, and gyroscope signals.

9. The method according to claim 8, characterized in that The external equipment includes a communication identification terminal, a task management computer, an altimeter, a radar transponder, a remote interface device, an anti-skid brake control box, and a power supply control device.

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