CN113071704B - Test method and system for simulating wing deformation - Google Patents
Test method and system for simulating wing deformation Download PDFInfo
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- CN113071704B CN113071704B CN202110342026.4A CN202110342026A CN113071704B CN 113071704 B CN113071704 B CN 113071704B CN 202110342026 A CN202110342026 A CN 202110342026A CN 113071704 B CN113071704 B CN 113071704B
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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
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention relates to a test method and a test system for simulating wing deformation. The test method for simulating the deformation of the wing comprises the following steps: obtaining deformation curves of the wings under different deflections according to simulation calculation; determining support mounting points of a plurality of actuating mechanisms, acquiring a plurality of corresponding pairs of support mounting points on a natural state curve and a maximum wing deformation curve when the wing is unloaded, and connecting the support mounting points of each pair to be used as the actuating direction of the actuating mechanism so as to acquire the corresponding actuating direction angle of each actuating mechanism; determining the installation directions of the stand columns of the plurality of actuating mechanisms according to the corresponding actuating direction angle of each actuating mechanism; and controlling the actuating mechanisms to perform corresponding actions so as to simulate the deformation of the wings. According to the technical scheme, the invention can achieve the following beneficial technical effects: the test for simulating the wing deformation can be developed before the complete machine manufacturing is completed, and the fidelity of the iron bird test and the capability of indicating the airworthiness conformance are improved.
Description
Technical Field
The invention relates to the technical field of aircraft test verification, in particular to a test method and a test system for simulating wing deformation.
Background
In the flying process of the airplane, under the action of aerodynamic load, the real wings can generate larger deformation in a plane perpendicular to the chord direction, and the torsion tube structures, the flap slide rails and the retractable actuator structures which are arranged at different positions on the real wings can move along with the real wings, so that wing surfaces such as flaps, slats and the like are driven to deform.
There are two types of test scenarios that need to simulate wing deformation: the other type is an airplane static test, and the real wing is driven to deform through a loading device, so that the state of the wing test is closer to the state in flight. In the prior art of airplane structure test, a mechanism for simulating wing deformation exists, but a test object is a real wing, and the system characteristics are different from the purposes and attributes of a laboratory test. The static test of the wing structure is in the final stage of the project development stage, the test cost is very high, the design problem is discovered at the moment, and the change period is long and the cost is high.
The other type is a laboratory test of the high-lift system of the airplane, and the laboratory test verifies the function and the performance of the high-lift system through the iron bird rack. The laboratory test comprises a research and development test and an airworthiness test, aims to expose the problem of the system before the whole machine is manufactured, and adopts real (consistent with an airplane) flight control electronic equipment, an actuator, a control surface, hydraulic pipeline arrangement and cable arrangement to improve the fidelity of the test configuration. However, there is a lack of systems for simulating wing deformation in existing laboratory tests.
The wing section simulation structure of the existing airplane iron bird test bed comprises a main body structure, a support frame, a front beam box-shaped part, a rear beam box-shaped part, a connecting piece, a front edge simulation beam and a rear edge simulation beam, and cannot simulate wing deformation.
Disclosure of Invention
One object of the present invention is to provide a test method and system for simulating wing deformation, which can overcome the disadvantages of the iron bird test bed, and is suitable for the deformation driving of leading edge slat and trailing edge flap, and can improve the fidelity of iron bird test and the capability of indicating airworthiness by simulating the deformation of the airfoil of high-lift system along with the wing.
The above object of the invention is achieved by a test method for simulating wing deformation, comprising:
obtaining deformation curves of the wings under different deflections according to simulation calculation, wherein the deformation curves comprise a natural state curve of the wings under no load and a maximum deformation curve of the wings;
determining support mounting points of a plurality of actuating mechanisms, acquiring a plurality of corresponding pairs of support mounting points on a natural state curve and a maximum wing deformation curve when the wing is unloaded, and connecting the support mounting points of each pair to be used as the actuating direction of the actuating mechanism so as to acquire the corresponding actuating direction angle of each actuating mechanism;
determining the installation direction of the stand column of each actuating mechanism according to the corresponding actuating direction angle of each actuating mechanism;
and controlling the actuating mechanisms to perform corresponding actions so as to simulate wing deformation.
