CN210912934U - Detection device for fly-by-wire control system of airplane - Google Patents
Detection device for fly-by-wire control system of airplane Download PDFInfo
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- CN210912934U CN210912934U CN201921766291.XU CN201921766291U CN210912934U CN 210912934 U CN210912934 U CN 210912934U CN 201921766291 U CN201921766291 U CN 201921766291U CN 210912934 U CN210912934 U CN 210912934U
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Abstract
The utility model relates to a detection apparatus for aircraft telex control system, including PXI bus data acquisition subsystem, for the uninterrupted power supply's of PXI bus data acquisition subsystem power subsystem, set up the switch subsystem on PXI bus data acquisition subsystem, through the test adapter that test cable and telex control system are connected, PXI bus data acquisition subsystem, power subsystem outside are equipped with and are used for protecting its shock attenuation machine case that does not receive the vibration influence. The utility model intensively puts on the shelf the instrument resource through the shock absorber case, thus improving the space utilization rate of the whole device and avoiding the problem of poor circuit contact caused by the influence of vibration; intensive standard extraction is carried out on instrument resource signals through a 9025 standard signal array interface, and the universality and the expansibility of the whole device are improved by matching with signal reference and conditioning of a test adapter; and the reusability of instrument resources is improved by switching the circuit of the switch subsystem.
Description
Technical Field
The utility model relates to an aviation machine carries electronic equipment test field, especially an aircraft telex control system's detection device.
Background
The fly-by-wire system of airplane is a nerve centre of more than three generations of airplane, and is used for converting the control instruction of pilot and the signals of airplane attitude, movement speed, angular speed, dynamic pressure and static pressure obtained by various sensors into electric signals and transmitting them to the fly-by-wire computer, and the fly-by-wire computer can calculate according to the current flying state and then produce control signal to drive control surface of airplane so as to change or retain flying state of airplane. The integrity of fly-by-wire systems directly affects the combat performance and flight safety of aircraft. Therefore, in the detection after the system is manufactured or repaired, performance items such as the control rate and redundancy management of the system need to be detected in detail, and the reliability, stability and accuracy of the test of the detection equipment are very important.
Search Wanfang data knowledge service platform, telex system inspection tester design based on PC/104 bus published in university of air force university of academic newspaper (Nature science edition) 2003 2, discloses a telex system inspection tester. The tester mainly comprises a CPU template, an A/D, D/A template and a DIO template based on a PC/104 bus, various simulators, an adapter (signal conditioning module), a display, a power supply and other parts, and has the characteristics of small volume, strong function, good universality and the like. The defects are that the connection stability of the hardware resource module interface based on the PC/104 bus is poor, the use in an external field is influenced by vibration, and the fault of poor line contact is easy to occur.
The design of a certain type of airplane telex control system detector based on PXI published in measurement and control technology, 30 nd volume of supplement in 2011 discloses an airplane telex control system test platform. The testing platform mainly comprises a PXI bus-based controller module, a universal meter module, a digital I/O module, a 4-channel high-speed acquisition module, 5 switch modules, an interface adapter (TUA), auxiliary testing equipment and the like, and has the characteristics of friendly human-computer interface, high testing flow automation degree, good testing flow expansibility and the like. The disadvantage is that the interface adapter adopts an aviation plug, which is not suitable for the actual working condition of repeated disassembly and assembly and test in the test field, and is easy to have a fault of bad line contact, and in addition, the expansibility of the test platform is further influenced; the second disadvantage is that the body structure of the test platform is not described in detail.
Disclosure of Invention
In order to solve the technical problem, the utility model provides an aircraft telex control system's detection device.
The utility model discloses the technical problem that will solve adopts following technical scheme to realize:
a detection device of an airplane telex control system comprises a PXI bus data acquisition subsystem, a power subsystem for uninterruptedly supplying power to the PXI bus data acquisition subsystem, a switch subsystem arranged on the PXI bus data acquisition subsystem, and a test adapter connected with the telex control system through a test cable, wherein shock absorption cases for protecting the PXI bus data acquisition subsystem and the power subsystem from being influenced by vibration are arranged outside the PXI bus data acquisition subsystem and the power subsystem.
Furthermore, a 9025 standard signal array interface correspondingly connected with the PXI bus data acquisition subsystem and the test adapter is arranged in the shock absorption case.
