CN108267285A - A kind of folded in three wing kinetic characteristics experimental provision using steering engine - Google Patents
A kind of folded in three wing kinetic characteristics experimental provision using steering engine Download PDFInfo
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- CN108267285A CN108267285A CN201810363819.2A CN201810363819A CN108267285A CN 108267285 A CN108267285 A CN 108267285A CN 201810363819 A CN201810363819 A CN 201810363819A CN 108267285 A CN108267285 A CN 108267285A
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- steering engine
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 21
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 21
- 239000004411 aluminium Substances 0.000 claims abstract description 21
- 238000002474 experimental method Methods 0.000 claims abstract description 16
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 33
- 239000004917 carbon fiber Substances 0.000 claims description 33
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 33
- 238000005452 bending Methods 0.000 claims description 24
- 229910001220 stainless steel Inorganic materials 0.000 claims description 7
- 239000010935 stainless steel Substances 0.000 claims description 7
- 239000003822 epoxy resin Substances 0.000 claims description 6
- 239000003292 glue Substances 0.000 claims description 6
- 229920000647 polyepoxide Polymers 0.000 claims description 6
- 239000000203 mixture Substances 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 3
- 238000012360 testing method Methods 0.000 claims description 3
- 230000008602 contraction Effects 0.000 claims description 2
- 230000003247 decreasing effect Effects 0.000 claims description 2
- 230000001737 promoting effect Effects 0.000 claims description 2
- 230000003068 static effect Effects 0.000 claims description 2
- 230000003319 supportive effect Effects 0.000 claims description 2
- 238000012545 processing Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 10
- 238000013461 design Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 1
Classifications
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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
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
-
- 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)
- General Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of folded in three wing kinetic characteristics experimental provisions using steering engine, belong to aircraft experimental technique field.The experimental provision includes firm banking, the folded wing inner segment wing, the outer section wing of the folded wing stage casing wing and folded wing, and the experimental provision is simulating the structure of folded wing.Firm banking in the folded wing inner segment wing support aluminium section bar, corner brace is threadedly coupled by bolt, the inner segment steering engine of the folded wing inner segment wing is threadedly coupled with the steering engine arm of the folded wing stage casing wing by bolt, the folded wing stage casing wing) steering engine arm and the outer section steering engine of the outer section wing of folded wing be threadedly coupled by bolt, form folded wing model equipment.The present invention keeps the inner segment wing and parallel relation of the outer section of wing in movement by closed-loop control system, while simple, convenient, largely reduces space, alleviates the total quality and difficulty of processing of mechanism, reduce cost.
Description
Technical field
The present invention relates to a kind of aviation aircraft experimental provisions, are particularly used to study the reality of folded wing dynamic characteristic
Experiment device, it is particularly possible to simulate vibration characteristics of the morphing aircraft folded wing during expansion, belong to aircraft experiment skill
Art field.
Background technology
As one kind of new concept deformable aircraft, flex-wing vehicle can pass through the stretching, extension of wing and folding active
Change wing area, so as to remain optimal state of flight, expand flight envelope to the maximum extent, different appoint can be performed
Business, meets different flight environment of vehicle requirements.When flex-wing vehicle is in different folding angles flight courses, due to wing configuration
Pneumatically it can make flex-wing vehicle that there is different vibration characteristics under different angle with the variation of structure caused by variation.Cause
This, vibration characteristics when designing a kind of experimental model to study to flex-wing vehicle difference folding angles folds guidance
The structure design and safe flight of rotor aircraft all have very important value.
For the design of aircraft, aircraft aerofoil is mostly using variable cross-section size design, and current experimental model is adopted more
It is designed with uniform section, affects the reliability of experimental study to a certain extent.This experimental model can carry out variable cross-section folding
The dynamic vibration characteristics analysis of the wing.
Invention content
The invention discloses a kind of folded in three wing kinetic characteristics experimental provision using steering engine as dynamical element,
The experimental provision reduces the floor space of current experimental model, while the dynamic vibration that can carry out variable cross-section folded wing is special
Property analysis.
The invention discloses a kind of folded in three wing kinetic characteristics experimental provision using steering engine, the experimental provision packets
Include the outer section wing (4) of firm banking (1), the folded wing inner segment wing (2), the folded wing stage casing wing (3) and folded wing, experiment dress
Put to simulate the structure of folded wing.Support aluminium section bar (7), corner brace in firm banking (1) and the folded wing inner segment wing (2)
(9) it is threadedly coupled by bolt, inner segment steering engine (10) and the folded wing stage casing wing (3) of the folded wing inner segment wing (2)
Steering engine arm (20) is threadedly coupled by bolt, the outer section wing of steering engine arm (20) and folded wing of the folded wing stage casing wing (3)
(4) outer section steering engine (22) is threadedly coupled by bolt, forms folded wing model equipment.