According to the technical scheme, the test method for simulating wing deformation can achieve the following beneficial technical effects: the actuating mechanisms distributed at the front and rear beams of the wing are uniformly installed and locally coordinated and processed according to a global coordinate system, and the simulation of wing deformation in the test is realized through control coordination; the defect that the wing deformation simulation cannot be realized by the traditional iron bird is overcome, so that the test for simulating the wing deformation can be developed before the whole machine is manufactured, and the fidelity of the iron bird test and the capability of indicating the airworthiness conformity are improved.
Preferably, the actuation mechanism comprises a slat torsion tube actuation mechanism, a flap torsion tube actuation mechanism and a flap slide rail actuation mechanism.
According to the technical scheme, the test method for simulating the wing deformation can have the following beneficial technical effects: by means of the actuating mechanism at the corresponding position, wing deformation is fully simulated.
Preferably, the plurality of actuating mechanisms are controlled by a closed loop control system.
According to the technical scheme, the test method for simulating the wing deformation can have the following beneficial technical effects: the closed-loop control system has a coordinated working mechanism and an overload protection mechanism, can ensure that all the actuating points (support mounting points) can move according to an input curve, and can also ensure that all the actuating points can work safely within the stroke range and the bearing range of the whole system.
Preferably, the mounting direction of the stand column of each actuating mechanism is an oblique direction with respect to the vertical direction.
According to the technical scheme, the test method for simulating the wing deformation can have the following beneficial technical effects: effective spanwise compensation can be provided in a suitable manner to more realistically reflect the deformation and loading of the high lift system airfoil.
Preferably, the installation direction of the stand column of each actuating mechanism is a vertical direction, and the wing is reversely deflected from the initial position by the corresponding actuating directional angle according to the corresponding actuating directional angle of each actuating mechanism.
According to the technical scheme, the test method for simulating the wing deformation can have the following beneficial technical effects: effective spanwise compensation can be provided in another suitable manner, which more realistically reflects the deformation and loading of the high lift system airfoil.
Preferably, the actuating mechanisms are controlled to actuate from the initial position to the maximum deformation position and then from the maximum deformation position to the initial position.
According to the technical scheme, the test method for simulating the wing deformation can have the following beneficial technical effects: the wing deformation can be simulated in a sufficient range, and the fidelity of the iron bird test is improved.
The above object of the present invention is also achieved by a test system for simulating wing deformation, comprising:
the deformation curve acquisition module is configured to acquire deformation curves of the wings under different deflections according to simulation calculation, wherein the deformation curves include a natural state curve of the wings under no load and a maximum deformation curve of the wings;
an actuating direction acquisition module configured to determine support mounting points of a plurality of actuating mechanisms, and acquire a plurality of corresponding pairs of support mounting points on a natural state curve and a maximum wing deformation curve when the wing is unloaded, and connect each pair of support mounting points as an actuating direction of the actuating mechanism, thereby acquiring a corresponding actuating direction angle of each actuating mechanism;
a column installation determination module configured to determine an installation direction of a gantry column of each actuation mechanism based on a corresponding actuation direction angle of the each actuation mechanism;
an actuation mechanism control module configured to control the plurality of actuation mechanisms to perform respective actions to simulate wing deformation.
According to the technical scheme, the test system for simulating wing deformation can achieve the following beneficial technical effects: the actuating mechanisms distributed at the front and rear beams of the wing are uniformly installed and locally coordinated and processed according to a global coordinate system, and the simulation of wing deformation in the test is realized through control coordination; the defect that the wing deformation simulation cannot be realized by the traditional iron bird is overcome, so that the test for simulating the wing deformation can be developed before the whole machine is manufactured, and the fidelity of the iron bird test and the capability of indicating the airworthiness conformity are improved.