Further, the shock absorption chassis comprises a shock absorption frame used for placing the PXI bus data acquisition subsystem, a plastic shell with a collision buffering function and a four-wheel mobile base meeting the timely displacement requirement.
Further, the shock absorbing frame has a size of 19 inches and a height of 21U.
Further, the power subsystem further comprises a fan assembly for dissipating heat inside the shock-absorbing chassis.
The utility model has the advantages that:
the utility model intensively puts on the shelf the instrument resource through the shock absorber case, thus improving the space utilization rate of the whole device and avoiding the problem of poor circuit contact caused by the influence of vibration; intensive standard extraction is carried out on instrument resource signals through a 9025 standard signal array interface, and the universality and the expansibility of the whole device are improved by matching with signal reference and conditioning of a test adapter; and the reusability of instrument resources is improved by switching the circuit of the switch subsystem.
Drawings
The invention will be further described with reference to the following figures and examples:
fig. 1 is a schematic diagram of an explosion structure of a detection device in the present invention;
fig. 2 is a block diagram of the system according to the present invention.
Detailed Description
In order to make the technical means, creation features, achievement purposes and effects of the present invention easy to understand, the present invention will be further explained with reference to the accompanying drawings and embodiments.
As shown in fig. 1 to fig. 2, a detection apparatus for an airplane telex control system includes a PXI bus data acquisition subsystem, a power supply subsystem for uninterruptedly supplying power to the PXI bus data acquisition subsystem, a switch subsystem disposed on the PXI bus data acquisition subsystem, and a test adapter connected to the telex control system through a test cable, where a shock-absorbing chassis for protecting the PXI bus data acquisition subsystem and the power supply subsystem from vibration is disposed outside the PXI bus data acquisition subsystem and the power supply subsystem, and the shock-absorbing chassis is used for realizing intensive shelving of instrument resources and providing a cable laying space.
The shock absorber case comprises a four-wheel mobile base 3, a shock absorbing frame 4 located on the four-wheel mobile base 3, a plastic shell 2 located outside the shock absorbing frame 4, a front cover plate 1 and a rear cover plate 8 located on the front side and the rear side of the plastic shell 2, the PXI bus data acquisition subsystem is located at the upper end of the shock absorbing frame 4, and the power supply subsystem is located at the lower end of the shock absorbing frame 4.
The four-wheel mobile base 3 can meet the requirements of rapid deployment and timely displacement of a detection device in the process of airplane general assembly or outfield maintenance; the shock absorption frame 4 ensures that the whole device is compact and stable, meets the shock absorption requirements of the device during transportation and use in an outfield, and in addition, the specification of the shock absorption frame 4 is 19 inches, the height of the shock absorption frame is 21U, wherein the 21U ensures that the shock absorption case has enough space for placing instrument resources, and is convenient for moving and carrying out tests on the periphery of the airplane body; the plastic shell 2 can provide good collision buffering measures, and prevent the detection device from damaging the airplane body and operators; the front cover plate 1 and the rear cover plate 8 are used for protection in the storage and transportation processes of the detection device.
Intensive putting on shelf is carried out instrument resource through shock attenuation machine case, has promoted the space utilization of whole equipment and has avoided because of receiving the vibration influence to lead to the problem of circuit contact failure.
The rear side of the middle of the shock absorption frame 4 is further provided with a 9025 standard signal array interface 7 correspondingly connected with the PXI bus data acquisition subsystem and the test adapter, the 9025 standard signal array interface 7 is an external signal interface of the whole detection device, and the interface adopts 25 standard signal modules to lead signals of instrument resources to a rear cover plate 8 of the shock absorption case according to signal types, so that the test adapter can conveniently and quickly quote and conveniently condition the signals according to the requirements of different models of telex control systems.
Intensive standard extraction is carried out on instrument resource signals through a 9025 standard signal array interface, and the universality and the expansibility of the whole device are improved by matching with signal reference and conditioning of a test adapter.
The PXI bus data acquisition subsystem comprises a PXI case 5 arranged at the upper end of the shock absorption frame 4, a zero slot controller, a universal meter board card, a data simulation and acquisition board card of PXI specifications such as D/A, A/D, I/O and the like are arranged in the PXI case 5, and the zero slot controller is connected with a screen keyboard mouse 11. The board card type test device can greatly reduce the volume and the scale of the whole set of device.
