CN109238634A - Hypersonic aircraft model in wind tunnel rudder-face device - Google Patents
Hypersonic aircraft model in wind tunnel rudder-face device Download PDFInfo
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- CN109238634A CN109238634A CN201811059333.6A CN201811059333A CN109238634A CN 109238634 A CN109238634 A CN 109238634A CN 201811059333 A CN201811059333 A CN 201811059333A CN 109238634 A CN109238634 A CN 109238634A
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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
- G01M9/08—Aerodynamic models
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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
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention relates to aircraft wind-tunnel technique fields, disclose a kind of hypersonic aircraft model in wind tunnel rudder-face device.Wherein, the rudder-face device is arranged on test model body, the rudder-face device includes rudder face, pedestal, rudder face installs plug, connector for being installed with body, connecting hole for being installed with body, with rudder face mounting groove, the rudder face is set in the side of the rudder face, plug is installed, the connecting hole and the rudder face mounting groove for installing with body is set on the pedestal, the rudder face installation plug matches with the rudder face mounting groove, the pedestal is arranged by the connector for installing with body and the connecting hole for installing with body in the test model body.Thus, it is possible to effectively overcome the defect that existing rudder face adjustment design factors finger setting precision is low, the different rudder faces of processing introduce rudder face mismachining tolerance.
Description
Technical field
The present invention relates to aircraft wind-tunnel technique field more particularly to a kind of hypersonic aircraft wind tunnel test moulds
Type rudder-face device.
Background technique
Air-breathing hypersonic vehicle aerodynamic configuration complexity and interior outflow very high integrity, make its aeroperformance predict ratio
Conventional aircraft is more difficult, and the uncertainty of aerodynamic data is bigger.On the one hand, Air-breathing hypersonic vehicle is due to hair
It is smaller that motivation pushes away resistance nargin, therefore Accurate Prediction aircraft is particularly important along the resistance performance of trajectory；On the other hand, from flight bullet
The angle that road accurately controls is set out, it is also desirable to the yawing characteristic of Accurate Prediction hypersonic aircraft, rolling moment characteristic,
Pitching moment performance and air steering quality.
Flight vehicle aerodynamic performance prediction research mainly has three big means, i.e. wind tunnel test, numerical value calculating and flight test.?
Numerical value calculates aspect, also has at present without flight test for the numerical computation method of Air-breathing hypersonic vehicle development
Effect card.It is the test that aircraft carries out under the conditions of true flight environment of vehicle, but due to testing expenses in terms of flight test
Valuableness is difficult to largely carry out, and is mainly used for the demonstration and verification stage.Wind tunnel test is discovery and confirmation flow phenomenon, exploration and announcement
Flowing law is sought and understood to flow mechanism, and excellent aerodynamic arrangement and air dynamic behaviour number are provided for Flight Vehicle Design
According to main means；Hypersonic aircraft aerodynamic force wind tunnel test is to explore hypersonic pneumatic phenomenon, solves aircraft and exists
All kinds of Aerodynamic Problems faced during hypersonic flight obtain Aerodynamic Characteristics, are aerodynamic configuration of aircraft
Design provides the important means in aerodynamic data library reliable, for flight test, compared with flight test, hypersonic wind
Low, easy to implement, the available mass data of hole experimentation cost, is to obtain hypersonic aircraft aeroperformance data and airvane
The important and necessary means of steerage data.
Test model is the object of aerodynamic force wind tunnel test, the degree of regulation of mould processing precision and adjusting part parameter
It will affect the precision of prediction of aerodynamic performance data, the precision that wherein rudder face angle of rudder reflection is adjusted is directly related to every pneumatic
The precision of force parameter and steerage parameter.However, rudder face generally uses in test in the prior art in order to reduce rudder face processing quantity
The structure type of angle pin class, the installation error of the operator that is put to the test, qualification influence, and the form installation error compared with
Greatly, aerodynamic test precision is influenced.
Summary of the invention
It is an object of the invention to overcome the shortage of prior art, a kind of hypersonic aircraft model in wind tunnel is provided
Rudder-face device is able to solve above-mentioned the problems of the prior art.
