CN111284727A - Testing device for moment arm regulator of airplane control system - Google Patents
Testing device for moment arm regulator of airplane control system Download PDFInfo
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- CN111284727A CN111284727A CN201811500041.1A CN201811500041A CN111284727A CN 111284727 A CN111284727 A CN 111284727A CN 201811500041 A CN201811500041 A CN 201811500041A CN 111284727 A CN111284727 A CN 111284727A
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- 238000012360 testing method Methods 0.000 title claims abstract description 70
- 230000003068 static effect Effects 0.000 claims abstract description 16
- 238000006073 displacement reaction Methods 0.000 claims abstract description 15
- 238000012544 monitoring process Methods 0.000 abstract description 2
- 230000007246 mechanism Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
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Classifications
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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
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
The invention discloses a test device for a force arm regulator of an aircraft control system, which comprises a device body, an operation display, a switch, a host, a data collector, a product test cabinet, a spring load, a product mounting rack, a displacement sensor, an electrical plug, a dynamic pressure pipeline, a speed sensor, a height sensor, a static pressure pipeline and a vacuum pump. The testing device for the force arm regulator of the aircraft control system is simple in structure, convenient to operate, capable of automatically recording test data and monitoring the working state of the force arm in real time.
Description
Technical Field
The invention relates to the technical field of performance testing of a moment arm regulator of an aircraft control system, in particular to a test device for the moment arm regulator of the aircraft control system.
Background
The aircraft control system is an important core component of the whole aircraft, and whether the operation of the aircraft control system is good or not directly influences the safety of the aircraft, so that the aircraft can ascend or descend in flight. The aircraft arm regulator in the aircraft control system is one of the more critical components, and changes the transmission ratio between the steering column and the load sensor when the height and the speed of the aircraft are changed, so that a pilot obtains a relatively real column force. The performance of the arm regulator of the aircraft arm directly influences the normal operation of the flight control system and the flight safety of the aircraft. Because the arm regulator works together with one set of three finished products, the problem that the arm regulator is difficult to disassemble and assemble when a fault is found after the arm regulator is assembled is solved, and performance index verification before the arm regulator is assembled needs to be carried out on the airplane arm regulator. The verification means of the performance index of the aircraft moment arm regulator tests the performance index of the aircraft moment arm regulator through an aircraft control system moment arm test device. At present, an arm force testing device of an airplane control system is used for manual testing, the output air leakage testing value of a dynamic and static pressure pump is not accurate enough, and the testing value of a large arm force and a small arm force is not accurate enough than the standard vernier caliper testing value.
Disclosure of Invention
In order to solve the technical problems, the invention provides the test device for the arm of force regulator of the aircraft control system, which can stably test the performance of the arm of force regulator of the aircraft, ensure the smooth test of the arm of force regulator of the aircraft and ensure the qualified supply of the arm of force regulator of the aircraft.
A testing device for a force arm regulator of an aircraft control system comprises a device body, an operation display, a switch, a host machine, a data collector, a product testing cabinet, a spring load, a product mounting rack, a displacement sensor, an electrical plug, a dynamic pressure pipeline, a speed sensor, a height sensor, a static pressure pipeline and a vacuum pump, wherein the product testing cabinet is arranged on the side edge of the device body, the operation display is arranged on the table-board of the device body, the switch is arranged on the table-board of the device body and is positioned below the operation display, the host machine and the data collector are arranged inside the device body, the product mounting rack is arranged on the table-board of the product testing cabinet, the spring load is arranged on the table-board of the product testing cabinet and is positioned above the product mounting rack, the displacement sensor is arranged on the table-board of the product testing cabinet and is positioned on the side edge of, the speed sensor, the height sensor and the vacuum pump are arranged in the product testing cabinet, one end of the dynamic pressure pipeline and one end of the static pressure pipeline are connected with the vacuum pump, the other end of the dynamic pressure pipeline and the other end of the static pressure pipeline extend out of the table surface of the product testing cabinet, the displacement sensor, the electrical plug, the speed sensor, the height sensor and the vacuum pump are connected with the data acquisition unit through wires, and the operation display and the switch are connected with the host through wires.
Further, a dynamic pressure pipeline and a static pressure pipeline of the testing device for the moment arm regulator of the aircraft control system are both rubber hoses.
Further, the operation display of the test device for the arm regulator of the aircraft control system is a touch screen display.
Further, the testing device for the arm of force regulator of the aircraft control system further comprises a frequency sensor, the frequency sensor is arranged inside the product testing cabinet, and the product testing cabinet is connected with the data acquisition unit through a wire.
