CN114661029A - Airworthiness identification test system and method for civil aircraft flight control system - Google Patents
Airworthiness identification test system and method for civil aircraft flight control system Download PDFInfo
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- CN114661029A CN114661029A CN202210256959.6A CN202210256959A CN114661029A CN 114661029 A CN114661029 A CN 114661029A CN 202210256959 A CN202210256959 A CN 202210256959A CN 114661029 A CN114661029 A CN 114661029A
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- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0218—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
- G05B23/0256—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults injecting test signals and analyzing monitored process response, e.g. injecting the test signal while interrupting the normal operation of the monitored system; superimposing the test signal onto a control signal during normal operation of the monitored system
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
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- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24065—Real time diagnostics
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Abstract
The invention discloses a seaworthiness identification test system and method for a civil aircraft flight control system, wherein the method comprises the following steps: the tested piece represents a civil aircraft flight control system product; the real load simulates corresponding hardware equipment crosslinked with the civil aircraft flight control system through an actual product and provides a real electrical load characteristic for a tested piece; the simulation load simulates the interface and the electrical characteristics of the tested piece and the digital cross-linking equipment and communicates with the tested piece and the data simulation recording equipment; and the data simulation recording equipment inputs digital excitation to the simulation load so that the digital excitation is transmitted to the tested piece through the simulation load, and acquires and records a test result of data simulation of the tested piece through the simulation load in real time. The embodiment of the invention solves the problem that the airworthiness identification test cannot directly reflect the authenticity of the flight control system in normal loaded condition because various conditions in the airworthiness identification of the civil aircraft cannot be completely covered by the traditional civil aircraft airworthiness identification test scheme.
Description
Technical Field
The invention belongs to the technical field of flight, and particularly relates to a airworthiness identification test system and method.
Background
Modern commercial aircraft use more new technology to reduce pilot handling burden and improve flight quality, and fly-by-wire systems are increasingly being used to replace traditional mechanical handling systems.
For the development needs of new systems and new products for civil use, a huge investment is made in authentication and certification. The new system and the new product need to be certified according to industrial standards such as RTCA DO-160 and civil aviation safety regulations, and must be subjected to strict airworthiness certification tests to be considered safe and ready for use.
The airworthiness identification of the civil aircraft flight control system is a key element for supporting a civil large aircraft to obtain an airworthiness certificate, and is a prerequisite for supporting an onboard airworthiness test, and the passing of the airworthiness identification test is generally defined as a major key node of airworthiness identification work. In the rapid development of the Chinese aviation industry and the difficult process of obtaining evidence of the airworthiness of the domestic large-scale airplane, the importance of airworthiness identification work is more obvious.
In the traditional civil aircraft airworthiness identification test scheme, the simulation capability of the test monitoring simulation equipment is poor, various conditions in airworthiness identification cannot be completely covered, for example, the real loading condition of a system is difficult to simulate, so that the airworthiness identification test cannot directly reflect the authenticity of the system running under the normal loading condition.
In practical application, the classification of civil aircraft airworthiness appraisal is various: according to the difference of sighting requirements, the sighting certification can be divided into sighting certification and non-sighting certification; according to different test types, the method can be divided into a natural environment type identification test and an electromagnetic type identification test; if the destruction loss is different, it can be divided into a loss test and a non-loss test; according to the difference of the research and development stages, the method can be divided into a first flight stage test and an identification stage test.
Although the variety division of the civil aircraft airworthiness appraisal is various, the existing civil aircraft airworthiness appraisal test system has the same or different composition structure. Fig. 1 is a schematic structural diagram of a conventional airworthiness qualification testing system for civil aircraft airborne equipment, which takes the conventional airworthiness qualification testing system shown in fig. 1 as an example, and includes five parts, which are a tested piece, a cable, a test monitoring simulation device, a power supply and a testing environment. In the airworthiness identification test system, a tested piece is used as a main test object, such as a flight control computer, and is placed in a test environment, such as an incubator, a vibration table, an electromagnetic darkroom and the like; the cable is mainly used for connecting crosslinking equipment and providing transmission and protection capabilities; the test monitoring simulation equipment provides functions of simulation input excitation, real-time data monitoring, data recording and the like; the power supply provides operating power for the tested piece.