A kind of technical solution of the invention: hypersonic aircraft model in wind tunnel rudder-face device, wherein described
Rudder-face device is arranged on test model body, and the rudder-face device includes rudder face, pedestal, rudder face installation plug, is used for and bullet
Connector, the connecting hole for being installed with body and the rudder face mounting groove of body installation, wherein
The rudder face is set in the side of the rudder face, plug is installed, is arranged on the pedestal described for pacifying with body
The connecting hole of dress and the rudder face mounting groove, the rudder face installation plug match with the rudder face mounting groove, and the pedestal is logical
It crosses the connector for installing with body and the connecting hole for installing with body is arranged in the test model bullet
On body.
Preferably, which further includes compressing connector and rudder face compression connecting hole, and the rudder face compresses connecting hole
On rudder face installation plug, the rudder face installation plug is inserted into the rudder face mounting groove and is tightly connected by described for setting
Part compresses connecting hole with the rudder face and is fixedly connected.
Preferably, the compression connector is the case where being fixedly connected with the rudder face installation plug and the rudder face mounting groove
It is located in the compression platform down, and the non-bulging rudder face mounting groove.
Preferably, the clamping joint is housing screw, and it is rudder face housing screw hole that the rudder face, which compresses connecting hole,.
Preferably, which further includes compressing platform, and the compression platform is arranged on the rudder face mounting groove.
Preferably, the pedestal, rudder face installation plug and the rudder face mounting groove are rectangular parallelepiped form.
Preferably, the range of the angle of the rudder face mounting groove with respect to the horizontal plane is 0 ° to n °, and wherein n is maximum test
Angle of rudder reflection.
Preferably, the connector for install with body is the screw for installing with body, and is used for and body
The connecting hole of installation is the screw hole for installing with body.
Preferably, the compression platform is circle.
Through the above technical solutions, a kind of hypersonic aircraft model in wind tunnel rudder-face device can be provided, by it
Applied to such as Air-breathing hypersonic vehicle model in wind tunnel, existing rudder face adjustment design factors pin can be effectively overcome
Positioning accuracy is low, the defect of the different rudder face introducing rudder face mismachining tolerances of processing.Also, utilize wind tunnel test mould proposed by the present invention
Type rudder-face device can effectively improve rudder effectiveness test data precision, and test data meets design requirement through flight test verifying,
Desired effect is reached.
Detailed description of the invention
Included attached drawing is used to provide to be further understood from the embodiment of the present invention, and which constitute one of specification
Point, for illustrating the embodiment of the present invention, and come together to illustrate the principle of the present invention with verbal description.It should be evident that below
Attached drawing in description is only some embodiments of the present invention, for those of ordinary skill in the art, is not paying creation
Property labour under the premise of, be also possible to obtain other drawings based on these drawings.
Fig. 1 is a kind of schematic diagram of hypersonic aircraft model in wind tunnel provided in an embodiment of the present invention；
Fig. 2 is a kind of signal of hypersonic aircraft model in wind tunnel rudder-face device provided in an embodiment of the present invention
Figure；
Fig. 3 is that a kind of rudder face of hypersonic aircraft model in wind tunnel rudder-face device provided in an embodiment of the present invention shows
It is intended to；
Fig. 4 is that a kind of pedestal of hypersonic aircraft model in wind tunnel rudder-face device provided in an embodiment of the present invention shows
It is intended to；
Fig. 5 is the sectional view of the pedestal in the embodiment of the present invention with 0 degree of angle of rudder reflection slot；
Fig. 6 is the schematic diagram of the pedestal in the embodiment of the present invention with n degree angle of rudder reflection slot；
Fig. 7 A-7C is the different train number Air-breathing hypersonic vehicles resistance under existing angle pin rudder-face device respectively
Power, lift, pitching moment correlation curve；
Fig. 8 A-8C be respectively different train number Air-breathing hypersonic vehicle resistances under rudder-face device of the present invention, lift,
Pitching moment correlation curve.
Description of symbols
1 test model body；2 rudder-face devices；3 rudder faces；
4 pedestals；5 compress connector；6 rudder faces compress connecting hole；
7 rudder faces install plug；8 connecting hole for being installed with body；
9 rudder face mounting grooves；10 compress platform.
