CN105486453A - Test equipment for measuring inertial load of aircraft under vacuum condition - Google Patents
Test equipment for measuring inertial load of aircraft under vacuum condition Download PDFInfo
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- CN105486453A CN105486453A CN201510838155.7A CN201510838155A CN105486453A CN 105486453 A CN105486453 A CN 105486453A CN 201510838155 A CN201510838155 A CN 201510838155A CN 105486453 A CN105486453 A CN 105486453A
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- vacuum
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/10—Determining the moment of inertia
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- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to test equipment for measuring inertial load of an aircraft under vacuum condition. In china, at present, when aircraft experiment is carried out, data is processed with a method of subtracting windless data from wind data, such that aerodynamic damping is deducted, the obtained result is not accurate, and dynamic test data precision is influenced. The test equipment comprises a vacuum cavity (1), wherein the vacuum cavity is connected with a vacuum-pumping system. The vacuum-pumping system comprises a group of pre-vacuum-pumping units (2), wherein the pre-vacuum-pumping units are arranged at the two sides of the vacuum cavity. One side of the vacuum cavity is equipped with a group of reserved high-vacuum connecting flanges (3), a vacuum observation window (4) and a vacuum measurement gauge tube interface (5). The front end of the vacuum cavity is provided with a vacuum connecting flange (8), a quakeproof corrugated pipe (7) and a test equipment support rod (6). The vacuum cavity is internally provided with a slide guide rail (9). The test equipment is applied to the inertial load test of the aircraft.
Description
technical field:
based on the testing equipment measuring aircraft inertia load under vacuum condition.
background technology:
the unsteady flo w test technology investigation of China starts from the eighties in last century, for meeting aircraft Dynamic stability characteristic research needs, establishing many cover low-speed wind tunnel dynamic derivative testing devices, having carried out multiple model dynamic derivative testing research.Enter the nineties, particularly since " 95 ", under the support of aerodynamics pre research project, each pneumatic research unit establishes a series of test unit for dynamic aerodynamics research, as the At High Angle of Attack dynamic derivative testing device, Rolling Balance Experimental Equipment, wing rock test unit, single-degree-of-freedom large amplitude shaking test device etc. of 3 meters of magnitude low-speed wind tunnels at type of production high, low speed wind-tunnel all in succession.Enter the new century, the cultivation of " 15 " and Eleventh Five-Year Plan two five-year plans is done through general assembly beforehand research, low-speed wind tunnel multiple degrees of freedom dynamic test technique is developed rapidly, domestic main aerodynamic force research institution has substantially possessed the dynamic flow tunnel testing device of research advanced opportunity of combat post stall maneuver problem in low-speed wind tunnel, comprise: free vibration, forced vibration, large-amplitude vibration and rotary balance, and the checking that all have passed calibration model test.In the accurate Research on Accuracy of raising, the development of dynamic test technique exists the thought of " first solving to have does not have, and rear solution is accurate inaccurate ", so constituent parts has all been placed on focus in development new technology, have ignored the research of dynamic test modification method.
carrying out dynamic test at present both at home and abroad when measuring moment of inertia and carrying out data correction, usually with there being wind data to deduct without wind data, obtaining the influence amount of flow motivating gas.But in static moment is measured, static force measurement tests only measurement model gravity, dynamic test measurement model gravity and air damping, if deduct calm method with there being wind to process data, air damping deduction will be fallen, cause result inaccurate, affect dynamic test data precision.
summary of the invention:
the object of this invention is to provide a kind of testing equipment based on measuring aircraft inertia load under vacuum condition, solving the inaccurate problem of test findings of aircraft inertia load.
above-mentioned object is realized by following technical scheme:
a kind of testing equipment based on measuring aircraft inertia load under vacuum condition, its composition comprises: vacuum cavity, described vacuum cavity is connected with pumped vacuum systems, described pumped vacuum systems comprises one group of forvacuum unit, described forvacuum units' installation is in the both sides of vacuum cavity, described vacuum cavity side is provided with one group and reserves high vacuum joint flange, vacuum view window, interface is regulated in vacuum measurement, described vacuum cavity front end is provided with bonding in vacuum flange, shockproof corrugated tube, experimental facilities support bar, described vacuum cavity inside is provided with rail plate.
described based on the testing equipment measuring aircraft inertia load under vacuum condition, described vacuum cavity comprises vacuum cavity A, vacuum cavity B, and described vacuum cavity A, the port of vacuum cavity B have door respectively.
described based on the testing equipment measuring aircraft inertia load under vacuum condition, described vacuum cavity A is of a size of 3000mm*H3000mm, and described vacuum cavity B is of a size of 3000mm*H2000mm, and the diameter of described vacuum view window is 200mm.
the described testing equipment based on aircraft inertia load under vacuum condition, described cavity body A, described vacuum cavity B material are 304 stainless steels.