Preferably, the actuation mechanism comprises a slat torsion tube actuation mechanism, a flap torsion tube actuation mechanism and a flap slide rail actuation mechanism.
According to the technical scheme, the test system for simulating wing deformation can achieve the following beneficial technical effects: by means of the actuating mechanism at the corresponding position, wing deformation is fully simulated.
Preferably, the plurality of actuating mechanisms are controlled by a closed loop control system.
According to the technical scheme, the test system for simulating wing deformation can achieve the following beneficial technical effects: the closed-loop control system has a coordinated working mechanism and an overload protection mechanism, can ensure that all the actuating points (support mounting points) can move according to an input curve, and can also ensure that all the actuating points can work safely within the stroke range and the bearing range of the whole system.
Preferably, the mounting direction of the stand column of each actuating mechanism is an oblique direction relative to the vertical direction.
According to the technical scheme, the test system for simulating wing deformation can achieve the following beneficial technical effects: effective spanwise compensation can be provided in a suitable manner to more realistically reflect the deformation and loading of the high lift system airfoil.
Preferably, the installation direction of the gantry upright of each actuating mechanism is a vertical direction, and the wing is reversely deflected from the initial position by a corresponding actuating direction angle according to the corresponding actuating direction angle of each actuating mechanism.
According to the technical scheme, the test system for simulating wing deformation can achieve the following beneficial technical effects: effective spanwise compensation can be provided in another suitable manner, which more realistically reflects the deformation and loading of the high lift system airfoil.
Preferably, the actuating mechanism control module is configured to control the actuating mechanisms to actuate from an initial position to a maximum deformation position and then from the maximum deformation position to the initial position.
According to the technical scheme, the test system for simulating wing deformation can achieve the following beneficial technical effects: the wing deformation can be simulated in a sufficient range, and the fidelity of the iron bird test is improved.
Drawings
Fig. 1 is a schematic layout diagram of each actuator in a test method and system for simulating wing deformation according to an embodiment of the present invention.
FIG. 2 is a schematic diagram of the acquisition of actuation direction in the test method and system for simulating wing deformation according to an embodiment of the invention.
FIG. 3 is a flow chart of a test method for simulating wing deformation in accordance with an embodiment of the invention.
FIG. 4 is a schematic diagram of a test system for simulating wing deformation in accordance with an embodiment of the present invention.
List of reference numerals
1. Slat torsion tube actuation mechanism;
2. a flap torque tube actuation mechanism;
3. a flap track actuation mechanism;
P i a support mounting point on the natural state curve of the wing;
Q i a support mounting point on the maximum deformation curve of the wing;
α i and an operating direction angle.
Detailed Description
While specific embodiments of the invention will be described below, it should be noted that in the course of the detailed description of these embodiments, in order to provide a concise and concise description, all features of an actual implementation may not be described in detail. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions are made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be further appreciated that such a development effort might be complex and tedious, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure, and thus should not be construed as a complete understanding of this disclosure.
Unless otherwise defined, technical or scientific terms used in the claims and the specification should have the ordinary meaning as understood by those of ordinary skill in the art to which the invention belongs. The use of "first," "second," and similar terms in the description and claims of the present application do not denote any order, quantity, or importance, but rather the terms are used to distinguish one element from another. The terms "a" or "an," and the like, do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprise" or "comprises", and the like, means that the element or item listed before "comprises" or "comprising" covers the element or item listed after "comprising" or "comprises" and its equivalent, and does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, nor are they restricted to direct or indirect connections.