The airworthiness qualification test system of the conventional civil aircraft airborne equipment shown in the figure 1 has the following defects:
(1) the test monitoring simulation equipment does not have the load capacity of simulating the cross-linking equipment of the tested piece, so that the equipment-level identification cannot simulate the real load condition of the system and cannot directly reflect the authenticity of the system in the normal load condition;
(2) for electromagnetic tests, test monitoring simulation cannot represent the assessment of mutual electromagnetic influence between equipment cross-links in the airworthiness identification system.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a seaworthiness identification test system and method of a civil aircraft flight control system, which comprises the following steps: the tested piece represents a civil aircraft flight control system product; the real load is realized by simulating corresponding hardware equipment crosslinked with the civil aircraft flight control system through an actual product and providing the real electrical load characteristic for a tested piece; the simulation load simulates the interface and the electrical characteristics of the tested piece and the digital cross-linking equipment and communicates with the tested piece and the data simulation recording equipment; and the data simulation recording equipment inputs digital excitation to the simulation load so that the digital excitation is transmitted to the tested piece through the simulation load, and acquires and records a test result of data simulation of the tested piece through the simulation load in real time. The embodiment of the invention solves the problem that the airworthiness identification test cannot directly reflect the authenticity of the flight control system in normal loaded condition because various conditions in the airworthiness identification of the civil aircraft cannot be completely covered by the traditional civil aircraft airworthiness identification test scheme.
The technical scheme adopted by the invention for solving the technical problem comprises the following steps:
a airworthiness identification test system of a civil aircraft flight control system comprises a tested piece, a real load, a simulation load and data simulation recording equipment;
the tested piece represents a civil aircraft flight control system;
the real load comprises a discrete quantity load and an analog quantity load; the real load is used for simulating hardware equipment cross-linked with the civil aircraft flight control system through an actual product and providing real electrical load characteristics for a tested piece;
the artificial loads comprise A429 bus loads, actuator data bus loads and intra-system bus loads; the simulation load is used for simulating the interface characteristic and the electrical characteristic of the tested piece and the digital cross-linking equipment and communicating with the tested piece and the data simulation recording equipment;
the data simulation recording equipment is used for inputting digital excitation to the simulation load so that the digital excitation is transmitted to the tested piece through the simulation load and acquiring and recording a test result of the response of the tested piece in real time; the data simulation recording equipment comprises a data conversion box, an A429 computer, an actuator data computer, an in-system computer and a data exchange computer; the A429 computer is used for realizing A429 bus communication with a civil aircraft flight control system and comprises atmosphere, attitude and inertial navigation electric information; the actuator data computer is used for realizing the transmission of an actuating instruction with a civil aircraft flight control system and the safety monitoring of information such as an actuating state, a position and the like; the system internal bus computer is used for monitoring the state of the civil aircraft flight control system in real time and has the functions of fault synthesis and fault monitoring and reporting;
the A429 computer, the actuator data computer and the computer in the system are crosslinked with the corresponding A429 bus load, the actuator data bus load and the bus load in the system through the data conversion box, and the data communication and real-time monitoring functions with the tested piece are realized through the data conversion box;
the data exchange computer is connected with the simulation load through the data conversion box and is used for converting data of the data simulation recording equipment, providing power for the simulation load and carrying out electrical isolation protection on the simulation recording equipment.
Preferably, the piece under test comprises an actuator control electronics ACE and a flight control computer FCC.
Preferably, the real load is used for representing the input and interaction states of real sensors or discrete quantities in the civil aircraft flight control system.
Preferably, the discrete quantity load is a load simulating a real discrete state signal required by the flight control system, and is used for providing the aircraft or the system operation state to the flight control system.
Preferably, the discrete amount of loading is landing gear loading or primary flight mode switch loading.
Preferably, the analog load is a load simulating a real analog signal required by the flight control system to operate, and is used for providing a cockpit control or an airplane real sensor instruction for flight control.
Preferably, the analog load is a pitch analog load, a roll analog load, a foot pedal analog load and an attack angle sensor real load.
Preferably, the communication mode of the simulation load and the data simulation recording device is bus communication.
Preferably, the simulation load simulates the characteristics of a digital input/output interface of a real product to a tested piece, so that the integrity of the flight control system in an identification test is ensured; the artificial load has the following functions:
providing the same input and output interface characteristics as the real part to the flight control system;
the lightning-resistant and electromagnetic interference-resistant protection circuit is the same as the real part;
the simulation load powered by the secondary power supply of the flight control system has the same power consumption and power supply monitoring function as the real load;
the monitoring circuit can realize the functions of fault latching and clearing while realizing the monitoring function;
the data simulation recording device is provided with a data interface for communicating with the data simulation recording device.
