CN114486151B - Add oil pipe wind-tunnel flight test device - Google Patents
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- CN114486151B CN114486151B CN202210387221.3A CN202210387221A CN114486151B CN 114486151 B CN114486151 B CN 114486151B CN 202210387221 A CN202210387221 A CN 202210387221A CN 114486151 B CN114486151 B CN 114486151B
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- wind tunnel
- rolling
- flight test
- test device
- oil filling
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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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
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to the field of wind tunnel tests, and particularly relates to a wind tunnel flight test device for an oil filling pipe. The device comprises a rolling component, an upper retracting rope, a lower retracting rope and a retracting seat; the rolling assembly is used for enabling the oil filling pipe model to rotate in a rolling mode; the rolling assembly is rotationally connected with the oil filling pipe model, so that the oil filling pipe model has pitching rotation; the upper retracting rope is movably arranged in the retracting seat; the upper retracting rope is used for controlling the retraction of the oil filling pipe model. The invention can simulate the motion of the oil filling pipe and realize the wind tunnel flight test of the oil filling pipe.
Description
Technical Field
The invention belongs to the field of wind tunnel tests, and particularly relates to a wind tunnel flight test device for an oil filling pipe.
Background
The wind tunnel flight test is one of important means for verifying the flight characteristics of the test object, and the dynamic characteristics of the test object are verified through the test. Compared with the atmospheric free flight test, the wind tunnel flight test has controllable test conditions, real and reliable data and higher safety. The three-freedom-degree flight test support of the airplane is usually arranged on the belly of the airplane. To adding the elongated body structure of oil pipe this kind, its motion and manipulation characteristic have great difference with the aircraft, and current aircraft flight test device can not be used for adding oil pipe flight test, need design one kind and can be used for the test device that adds the flight of oil pipe wind-tunnel.
Disclosure of Invention
The invention provides a wind tunnel flight test device for an oil filling pipe. The invention can simulate the motion of the oil filling pipe and realize the wind tunnel flight test of the oil filling pipe.
The invention is realized by the following technical scheme:
the invention provides a wind tunnel flight test device for an oil filling pipe, which comprises a rolling component, an upper retracting rope, a lower retracting rope and a retracting seat, wherein the upper retracting rope is connected with the lower retracting rope;
the rolling assembly is used for enabling the oil filling pipe model to rotate in a rolling mode;
the rolling assembly is rotationally connected with the oil filling pipe model, so that the oil filling pipe model has pitching rotation;
the upper retracting rope is movably arranged in the retracting seat;
the upper retracting rope is used for controlling the retraction of the refueling pipe model.
Further, the rolling assembly comprises a rolling shaft, a rolling shaft support and a bearing, and the rolling shaft support is connected to the top of the wind tunnel; one end of the rolling shaft is connected in the rolling shaft support through a bearing, and the other end of the rolling shaft is positioned outside the rolling shaft support and connected with an oil filling pipe model.
Further, the number of the bearings is two.
Further, be provided with positioning sleeve between two bearings, positioning sleeve cover is established on the roll-over axle, positioning sleeve's both ends all with the bearing butt.
Further, the rolling shaft of the rolling assembly is connected with the oil filling pipe model through a rotating shaft.
Further, a fairing is arranged outside the rolling assembly.
Furthermore, the rolling assembly is arranged at the top of the wind tunnel, and the retractable seat is arranged at the top of the wind tunnel.
Further, the wind tunnel further comprises a lower retractable rope, and the lower retractable rope is arranged at the bottom of the wind tunnel.
Furthermore, the outer surface of the rolling assembly is fixedly connected with a support, and the support is used for being connected with the top of the wind tunnel.
The device further comprises a fixed plate, wherein a rolling assembly or a support is fixedly arranged on the fixed plate, and the fixed plate is used for being fixedly connected with the top of the wind tunnel; or the fixed plate is fixedly provided with a rolling assembly or a support, the fixed plate is fixedly provided with a retractable seat, and the fixed plate is fixedly connected with the top of the wind tunnel.
By adopting the technical scheme, the invention has the following advantages:
1. the invention can simulate the motion of the oil filling pipe and realize the wind tunnel flight test of the oil filling pipe.
2. The rolling assembly has simple structure and easy manufacture.
3. The fairing is arranged outside the rolling assembly, so that the fairing can avoid the influence of the rolling assembly on a flow field and improve the test accuracy.
