CN109855651B - Ground test system and test method for modern aircraft radio communication navigation system - Google Patents
Ground test system and test method for modern aircraft radio communication navigation system Download PDFInfo
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- 238000012360 testing method Methods 0.000 title claims abstract description 109
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- 238000004088 simulation Methods 0.000 claims abstract description 57
- 238000005516 engineering process Methods 0.000 claims abstract description 12
- 238000005259 measurement Methods 0.000 claims abstract description 6
- 238000013461 design Methods 0.000 claims abstract description 4
- 230000003068 static effect Effects 0.000 claims description 11
- 238000012795 verification Methods 0.000 claims description 11
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Abstract
The invention relates to a ground test system and a ground test method of a modern aircraft radio communication navigation system, which are characterized in that: the test system consists of a test master control module, an excitation module and a simulation module, wherein the master control module controls the excitation module and the simulation module through the Ethernet, and the excitation module and the simulation module are used as independent devices to respectively realize excitation and simulation; the ground test system is based on PXI bus synthesis instrument technology, adopts a modularized design, realizes signal excitation and measurement by means of computer application and Ethernet control, and verifies the correctness of functions and input/output interfaces of the development equipment.
Description
Technical Field
The invention belongs to the field of aircraft avionics system design, and discloses a system ground test method for optimizing a space architecture of a radio communication navigation system by using a PXI modularized technology to realize real-time reliability of radio communication navigation test excitation and simulation.
Background
In order to ensure smooth development of the large-scale aircraft avionics system, the radio communication navigation excitation system is matched with an integrated verification environment to finish verification of functions and performances of the aircraft avionics system. With the development of general aviation, modular instrument technology is widely adopted at home and abroad to perform excitation, simulation and test of radio communication navigation. BAE System company has developed the radio communication navigation test equipment based on PXI radio frequency module, and some type of machine of China precious flying company has also used the radio compass, takang, altimeter comprehensive simulator based on PXI radio frequency module. The development technology of the aviation radio comprehensive test equipment based on the PXI radio frequency module is increasingly developed, and compared with the traditional PXI integrated radio communication navigation system PXI modularized instrument technology integration framework, the system has the advantages of more advanced, miniaturized, easy maintenance, expandability and the like in space and performance, the radio communication navigation system optimized by adopting the PXI modularized technology is more convenient and efficient in use and test method, and the ground test verification of the airplane development is more sufficient.
Disclosure of Invention
The invention provides a ground test method of a modern aircraft radio communication navigation system, which utilizes dynamic flight data of a radio communication navigation excitation system and an avionic system integrated verification environment to manufacture a dynamic and comprehensive communication, navigation and monitoring radio frequency signal environment for a tested aircraft avionic system under the condition of a laboratory, simultaneously has the functions of simulating each device required by the participation of the radio communication navigation system in the avionic system integrated verification test, and can replace real devices to verify the functions of the research devices and the correctness of input and output interfaces.
The technical proposal of the invention is that
The ground test system of the modern aircraft radio communication navigation system consists of a test master control module, an excitation module and a simulation module, wherein the master control module controls the excitation module and the simulation module through Ethernet, and the excitation module and the simulation module are used as independent devices to realize excitation and simulation respectively.
The ground test system adopts PXI bus integrated modularized design, realizes signal excitation and measurement through software programming by combining with an FPGA technology, wherein a test master control module realizes overall control, flight parameter analysis and excitation simulation parameter setting; the excitation module receives the excitation parameters transmitted by the test master control module, outputs a radio frequency excitation signal to a test environment, and completes a radio frequency excitation function and a test function; the simulation module receives the simulation parameters transmitted by the test master control module, simulates the signal processing flow and input and output of the real equipment, and completes the simulation function of the airborne equipment.
The test master control module consists of a master control computer, an integrated keyboard display and an electric control assembly, wherein the master control computer receives dynamic flight data of a test environment through a LAN bus, processes required parameters, and then sends commands and data to the excitation module and the simulation module through the LAN bus to enable the excitation module and the simulation module to output corresponding signals; the man-machine interaction port is used for displaying test states and test data, inputting parameters, test operation and the like; the electric control assembly realizes power control and electric protection of the whole system and comprises a main control computer, an excitation module and a simulation module for providing stable power supply.
