CN112193436B - Integrated verification test environment system for civil passenger plane cabin system - Google Patents
Integrated verification test environment system for civil passenger plane cabin system Download PDFInfo
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- CN112193436B CN112193436B CN202011149434.XA CN202011149434A CN112193436B CN 112193436 B CN112193436 B CN 112193436B CN 202011149434 A CN202011149434 A CN 202011149434A CN 112193436 B CN112193436 B CN 112193436B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
The invention discloses an integrated verification test environment system of a passenger cabin system of a civil passenger plane, which consists of a management control subsystem test board, an interface management subsystem test board and a PA subsystem test board; the management control subsystem test board, the interface management subsystem test board and the PA subsystem test board are in communication connection through a wiring management system; the device to be tested or the system to be tested is managed through the custom wiring management system, and the number of the tested pieces, the switching and the combination of the tested pieces and the simulator can be flexibly configured; meanwhile, the integrated verification work of the passenger cabin systems with different architectures is completed through the switching and the adaptation of signals in the wiring management system. The method can provide support for the development of the passenger cabin system of the civil passenger plane and the verification of the system requirements.
Description
Technical Field
The invention belongs to the technical field of civil passenger plane test, and particularly relates to an integrated verification test environment system for a passenger cabin system of a civil passenger plane.
Background
The design of the cabin system integration verification test environment is designed for meeting the integration test verification of a certain type of civil aircraft cabin system, can support the fault isolation and recurrence of an onboard ground verification test and a flight verification test of the aircraft cabin system, can be used for the integration verification and test between the cabin system and other aviation systems, and is used for confirming whether the system level requirement is met. And supports integrated validation of a variety of cabin system configurations based thereon.
However, the existing integrated verification test environment cannot meet the requirement of the integrated test of the passenger cabin system of the civil passenger aircraft, and therefore, a passenger cabin system integrated verification test environment technology which can meet the requirement of the integrated test of the passenger cabin system of the civil passenger aircraft is urgently needed to be researched.
Disclosure of Invention
The invention provides an integrated verification test environment system of a civil passenger plane cabin system with a novel architecture. The method can provide support for the development of the passenger cabin system of the civil passenger plane and the verification of the system requirements.
The invention is realized by the following technical scheme:
the civil passenger plane cabin system integration verification test environment system is composed of a management control subsystem test board, an interface management subsystem test board and a PA subsystem test board;
the management control subsystem test board, the interface management subsystem test board and the PA subsystem test board are in communication connection through a wiring management system; the device to be tested or the system to be tested is managed through the custom wiring management system, and the number of the tested pieces, the switching and the combination of the tested pieces and the simulator can be flexibly configured; meanwhile, the integrated verification work of the passenger cabin systems with different architectures is completed through the switching and the adaptation of signals in the wiring management system.
The integrated verification test environment system adopts a framework based on a wiring management system, manages the tested equipment or the tested system through the flexible self-defined wiring management system, and can flexibly match the number of the tested pieces and the switching and combination of the tested pieces and the simulator; the integrated verification test environment system can also expand and support the integrated verification work of the passenger cabin systems of other different types, and the integrated verification work of the passenger cabin systems of different architectures can be completed through switching and adapting of signals in the wiring system.
Preferably, the management control subsystem test board comprises a first Ethernet switch, a main control computer, a data acquisition and analysis computer, a first Ethernet shunt guider, a first electronic distribution system and a first interface simulator;
the first Ethernet switch is in communication connection with the wiring management system and used for transmitting test control signals, and the Ethernet switch realizes power distribution control on the first power distribution subsystem and simulator control on the first interface simulator based on the received test control signals;
the main control computer is in communication connection with the wiring management system and is used for testing the transmission of control signals;
the data acquisition and analysis computer is used for acquiring data of the wiring management system;
the distribution management system is used for collecting data of the first Ethernet shunt guider;
and the first Ethernet shunt guider is also respectively in data interaction with the first interface simulator and the interface management subsystem.
The management control subsystem of the invention mainly realizes the integral control of the integrated verification test environment of the whole cabin system and also undertakes the functions of part of the integrated verification test environment system.