Firm banking (1) is bolted on actuating vibration table, and the folded wing inner segment wing (2) is installed on firm banking (1)
Side；Steering engine is directly connected to folded wing model equipment, and firm banking (1) is made of multiple aluminium section bars (5), each aluminium section bar
(5) it is connected between by corner brace (6).
The folded wing inner segment wing (2) is by support aluminium section bar (7), inner segment carbon fiber skin (8), corner brace (9), inner segment steering engine
(10), inner segment bending floor (11) and stainless steel fixed plate (12) composition, wherein, support aluminium section bar (7) carries for proof strength
High single unit system rigidity.Inner segment carbon fiber skin (8) is directly connected to support aluminium by epoxy resin glue by bonding way
On section bar (7), inner segment bending floor (11) and stainless steel fixed plate (12) carry out being threaded in support aluminium section bar by bolt
(7) on.The upper surface of inner segment carbon fiber skin (8) is mounted directly vibration-testing sensor.Corner brace (9) is for two support aluminium section bars
(7) connection will support aluminium section bar (7) to be connected with corner brace (9) by bolt, and wherein bolt has omitted.Inner segment steering engine (10)
Power is provided for the lifting folded wing stage casing wing (3), inner segment steering engine (10) is connected by bolt with stainless steel fixed plate (12).
Inner segment bending floor (11) makes the folded wing inner segment wing (2) for promoting the local strength on the outside of the folded wing inner segment wing (2)
Outside and inside shape it is integral.
The folded wing stage casing wing (3) is by outer-hexagonal bolts (13), nut (14), flake bearing (15), screw rod (16), stage casing
Bending floor (18), stage casing floor (19), steering engine arm (20) and stage casing carbon fiber skin on the outside of inside bending floor (17), stage casing
(21) it forms.Steering engine arm (20) comes from the power of inner segment steering engine (10) and outer section of steering engine (24) offer, steering engine arm for being driven
(20) it is threadedly coupled with stage casing floor (19) by bolt, the Foldable wing stage casing wing (3) movement.Outer-hexagonal bolts
(13), nut (14), flake bearing (15) and screw rod (16), which by its included threaded line be threadedly coupled, forms a structure,
Structure provides the intensity of the folded wing stage casing wing (3), plays the role of support.Outside stage casing inside bending floor (17) and stage casing
Side bending floor (18) is directly connected to by bonding way on stage casing carbon fiber skin (21) by epoxy resin glue, is used for
The local strength of the folded wing stage casing wing (3) is promoted, and makes screw rod (16) and stage casing carbon fiber skin (21) shape integral,
Flake bearing (15) and stage casing carbon fiber skin (21) shape for making outside are integral.
The outer section wing (4) of folded wing is by outer section of steering engine (22), outer section of carbon fiber floor (23), outer section of carbon fiber skin (24)
And outer section of bending floor (25) composition.Outer section of steering engine (22) is threadedly coupled with steering engine arm (20) by bolt, is folding machine
The outer section wing (4) movement of the wing provides power, while servo motor is driven to make the section wing (4) and folded wing outside folded wing by pwm
The inner segment wing (2) remains parallel.Outer section of carbon fiber floor (23) and outer section of bending floor (25) play a supportive role.Outer section of carbon fibre
Dimension covering (24) is connected to by epoxy resin glue on outer section of carbon fiber floor (23) and outer section of bending floor (25).
The outer section carbon fiber skin (24) of inner segment carbon fiber skin (8), stage casing carbon fiber skin (21) is used for mould in an experiment
Intend the covering of wing.
The invention can carry out following action in actual use：
S1：Inner segment steering engine (10) and outer section of steering engine (22) is controlled to remain that one is constant in an experiment by SCM PWM
Angle, meanwhile, make to remain parallel with the folded wing inner segment wing (2) and with the upper surface of the section wing (4) outside folded wing, it can
With reference to the configuration state of Fig. 1 Fig. 2 Fig. 3 Fig. 4 Fig. 5 in Figure of description, the folded wing inner segment wing (2) and the folded wing stage casing wing
(3) the angle working condition at 0 °, 30 °, 60 °, 90 °, 120 ° respectively between, to simulate the static parameter of folded wing.
S2：Inner segment steering engine (10) and outer section of steering engine (22) is controlled to keep a specific speed in an experiment by SCM PWM
Circular motion is carried out, makes angle between the folded wing inner segment wing (2) and the folded wing stage casing wing (3) that can be gradually increased to from 0 °
120 °, then 0 ° is gradually decreased as from 120 °, at the same should ensure that the folded wing inner segment wing (2) and with the section wing (4) outside folded wing
Upper surface keeping parallelism, to simulate dynamic parameter of the folded wing in wing expansion and contraction process.