Specific embodiment
Specific embodiments of the present invention are described in detail below in conjunction with attached drawing.In the following description, for solution
Purpose and not restrictive is released, elaborates detail, to help to be apparent from the present invention.However, to those skilled in the art
It is readily apparent that the present invention can also be practiced in the other embodiments departing from these details for member.
It should be noted that only showing in the accompanying drawings in order to avoid having obscured the present invention because of unnecessary details
Gone out with closely related device structure and/or processing step according to the solution of the present invention, and be omitted with relationship of the present invention not
Big other details.
Fig. 1 is a kind of schematic diagram of hypersonic aircraft model in wind tunnel provided in an embodiment of the present invention.
Fig. 2 is a kind of signal of hypersonic aircraft model in wind tunnel rudder-face device provided in an embodiment of the present invention
Figure.
Fig. 3 is that a kind of rudder face of hypersonic aircraft model in wind tunnel rudder-face device provided in an embodiment of the present invention shows
It is intended to.
Fig. 4 is that a kind of pedestal of hypersonic aircraft model in wind tunnel rudder-face device provided in an embodiment of the present invention shows
It is intended to.
As shown in Figs 1-4, the embodiment of the invention provides a kind of hypersonic aircraft model in wind tunnel rudder-face device,
Wherein, the rudder-face device 2 is arranged on test model body 1, and the rudder-face device 2 includes rudder face 3, pedestal 4, rudder face installation
Plug 7, the connector for being installed with body, connecting hole 8 and rudder face mounting groove 9 for being installed with body, wherein
The rudder face is set in the side of the rudder face 3, plug 7 is installed, described be used for and bullet is set on the pedestal 4
The connecting hole 8 and the rudder face mounting groove 9 of body installation, the rudder face installation plug 7 match with the rudder face mounting groove 9, institute
Pedestal 4 is stated to set by the connector (not shown) for installing with body and the connecting hole 8 for installing with body
It sets on the test model body 1 (it is, by connector for being installed with body and described being used for and body is installed
Connecting hole 8 cooperation pedestal 4 can be mounted on the test model body 1 by face contact mode, and then realize described in
Rudder-face device 2 is arranged on test model body 1).
Wherein, by the way that the rudder face of the rudder face 3 to be installed to 9 Matching installation of rudder face mounting groove of plug 7 and the pedestal 4,
The connection of rudder face 3 and pedestal 4 may be implemented, to obtain base type rudder face (device).
Through the above technical solutions, a kind of hypersonic aircraft model in wind tunnel rudder-face device can be provided, by it
Applied to such as Air-breathing hypersonic vehicle model in wind tunnel, existing rudder face adjustment design factors pin can be effectively overcome
Positioning accuracy is low, the defect of the different rudder face introducing rudder face mismachining tolerances of processing.Also, utilize wind tunnel test mould proposed by the present invention
Type rudder-face device can effectively improve rudder effectiveness test data precision, and test data meets design requirement through flight test verifying,
Desired effect is reached.
According to an embodiment of the present invention, which can also include compressing connector 5 and rudder face compression connecting hole
6, the rudder face compresses the setting of connecting hole 6 on rudder face installation plug 7, and the rudder face installation plug 7 is inserted into the rudder face
In mounting groove 9 and connecting hole 6 is compressed with the rudder face by the clamping joint 5 to be fixedly connected.
As a result, after rudder face installation plug 7 is inserted into the rudder face mounting groove 9 by inserting mode, it can pass through
It compresses connector 5 and rudder face compresses the cooperation realization rudder face installation plug 7 of connecting hole 6 and consolidating for the rudder face mounting groove 9
Fixed connection, and then realize being fixedly connected for rudder face 3 and pedestal 4.
For example, the rudder face compresses connecting hole (that is, counter sink) 6 and can install on plug 7 in the rudder face along rudder
The setting of face direction, quantity for example can be two.
According to an embodiment of the present invention, the compression connector 5 is being fixedly connected with rudder face installation plug 7 and described
It is located in the compression platform 10 in the case where rudder face mounting groove 9, and the non-bulging rudder face mounting groove 9.