The excitation module adopts a PXI bus technology, and consists of a PXI chassis, an embedded computer and a plurality of PXI modules, wherein the embedded computer and the PXI modules perform data interaction and trigger synchronization through a PXI backboard bus; the embedded computer receives the excitation parameters transmitted by the test master control module through the Ethernet, controls the PXI module to output the required radio frequency excitation signals after analysis and processing, and realizes the excitation function through the test system.
The simulation module adopts PXI bus technology, and consists of a PXI chassis, an embedded computer and the PXI module, wherein the embedded computer and the PXI module carry out data interaction and trigger synchronization through a PXI backboard bus, the embedded computer receives simulation parameters transmitted by the test master control module through the Ethernet, and the simulation module controls an ARINC-429 bus board card and a discrete IO board card in the simulation module to input and output data and signals through a corresponding simulation model algorithm, so that the input and output of real equipment are simulated, and the function of simulating the real equipment is realized.
The ground test method of the modern aircraft radio communication navigation system comprises the steps that the ground test system receives control data from a flight simulation system in a remote state or receives related excitation parameters such as communication, navigation, monitoring and the like which are manually input in a local control state; the system generates corresponding radio frequency excitation under the control of the parameters, simulates radio frequency signals received by aircraft airborne communication, navigation and monitoring equipment from corresponding airborne antennas, enables a platform to communicate with an airborne system when certain parameters in the signals are changed randomly according to requirements, calculates expected navigation data through an airborne navigation receiver, and provides a radio frequency signal environment for a tested aircraft avionic system under the ground laboratory condition to realize laboratory simulated flight verification; the ground test method adopts a mode of combining dynamic test with static test to complete display, control, data transmission and data processing of the ground test of the radio communication navigation system, and relates to functional verification of test objects.
The static test of the radio communication navigation system comprises the following specific processes: the static test utilizes a measurement and control computer in a test platform to control an excitation unit to load excitation or input signals to related equipment, and a control box or a simulation control box is used for setting radio navigation equipment to be in a corresponding working state, and the PXI platform acquires the working state and corresponding working data of the tested avionics through signal acquisition and data communication, so that the aim of testing the tested avionics is fulfilled; when the test system joint test is abnormal, manual test can be performed, and fault injection debugging is performed in a manual state; the method comprises the steps of constructing an open circuit fault for physical line break through a switch switching system, constructing a short circuit fault through a debugging interface ground, and constructing related communication faults through setting of parity check, code rate, coding and label bits through software communication.
The dynamic test of the radio communication navigation system comprises the following specific processes: dynamic testing sends and receives various data to and from the on-board device through the simulation environment. Adopting a multi-task distributed real-time simulation system to realize signal injection and signal acquisition analysis; the flight simulation environment in the system test platform realizes remote control of the excitation module through the Ethernet, and the excitation module simultaneously sets working parameters through system software to realize real-time excitation of the excitation module.
The invention has the following beneficial effects: the system based on PXI bus synthesis synthesizes, the modularized test environment construction, breaks through the shortcomings of fixed functions, huge test system volume, poor expandability and the like of the traditional radio equipment, and the limitation of taking special hardware as a core, establishes a general hardware platform as a basis, has the capability of real-time configuration, and realizes various test cases of application software in an open mode. Different application software can be configured on the same hardware platform to meet the requirements of different periods, different use environments and different system functions. The test system releases the testers from the manual test process with large operation amount and complexity, and more attention is paid to the analysis of the tested system. The ground test method can generate great economic benefit on civil airliners, and can be widely applied to the field of integration verification of avionics systems of civil airliners.