Fig. 1 is a schematic layout diagram of each actuator in a test method and system for simulating wing deformation according to an embodiment of the present invention. FIG. 2 is a schematic diagram of the acquisition of actuation direction in the test method and system for simulating wing deformation according to an embodiment of the invention. FIG. 3 is a flow chart of a test method for simulating wing deformation in accordance with an embodiment of the present invention. FIG. 4 is a schematic diagram of a test system for simulating wing deformation in accordance with an embodiment of the present invention.
As shown in fig. 1-3, a test method for simulating wing deformation according to an embodiment of the present invention includes:
firstly, obtaining deformation curves of wings under different deflections according to simulation calculation, wherein the deformation curves comprise a natural state curve and a maximum wing deformation curve when the wings are unloaded;
step two, determining support mounting points P of a plurality of actuating mechanisms 1 、P 2 ……P n (wherein, n is generally between 20 and 30 for a single wing), and obtaining a plurality of corresponding pairs of support mounting points P on a natural state curve and a maximum deformation curve of the wing under no load 1 、Q 1 、P 2 、Q 2 ……P n 、Q n Each pair of support mounting points P i 、Q i (i is 1, 2 … … n) as the actuating direction of the actuating mechanism, so as to obtain the corresponding actuating direction angle α of each actuating mechanism i ；
Step three, according to the corresponding actuating direction angle alpha of each actuating mechanism i Determining the installation direction of the stand column of each actuating mechanism;
and step four, controlling the plurality of actuating mechanisms to perform corresponding actuation so as to simulate wing deformation.
According to the technical scheme, the test method for simulating wing deformation can achieve the following beneficial technical effects: the actuating mechanisms distributed at the front and rear beams of the wing are uniformly installed and locally coordinated and processed according to a global coordinate system, and the simulation of wing deformation in a test is realized through control coordination; the defect that the wing deformation simulation cannot be realized by the traditional iron bird is overcome, so that the test for simulating the wing deformation can be developed before the whole machine is manufactured, and the fidelity of the iron bird test and the capability of indicating the airworthiness conformity are improved.
Preferably, as shown in fig. 1, the actuating mechanism mainly includes three types according to the installation position, namely: a slat torsion tube actuating mechanism 1, a flap torsion tube actuating mechanism 2 and a flap slide rail actuating mechanism 3. The actuating mechanisms are arranged according to the actual design position of the high-lift system of the airplane. The flaps, slat wings and transfer rods are mounted on the mounting surface (pedestal mounting point) of the actuating mechanism according to the actual mounting form in the wing.
The slat torsion tube actuating mechanisms 1 can be distributed at the joint of the slat torsion tube mounting bracket and the wing front beam and are used for actuating the slat torsion tube; the flap torsion tube actuating mechanism 2 can be distributed at the joint of the flap torsion tube mounting bracket and the wing back beam and is used for actuating the flap torsion tube; the flap slide rail actuating mechanism 3 can be used for actuating the flap slide rail and the retractable actuator structure.
Preferably, in step one, the wing deformation result obtained by the finite element analysis of the structure is used as an input for the installation and use of the wing deformation system. The deformation result comprises the deflection line under different deformation of each required stage and the deflection line corresponding to the maximum deformation.
The global coordinate system of the wing deformation actuating system is that the Y-axis numerical value is upward, the X-axis points to the tail along the course, and the original point position is the head position. The coordinate system may be used during the construction of the finite element model, or the result of the finite element analysis may be transformed to the result in the coordinate system.
The initial position of the deformation is the state when the wing is mounted on the fuselage (considering the actual mounting position such as the dihedral angle) and does not have aerodynamic force and naturally sags under the action of gravity (namely, the natural state when the wing has no load). The wing deformation result also comprises the initial coordinates and the deformed coordinates of the torsion tube and the flap slide rail on the wing under various deformation conditions.