As a result, by ensuring to compress connector non-bulging rudder face mounting groove in the case where being used cooperatively with rudder face connecting hole
Surface can make rudder face mounting groove surface flattening.
According to an embodiment of the present invention, the clamping joint 5 can be housing screw, and the rudder face compresses connecting hole
6 can be rudder face housing screw hole.
It is, can be used cooperatively by housing screw and rudder face housing screw hole, the rudder face installation plug is realized
With being fixedly connected for the rudder face mounting groove.
According to an embodiment of the present invention, which can also include compressing platform 10, and the compression platform 10 is set
It sets on the rudder face mounting groove 9.
Platform is compressed by setting, the fastening effect for compressing connector (for example, housing screw) can be made more preferable.
According to an embodiment of the present invention, the pedestal 4, rudder face installation plug 7 and the rudder face mounting groove 9 can be with
It is rectangular parallelepiped form.
It will be appreciated by those skilled in the art that the description of above-mentioned shape is only exemplary, it is not intended to limit this hair
It is bright.
According to an embodiment of the present invention, the angle of the rudder face mounting groove (slot) 9 with respect to the horizontal plane (can also claim
For slot angle, i.e., required angle of rudder reflection angle) may range from 0 ° to n °, wherein n is maximum test angle of rudder reflection.
Fig. 5 is the sectional view of the pedestal in the embodiment of the present invention with 0 degree of angle of rudder reflection slot；Fig. 6 is the embodiment of the present invention
In with n degree angle of rudder reflection slot pedestal schematic diagram.
As shown in figure 5, the angle of the rudder face mounting groove 9 with respect to the horizontal plane may range from 0 °.Alternatively, such as
Shown in Fig. 6, the angle of the rudder face mounting groove 9 with respect to the horizontal plane may range from n °.
As a result, by the way that the slot of pedestal is designed as different angle, available multiple pedestals with different angle, from
And it can satisfy in test and the rudder effectiveness of multiple angle of rudder reflection arranged to test.
According to an embodiment of the present invention, the connector for installing with body can be for installing with body
Screw, and the connecting hole 8 for being used to install with body can be the screw hole for installing with body.
It is, can be by base type rudder by the screw for being installed with body and the screw hole for being installed with body
Face is fixed on test model body, so as to for carrying out wind tunnel test.
For example, the quantity of the connecting hole 8 for installing with body can be 6, be separately positioned on 4 two sides of pedestal
(for example, two long sides of the pedestal 4 of rectangular parallelepiped form are respectively arranged 3) realizes installation of the pedestal on body model.
According to an embodiment of the present invention, the compression platform 10 can be circle.
It will be appreciated by those skilled in the art that the description of above-mentioned compression planform shape is only exemplary, it is not intended to
Limit the present invention.
Fig. 7 A-7C is the different train number Air-breathing hypersonic vehicles resistance under existing angle pin rudder-face device respectively
Power, lift, pitching moment correlation curve.Wherein, Fig. 7 A is the different train number air suction types under existing angle pin rudder-face device
Hypersonic aircraft resistance versus curve, Fig. 7 B are that the different train number air suction types under existing angle pin rudder-face device are superb
Velocity of sound aircraft lift correlation curve, Fig. 7 C are that the different train number air suction types under existing angle pin rudder-face device are hypersonic
Aircraft pitching moment correlation curve.Abscissa α indicates the angle of attack in figure.
From Fig. 7 A-7C as can be seen that for existing angle pin positioning structure, its positioning accuracy is analyzed and its to pneumatic
Force data influences, and carries out rudder face by different model installation personnels in experiment and repeatedly installs, measure rudder face installation accuracy, finds rudder
Face maximum installation deviation is up to 0.9 degree, and from the point of view of the Aerodynamic Analysis result of test of many times, full elastic resistance, lift test are repeated
Property error reached 4.3%, 7.7%, the equivalent elevator angle of rudder reflection of pitching moment maximum deviation is 1.16 degree.