4. The lower protection rope is added, and can be tensioned together with the upper protection rope in an emergency, so that the movement of the refueling pipe model is limited, the test safety is ensured, and a double-safety function is achieved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments of the present invention or the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained based on these drawings without creative efforts.
FIG. 1 is a first structural schematic diagram of a wind tunnel flight test device for an oil filling pipe in an embodiment of the invention;
FIG. 2 is a structural schematic diagram II of a wind tunnel flight test device for an oil filling pipe in the embodiment of the invention;
FIG. 3 is a schematic view of a part of a structure of a wind tunnel flight test device for an oil filling pipe in the embodiment of the invention;
FIG. 4 is a schematic structural diagram II of a part of a wind tunnel flight test device for an oil filling pipe in the embodiment of the invention;
FIG. 5 is a schematic view of a part of a structure of a wind tunnel flight test device for an oil filling pipe in the embodiment of the invention;
FIG. 6 is a third schematic structural diagram of a wind tunnel flight test device for an oil filling pipe in the embodiment of the invention;
FIG. 7 is a schematic structural diagram of a retractable seat in an embodiment of the present invention;
in the drawings: 10-rolling component, 11-rolling shaft, 12-rolling shaft support, 121-rolling shaft connecting hole, 13-bearing, 131-radial rotation, 132-axis movement, 20-upper retracting rope, 30-lower retracting rope, 50-positioning sleeve, 60-fairing, 70-support, 80-retracting seat, 81-U-shaped groove, 100-oil filling pipe model, 110-wind tunnel, 111-wind tunnel top, 112-wind tunnel bottom, 120-fixing plate, 130-rotating shaft and 140-bearing end cover.
Detailed Description
The following description provides many different embodiments, or examples, for implementing different features of the invention. The particular examples set forth below are illustrative only and are not intended to be limiting.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, are merely for convenience of description and simplicity of description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present invention, "a plurality" means a plurality or more unless specifically limited otherwise.
In the description of the present invention, it should be noted that, unless otherwise specifically stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may include, for example, a fixed connection, a removable connection, or an integral connection: may be mechanically, electrically or may be in communication with each other; the connection may be direct or indirect through an intermediate medium, and may be a connection between a plurality of elements or an interaction relationship between a plurality of elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
As shown in fig. 1, 2 and 6, the embodiment provides a fuel filler pipe wind tunnel flight test device, which includes a rolling assembly 10, an upper retractable rope 20, a lower retractable rope 30 and a retractable seat 80;
the rolling assembly 10 is used for rolling and rotating the fuel filler pipe model 100;
the rolling assembly 10 is rotationally connected with the oil filling pipe model 100, so that the oil filling pipe model 100 has pitching rotation;
the retractable rope 20 is movably arranged in the retractable seat 80;
the upper retracting rope 20 is used for controlling the retracting of the oil filling pipe model 100.
Further, in some embodiments, as shown in FIG. 3, the roll assembly 10 includes a roll shaft 11, a roll shaft support 12, and a bearing 13, the roll shaft support 12 being coupled to the wind tunnel top 111; one end of the rolling shaft 11 is connected in the rolling shaft support 12 through a bearing 13, and the other end is positioned outside the rolling shaft support 12 and connected with the oil filling pipe model 100. The rolling component 10 is formed by only connecting a rolling shaft 11, a rolling shaft support 12 and a bearing 13, and is simple in composition and easy to manufacture; and the roll shaft 11, the roll shaft support 12 and the bearing 13 can be purchased and used directly, so that the universality degree is high, and the cost is reduced.
Further, in some embodiments, two bearings 13 are provided. The bearing 13 has the advantage of reducing frictional loads.
Further, in some embodiments, a positioning sleeve 50 is disposed between the two bearings 13, the positioning sleeve 50 is sleeved on the rolling shaft 11, and both ends of the positioning sleeve 50 are abutted against the bearings 13. Because the bearing 13 has axial movement in addition to the radial rotation 131, the axial movement does not affect the roll of the roll shaft 11, which may cause damage to the bearing 13 and reduce the service life of the device; therefore, the positioning sleeve 50 can limit the axial movement of the two bearings 13, the bearings 13 are prevented from being damaged, and the service life of the device is prolonged.
Further, in some embodiments, as shown in fig. 5, a bearing cover 140 is further provided, the bearing cover 140 abuts against the bearing 13, the bearing cover 140 also limits the axial movement of the bearing 13, of course, the bearing cover 140 and the positioning sleeve 50 are respectively located at two sides of the bearing 13, and the axial movement of the bearing 13 in both directions is limited, so that the bearing 13 does not have the axial movement.