A airworthiness identification test method for a civil aircraft flight control system comprises the following steps:
step 1: electrifying the data simulation recording equipment, and loading digital excitation to a simulation load connected with the data simulation recording equipment;
step 2; electrifying the tested piece, establishing bus communication with the simulation load, and loading the digital excitation on the tested piece;
and step 3: adjusting real load input end parameters;
and 4, step 4: operating a seaworthiness identification test system in a preset working scene to enable a flight control system to meet test conditions;
and 5: after the flight control system operates stably, applying environmental conditions for carrying out airworthiness identification tests; the environmental condition includes at least one of the following environmental threats: temperature, vibration, electromagnetic, lightning;
step 6: and acquiring and recording the response test result of the tested piece in real time.
The invention has the following beneficial effects:
compared with the traditional airborne equipment identification test system which only has the component-level function, the simulation monitoring equipment has no loading capacity, only has the real-time monitoring capacity of the component state, does not have the large data recording and storing capacity and the like, so that the traditional identification test system cannot meet the defect that the traditional identification test system cannot meet the evaluation of system-level HIRF protection and indirect lightning effect subjects in DO-160G; the airworthiness identification test system of the civil aircraft flight control system provided by the embodiment of the invention has the following beneficial effects:
(1) the system has the capability of representing system level functions, including a control law function, a redundancy management function, a system maintenance function and the like in a specified flight scene;
(2) the method has the characteristics of representing the interface load of the flight control system, specifically, in a system test, a part of cross-linked components of the flight control system adopts loads to replace physical components, including bus simulation loads and equivalent physical real loads, and represents the interface load characteristics of the flight control system;
(3) the system has the capability of realizing real-time monitoring of the system state, particularly, the internal data and the state of the flight control system can be read in real time through data simulation recording equipment, the flight control system is monitored in real time, and whether a fault occurs is answered;
(4) the regulation compliance can specifically conform to the assessment under all subjects of DO-160G.
Drawings
FIG. 1 is a schematic structural diagram of a airworthiness identification test system of a conventional civil aircraft airborne device;
FIG. 2 is a schematic diagram of the test system of the present invention.
FIG. 3 is a schematic diagram showing a detailed structure of the testing system of the present invention.
Detailed Description
The invention is further illustrated with reference to the following figures and examples.
The invention provides a seaworthiness identification test system of a civil aircraft flight control system, which aims to solve the problem that the authenticity of the flight control system in normal loaded condition is difficult to directly reflect by a seaworthiness identification test because various conditions in civil aircraft seaworthiness identification cannot be completely covered by a traditional civil aircraft seaworthiness identification test scheme.
A airworthiness identification test system of a civil aircraft flight control system comprises a tested piece, a real load, a simulation load and data simulation recording equipment;
the tested piece represents a civil aircraft flight control system and comprises an ACE and an FCC;
the real load comprises a discrete load and an analog load, the discrete load is a load of a real discrete state signal required by the operation of the flight control system and used for providing an aircraft or system operation state for the flight control system, and the discrete load is an undercarriage load or a main flight mode switch load and the like; the analog load is a load of a real analog signal required by the operation of a simulation flight control system and used for providing a cockpit control or an airplane real sensor instruction for flight control, and the analog load is a pitching analog load, a rolling analog load, a pedal analog load, an attack angle sensor real load and the like; the real load is used for simulating hardware equipment crosslinked with the civil aircraft flight control system through an actual product, providing real electric load characteristics for a tested piece and representing input and interaction states of a real sensor or discrete quantity in the civil aircraft flight control system;
the artificial loads comprise an A429 bus load, an actuator data bus load and an intra-system bus load; the simulation load is used for simulating the interface characteristic and the electrical characteristic of the tested piece and the digital cross-linking equipment and communicating with the tested piece and the data simulation recording equipment;
the simulation load simulates the characteristics of a digital input/output interface of a real product to a tested piece, and the integrity of the flight control system in an identification test is ensured; the artificial load has the following functions:
providing the same input and output interface characteristics as the genuine part to the flight control system;
the lightning-resistant and electromagnetic interference-resistant protection circuit is the same as the real part;
the simulation load powered by the secondary power supply of the flight control system has the same power consumption and power supply monitoring function as the real load;