Fig. 8 A-8C be respectively different train number Air-breathing hypersonic vehicle resistances under rudder-face device of the present invention, lift,
Pitching moment correlation curve.Wherein, Fig. 8 A is the different train number Air-breathing hypersonic vehicles resistance under rudder-face device of the present invention
Power correlation curve, Fig. 8 B are the different train number Air-breathing hypersonic vehicle lift correlation curves under rudder-face device of the present invention,
Fig. 8 C is the different train number Air-breathing hypersonic vehicle pitching moment correlation curves under rudder-face device of the present invention.Horizontal seat in figure
Marking α indicates the angle of attack.
As can be seen that using base type rudder face mounting device proposed by the present invention from Fig. 8 A-8C, rudder face installation accuracy has
Effect improves, installation deviation very little, and from the point of view of the Aerodynamic Analysis result of test of many times, full elastic resistance, lift test repeatability are missed
Subtractive as low as 2.4%, 1.1%, the equivalent elevator angle of rudder reflection of pitching moment maximum deviation are 0.28 degree.It can be seen that using this
After the base type rudder-face device of invention, hypersonic aerodynamic test has reached preferable measurement accuracy, has reached desired effect.
As above it describes for a kind of embodiment and/or the feature that shows can be in a manner of same or similar at one or more
It is used in a number of other embodiments, and/or combines or substitute the feature in other embodiments with the feature in other embodiments
It uses.
It should be emphasized that term "comprises/comprising" refers to the presence of feature, one integral piece, step or component when using herein, but simultaneously
It is not excluded for the presence or additional of one or more other features, one integral piece, step, component or combinations thereof.
The many features and advantage of these embodiments are clear according to the detailed description, therefore appended claims are intended to
Cover all these feature and advantage of these embodiments fallen into its true spirit and range.Further, since this field
Technical staff is readily apparent that many modifications and changes, therefore is not meant to for the embodiment of the present invention to be limited to illustrated and description essence
Really structurally and operationally, but all suitable modifications and the equivalent fallen within the scope of its can be covered.
Unspecified part of the present invention is known to the skilled person technology.
Claims (9)
1. a kind of hypersonic aircraft model in wind tunnel rudder-face device, which is characterized in that rudder-face device (2) setting exists
On test model body (1), the rudder-face device (2) includes rudder face (3), pedestal (4), rudder face installation plug (7), is used for and bullet
Connector, the connecting hole (8) and rudder face mounting groove (9) for being installed with body of body installation, wherein
In the side of the rudder face (3), rudder face installation plug (7) is set, be arranged on the pedestal (4) it is described for
The connecting hole (8) and the rudder face mounting groove (9) of body installation, rudder face installation plug (7) and the rudder face mounting groove (9)
Match, the pedestal (4) passes through the connector and the connecting hole for installing with body for installing with body
(8) it is arranged on the test model body (1).
2. rudder-face device according to claim 1, which is characterized in that the rudder-face device further include compress connector (5) and
Rudder face compresses connecting hole (6), and the rudder face compresses connecting hole (6) setting in rudder face installation plug (7), the rudder face peace
Plug (7) is inserted into the rudder face mounting groove (9) and compresses connecting hole (6) by the clamping joint (5) and the rudder face
It is fixedly connected.
3. rudder-face device according to claim 2, which is characterized in that the compression connector (5) be fixedly connected it is described
Rudder face is located in the compression platform (10) in the case where installing plug (7) and the rudder face mounting groove (9), and non-bulging described
Rudder face mounting groove (9).
4. rudder-face device according to claim 3, which is characterized in that the clamping joint (5) is housing screw, and described
It is rudder face housing screw hole that rudder face, which compresses connecting hole (6),.
5. rudder-face device according to claim 4, which is characterized in that the rudder-face device further includes compressing platform (10), institute
It states and compresses platform (10) setting on the rudder face mounting groove (9).
6. rudder-face device according to any one of claims 1-5, which is characterized in that the pedestal (4), rudder face peace
Plug (7) and the rudder face mounting groove (9) are rectangular parallelepiped form.
7. rudder-face device according to claim 6, which is characterized in that the rudder face mounting groove (9) is with respect to the horizontal plane
The range of angle is 0 ° to n °, and wherein n is maximum test angle of rudder reflection.