the described testing equipment based on aircraft inertia load under vacuum condition, described pumped vacuum systems is equipped with 2 Node Controllers, the vacuum tightness of automatic control vacuum cavity, and vacuum pump is equipped with, the vacuum tightness of Non-follow control vacuum cavity, meets the different demands of vacuum cavity to various vacuum tightness.
beneficial effect of the present invention:
the present invention can measure inertial load and the air damping of the test such as dynamic derivative, significantly vibration, rotary balance, rotation/vibration kind; Can under vacuum conditions, inspection rotates kind equipment rotating measurement result consistance; Whether suitablely can be used in inspection pole stiffness; Can for the test of rotation class, the accuracy of measurement of research two kinds of supporting way.
vacuum of the present invention takes out system disposition in advance 2 Node Controllers, automatically can control the vacuum tightness of vacuum cavity, and be equipped with vacuum pump, can the vacuum tightness of Non-follow control vacuum cavity, meets the different demands of vacuum cavity to various vacuum tightness.
vacuum cavity of the present invention is equipped with the vacuum view window of 4 diameters 200, can the duty of normal observation vacuum cavity inside, and can not affect the serviceability of cavity, and inside cavity is equipped with mounting guide rail, facilitates the later stage to change experimental facilities
vacuum cavity of the present invention is connected with experimental facilities: experimentally equipment matched design bonding in vacuum flange and shockproof vacuum corrugated pipe, the installation of vacuum corrugated pipe can well the absorption experiment equipment lower shock-effect produced in working order, better can ensure the vacuum tightness of vacuum cavity and vacuum-packed serviceable life.
accompanying drawing illustrates:
accompanying drawing 1 is structural representation of the present invention.
accompanying drawing 2 is schematic internal view of vacuum cavity of the present invention.
embodiment:
embodiment 1:
a kind of testing equipment based on measuring aircraft inertia load under vacuum condition, its composition comprises: vacuum cavity 1, described vacuum cavity is connected with pumped vacuum systems, described pumped vacuum systems comprises one group of forvacuum unit 2, described forvacuum units' installation is in the both sides of vacuum cavity, described vacuum cavity side is provided with one group and reserves high vacuum joint flange 3, vacuum view window 4, interface 5 is regulated in vacuum measurement, described vacuum cavity front end is provided with bonding in vacuum flange 8, shockproof corrugated tube 7, experimental facilities support bar 6, described vacuum cavity inside is provided with rail plate 9.
embodiment 2:
according to embodiment 1 based on the testing equipment measuring aircraft inertia load under vacuum condition, described vacuum cavity comprises vacuum cavity A, vacuum cavity B, and described vacuum cavity A, the port of vacuum cavity B have door 10 respectively.
embodiment 3:
according to embodiment 1 or 2 based on the testing equipment measuring aircraft inertia load under vacuum condition, described vacuum cavity A is of a size of 3000mm*H3000mm, described vacuum cavity B is of a size of 3000mm*H2000mm, and the diameter of described vacuum view window is 200mm.
embodiment 4:
according to embodiment 1 or 2 or 3 based on the testing equipment measuring aircraft inertia load under vacuum condition, described cavity body A, described vacuum cavity B material are 304 stainless steels.
embodiment 5:
according to embodiment 1 or 2 or 3 or 4 based on the testing equipment measuring aircraft inertia load under vacuum condition, described pumped vacuum systems is equipped with 2 Node Controllers, the vacuum tightness of automatic control vacuum cavity, and vacuum pump is equipped with, the vacuum tightness of Non-follow control vacuum cavity, meets the different demands of vacuum cavity to various vacuum tightness.
embodiment 6:
the technical requirement of equipment is: even weld, inside cavity wire drawing polishing, outside can wire drawing polishing or process of spraying paint, and cavity helium mass spectrometer leak detector detects leak rate and is better than 1.3 × 10-8PaM3/S, the end vacuum of vacuum cavity design can reach 6.0 × 10-4Pa, and is equipped with vacuum breaker valve.
embodiment 7:
two cavitys can be dismantled, if test model only does significantly vibration, pitching cross coupling, rotary balance, space is little, only need a cavity, as done heave or other tests, can connect two cavitys, device power-up 10 minutes vacuum tightness is better than 1000Pa, 20 minutes vacuum tightness of starting shooting is better than 100Pa, and 30 minutes vacuum tightness of starting shooting is better than 20Pa.
Claims (5)
1. one kind based on the testing equipment measuring aircraft inertia load under vacuum condition, its composition comprises: vacuum cavity, it is characterized in that: described vacuum cavity is connected with pumped vacuum systems, described pumped vacuum systems comprises one group of forvacuum unit, described forvacuum units' installation is in the both sides of vacuum cavity, described vacuum cavity side is provided with one group and reserves high vacuum joint flange, vacuum view window, interface is regulated in vacuum measurement, described vacuum cavity front end is provided with bonding in vacuum flange, shockproof corrugated tube, experimental facilities support bar, described vacuum cavity inside is provided with rail plate.