the monitoring circuit can realize the functions of fault latching and clearing while realizing the monitoring function;
the data simulation recording device is provided with a data interface for communicating with the data simulation recording device, and the communication mode of the simulation load and the data simulation recording device is bus communication;
the data simulation recording equipment is used for inputting digital excitation to the simulation load so that the digital excitation is transmitted to the tested piece through the simulation load and acquiring and recording a test result of the response of the tested piece in real time; the data simulation recording equipment comprises a data conversion box, an A429 computer, an actuator data computer, an in-system computer and a data exchange computer; the A429 computer is used for realizing A429 bus communication with a civil aircraft flight control system and comprises atmosphere, attitude and inertial navigation electric information; the actuator data computer is used for realizing the transmission of an actuating instruction with a civil aircraft flight control system and the safety monitoring of information such as an actuating state, a position and the like; the system internal bus computer is used for monitoring the state of the civil aircraft flight control system in real time and has the functions of fault synthesis and fault monitoring and reporting;
the A429 computer, the actuator data computer and the computer in the system are crosslinked with the corresponding A429 bus load, the actuator data bus load and the bus load in the system through the data conversion box, and the data communication and real-time monitoring functions with the tested piece are realized through the data conversion box;
the data exchange computer is connected with the simulation load through the data conversion box and is used for converting data of the data simulation recording equipment, providing power for the simulation load and carrying out electrical isolation protection on the simulation recording equipment.
A airworthiness identification test method for a civil aircraft flight control system comprises the following steps:
step 1: electrifying the data simulation recording equipment, and loading digital excitation to a simulation load connected with the data simulation recording equipment;
step 2; electrifying the tested piece, establishing bus communication with the simulation load, and loading the digital excitation on the tested piece;
and step 3: adjusting real load input end parameters;
and 4, step 4: operating a seaworthiness identification test system in a preset working scene to enable a flight control system to meet test conditions;
and 5: after the flight control system operates stably, applying environmental conditions for carrying out airworthiness identification tests; the environmental condition includes at least one of the following environmental threats: temperature, vibration, electromagnetic, lightning;
step 6: and acquiring and recording the response test result of the tested piece in real time.
The specific embodiment is as follows:
fig. 2 is a schematic structural diagram of an airworthiness qualification test system of a civil aircraft flight control system according to an embodiment of the present invention. The airworthiness identification test system for the civil aircraft flight control system provided by the embodiment of the invention can comprise: the device comprises a tested piece arranged in a test environment, a real load and a simulation load which are respectively connected with the tested piece, and data simulation recording equipment connected with the simulation load.
In the structure of the airworthiness qualification test system shown in fig. 2, the tested piece in the embodiment of the invention is used for representing a civil aircraft flight control system product; the measured object includes ACE and FCC, for example.
The real load in the embodiment of the invention is used for simulating corresponding hardware equipment crosslinked with the civil aircraft flight control system through an actual product and providing the real electrical load characteristic for the tested piece.
The simulation load in the embodiment of the invention is used for simulating the interface characteristic and the electrical characteristic of the tested piece and the digital cross-linking equipment and communicating with the tested piece and the data simulation recording equipment.
And the data simulation recording equipment is used for inputting digital excitation to the simulation load, so that the digital excitation is transmitted to the tested piece through the simulation load, and the test result of the response of the tested piece is acquired and recorded in real time.
Fig. 3 is a further refinement of fig. 2 for characterizing the input and interaction states of real sensors or discrete quantities in a civil aircraft flight control system. In a particular implementation, the real load may include a discrete magnitude load and a simulated load, as shown in FIG. 3.
The discrete quantity load is a load of a real discrete state signal required by the simulation of the flight control system, and is used for providing the operation state of the airplane or the system for the flight control system.
The simulated load is a load simulating a real simulated signal required by the operation of the flight control system and is used for providing a cockpit control or an airplane real sensor instruction for the flight control.
In the airworthiness qualification test system shown in fig. 3, the communication mode between the simulation load and the data simulation recording device is bus communication; that is, the artificial loads are bus loads, which may include A429 bus loads, actuator data bus loads (e.g., SIB bus loads in FIG. 3), and intra-system bus loads (e.g., ADB bus loads in FIG. 3), among others.