Preferably, as shown in fig. 2, in step two, the actuating direction angle α of each actuating mechanism i The included angle between the actuating direction and the vertical direction is defined. Using an angle alpha of direction of action compared to the vertical direction as direction of action i The actuating direction of the high lift system can provide effective spanwise compensation, and can reflect the deformation and loading of the airfoil surface of the high lift system more truly.
Preferably, in step three, there are mainly two ways to determine the mounting direction of the gantry column of each actuation mechanism. In one mode, the mounting direction of the stand column of each actuating mechanism is an inclined direction relative to the vertical direction, namely the actuating direction angle alpha i . The stand column is cut off and processed according to the installation direction and then fixed on the ground. The global coordinate when the platform frame upright post is installed is consistent with the global coordinate adopted by the wing deformation analysis.
In another mode, the mounting direction of the stand column of each actuating mechanism is a vertical direction, and the angle α is determined according to the corresponding actuating direction of each actuating mechanism i And reversely deflecting the wing from the initial position by a corresponding actuating direction angle.
Preferably, in step four, the plurality of actuating mechanisms are controlled by a closed loop control system. The closed-loop control system has a coordinated working mechanism and an overload protection mechanism, can ensure that all the actuating points (support mounting points) can move according to an input curve, and can also ensure that all the actuating points can work safely within the stroke range and the bearing range of the whole system.
Preferably, in the fourth step, the plurality of actuating mechanisms are controlled to actuate from the initial position to the maximum deformation position, and then actuate from the maximum deformation position to the initial position.
Preferably, in the fourth step, according to the deformation curve required by the test, the actuation mechanisms are controlled to actuate, so that each torque tube support mounting point and each flap slide rail support mounting point move to respective interpolation points, a deformation state consistent with the input deformation curve is formed, and meanwhile, the structures of the flap cabin, the flap slide rail, the flap wing surface, the slat wing surface and the like are driven to move consistently, so that the accurate simulation of the wing deformation test environment is realized.
As shown in fig. 1-4, a test system for simulating wing deformation according to an embodiment of the present invention includes:
the deformation curve acquisition module is configured to acquire deformation curves of the wings under different deflections according to simulation calculation, wherein the deformation curves include a natural state curve when the wings are unloaded and a maximum deformation curve of the wings;
an actuation direction acquisition module configured to determine a plurality of support mounting points P of the actuation mechanism 1 、P 2 ……P n (wherein, n is generally between 20 and 30 for a single wing), and obtaining a plurality of corresponding pairs of support mounting points P on a natural state curve and a maximum deformation curve of the wing under no load 1 、Q 1 、P 2 、Q 2 ……P n 、Q n Each pair of support mounting points P i 、Q i (i is 1, 2 … … n) as the actuating direction of the actuating mechanism, thereby obtaining the corresponding actuating direction angle α of each actuating mechanism i ；
A column installation determination module configured to determine a corresponding actuation direction angle alpha for each actuation mechanism i Determining the installation direction of the stand column of each actuating mechanism;
and the actuating mechanism control module is configured to control the actuating mechanisms to perform corresponding actuation so as to simulate the deformation of the wing.
According to the technical scheme, the test system for simulating wing deformation can achieve the following beneficial technical effects: the actuating mechanisms distributed at the front and rear beams of the wing are uniformly installed and locally coordinated and processed according to a global coordinate system, and the simulation of wing deformation in the test is realized through control coordination; the defect that the wing deformation simulation cannot be realized by the traditional iron bird is overcome, so that the test for simulating the wing deformation can be developed before the whole machine is manufactured, and the fidelity of the iron bird test and the capability of indicating the airworthiness conformity are improved.
While particular embodiments of the present invention have been described above, it will be understood by those skilled in the art that they are not intended to limit the invention, and that various modifications may be made by those skilled in the art based on the above disclosure without departing from the scope of the invention.