8. rudder-face device according to any one of claims 1-5, which is characterized in that the company for being installed with body
Fitting is the screw for installing with body, and being used for is the screw for installing with body with the connecting hole (8) that body is installed
Hole.
9. the rudder-face device according to any one of claim 2-5, which is characterized in that the compression platform (10) is circle
Shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811059333.6A CN109238634B (en) | 2018-09-12 | 2018-09-12 | Hypersonic aircraft wind tunnel test model control surface device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811059333.6A CN109238634B (en) | 2018-09-12 | 2018-09-12 | Hypersonic aircraft wind tunnel test model control surface device |
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| CN109238634A true CN109238634A (en) | 2019-01-18 |
| CN109238634B CN109238634B (en) | 2021-06-08 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110207931A (en) * | 2019-06-25 | 2019-09-06 | 中国航天空气动力技术研究院 | A kind of model in wind tunnel steering engine impact-proof loading device and application method |
| CN111780941A (en) * | 2020-07-23 | 2020-10-16 | 北京空天技术研究所 | Aircraft force measurement test model and method |
| CN112693626A (en) * | 2021-03-23 | 2021-04-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Control surface angle sheet applied to wind tunnel test model and installation method |
Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU421933A1 (en) * | 1972-01-07 | 1974-03-30 | ||
| CN1748089A (en) * | 2003-02-13 | 2006-03-15 | 弗里德里希·克纳普 | Fitting with an arresting device |
| CN201126400Y (en) * | 2007-12-17 | 2008-10-01 | 中国航天空气动力技术研究院 | Novel aviation aerospace vehicle tunnel test model aerial rudder derivation angle fixture mechanism |
| US20090108586A1 (en) * | 2007-10-25 | 2009-04-30 | Nelson Koury | Wind Plant |
| US20090166475A1 (en) * | 2007-12-27 | 2009-07-02 | Airbus Deutschland Gmbh | Apparatus for the pivotal fastening of an active surface, in particular a spoiler on a wind tunnel model of an aircraft |
| FR2937730A1 (en) * | 2008-10-27 | 2010-04-30 | Airbus France | Movable element's e.g. aileron, rotation angle adjusting device for use during testing of aircraft model in wind tunnel, has actuator acting on element's axis moved with respect to fixed axis, and remote control unit arranged on gear motor |
| CN202033945U (en) * | 2011-05-04 | 2011-11-09 | 中国航空工业集团公司西安飞机设计研究所 | Wind tunnel experiment model |
| CN102873383A (en) * | 2012-09-26 | 2013-01-16 | 湖北三江航天江北机械工程有限公司 | Processing method of nonmetal special-shaped rudder sheet and clamp for processing |
| CN103207057A (en) * | 2013-03-19 | 2013-07-17 | 大连理工大学 | Piezoelectric type measuring device of control surface hinge moment |
| CN103322066A (en) * | 2013-05-30 | 2013-09-25 | 江西洪都航空工业集团有限责任公司 | Control surface bearing structure |
| CN103954427A (en) * | 2014-04-28 | 2014-07-30 | 中国航天空气动力技术研究院 | Control plane model two-degree-of-freedom supporting mechanism |
| CN104712459A (en) * | 2013-12-12 | 2015-06-17 | 上海机电工程研究所 | Solid rocket power control device and control method |
| CN205908192U (en) * | 2016-07-26 | 2017-01-25 | 亿丰综合工业股份有限公司 | Connection structure and be used for building open -ended shielding device |
| CN106768831A (en) * | 2016-11-30 | 2017-05-31 | 江西洪都航空工业集团有限责任公司 | A kind of dummy vehicle rudder face connection combination apparatus |
| CN206968964U (en) * | 2017-06-02 | 2018-02-06 | 广州长天航空科技有限公司 | A kind of unmanned airplane empennage rudder face directly drives control device |