Preferably, the first ethernet offload director of the present invention also interacts with on-board LRU devices.
Preferably, the first interface simulator of the present invention is further communicatively connected to the wiring management system.
Preferably, the first interface simulator of the present invention includes a maintenance interface simulator, an avionics interface simulator, a light interface simulator, an information system simulator, a battery interface simulator, an on-board entertainment simulator, and an external communication interface simulator.
Preferably, the interface management subsystem test board of the invention comprises a second ethernet switch, a second ethernet shunting guider, a first data collector, a second electronic distribution system and a second interface simulator;
the second Ethernet switch is in communication connection with the wiring management system and used for testing transmission of control signals; the second Ethernet switch realizes power distribution control over a second power distribution subsystem and simulator control over a second interface simulator based on the received test control signal;
the second Ethernet shunt guider is respectively in data interaction with the second interface simulator, the management control subsystem test board and the PA subsystem test board;
the first data acquisition device is used for acquiring data of the second Ethernet shunt guider;
the wiring management system is used for collecting the data of the first data collector.
Preferably, the second ethernet offload director of the present invention further performs data interaction with the first on-board device.
Preferably, the PA subsystem test board of the present invention includes a third ethernet switch, a third ethernet shunt director, a third power distribution subsystem, a third interface simulator, and a second data collector;
the third Ethernet switch is in communication connection with the wiring management system and used for testing transmission of control signals; the third Ethernet switch realizes power distribution control over the third power distribution subsystem and simulator control over the third interface simulator based on the received test control signal;
the third Ethernet shunt guider is respectively in data interaction with the third interface simulator and the interface management subsystem test board;
the second data collector is used for collecting data of the third Ethernet shunt guider and the second airborne equipment;
and the wiring management system is used for acquiring the data of the second data acquisition unit.
Preferably, the third ethernet offload director of the present invention further performs data interaction with the second onboard device.
Preferably, the cable access connector of the wire harness management system of the present invention is: the network signal interface adopts an RJ45 interface connector; the discrete signal, the power signal and the audio signal adopt an aviation level and crimping form and are provided with connectors with quick locking functions.
The invention has the following advantages and beneficial effects:
1. the invention provides a novel framework of a cabin system integration verification test environment adopting a wiring management system, which can provide effective support for development of a cabin system of a civil passenger plane and verification of system requirements and support for management of test cases and compilation of test programs.
2. The integrated verification test environment system can also expand and support integrated verification work of the passenger cabin systems of other different types, and can provide support for interface tests of the passenger cabin systems and external avionic systems.
3. The integrated verification test environment system can provide support for the civil passenger plane laboratory integrated test, the onboard ground test and the test flight test, and can finish the reproduction and positioning of faults; meanwhile, the invention also supports the expansion design and architecture upgrade of the cabin system.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
FIG. 1 is a schematic diagram of the system architecture of the present invention.
FIG. 2 is a schematic diagram of a test bench of the management control subsystem according to the present invention.
FIG. 3 is a schematic diagram of an interface management subsystem test bench according to the present invention.
FIG. 4 is a schematic diagram of a PA subsystem test bench according to the present invention.
Detailed Description
Hereinafter, the term "comprising" or "may include" used in various embodiments of the present invention indicates the presence of the invented function, operation or element, and does not limit the addition of one or more functions, operations or elements. Furthermore, as used in various embodiments of the present invention, the terms "comprises," "comprising," "includes," "including," "has," "having" and their derivatives are intended to mean that the specified features, numbers, steps, operations, elements, components, or combinations of the foregoing, are only meant to indicate that a particular feature, number, step, operation, element, component, or combination of the foregoing, and should not be construed as first excluding the existence of, or adding to the possibility of, one or more other features, numbers, steps, operations, elements, components, or combinations of the foregoing.
In various embodiments of the invention, the expression "or" at least one of a or/and B "includes any or all combinations of the words listed simultaneously. For example, the expression "a or B" or "at least one of a or/and B" may include a, may include B, or may include both a and B.