Claims (10)
1. A test method for simulating wing deformation, comprising:
obtaining deformation curves of the wings under different deflections according to simulation calculation, wherein the deformation curves comprise a natural state curve and a maximum deformation curve of the wings when the wings are unloaded;
determining support mounting points of a plurality of actuating mechanisms, acquiring a plurality of corresponding pairs of support mounting points on a natural state curve and a maximum wing deformation curve when the wing is unloaded, and connecting lines of each pair of support mounting points to be used as actuating directions of the actuating mechanisms so as to acquire corresponding actuating direction angles of each actuating mechanism, wherein the actuating direction angle of each actuating mechanism is an included angle between the actuating direction and the vertical direction;
determining the installation direction of the stand column of each actuating mechanism according to the corresponding actuating direction angle of each actuating mechanism;
and controlling the actuating mechanisms to perform corresponding actions so as to simulate the deformation of the wing.
2. The method of claim 1, wherein the actuation mechanism comprises a slat torsion tube actuation mechanism, a flap torsion tube actuation mechanism, and a flap slide rail actuation mechanism.
3. A test method for simulating wing deformation according to claim 1, wherein the plurality of actuators are controlled by a closed loop control system.
4. A test method for simulating wing deformation according to claim 1, wherein the mounting direction of the gantry column of each of the actuating mechanisms is an oblique direction relative to the vertical direction.
5. A test method for simulating wing deformation according to claim 1, wherein the plurality of actuators are controlled to move from an initial position to a maximum deformation position and then from the maximum deformation position to the initial position.
6. A test system for simulating wing deformation, comprising:
the deformation curve acquisition module is configured to acquire deformation curves of the wings under different deflections according to simulation calculation, wherein the deformation curves include a natural state curve of the wings under no load and a maximum deformation curve of the wings;
an actuating direction acquisition module, configured to determine support mounting points of a plurality of actuating mechanisms, and acquire a plurality of corresponding pairs of support mounting points on a natural state curve and a maximum wing deformation curve when the wing is unloaded, and connect each pair of support mounting points as an actuating direction of the actuating mechanism, thereby acquiring a corresponding actuating direction angle of each actuating mechanism, wherein the actuating direction angle of each actuating mechanism is an included angle between the actuating direction and a vertical direction;
a column mount determination module configured to determine a mounting direction of a gantry column of each of the actuating mechanisms based on a corresponding actuating direction angle of each of the actuating mechanisms;
an actuation mechanism control module configured to control the plurality of actuation mechanisms to perform respective actions to simulate wing deformation.
7. A test system for simulating wing deformation according to claim 6, wherein the actuation mechanisms include a slat torsion tube actuation mechanism, a flap torsion tube actuation mechanism, and a flap slide rail actuation mechanism.
8. A test system for simulating wing deformation according to claim 6 wherein the plurality of actuators are controlled by a closed loop control system.
9. A test system for simulating wing deformation according to claim 6 wherein the mounting orientation of the gantry column of each of the actuating mechanisms is inclined relative to vertical.
10. A test system for simulating wing deformation according to claim 6, wherein the actuator control module is configured to control the plurality of actuators to move from an initial position to a maximum deformation position and then from the maximum deformation position to the initial position.