The power subsystem comprises a fan assembly 6 arranged at the lower end of the shock absorption frame 4 and positioned below the PXI case 5, a power distribution device 9 and a UPS (uninterrupted power supply) 10 which are positioned at the bottom of the shock absorption frame 4, and a PDU (Power Unit) power supply device 12 which is positioned at the front side of the middle part of the shock absorption frame 4; the fan assembly 6 can ensure a good heat dissipation and ventilation state inside the vibration reduction case; the power distribution device 9 and the PDU power supply device 12 are used for providing power utilization control and safety protection of instrument resources; the UPS 10 is used to ensure that the detection device can keep working properly when the external power supply is absent or there is an unexpected power outage in the field.
The switch subsystem comprises a PXI-specification 80-channel SPST-type universal switch board card and 4 × 32 matrix switch board cards which are positioned in a PXI case 5, and in addition, the switch subsystem further comprises 1 state judgment contact switch positioned on a 9025 standard signal array interface 7. And the reusability of instrument resources is improved by switching the circuit of the switch subsystem.
The test adapter comprises a shell, a connector, a socket, a signal disconnection detection point, a signal conditioning board and an internal electric wiring cable, wherein the connector is positioned in the shell and is in butt joint with the 9025 standard signal array interface 7; the flexibility of the debugging process of the telex control system is improved by arranging the signal break detection point.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments, and the above embodiments and what is described in the specification are the principles of the present invention, and that various changes and modifications may be made without departing from the spirit and scope of the present invention, and these changes and modifications are intended to fall within the scope of the present invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (5)
1. A detection device of an airplane telex control system comprises a PXI bus data acquisition subsystem, a power subsystem for uninterruptedly supplying power to the PXI bus data acquisition subsystem, a switch subsystem arranged on the PXI bus data acquisition subsystem, and a test adapter connected with the telex control system through a test cable, and is characterized in that: and a shock absorption case for protecting the PXI bus data acquisition subsystem and the power subsystem from vibration is arranged outside the PXI bus data acquisition subsystem and the power subsystem.
2. A test device for an aircraft fly-by-wire system according to claim 1, wherein: and a 9025 standard signal array interface (7) correspondingly connected with the PXI bus data acquisition subsystem and the test adapter is arranged in the shock absorption case.
3. A test device for an aircraft fly-by-wire system according to claim 1, wherein: the shock absorption machine box comprises a shock absorption frame (4) used for placing a PXI bus data acquisition subsystem, a plastic shell (2) with a collision buffering function and a four-wheel mobile base (3) meeting the timely displacement requirement.
4. A test device for an aircraft fly-by-wire system according to claim 3, wherein: the shock absorption frame (4) is 19 inches in specification and 21U in height.
5. A test device for an aircraft fly-by-wire system according to claim 1, wherein: the power subsystem also includes a fan assembly (6) for dissipating heat from the interior of the shock-absorbing housing.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921766291.XU CN210912934U (en) | 2019-10-21 | 2019-10-21 | Detection device for fly-by-wire control system of airplane |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921766291.XU CN210912934U (en) | 2019-10-21 | 2019-10-21 | Detection device for fly-by-wire control system of airplane |
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| CN210912934U true CN210912934U (en) | 2020-07-03 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114325304A (en) * | 2021-11-24 | 2022-04-12 | 国营芜湖机械厂 | Universal detection device and detection method for airborne radio frequency circuit board |
| CN116873220A (en) * | 2023-08-08 | 2023-10-13 | 南京航空航天大学 | Multi-agent technology-based aircraft telex bench test system and method |
-
2019
- 2019-10-21 CN CN201921766291.XU patent/CN210912934U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114325304A (en) * | 2021-11-24 | 2022-04-12 | 国营芜湖机械厂 | Universal detection device and detection method for airborne radio frequency circuit board |
| CN116873220A (en) * | 2023-08-08 | 2023-10-13 | 南京航空航天大学 | Multi-agent technology-based aircraft telex bench test system and method |
| CN116873220B (en) * | 2023-08-08 | 2024-03-08 | 南京航空航天大学 | Multi-agent technology-based aircraft telex bench test system and method |
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