Drawings
FIG. 1 is a schematic diagram of a ground test system of a modern aircraft radio navigation system;
FIG. 2 is a schematic diagram of a static test block diagram of a radio communication navigation system;
FIG. 3 is a schematic diagram of a dynamic test block diagram of a radio communication navigation system;
FIG. 4 is a functional logic diagram of a ground test system of the radio communication navigation system;
FIG. 5 is a schematic diagram of a radio communication navigation system software logic information flow;
fig. 6 is a schematic diagram of a radio communication navigation system software workflow.
Detailed Description
As shown in FIG. 1, the ground test system provided by the embodiment of the invention mainly adopts a mode of combining dynamic test with static test, and can effectively complete display, control, data transmission and data processing of the ground test of the radio communication navigation system, and relates to functional verification of test objects.
Static test of radio communication navigation system:
the static test utilizes a measurement and control computer in a test platform to control an excitation unit to load excitation (or input) signals to related equipment, and a control box or a simulation control box sets radio navigation equipment to be in a corresponding working state, and the PXI platform acquires the working state and corresponding working data of the tested avionics through signal acquisition and data communication, so that the purpose of testing the tested avionics is achieved. As in figure 2
In addition, the test system can also carry out manual test, and is mainly used for carrying out fault injection debugging in a manual state when the system joint test is abnormal; the method comprises the steps of constructing an open circuit fault for physical line break through a switch switching system, constructing a short circuit fault through a debugging interface ground, and constructing related communication faults through setting of parity check, code rate, coding and label bits through software communication.
Dynamic test of radio communication navigation system:
dynamic testing sends and receives various data to and from the on-board device through the simulation environment. And a multitasking distributed real-time simulation system is adopted to realize the researches such as signal injection, signal acquisition analysis and the like. The flight simulation environment in the system test platform realizes remote control of the excitation module through the Ethernet, and the excitation module simultaneously sets working parameters through system software to realize real-time excitation of the excitation module. As shown in FIG. 3
The hardware scheme of the ground test method provided by the embodiment of the invention is divided into a test master control module, an HF communication excitation module, a VHF communication excitation module, a VOR/MB combined excitation module, a DME excitation module, an ILS excitation module, an RA excitation module, an ADF excitation module, an ATC excitation module, a TCAS excitation module, a GPS excitation module, a radio communication navigation simulation module and a radio communication navigation test module according to functional logic. As shown in FIG. 4
The ground test method software proposal provided by the embodiment of the invention comprises a test master control software module, an excitation software module and a simulation software module, adopts a main dispatching program to call each functional module, and is required to realize the static output control of the excitation signal of an excitation system, receive the remote simulation data of a flight simulation system to control the output of the excitation signal in real time, and output the excitation signal according to a data script (the script format is provided by the flight simulation system) so as to realize the test flow. The test master control software module runs in a master control computer of the master control software module, a main program of the excitation software module runs in an embedded computer of the excitation software module, a PFGA program of the excitation software module runs in a PFGA of a FlexRIO board card of the excitation software module, and the simulation software module runs in the embedded computer of the simulation software module. The test function is realized by a test master control software module, an excitation software module and a simulation software module. As shown in FIG. 5
The ground test method provided by the embodiment of the invention has the advantages that the system software workflow covers a human-computer interface, remote control, test log management and excitation module control several functional modules. The human-computer interface module is responsible for generating various human-computer interfaces and completing the input of excitation parameters and the reality of the states and return parameters of the excitation module; the remote control module is in charge of interfacing with the flight simulation system, receiving remote control data and resolving, thereby generating excitation parameters; the test log management module is responsible for generating and storing test logs and realizing the playback and retrieval functions of the logs; the excitation control module is responsible for issuing excitation parameters and excitation control and receiving return states and parameters thereof. As shown in FIG. 6
While the foregoing is directed to the preferred embodiments of the present invention, it will be appreciated by those skilled in the art that changes and modifications may be made without departing from the principles of the invention, such changes and modifications are also intended to be within the scope of the invention.