Expressions (such as "first", "second", and the like) used in various embodiments of the present invention may modify various constituent elements in various embodiments, but may not limit the respective constituent elements. For example, the above description does not limit the order and/or importance of the elements described. The foregoing description is for the purpose of distinguishing one element from another. For example, the first user device and the second user device indicate different user devices, although both are user devices. For example, a first element could be termed a second element, and, similarly, a second element could be termed a first element, without departing from the scope of various embodiments of the present invention.
It should be noted that: if it is described that one constituent element is "connected" to another constituent element, the first constituent element may be directly connected to the second constituent element, and a third constituent element may be "connected" between the first constituent element and the second constituent element. In contrast, when one constituent element is "directly connected" to another constituent element, it is understood that there is no third constituent element between the first constituent element and the second constituent element.
The terminology used in the various embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the various embodiments of the invention. As used herein, the singular forms are intended to include the plural forms as well, unless the context clearly indicates otherwise. Unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which various embodiments of the present invention belong. The terms (such as those defined in commonly used dictionaries) should be interpreted as having a meaning that is consistent with their contextual meaning in the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein in various embodiments of the present invention.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Examples
The embodiment provides an integrated verification test environment system for a passenger cabin system of a civil passenger plane. The civil passenger plane cabin system integration verification test environment system of the embodiment adopts a brand-new architecture based on a wiring management system.
Specifically, as shown in fig. 1, the integrated verification test environment system of this embodiment is composed of a management control subsystem test board, an interface management subsystem test board, and a PA subsystem test board. The integrated verification test environment system of the embodiment mainly comprises a complete set of cabin system test pieces, an external related cross-linking system simulator, a connecting cable, test software, a test bench, related installation accessories and the like.
The management control subsystem test bench, the interface management subsystem test bench and the PA subsystem test bench of the embodiment are in communication connection through a wiring management system; the device to be tested or the system to be tested is managed through the custom wiring management system, and the number of the tested pieces, the switching and the combination of the tested pieces and the simulator can be flexibly configured; meanwhile, the integrated verification work of the passenger cabin systems with different architectures is completed through the switching and the adaptation of signals in the wiring management system.
The integrated verification test environment system of the embodiment adopts a framework based on a wiring management system, and manages the tested equipment or the tested system by a flexible self-defined wiring management method (the self-defined wiring management method refers to the fact that the system is subjected to wiring management according to actual needs and wiring requirements of different system frameworks, so that the current system can flexibly connect equipment with different quantities or frameworks), and the quantity of the tested pieces and the switching and combination of the tested pieces and the simulator can be flexibly matched; the integrated verification test environment system can also expand and support the integrated verification work of the passenger cabin systems of other different types, and the integrated verification work of the passenger cabin systems of different architectures can be completed through switching and adapting of signals in the wiring system.
As shown in fig. 2, the management control subsystem test bench of this embodiment includes a first ethernet switch, a main control computer, a data acquisition and analysis computer, a first ethernet shunting director, a first electronic distribution system, and a first interface simulator.
The first ethernet switch of this embodiment is in communication connection with the wiring management system, and is used for transmission of a test control signal, and the ethernet switch realizes power distribution control over the first power distribution subsystem and simulator control over the first interface simulator based on the received test control signal.
The first power distribution subsystem of the embodiment comprises a DC 28V power distribution device, an AC 220V power distribution device and a DC 28V power supply; and the power supply in the first power distribution subsystem of the present embodiment supplies power to the first interface simulator and the on-board LRU device, respectively.
The first interface simulator of the present embodiment includes a maintenance interface simulator, an avionics interface simulator, a lighting interface simulator, an information system simulator, a battery interface simulator, an on-board entertainment simulator, and an external communication interface simulator.
The main control computer of the embodiment is in communication connection with the wiring management system and is used for testing transmission of control signals.
The data acquisition and analysis computer of the present embodiment is used for acquiring data of the wiring management system. The data acquisition and analysis computer of this embodiment transmits other signals (not shown in the figure) through the wiring management system.
The wiring management system of the embodiment is used for collecting data of the first ethernet shunt director.