| CN108007280A (en) * | 2017-12-28 | 2018-05-08 | 北京威标至远科技发展有限公司 | A kind of steering engine thermal protection struc ture |
| CN207333392U (en) * | 2017-10-27 | 2018-05-08 | 王建良 | Assemble plank connection structure and its connector |
-
2018
- 2018-09-12 CN CN201811059333.6A patent/CN109238634B/en active Active
Patent Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU421933A1 (en) * | 1972-01-07 | 1974-03-30 | ||
| CN1748089A (en) * | 2003-02-13 | 2006-03-15 | 弗里德里希·克纳普 | Fitting with an arresting device |
| US20090108586A1 (en) * | 2007-10-25 | 2009-04-30 | Nelson Koury | Wind Plant |
| CN201126400Y (en) * | 2007-12-17 | 2008-10-01 | 中国航天空气动力技术研究院 | Novel aviation aerospace vehicle tunnel test model aerial rudder derivation angle fixture mechanism |
| US20090166475A1 (en) * | 2007-12-27 | 2009-07-02 | Airbus Deutschland Gmbh | Apparatus for the pivotal fastening of an active surface, in particular a spoiler on a wind tunnel model of an aircraft |
| FR2937730A1 (en) * | 2008-10-27 | 2010-04-30 | Airbus France | Movable element's e.g. aileron, rotation angle adjusting device for use during testing of aircraft model in wind tunnel, has actuator acting on element's axis moved with respect to fixed axis, and remote control unit arranged on gear motor |
| CN202033945U (en) * | 2011-05-04 | 2011-11-09 | 中国航空工业集团公司西安飞机设计研究所 | Wind tunnel experiment model |
| CN102873383A (en) * | 2012-09-26 | 2013-01-16 | 湖北三江航天江北机械工程有限公司 | Processing method of nonmetal special-shaped rudder sheet and clamp for processing |
| CN103207057A (en) * | 2013-03-19 | 2013-07-17 | 大连理工大学 | Piezoelectric type measuring device of control surface hinge moment |
| CN103322066A (en) * | 2013-05-30 | 2013-09-25 | 江西洪都航空工业集团有限责任公司 | Control surface bearing structure |
| CN104712459A (en) * | 2013-12-12 | 2015-06-17 | 上海机电工程研究所 | Solid rocket power control device and control method |
| CN103954427A (en) * | 2014-04-28 | 2014-07-30 | 中国航天空气动力技术研究院 | Control plane model two-degree-of-freedom supporting mechanism |
| CN205908192U (en) * | 2016-07-26 | 2017-01-25 | 亿丰综合工业股份有限公司 | Connection structure and be used for building open -ended shielding device |
| CN106768831A (en) * | 2016-11-30 | 2017-05-31 | 江西洪都航空工业集团有限责任公司 | A kind of dummy vehicle rudder face connection combination apparatus |
| CN206968964U (en) * | 2017-06-02 | 2018-02-06 | 广州长天航空科技有限公司 | A kind of unmanned airplane empennage rudder face directly drives control device |
| CN207333392U (en) * | 2017-10-27 | 2018-05-08 | 王建良 | Assemble plank connection structure and its connector |
| CN108007280A (en) * | 2017-12-28 | 2018-05-08 | 北京威标至远科技发展有限公司 | A kind of steering engine thermal protection struc ture |
Non-Patent Citations (3)
| Title |
|---|
| 上海钱豹机电设备有限公司: ""端面连接板"", 《第1枪》 * |
| 张来平，马戎 等: ""虚拟飞行中气动、运动和控制耦合的数值模拟技术"", 《力学进展》 * |
| 杨炳渊: ""舵模型风洞颤振试验中亚临界技术的应用研究"", 《上海航天》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110207931A (en) * | 2019-06-25 | 2019-09-06 | 中国航天空气动力技术研究院 | A kind of model in wind tunnel steering engine impact-proof loading device and application method |
| CN110207931B (en) * | 2019-06-25 | 2020-11-20 | 中国航天空气动力技术研究院 | Steering engine anti-impact load device for wind tunnel test model and use method |
| CN111780941A (en) * | 2020-07-23 | 2020-10-16 | 北京空天技术研究所 | Aircraft force measurement test model and method |
| CN111780941B (en) * | 2020-07-23 | 2022-07-15 | 北京空天技术研究所 | Aircraft force measurement test model and method |
| CN112693626A (en) * | 2021-03-23 | 2021-04-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Control surface angle sheet applied to wind tunnel test model and installation method |
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