The testing device for the arm regulator of the airplane control system has the advantages of simple structure, convenience in operation, capability of automatically recording test data and monitoring the working state of the arm in real time. And moreover, the stability of the height, the speed and the large and small arm values of the force arm of the airplane in the test process is well guaranteed, the test result is guaranteed, the qualified supply of the force arm of the airplane is ensured, and the test efficiency is improved.
Drawings
FIG. 1: is a structural schematic diagram of the invention.
In the figure: 1. a device body; 2. an operation display; 3. a switch; 4. a host; 5. a data acquisition unit; 6. a product testing cabinet; 7. a spring load; 8. a product mounting rack; 9. a displacement sensor; 10. an electrical plug; 11. a dynamic pressure pipeline; 12. a speed sensor; 13. a height sensor; 14. a static pressure pipeline; 15. a vacuum pump.
Detailed Description
Embodiments of the present invention will be described in more detail below with reference to the accompanying drawings.
A testing device for a force arm regulator of an aircraft control system comprises a device body 1, an operation display 2, a switch 3, a host machine 4, a data acquisition unit 5, a product testing cabinet 6, a spring load 7, a product mounting rack 8, a displacement sensor 9, an electrical plug 10, a dynamic pressure pipeline 11, a speed sensor 12, a height sensor 13, a static pressure pipeline 14 and a vacuum pump 15, wherein the product testing cabinet 6 is arranged on the side edge of the device body 1, the operation display 2 is arranged on the table-board of the device body 1, the switch 3 is arranged on the table-board of the device body 1 and is positioned below the operation display 2, the host machine 4 and the data acquisition unit 5 are arranged inside the device body 1, the product mounting rack 8 is arranged on the table-board of the product testing cabinet 6, the spring load 7 is arranged on the table-board of the product testing cabinet 6 and is positioned above the product mounting rack 8, the displacement sensor 9 is arranged on the table-board of, the electric plug 10 is arranged on the table top of the product testing cabinet 6, the speed sensor 12, the height sensor 13 and the vacuum pump 15 are arranged inside the product testing cabinet 6, one end of the dynamic pressure pipeline 11 and one end of the static pressure pipeline 14 are connected with the vacuum pump 15, the other end of the dynamic pressure pipeline and the other end of the static pressure pipeline extend out of the table top of the product testing cabinet 6, the displacement sensor 9, the electric plug 10, the speed sensor 12, the height sensor 13 and the vacuum pump 15 are connected with the data acquisition unit 5 through wires, and the operation display 2 and the switch 3 are connected with the host 4 through.
In order to facilitate the operation and improve the testing efficiency. The dynamic pressure pipeline 11 and the static pressure pipeline 14 of the testing device for the moment arm regulator of the aircraft control system are both rubber hoses.
In order to improve the operability and meet the use requirements. The operation display 2 of the testing device for the arm regulator of the aircraft control system is a touch screen display.
The dynamic pressure and static pressure of the regulator of the force-measured arm can be monitored. The testing device for the force arm regulator of the aircraft control system further comprises a frequency sensor, wherein the frequency sensor is arranged inside the product testing cabinet 6, and the product testing cabinet 6 is connected with the data acquisition unit 5 through a wire.
The working principle of the invention is as follows: installing a control box and an electric mechanism of the force-measured arm regulator on the upper part of a product mounting rack 8, butting a control box plug of the force-measured arm regulator with an electric plug 10, and connecting the electric mechanism of the force-measured arm regulator with a displacement sensor 9; the operation display 2 is mainly used for setting data and displaying detection parameters and other product tests, the host 4 is a central pivot of the whole control system to complete data acquisition processing and control, and the data acquisition unit 5 converts all signals into digital signals which can be identified by a computer through signals acquired by various sensors; a starting test instruction is sent by the operation display 2, the vacuum pump 15 works after receiving a signal of the host 1 to provide dynamic and static pressure signals for the measured force arm regulator, the measured force arm regulator generates speed and height, the speed and height are transmitted to the speed sensor 12 and the height sensor 13 to be measured and transmitted to the data collector 5, an electric mechanism of the measured force arm regulator generates displacement, the displacement is measured by the displacement sensor 9 and transmitted to the data collector 5, current and voltage generated by the measured force arm regulator are transmitted to the data collector 5, the data collector 5 transmits the converted signal to the host 4 to be processed, the host 4 transmits the processed signal to the operation display 5 to be displayed, and the test process is completed.