The first ethernet shunting director of this embodiment also performs data interaction with the first interface simulator and the interface management subsystem, respectively. The first ethernet offload director of this embodiment also performs data interaction with the device under test (on-board LRU device) that is independent from the integrated verification environment system.
The first interface simulator of the present embodiment is also in communication with the wiring management system.
In this embodiment, signals transmitted by the first ethernet switch, the main control computer, the first ethernet shunt director and the distribution management system are ethernet signals; signals transmitted between the first Ethernet switch and the first electronic distribution system and the first interface simulator are Ethernet signals; signals transmitted by the first Ethernet shunt guider, the first interface simulator and the airborne LRU equipment are Ethernet signals; the first interface simulator and the wiring management system are transmitted into other signals; the signals transmitted by the data acquisition and analysis computer and the wiring management system comprise Ethernet signals and other signals.
The management control subsystem of the embodiment mainly realizes the overall control of the integrated verification test environment of the whole cabin system, and simultaneously also undertakes the functions of part of the integrated verification test environment system.
As shown in fig. 3, the interface management subsystem test board of this embodiment includes a second ethernet switch, a second ethernet shunting director, a first data collector, a second power distribution system, and a second interface simulator.
The second ethernet switch of the present embodiment is in communication connection with the wiring management system, and is used for testing transmission of the control signal; the second ethernet switch implements power distribution control for the second power distribution subsystem and simulator control for the second interface simulator based on the received test control signal.
The second power distribution subsystem of the embodiment comprises a DC 28V power distribution device, an AC 220V power distribution device and a DC 28V power supply; and the power supply in the first power distribution subsystem of this embodiment supplies power for the second interface simulator and the first onboard device, respectively.
The second interface simulator of the present embodiment includes an LRU3 interface simulator (simulating an interface between a plurality of LRUs 3 and LRU 2).
The second ethernet shunting guider of this embodiment performs data interaction with the second interface simulator, the management control subsystem test bench (first ethernet shunting guider), and the PA subsystem test bench (third ethernet shunting guider), respectively; the second ethernet offload director of this embodiment also performs data interaction with the first onboard device, which includes the LRU1 device and the LRU2 device (N), and which is independent as a device under test from the integrated verification environment.
The first onboard device of this embodiment also provides an LRU2 audio input interface and an LRU2 power input interface (not shown).
The first data collector of this embodiment is configured to collect data of the second ethernet offload director.
The wiring management system of the embodiment is used for collecting data of the first data collector.
In this embodiment, signals transmitted by the second ethernet shunt director, the second interface simulator, the management control subsystem test board (the first ethernet shunt director), the PA subsystem test board (the third ethernet shunt director), the first onboard device, and the data acquisition device are ethernet signals; the signals transmitted between the data acquisition unit and the wiring management system are Ethernet signals; signals transmitted between the second Ethernet switch and the wiring management system, the second power distribution system and the second interface simulator are all Ethernet signals; the second interface simulator transmits other signals through the wiring management system; in addition, other signals (not shown in the figure) are also transmitted between the second interface simulator and the first onboard device in the embodiment.
As shown in fig. 4, the PA subsystem test bench of this embodiment includes a third ethernet switch, a third ethernet shunt director, a third power distribution subsystem, a third interface simulator, and a second data collector.
The third ethernet switch of the present embodiment is in communication connection with the distribution management system, and is used for testing transmission of the control signal; the third ethernet switch implements power distribution control for the third power distribution subsystem and simulator control for the third interface simulator based on the received test control signal.
The third power distribution subsystem of the present embodiment includes a DC 28V power distribution device, an AC 220V power distribution device, and a DC 28V power supply; and the power supply in the third power distribution subsystem of this embodiment supplies power to the third interface simulator and the second onboard device, respectively.
The third interface simulator of the present embodiment includes an interface simulator between communication navigation and LRU4, and an interface simulator between avionics and LRU 4.
The third ethernet shunting guider of this embodiment performs data interaction with the third interface simulator and the interface management subsystem test bench (second ethernet shunting guider) respectively; the third ethernet offload director of this embodiment also performs data interaction with the second onboard device. The second on-board device of the present embodiment includes an LRU4 device, an LRU5 device (N), an LRU6 device (N), an LRU7 device (N), and the like, and is independent as a device under test from the integrated verification environment.