It should be noted that bearing cap 140 may also be a part of the quill support 12, such as bearing cap 140 may be integrally formed with the quill support 12.
Further, in some embodiments, as shown in FIG. 3, the roll shaft 11 of the roll assembly 10 is coupled to the filler tube mold 100 via a rotating shaft 130. The pitching rotation of the oil filling pipe model 100 can be realized only by the connection of the rotating shaft 130, and the oil filling pipe model has the advantages of simple structure, cost reduction, simple connection mode and easy operation.
Further, in certain embodiments, as shown in FIG. 3, a fairing 60 is provided external to the roll assembly 10. The influence of the roll assembly 10 on the flow field is avoided, and the test accuracy is improved.
Further, in some embodiments, the roll assembly 10 is disposed at the top 111 of the wind tunnel, and the retractable seat 80 is disposed at the top 111 of the wind tunnel. The storage seat 80 has a function of guiding the upper storage string 20.
Further, the wind tunnel further comprises a lower retractable rope 30, and the lower retractable rope 30 is arranged at the bottom 112 of the wind tunnel.
Further, in some embodiments, as shown in fig. 7, the storage seat 80 is further provided with a U-shaped groove 81, and the U-shaped groove 81 has a guiding and limiting function on the filler pipe mold 100.
It should be noted that in the actual use process, the upper retractable rope 20 needs to pass through the top 111 of the wind tunnel, the lower retractable rope 30 needs to pass through the bottom 112 of the wind tunnel, and an operator can control the fuel filler pipe model 100 by pulling the upper retractable rope 20 and the lower retractable rope 30 outside the wind tunnel.
Further, in some embodiments, as shown in FIG. 3, a support 70 is fixedly attached to an outer surface of roll assembly 10, and support 70 is configured to be attached to a top portion 111 of the wind tunnel. Connecting the roll assembly 10 to the wind tunnel top 111 via the support 70 enables the roll assembly 10 to be closer to the center of the wind tunnel 110, which has the advantage of improving the accuracy of the test.
Further, in some embodiments, as shown in fig. 3, 4, and 6, the wind tunnel further includes a fixing plate 120, the fixing plate 120 is fixedly provided with the roll assembly 10 or the support 70, and the fixing plate 120 is fixedly connected to the wind tunnel top 111; or the fixed plate 120 is fixedly provided with the rolling assembly 10 or the support 70, the fixed plate 120 is fixedly provided with the upper retractable seat 80, and the fixed plate 120 is used for being fixedly connected with the top 111 of the wind tunnel.
It is also possible to fix the fairing 60 to the fixed plate 120 by providing the roll assembly 10 (i.e., without the support 70) or the support 70 on the fixed plate, by providing the fairing 60 outside the roll assembly 10 or the roll assembly 10 to which the support 70 is attached, and by fixing the fairing 60 to the fixed plate. Based on the structure, the invention has the advantage of convenient installation.
The wind tunnel flight test device for the oil filling pipe of the embodiment is specifically used as follows: as shown in fig. 1, 2 and 6, the end of the filler pipe model 100 is connected with the rolling shaft 11 of the rolling assembly 10 through a rotating shaft 130, the upper surface of the middle part of the filler pipe model 100 is connected with an upper retractable rope 20, the lower surface of the middle part of the filler pipe model 100 is connected with a lower retractable rope 30, before the test, the filler pipe model 100 is pulled up through the upper retractable rope 20 to set the airflow environment in the wind tunnel 110, the upper retractable rope 20 is loosened to start the test, and the test data is collected.
In the actual air refueling process, the root part of the refueling pipe is connected with the body of the refueling machine, and the refueling pipe has rolling and pitching movement and manipulation capabilities. The true motion of the filler tube can be simulated by connecting the filler tube model 100 and the rolling assembly 10 through a rotating shaft.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (9)
1. The utility model provides an add oil pipe wind-tunnel flight test device which characterized in that: comprises a rolling component (10), an upper retracting rope (20), a lower retracting rope (30) and a retracting seat (80);
the rolling assembly (10) is used for rolling and rotating the fuel filling pipe model (100);
the rolling assembly (10) is rotationally connected with the oil filling pipe model (100) to enable the oil filling pipe model (100) to have pitching rotation;
the upper retracting rope (20) is movably arranged in the retracting seat (80);
the upper retracting rope (20) is used for controlling the retracting of the refueling pipe model (100);
the roll assembly (10) comprises a roll shaft (11), a roll shaft support (12) and a bearing (13), and the roll shaft support (12) is connected to the top (111) of the wind tunnel; one end of the rolling shaft (11) is connected in the rolling shaft support (12) through a bearing (13), and the other end of the rolling shaft (11) is positioned outside the rolling shaft support (12) and is connected with the oil filling pipe model (100).