2. the testing equipment based on measuring aircraft inertia load under vacuum condition according to claim 1, is characterized in that: described vacuum cavity comprises vacuum cavity A, vacuum cavity B, and described vacuum cavity A, the port of vacuum cavity B have door respectively.
3. the testing equipment based on measuring aircraft inertia load under vacuum condition according to claim 1 and 2, it is characterized in that: described vacuum cavity A is of a size of 3000mm*H3000mm, described vacuum cavity B is of a size of 3000mm*H2000mm, and the diameter of described vacuum view window is 200mm.
4. according to claim 1 or 2 or 3 based on the testing equipment measuring aircraft inertia load under vacuum condition, it is characterized in that: described cavity body A, described vacuum cavity B material are 304 stainless steels.
5. according to claim 1 or 2 or 3 or 4 based on the testing equipment measuring aircraft inertia load under vacuum condition, it is characterized in that: described pumped vacuum systems is equipped with 2 Node Controllers, the vacuum tightness of automatic control vacuum cavity, and vacuum pump is equipped with, the vacuum tightness of Non-follow control vacuum cavity, meets the different demands of vacuum cavity to various vacuum tightness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510838155.7A CN105486453A (en) | 2015-11-26 | 2015-11-26 | Test equipment for measuring inertial load of aircraft under vacuum condition |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510838155.7A CN105486453A (en) | 2015-11-26 | 2015-11-26 | Test equipment for measuring inertial load of aircraft under vacuum condition |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105486453A true CN105486453A (en) | 2016-04-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510838155.7A Pending CN105486453A (en) | 2015-11-26 | 2015-11-26 | Test equipment for measuring inertial load of aircraft under vacuum condition |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109387350A (en) * | 2018-12-06 | 2019-02-26 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of interior formula coaxial corrugated pipe balance system |
| CN119085994A (en) * | 2024-11-06 | 2024-12-06 | 中国航空工业集团公司沈阳空气动力研究所 | A test method for measuring unsteady aerodynamic force during wing deployment |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JPS6042408B2 (en) * | 1980-08-19 | 1985-09-21 | 日本電気株式会社 | Dynamic balance test method |
| JPS61281933A (en) * | 1985-06-07 | 1986-12-12 | Mitsubishi Heavy Ind Ltd | Balance testing instrument for high-speed centrifugal compressor |
| US4918985A (en) * | 1988-01-12 | 1990-04-24 | Aerospatiale Societe Nationale Industrielle | Dynamic balancing system overcoming aerodynamic forces |
| CN103674428A (en) * | 2013-11-29 | 2014-03-26 | 上海卫星装备研究所 | Low-vacuum dynamic test device |
-
2015
- 2015-11-26 CN CN201510838155.7A patent/CN105486453A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6042408B2 (en) * | 1980-08-19 | 1985-09-21 | 日本電気株式会社 | Dynamic balance test method |
| JPS61281933A (en) * | 1985-06-07 | 1986-12-12 | Mitsubishi Heavy Ind Ltd | Balance testing instrument for high-speed centrifugal compressor |
| US4918985A (en) * | 1988-01-12 | 1990-04-24 | Aerospatiale Societe Nationale Industrielle | Dynamic balancing system overcoming aerodynamic forces |
| CN103674428A (en) * | 2013-11-29 | 2014-03-26 | 上海卫星装备研究所 | Low-vacuum dynamic test device |
Non-Patent Citations (4)
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| 曹占龙 等: "基于 ANSYS 的中性束注入器主真空室结构力学分析", 《机械设计与制造》 * |
| 朱毓坤: "《核真空科学技术》", 31 July 2010, 原子能出版社 * |
| 马爱军: "《载人航天环境模拟舱（上册）》", 31 October 2014, 国防工业出版社 * |
| 黄本诚: "《中国航天空间环境工程著名专家黄本诚文集》", 31 January 2007 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109387350A (en) * | 2018-12-06 | 2019-02-26 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of interior formula coaxial corrugated pipe balance system |
| CN109387350B (en) * | 2018-12-06 | 2023-08-25 | 中国航空工业集团公司沈阳空气动力研究所 | Internal coaxial corrugated pipe balance system |
| CN119085994A (en) * | 2024-11-06 | 2024-12-06 | 中国航空工业集团公司沈阳空气动力研究所 | A test method for measuring unsteady aerodynamic force during wing deployment |
| CN119085994B (en) * | 2024-11-06 | 2025-02-28 | 中国航空工业集团公司沈阳空气动力研究所 | A test method for measuring unsteady aerodynamic force during wing deployment |
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Application publication date: 20160413 |