The scope of the invention is not limited to the embodiments disclosed in the detailed description, and the examples and descriptions set forth above are intended to illustrate the principles of the invention and are intended to cover various modifications and improvements within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (4)
1. The utility model provides an aircraft control system arm of force regulator test device which characterized in that: the testing device for the moment arm regulator of the aircraft control system comprises a device body (1), an operation display (2), a switch (3), a host (4), a data collector (5), a product testing cabinet (6), a spring load (7), a product mounting rack (8), a displacement sensor (9), an electrical plug (10), a dynamic pressure pipeline (11), a speed sensor (12), a height sensor (13), a static pressure pipeline (14) and a vacuum pump (15), wherein the product testing cabinet (6) is arranged on the side edge of the device body (1), the operation display (2) is arranged on the table top of the device body (1), the switch (3) is arranged on the table top of the device body (1) and is positioned below the operation display (2), the host (4) and the data collector (5) are arranged inside the device body (1), the product mounting rack (8) is arranged on the table top of the product testing cabinet (6), the spring load (7) is arranged on the table surface of the product testing cabinet (6) and is positioned above the product mounting rack (8), the displacement sensor (9) is arranged on the table surface of the product testing cabinet (6) and is positioned at the side edge of the product mounting rack (8), the electrical plug (10) is arranged on the table-board of the product testing cabinet (6), the speed sensor (12), the height sensor (13) and the vacuum pump (15) are arranged inside the product testing cabinet (6), one end of the dynamic pressure pipeline (11) and one end of the static pressure pipeline (14) are connected with the vacuum pump (15), and the other end extends out of the table surface of the product testing cabinet (6), the displacement sensor (9), the electrical plug (10), the speed sensor (12), the height sensor (13) and the vacuum pump (15) are connected with the data acquisition unit (5) through wires, the operation display (2) and the switch (3) are connected with the host (4) through wires.
2. The aircraft handling system moment arm adjuster test device of claim 1, wherein: the dynamic pressure pipeline (11) and the static pressure pipeline (14) are both rubber hoses.
3. An aircraft handling system moment arm adjuster test device according to claim 1 or claim 2, wherein: the operation display (2) is a touch screen display.
4. The aircraft handling system moment arm adjuster test device of claim 3, wherein: the testing device for the arm of force regulator of the aircraft control system further comprises a frequency sensor, wherein the frequency sensor is arranged inside a product testing cabinet (6), and the product testing cabinet (6) is connected with a data acquisition unit (5) through a wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811500041.1A CN111284727A (en) | 2018-12-07 | 2018-12-07 | Testing device for moment arm regulator of airplane control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811500041.1A CN111284727A (en) | 2018-12-07 | 2018-12-07 | Testing device for moment arm regulator of airplane control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111284727A true CN111284727A (en) | 2020-06-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811500041.1A Pending CN111284727A (en) | 2018-12-07 | 2018-12-07 | Testing device for moment arm regulator of airplane control system |
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| Country | Link |
|---|---|
| CN (1) | CN111284727A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080157042A1 (en) * | 2005-01-06 | 2008-07-03 | Quoin International, Inc. | Powered personnel ascender |
| CN102001444A (en) * | 2010-11-19 | 2011-04-06 | 陕西飞机工业（集团）有限公司 | Neutral position adjustment device of flight control system and neutral position setting method thereof |
| CN202110062U (en) * | 2011-06-20 | 2012-01-11 | 山西省交通科学研究院 | Automobile manual transmission testing device |
| CN103871292A (en) * | 2014-03-27 | 2014-06-18 | 芜湖航飞科技股份有限公司 | Full-function flight simulator |
-
2018
- 2018-12-07 CN CN201811500041.1A patent/CN111284727A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080157042A1 (en) * | 2005-01-06 | 2008-07-03 | Quoin International, Inc. | Powered personnel ascender |
| CN102001444A (en) * | 2010-11-19 | 2011-04-06 | 陕西飞机工业（集团）有限公司 | Neutral position adjustment device of flight control system and neutral position setting method thereof |
| CN202110062U (en) * | 2011-06-20 | 2012-01-11 | 山西省交通科学研究院 | Automobile manual transmission testing device |
| CN103871292A (en) * | 2014-03-27 | 2014-06-18 | 芜湖航飞科技股份有限公司 | Full-function flight simulator |
Non-Patent Citations (2)
| Title |
|---|
| 杨文杰等: "力臂自动调节装置智能综合测试系统的设计", 《西安航空技术高等专科学校学报》 * |
| 邹涛等: "LB-703型力臂智能综合测试系统", 《计算机测量与控制》 * |
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Application publication date: 20200616 |
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