2. The fuel filler pipe wind tunnel flight test device of claim 1, wherein: the number of the bearings (13) is two.
3. The fuel filler pipe wind tunnel flight test device of claim 2, wherein: be provided with between two bearings (13) positioning sleeve (50), positioning sleeve (50) cover is established on roll-off axle (11), the both ends of positioning sleeve (50) all with bearing (13) butt.
4. The fuel filler pipe wind tunnel flight test device of claim 1, wherein: the rolling shaft (11) of the rolling assembly (10) is connected with the oil filling pipe model (100) through a rotating shaft (130).
5. The fuel filler pipe wind tunnel flight test device of claim 1, wherein: a fairing (60) is arranged outside the rolling assembly (10).
6. The fuel filler pipe wind tunnel flight test device of claim 1, wherein: the rolling assembly (10) is arranged at the top (111) of the wind tunnel, and the retractable seat (80) is arranged at the top (111) of the wind tunnel.
7. The fuel filler pipe wind tunnel flight test device according to claim 1 or 6, characterized in that: the wind tunnel is characterized by further comprising a lower retracting rope (30), wherein the lower retracting rope (30) is arranged at the bottom (112) of the wind tunnel.
8. The fuel filler pipe wind tunnel flight test device of claim 1, wherein: the outer surface of the rolling assembly (10) is fixedly connected with a support (70), and the support (70) is used for being connected with the top (111) of the wind tunnel.
9. The fuel filler pipe wind tunnel flight test device according to claim 1 or 8, characterized in that: the device is characterized by further comprising a fixing plate (120), wherein the rolling assembly (10) or the support (70) is fixedly arranged on the fixing plate (120), and the fixing plate (120) is fixedly connected with the top (111) of the wind tunnel; or the fixed plate (120) is fixedly provided with a rolling component (10) or a support (70), the fixed plate (120) is fixedly provided with a retractable seat (80), and the fixed plate (120) is fixedly connected with the top (111) of the wind tunnel.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210387221.3A CN114486151B (en) | 2022-04-14 | 2022-04-14 | Add oil pipe wind-tunnel flight test device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210387221.3A CN114486151B (en) | 2022-04-14 | 2022-04-14 | Add oil pipe wind-tunnel flight test device |
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| CN114486151A CN114486151A (en) | 2022-05-13 |
| CN114486151B true CN114486151B (en) | 2022-06-17 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115597819B (en) * | 2022-11-30 | 2023-03-21 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel simulation aerial refueling hose-taper sleeve winding and unwinding devices |
| CN115808286B (en) * | 2023-02-08 | 2023-06-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Simulation device and simulation method for virtual flight of hard type air refueling docking wind tunnel |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3428272A1 (en) * | 1983-07-29 | 1985-02-14 | Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5000 Köln | Device for quantitative measurement of sound pressures in gases |
| CA2344612A1 (en) * | 2000-04-17 | 2001-10-17 | Wolfgang Gleine | Aerodynamic noise reducing structure for aircraft wing slats |
| CN101898640A (en) * | 2010-03-15 | 2010-12-01 | 王雪松 | Air refueling device of helicopter |
| EP2466288A2 (en) * | 2010-12-14 | 2012-06-20 | Japan Aerospace Exploration Agency | Method of designing natural laminar flow wing for reynolds numbers equivalent to actual supersonic aircraft |
| DE102011054535B3 (en) * | 2011-10-17 | 2013-03-28 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method for oil film interferometric measurement of wall shear stress on surface, involves extracting oil adjacent to surface such that oil flows through surface, where oil is applied on rotor near rotation axis |
| KR20140024109A (en) * | 2012-08-20 | 2014-02-28 | 한국항공우주산업 주식회사 | Method to improve the buffet property of t-50 |
| CN104359643A (en) * | 2014-10-29 | 2015-02-18 | 中国航空工业集团公司哈尔滨空气动力研究所 | Pitching-rolling two-degree-of-freedom experimental platform based on electromechanical hydraulic coupling drive |
| CN105784314A (en) * | 2016-03-04 | 2016-07-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-speed wind tunnel virtual flying experimental support device |
| CN107065593A (en) * | 2016-12-28 | 2017-08-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of attitude control system of aircraft refuelling lever apparatus |