The simulation load simulates the characteristics of a digital input/output interface of a real product to a tested piece, and the integrity of the flight control system in an identification test is ensured. The artificial load has the following functions:
providing the same input and output interface characteristics as the real part to the flight control system;
the lightning-resistant and electromagnetic interference-resistant protection circuit is the same as the real part;
the simulation load powered by the secondary power supply of the flight control system has the same power consumption and power supply monitoring functions as the real load;
the monitoring circuit can realize the functions of fault latching and clearing while realizing the monitoring function;
the data simulation recording device is provided with a data interface for communicating with the data simulation recording device.
In correspondence with the above-described bus load, as shown in fig. 3, the data emulation recording device includes: a data conversion box switching connected with the artificial load respectively, and an A429 computer, an actuator data computer and an in-system computer connected with the data conversion box respectively.
In the embodiment of the invention, the A429 computer, the actuator data computer and the computer in the system, which correspond to the corresponding type of bus load, are connected with the corresponding bus load through the data conversion box, and are used for realizing the functions of data communication and real-time monitoring with the tested piece through the data conversion box.
In practical application, an A429 computer, an actuator data computer and in-system calculation in the data simulation recording equipment are particularly used for monitoring the criterion loading function of the airworthiness identification test system in real time.
Further, the data emulation recording device in the embodiment of the present invention further includes: and the data exchange computer is connected with the data conversion box and is used for converting data of the data simulation recording equipment, providing power for the data simulation load and carrying out electrical isolation protection on the simulation recording equipment.
The airworthiness identification test system of the civil aircraft flight control system provided by each embodiment of the invention is specifically used for identifying the airworthiness of the civil aircraft flight control system, and in the embodiment of the invention, a mode of executing the airworthiness identification test by adopting the airworthiness identification test system comprises the following steps:
1. the data simulation recording equipment is powered on, and digital excitation is loaded through a simulation load connected with the data simulation recording equipment;
2. powering on the tested piece, and establishing bus communication with the simulation load so as to load the digital excitation on the tested piece;
3. adjusting real load input end parameters;
4. the method is operated in an expected working scene, so that the flight control system meets the condition of starting the test;
5. after the flight control system operates stably, applying environmental conditions for airworthiness qualification tests, wherein the environmental conditions include the following environmental threats including but not limited to: temperature, vibration, electromagnetic, lightning, etc.
6. And acquiring and recording the response test result of the tested piece in real time.
The airworthiness identification test result of the airworthiness identification test system of the civil aircraft flight control system provided by the embodiment of the invention is compared with the test result of the traditional airworthiness identification test, and is shown in the following table 1:
TABLE 1 comparison of the present invention identification test with conventional methods
From the above comparison it can be seen that:
compared with the traditional airborne equipment identification test system which only has a component-level function, the simulation monitoring equipment has no carrying capacity, only has the real-time monitoring capacity of the component state, does not have the large data recording and storing capacity and the like, so that the traditional identification test system cannot meet the defect of assessment on system-level HIRF protection and indirect lightning effect subjects in DO-160G; the airworthiness identification test system of the civil aircraft flight control system provided by the embodiment of the invention has the following beneficial effects:
(1) the system has the capability of representing system level functions, including a control law function, a redundancy management function, a system maintenance function and the like in a specified flight scene;
(2) the method has the characteristics of representing the interface load of the flight control system, specifically, in a system test, a part of cross-linked components of the flight control system adopts loads to replace physical components, including bus simulation loads and equivalent physical real loads, and represents the interface load characteristics of the flight control system;
(3) the system has the capability of realizing real-time monitoring of the system state, particularly, the internal data and the state of the flight control system can be read in real time through data simulation recording equipment, the flight control system is monitored in real time, and whether a fault occurs is answered;
(4) the regulation compliance can specifically conform to the assessment under all subjects of DO-160G.
The details will be described below.
Referring to the seaworthiness qualification testing system shown in fig. 2 and 3, the present embodiment provides a seaworthiness qualification testing system designed mainly for the following problems of the conventional onboard equipment qualification testing system:
(1) the test monitoring simulation equipment does not have the load carrying capacity of the cross-linking equipment of the tested piece, so that the equipment-level identification cannot simulate the real load carrying condition of the system and cannot directly reflect the authenticity of the system in the normal load carrying condition;
(2) for electromagnetic tests, test monitoring simulation cannot represent the assessment of mutual electromagnetic influence between equipment cross-links in the airworthiness identification system.