The second on-board device of the present embodiment also provides the LRU5 external power supply interface for the LRU2 power input interface; the second on-board device of the present embodiment also provides the LRU5 external audio interface for the LRU2 audio input interface.
The second data collector of this embodiment is configured to collect data of the third ethernet offload director. The second data collector of this embodiment is further configured to collect a signal of the second airborne device.
The wiring management system of the embodiment is used for collecting data of the second data collector.
Signals transmitted between the third ethernet shunt director and the interface management subsystem test board (second ethernet shunt director), the third interface simulator, the second airborne equipment and the data acquisition device in this embodiment are ethernet signals; signals transmitted between the third ethernet switch and the wiring management system, the third power distribution system and the third interface simulator in this embodiment are ethernet signals; other signals are also transmitted between the third interface simulator and the wiring management system; the signal transmitted between the second data collector and the wiring management system is an Ethernet signal; other signals are transmitted between the second data collector and the second airborne equipment; other signals are also transmitted between the third interface simulator and the second onboard equipment.
The cable access connector of the wiring management system of the present embodiment is: the network signal interface adopts an RJ45 interface connector; the discrete signal, the power signal and the audio signal adopt an aviation level and crimping form and are provided with connectors with quick locking functions.
The cabin system integration verification test environment system of the embodiment can realize the following functions:
a) a system time service function;
the integrated verification test environment adopts an NTP mode to perform clock synchronization, the NTP clock synchronization is realized through the Ethernet, NTP service is installed on the main control computer to serve as a time service clock source, and the test board computers of other subsystems are synchronized with the main control computer through NTP client software.
b) An interface simulator function;
the interface simulator performs unified management, including initialization parameters, selection and configuration of test cases, ICD configuration, fault injection and the like.
c) Signal distribution and control functions;
the discrete quantity, the Ethernet bus and the Arinc429 bus signals can be distributed, switched, bypass collected and the like in an automatic or manual mode, and the integration verification work of the cabin systems in different stages and different architectures can be completed through the switching and the adaptation of the signals.
And the redundancy of 30% of various signal designs is used for expansion, including PCI interfaces, avionics bus interfaces and the like.
d) A power management function;
the power supply of each device provides independent power supply control and overcurrent and overvoltage protection, and unified control is performed through the main control computer.
e) Data acquisition and recording functions;
the discrete magnitude and the Arinc429 bus data are acquired through a bypass, the Ethernet bus realizes Ethernet signal bypass acquisition by using an Ethernet shunt guider, the integrated verification test environment automatically analyzes and displays the acquired data, and the original value of the data and the engineering value analyzed based on the ICD are displayed. And the collected data can be filtered according to the set screening conditions.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (9)
1. The civil passenger plane cabin system integration verification test environment system is characterized in that the test environment system consists of a management control subsystem test board, an interface management subsystem test board and a PA subsystem test board;
the management control subsystem test board, the interface management subsystem test board and the PA subsystem test board are in communication connection through a wiring management system; the device to be tested or the system to be tested is managed through the custom wiring management system, and the number of the tested pieces, the switching and the combination of the tested pieces and the simulator can be flexibly configured; meanwhile, the integrated verification work of the passenger cabin systems with different frameworks is completed through the switching and the adaptation of signals in the wiring management system; the management control subsystem test board comprises a first Ethernet switch, a main control computer, a data acquisition and analysis computer, a first Ethernet shunt guider, a first electronic distribution system and a first interface simulator;
the first Ethernet switch is in communication connection with the wiring management system and used for transmitting test control signals, and the Ethernet switch realizes power distribution control on the first power distribution subsystem and simulator control on the first interface simulator based on the received test control signals;
the main control computer is in communication connection with the wiring management system and is used for testing the transmission of control signals;
the data acquisition and analysis computer is used for acquiring data of the wiring management system;
the distribution management system is used for collecting data of the first Ethernet shunt guider;
and the first Ethernet shunt guider is also respectively in data interaction with the first interface simulator and the interface management subsystem test bench.