| CN109470445A (en) * | 2018-12-24 | 2019-03-15 | 浙江大学 | A kind of freely-supported type air tunnel testing device for growing thin component resistance coefficient |
| CN110470453A (en) * | 2019-08-13 | 2019-11-19 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of low-speed wind tunnel air refuling hose-tapered sleeve dynamic property tester |
| CN110940483A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Pitching yawing free vibration dynamic derivative test device for large slenderness ratio aircraft |
| CN110940480A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Pitching yawing forced vibration dynamic derivative test device used under high attack angle of high-speed flying wing model |
| CN111721493A (en) * | 2019-07-03 | 2020-09-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Helicopter combined model wind tunnel test device with independent tail rotor device |
| CN112179608A (en) * | 2020-09-28 | 2021-01-05 | 厦门大学 | Supporting device and testing system for wind tunnel dynamic test of rotary rocket model |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2291093B1 (en) * | 2005-10-31 | 2008-12-16 | Airbus España, S.L. | SYSTEM FOR TRANSMITTING PRESSURES BETWEEN A REMOVABLE PIECE AND A FIXED PIECE OF A MODEL AVAILABLE IN AN AERODYNAMIC TUNNEL. |
| CN105588702B (en) * | 2016-03-04 | 2017-09-29 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of low-speed wind tunnel model drive flight experiment dynamical system |
| CN110356574B (en) * | 2018-04-11 | 2022-12-16 | 闵杰 | Device for improving hose type air refueling speed |
-
2022
- 2022-04-14 CN CN202210387221.3A patent/CN114486151B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3428272A1 (en) * | 1983-07-29 | 1985-02-14 | Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5000 Köln | Device for quantitative measurement of sound pressures in gases |
| CA2344612A1 (en) * | 2000-04-17 | 2001-10-17 | Wolfgang Gleine | Aerodynamic noise reducing structure for aircraft wing slats |
| CN101898640A (en) * | 2010-03-15 | 2010-12-01 | 王雪松 | Air refueling device of helicopter |
| EP2466288A2 (en) * | 2010-12-14 | 2012-06-20 | Japan Aerospace Exploration Agency | Method of designing natural laminar flow wing for reynolds numbers equivalent to actual supersonic aircraft |
| DE102011054535B3 (en) * | 2011-10-17 | 2013-03-28 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method for oil film interferometric measurement of wall shear stress on surface, involves extracting oil adjacent to surface such that oil flows through surface, where oil is applied on rotor near rotation axis |
| KR20140024109A (en) * | 2012-08-20 | 2014-02-28 | 한국항공우주산업 주식회사 | Method to improve the buffet property of t-50 |
| CN104359643A (en) * | 2014-10-29 | 2015-02-18 | 中国航空工业集团公司哈尔滨空气动力研究所 | Pitching-rolling two-degree-of-freedom experimental platform based on electromechanical hydraulic coupling drive |
| CN105784314A (en) * | 2016-03-04 | 2016-07-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-speed wind tunnel virtual flying experimental support device |
| CN107065593A (en) * | 2016-12-28 | 2017-08-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of attitude control system of aircraft refuelling lever apparatus |
| CN109470445A (en) * | 2018-12-24 | 2019-03-15 | 浙江大学 | A kind of freely-supported type air tunnel testing device for growing thin component resistance coefficient |
| CN111721493A (en) * | 2019-07-03 | 2020-09-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Helicopter combined model wind tunnel test device with independent tail rotor device |
| CN110470453A (en) * | 2019-08-13 | 2019-11-19 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of low-speed wind tunnel air refuling hose-tapered sleeve dynamic property tester |
| CN110940483A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Pitching yawing free vibration dynamic derivative test device for large slenderness ratio aircraft |
| CN110940480A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Pitching yawing forced vibration dynamic derivative test device used under high attack angle of high-speed flying wing model |
| CN112179608A (en) * | 2020-09-28 | 2021-01-05 | 厦门大学 | Supporting device and testing system for wind tunnel dynamic test of rotary rocket model |
Non-Patent Citations (2)
| Title |
|---|
| 空中加油机加油软管锥套气动稳定性风洞试验技术;黄霞等;《空气动力学学报》;20190228;第37卷(第1期);第140-146页 * |
| 空中受油装置降噪研究;罗乖林等;《北京航空航天大学学报》;20030228;第29卷(第2期);第95-98页 * |
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