The airworthiness qualification testing system provided by the specific embodiment comprises a tested piece arranged in a testing environment, a real load and a simulation load which are respectively connected with the tested piece, data simulation recording equipment connected with the simulation load, and cables used for connecting all parts. The following describes each component:
firstly, the measured piece
(1) The tested piece is used as a main examination object (such as a flight control computer FCC/an actuator control electronic ACE) and is placed in an environmental condition (such as an incubator/a vibration table/an electromagnetic wave radiation area);
(2) and all interfaces of the tested piece are cross-linked through loads, so that the integrity of the interfaces of the tested piece in the civil aircraft flight control system is represented.
(3) The tested piece should run the expected flight control system and component functions by identifying the test system environment.
Second, load
The load is defined as a component satisfying the interface relationship and the on-load characteristic of the flight control system in the specific embodiment, and is used for verifying the interface and the on-load operation characteristic of the flight control system under normal operation.
(1) In the airworthiness qualification test system, the load includes a real load and a dummy load.
(2) The simulation load is a load which simulates the interface characteristics of the tested piece and the digital cross-linking equipment and is communicated with the tested piece and the data simulation recording equipment, and the communication mode can be bus communication. Specifically, the aviation qualification test system simulation load mainly comprises an A429 bus load, an actuator data bus load and an intra-system bus load. And the simulation load realizes data interaction with the tested piece through data driving of the data simulation recording equipment.
(3) The real load is characterized in that a real product is used as a load and used for representing the input and interaction states of a real sensor or discrete quantity of the civil aircraft flight control system, and the real load is given by replacing a simulation load. The real load of the navigation identification test system mainly comprises a discrete quantity load and a simulated load.
(4) The discrete quantity load is a load for simulating a real discrete state signal required by the flight control system to operate and is used for providing an aircraft or system operation state for flight control; such as landing gear loads, primary flight mode switch loads, etc.
(5) The simulated load is a load simulating a real simulation signal required by the operation of the flight control system and is used for providing a cockpit control or an airplane real sensor instruction for flight control, such as a pitching simulated load, a rolling simulated load, a pedal simulated load, an attack angle sensor real load and the like.
Third, the cable
The cable is connected in series with all the parts and equipment of the system, and the transmission of electric energy and signals is realized. The cable in the airworthiness certification testing system provided by this embodiment mainly includes a test cable/data simulation recording system cable.
The test cable is a cable which is directly crosslinked with a tested piece and has partial or all assessment requirements. The test cable is designed according to the design requirements of the on-board cable, the state of the test cable is kept consistent with that of the on-board cable as far as possible, and the length design can be cut according to the requirements of test standards.
The cable of the data simulation recording device is a communication cable which is crosslinked between the simulation load and the data simulation recording device, and the test and check requirements can not be made.
Fourth, data simulation recording equipment
The data simulation recording equipment realizes the functions of interface simulation of airworthiness identification system data, data transmission acquisition, real-time monitoring and system criterion loading. The data simulation recording equipment is switched through the data conversion box and is crosslinked with the corresponding bus load, so that the data communication and real-time monitoring functions of the tested piece are realized.
Based on the hardware connection relationship and the functions of the above components in this specific embodiment, the operational mode of the airworthiness identification test system of the civil aircraft flight control system provided by this specific embodiment is as follows:
after the airworthiness identification test system is connected and the basis is checked, firstly, a test operator firstly powers on the data simulation recording equipment, and sets input digital excitation through the data simulation recording equipment so that the digital excitation is transmitted to a tested piece through a simulation load; secondly, electrifying the tested piece, and establishing bus communication with the simulation load so as to load the digital excitation on the tested piece; and thirdly, after the tested piece and the test environment are stable, adjusting real load input end parameters (because the flight control system has a fault and needs global reset), and after the flight control system is globally reset, enabling the flight control system to operate in an expected working scene. And after the flight control system operates stably, applying an identification environment condition, checking the flight control system, monitoring in real time, and recording a data result. It is noted that environmental conditions include, for example, temperature, vibration, electromagnetic, lightning, and other environmental threats. And acquiring and recording the response test result of the tested piece in real time.