2. The civil passenger aircraft cabin system integration verification test environment system of claim 1, wherein the first ethernet offload director further interfaces data with an onboard LRU device.
3. The civil passenger aircraft cabin system integration verification test environment system of claim 1, wherein the first interface simulator is further communicatively coupled to the wiring management system.
4. The system of claim 1, wherein the first interface simulator comprises a maintenance interface simulator, an avionics interface simulator, a lighting interface simulator, an information system simulator, a battery interface simulator, an in-flight entertainment simulator, and an external communication interface simulator.
5. The system of claim 1, wherein the interface management subsystem test bench comprises a second ethernet switch, a second ethernet offload director, a first data collector, a second power distribution system, and a second interface simulator;
the second Ethernet switch is in communication connection with the wiring management system and used for testing transmission of control signals; the second Ethernet switch realizes power distribution control over a second power distribution subsystem and simulator control over a second interface simulator based on the received test control signal;
the second Ethernet shunt guider is respectively in data interaction with the second interface simulator, the management control subsystem test board and the PA subsystem test board;
the first data acquisition device is used for acquiring data of the second Ethernet shunt guider;
the wiring management system is used for collecting the data of the first data collector.
6. The civil passenger aircraft cabin system integration verification test environment system of claim 5, wherein the second Ethernet offload director is further in data communication with the first onboard device.
7. The civil passenger aircraft cabin system integration verification test environment system of claim 1, wherein the PA subsystem test bench comprises a third ethernet switch, a third ethernet shunt director, a third power distribution subsystem, a third interface simulator, and a second data collector;
the third Ethernet switch is in communication connection with the wiring management system and used for testing transmission of control signals; the third Ethernet switch realizes power distribution control over the third power distribution subsystem and simulator control over the third interface simulator based on the received test control signal;
the third Ethernet shunt guider is respectively in data interaction with the third interface simulator and the interface management subsystem test board;
the second data collector is used for collecting data of the third Ethernet shunt guider and the second airborne equipment;
and the wiring management system is used for acquiring the data of the second data acquisition unit.
8. The civil passenger aircraft cabin system integration verification test environment system of claim 7, wherein the third ethernet offload director is further in data communication with the second airborne device.
9. The civil passenger aircraft cabin system integration verification test environment system according to any of claims 1 to 8, wherein the cable access connectors of the wiring management system are: the network signal interface adopts an RJ45 interface connector; the discrete signal, the power signal and the audio signal adopt an aviation level and crimping form and are provided with connectors with quick locking functions.
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| US6421634B1 (en) * | 1999-03-04 | 2002-07-16 | Sun Microsystems, Inc. | Interface independent test system |
| KR20140002331A (en) * | 2012-06-29 | 2014-01-08 | 한국항공우주산업 주식회사 | Integration test apparatus for integration testing of avionics system |
| WO2015166223A1 (en) * | 2014-04-28 | 2015-11-05 | University Of Central Lancashire | Computer based system and method of functionally testing aircraft subsystems |
| CN105892305A (en) * | 2014-12-15 | 2016-08-24 | 北京空间技术研制试验中心 | General spacecraft ground test bed system |
| CN206384166U (en) * | 2016-12-30 | 2017-08-08 | 北京新兴东方航空装备股份有限公司 | Aircraft general-utility test platform |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US6421634B1 (en) * | 1999-03-04 | 2002-07-16 | Sun Microsystems, Inc. | Interface independent test system |
| KR20140002331A (en) * | 2012-06-29 | 2014-01-08 | 한국항공우주산업 주식회사 | Integration test apparatus for integration testing of avionics system |
| WO2015166223A1 (en) * | 2014-04-28 | 2015-11-05 | University Of Central Lancashire | Computer based system and method of functionally testing aircraft subsystems |
| CN105892305A (en) * | 2014-12-15 | 2016-08-24 | 北京空间技术研制试验中心 | General spacecraft ground test bed system |
| CN206384166U (en) * | 2016-12-30 | 2017-08-08 | 北京新兴东方航空装备股份有限公司 | Aircraft general-utility test platform |
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