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Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202599650U (en) * | 2012-05-11 | 2012-12-12 | 中国航空工业集团公司西安飞机设计研究所 | Testing device used for imitating slat motion characteristics under wing deformation working conditions |
| CN103303493A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Wing load applying device for large aircraft strength test |
| CN103558019A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Three-slideway wing flap test method for simulating deformation of wings |
| CN103723285A (en) * | 2013-12-04 | 2014-04-16 | 中国飞机强度研究所 | Empennage load applying device used for plane structure strength tests |
| CN103963993A (en) * | 2013-01-29 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Wing section simulation structure of aircraft iron bird test platform |
| CN104931250A (en) * | 2015-06-29 | 2015-09-23 | 中国航空工业集团公司西安飞机设计研究所 | High-lift system whole-aircraft loading dynamic test method |
| US9227721B1 (en) * | 2011-10-07 | 2016-01-05 | The United States of America as represented by the Administrator of the National Aeronautics & Space Administration (NASA) | Variable camber continuous aerodynamic control surfaces and methods for active wing shaping control |
| CN105758629A (en) * | 2014-12-19 | 2016-07-13 | 成都飞机设计研究所 | Servo loading method in aircraft strength test |
| CN207631527U (en) * | 2017-12-04 | 2018-07-20 | 西安庆安航空试验设备有限责任公司 | Load motion during the experiment of wing flap acting device |
| CN108363840A (en) * | 2018-01-23 | 2018-08-03 | 中国人民解放军战略支援部队航天工程大学 | A kind of cluster magnetic moment of spacecraft optimum allocation method based on electromagnetic force |
| CN109163961A (en) * | 2018-08-22 | 2019-01-08 | 中国飞机强度研究所 | A kind of loading device of big deformation wing |
| CN109502052A (en) * | 2018-12-12 | 2019-03-22 | 西北工业大学 | One kind is test bed for Variable Geometry Wing deformation parameter |
| CN109573100A (en) * | 2018-12-24 | 2019-04-05 | 中国航空工业集团公司西安飞机设计研究所 | Iron bird testing stand |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7712703B2 (en) * | 2006-01-18 | 2010-05-11 | Pentastar Aviation, Inc. | Flap simulators |
-
2021
- 2021-03-30 CN CN202110342026.4A patent/CN113071704B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9227721B1 (en) * | 2011-10-07 | 2016-01-05 | The United States of America as represented by the Administrator of the National Aeronautics & Space Administration (NASA) | Variable camber continuous aerodynamic control surfaces and methods for active wing shaping control |
| CN202599650U (en) * | 2012-05-11 | 2012-12-12 | 中国航空工业集团公司西安飞机设计研究所 | Testing device used for imitating slat motion characteristics under wing deformation working conditions |
| CN103303493A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Wing load applying device for large aircraft strength test |
| CN103963993A (en) * | 2013-01-29 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Wing section simulation structure of aircraft iron bird test platform |
| CN103558019A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Three-slideway wing flap test method for simulating deformation of wings |
| CN103723285A (en) * | 2013-12-04 | 2014-04-16 | 中国飞机强度研究所 | Empennage load applying device used for plane structure strength tests |
| CN105758629A (en) * | 2014-12-19 | 2016-07-13 | 成都飞机设计研究所 | Servo loading method in aircraft strength test |
| CN104931250A (en) * | 2015-06-29 | 2015-09-23 | 中国航空工业集团公司西安飞机设计研究所 | High-lift system whole-aircraft loading dynamic test method |
| CN207631527U (en) * | 2017-12-04 | 2018-07-20 | 西安庆安航空试验设备有限责任公司 | Load motion during the experiment of wing flap acting device |
| CN108363840A (en) * | 2018-01-23 | 2018-08-03 | 中国人民解放军战略支援部队航天工程大学 | A kind of cluster magnetic moment of spacecraft optimum allocation method based on electromagnetic force |
| CN109163961A (en) * | 2018-08-22 | 2019-01-08 | 中国飞机强度研究所 | A kind of loading device of big deformation wing |
| CN109502052A (en) * | 2018-12-12 | 2019-03-22 | 西北工业大学 | One kind is test bed for Variable Geometry Wing deformation parameter |
| CN109573100A (en) * | 2018-12-24 | 2019-04-05 | 中国航空工业集团公司西安飞机设计研究所 | Iron bird testing stand |
Non-Patent Citations (2)
| Title |
|---|
| 基于飞机铁鸟台架的模拟机翼气动变形;陆伟铭;《航空精密制造技术》;20180815;37-39页 * |
| 机翼模拟变形加载的控制方法;孙宇飞;《第六届中国航空学会青年科技论坛》;20140624;416-419页 * |
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