Claims (4)
1. The ground test system of the modern aircraft radio communication navigation system is characterized in that: the ground test system consists of a test master control module, an excitation module and a simulation module, wherein the master control module controls the excitation module and the simulation module through the Ethernet, and the excitation module and the simulation module are used as independent equipment to respectively realize excitation and simulation so as to verify the correctness of functions of developing equipment and input/output interfaces; the ground test system adopts PXI bus integrated modularized design, realizes signal excitation and measurement through software programming by combining with an FPGA technology, wherein a test master control module realizes overall control, flight parameter analysis and excitation simulation parameter setting; the excitation module receives the excitation parameters transmitted by the test master control module, outputs a radio frequency excitation signal to a test environment, and completes a radio frequency excitation function and a test function; the simulation module receives the simulation parameters transmitted by the test master control module, simulates the signal processing flow and input and output of real equipment, and completes the simulation function of the airborne equipment; the test master control module consists of a master control computer, an integrated keyboard display and an electric control assembly, wherein the master control computer receives dynamic flight data of a test environment through a LAN bus, processes required parameters, and then sends commands and data to the excitation module and the simulation module through the LAN bus to enable the excitation module and the simulation module to output corresponding signals; the man-machine interaction port is used for displaying the test state and test data, inputting parameters and test operation; the electric control assembly realizes power control and electric protection of the whole system and comprises a main control computer, an excitation module and a simulation module; the excitation module adopts a PXI bus technology, and consists of a PXI chassis, an embedded computer and a plurality of PXI modules, wherein the embedded computer and the PXI modules perform data interaction and trigger synchronization through a PXI backboard bus; the embedded computer receives the excitation parameters transmitted by the test master control module through the Ethernet, controls the PXI module to output the required radio frequency excitation signals after analysis and processing, and realizes the excitation function through the test system; the simulation module adopts PXI bus technology, and consists of a PXI chassis, an embedded computer and the PXI module, wherein the embedded computer and the PXI module carry out data interaction and trigger synchronization through a PXI backboard bus, the embedded computer receives simulation parameters transmitted by the test master control module through the Ethernet, and the simulation module controls an ARINC-429 bus board card and a discrete IO board card in the simulation module to input and output data and signals through a corresponding simulation model algorithm, so that the input and output of real equipment are simulated, and the function of simulating the real equipment is realized.
2. The test method of the modern aircraft radio communication navigation system is characterized in that: the ground test system of claim 1, receiving control data from a flight simulation system in a remote state, or receiving manually entered communication, navigation and monitoring related excitation parameters in a local control state; the system generates corresponding radio frequency excitation under the control of the parameters, simulates radio frequency signals received by aircraft airborne communication, navigation and monitoring equipment from corresponding airborne antennas, enables a platform to communicate with an airborne system when certain parameters in the signals are changed randomly according to requirements, calculates expected navigation data through an airborne navigation receiver, and provides a radio frequency signal environment for a tested aircraft avionic system under the ground laboratory condition to realize laboratory simulated flight verification; the ground test method adopts a mode of combining dynamic test with static test to complete display, control, data transmission and data processing of the ground test of the radio communication navigation system, and relates to functional verification of test objects.
3. The test method according to claim 2, wherein the radio communication navigation system static test is performed as follows: the static test utilizes a measurement and control computer in a test platform to control an excitation unit to load excitation or input signals to related equipment, and a control box or a simulation control box is used for setting radio navigation equipment to be in a corresponding working state, and the PXI platform acquires the working state and corresponding working data of the tested avionics through signal acquisition and data communication, so that the aim of testing the tested avionics is fulfilled; when the test system joint test is abnormal, performing manual test, and performing fault injection debugging in a manual state; the method comprises the steps of constructing an open circuit fault for physical line break through a switch switching system, constructing a short circuit fault through a debugging interface ground, and constructing related communication faults through setting of parity check, code rate, coding and label bits through software communication.
4. The test method according to claim 2, wherein the radio communication navigation system dynamically tests the following procedure: the dynamic test sends and receives various data to the airborne equipment through the simulation environment; adopting a multi-task distributed real-time simulation system to realize signal injection and signal acquisition analysis; the flight simulation environment in the system test platform realizes remote control of the excitation module through the Ethernet, and the excitation module simultaneously sets working parameters through system software to realize real-time excitation of the excitation module.
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