Claims (10)
1. A airworthiness identification test system of a civil aircraft flight control system is characterized by comprising a tested piece, a real load, a simulation load and data simulation recording equipment;
the tested piece represents a civil aircraft flight control system;
the real load comprises a discrete quantity load and an analog quantity load; the real load is used for simulating hardware equipment cross-linked with the civil aircraft flight control system through an actual product and providing real electrical load characteristics for a tested piece;
the artificial loads comprise A429 bus loads, actuator data bus loads and intra-system bus loads; the simulation load is used for simulating the interface characteristic and the electrical characteristic of the tested piece and the digital cross-linking equipment and communicating with the tested piece and the data simulation recording equipment;
the data simulation recording equipment is used for inputting digital excitation to the simulation load so that the digital excitation is transmitted to the tested piece through the simulation load and acquiring and recording a test result of the response of the tested piece in real time; the data simulation recording equipment comprises a data conversion box, an A429 computer, an actuator data computer, an in-system computer and a data exchange computer; the A429 computer is used for realizing A429 bus communication with a civil aircraft flight control system and comprises atmosphere, attitude and inertial navigation electric information; the actuator data computer is used for realizing the transmission of an actuating instruction with a civil aircraft flight control system and the safety monitoring of information such as an actuating state, a position and the like; the system internal bus computer is used for monitoring the state of the civil aircraft flight control system in real time and has the functions of fault synthesis, monitoring and fault reporting;
the A429 computer, the actuator data computer and the computer in the system are crosslinked with the corresponding A429 bus load, the actuator data bus load and the bus load in the system through the data conversion box, and the data communication and real-time monitoring functions with the tested piece are realized through the data conversion box;
the data exchange computer is connected with the simulation load through the data conversion box and is used for converting data of the data simulation recording equipment, providing power for the simulation load and carrying out electrical isolation protection on the simulation recording equipment.
2. The airworthiness qualification test system of civil aircraft flight control systems of claim 1, wherein the piece under test comprises an actuator control electronics ACE and a flight control computer FCC.
3. The airworthiness qualification testing system of the civil aircraft flight control system according to claim 1, characterized in that the real load is used for representing input and interaction states of real sensors or discrete quantities in the civil aircraft flight control system.
4. The airworthiness qualification test system of the civil aircraft flight control system according to claim 1, wherein the discrete quantity load is a load of a real discrete state signal required for simulating the operation of the flight control system, and is used for providing the operation state of the aircraft or the system to the flight control system.
5. The airworthiness qualification test system of the civil aircraft flight control system of claim 1, wherein the discrete quantity load is a landing gear load or a primary flight mode switch load.
6. The airworthiness qualification test system of the civil aircraft flight control system of claim 1, wherein the analog load is a load simulating a real analog signal required for the operation of the flight control system, and is used for providing a cockpit control or an airplane real sensor instruction to the flight control.
7. The airworthiness qualification test system of the civil aircraft flight control system according to claim 1, wherein the analog load is a pitch analog load, a roll analog load, a foot pedal analog load, and an attack angle sensor real load.
8. The airworthiness qualification test system of the civil aircraft flight control system according to claim 1, wherein the communication mode of the simulation load and the data simulation recording device is bus communication.
9. The airworthiness identification test system of the civil aircraft flight control system according to claim 1, wherein the simulation load simulates the digital input/output interface characteristics of a real product to a tested piece, and the integrity of the flight control system in an identification test is ensured; the artificial load has the following functions:
providing the same input and output interface characteristics as the real part to the flight control system;
the lightning-resistant and electromagnetic interference-resistant protection circuit is the same as the real part;
the simulation load powered by the secondary power supply of the flight control system has the same power consumption and power supply monitoring function as the real load;
the monitoring circuit can realize the functions of fault latching and clearing while realizing the monitoring function;
the data simulation recording device is provided with a data interface for communicating with the data simulation recording device.
10. A test method using the airworthiness certification test system of claim 1, comprising the steps of:
step 1: electrifying the data simulation recording equipment, and loading digital excitation to a simulation load connected with the data simulation recording equipment;
step 2; electrifying the tested piece, establishing bus communication with the simulation load, and loading the digital excitation on the tested piece;
and step 3: adjusting real load input end parameters;
and 4, step 4: operating a seaworthiness identification test system in a preset working scene to enable a flight control system to meet test conditions;
and 5: after the flight control system operates stably, applying environmental conditions for carrying out airworthiness identification tests; the environmental condition includes at least one of the following environmental threats: temperature, vibration, electromagnetic, lightning;
step 6: and acquiring and recording the response test result of the tested piece in real time.
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