The present invention can keep the inner segment wing to exist with the outer section of wing experimental provision of folded wing by closed-loop control system
Parallel relation in movement, at the same it is simple, convenient, largely reduce space, alleviate the whole of mechanism
Weight and difficulty of processing, reduce cost.It can carry out the mode experiment of folded wing and the dynamic vibration spy of folded wing
Property experiment.
The present invention is described further with reference to the accompanying drawings of the specification.
Description of the drawings
Fig. 1 is the general assembly schematic diagram of folded wing experimental provision.
Fig. 2 is the firm banking schematic diagram of folded wing experimental provision.
Fig. 3 is the assembling schematic diagram of the inner frame of the inner segment wing of folded wing experimental provision.
Fig. 4 is the assembling schematic diagram of the inner frame of the stage casing wing of folded wing experimental provision.
Fig. 5 is the assembling schematic diagram of the inner frame of the outer section wing of folded wing experimental provision.
Fig. 6 is the stage casing wing of folded wing experimental provision and the schematic diagram of the outer section wing holding level of the inner segment wing.
Fig. 7 is that the stage casing wing of folded wing experimental provision keeps 30 degree of schematic diagram with the outer section wing of the inner segment wing.
Fig. 8 is that the stage casing wing of folded wing experimental provision keeps 60 degree of schematic diagram with the outer section wing of the inner segment wing.
Fig. 9 is that the stage casing wing of folded wing experimental provision keeps 90 degree of schematic diagram with the outer section wing of the inner segment wing.
Figure 10 is that the stage casing wing of folded wing experimental provision keeps 120 degree of schematic diagram with the outer section wing of the inner segment wing.
In figure：1st, firm banking, 2, the folded wing inner segment wing, 3, the folded wing stage casing wing, 4, the outer section wing of folded wing, 5,
Firm banking aluminium section bar, 6, corner brace, 7, support aluminium section bar, 8, inner segment carbon fiber skin, 9, folding wings corner brace, 10, inner segment rudder
Machine, 11, inner segment bending floor, 12, stainless steel fixed plate, 13, outer-hexagonal bolts, 14, nut, 15, flake bearing, 16, screw rod,
17th, bending floor on the inside of stage casing, 18, bending floor on the outside of stage casing, 19, stage casing floor, 20, steering engine arm, 21, stage casing carbon fiber covers
Skin, 22, outer section of steering engine, 23, outer section of carbon fiber floor, 24, outer section of carbon fiber skin, 25, outer section of bending floor.
Specific embodiment
The experimental model of patent of the present invention is included in firm banking (Fig. 2), the folded wing inner segment wing (Fig. 3), folded wing
Duan Yi (Fig. 4) and the outer section wing (Fig. 5) of folded wing, to simulate the structure of folding wings.
When carrying out dynamic vibration characteristics test experiments, firm banking (Fig. 2) is installed on by bolt on actuating vibration table, is rolled over
The folded wing inner segment wing (Fig. 3), the folded wing stage casing wing (Fig. 4) and the outer section wing (Fig. 5) of folded wing are mounted on refer to as shown in Figure 1
Fixed position, makes whole device be fixed on pedestal, simulates the boundary condition of cantilever.Inner segment steering engine (10) and outer section of steering engine (22)
The circular motion for carrying out friction speed is controlled by pwm, while makes the outer section wing (Fig. 5) of folded wing and the folded wing inner segment wing
(Fig. 3) remains parallel during exercise, to simulate the state in folded wing real work.In the mistake that device is moved
Cheng Zhong applies initial excitation by actuating vibration table, and device occurs forced vibration, passes through sensor determination experiment numerical value.
A length of 700 millimeters of the size of firm banking (1), width are 550 millimeters, a height of 260 millimeters.
When carrying out mould measurement experiment, should be controlled by pwm makes steering engine angle be maintained in the angle set, makes machine
Wing remains stationary state under the angle set.Predetermined angle for 0 ° (Fig. 6), 30 ° (Fig. 7), 60 ° (Fig. 8), 90 ° (Fig. 9),
120 ° (Figure 10).Entire folded wing experimental provision is fixed on actuating vibration table, simple harmonic quantity power is given using vibrator and encourages, make dress
Generation forced vibration is put, passes through sensor determination experiment numerical value.
Finally it should be noted that above example is only to illustrate the present invention and not limits technology described in the invention
Scheme；Therefore, although the present invention has been described in detail in this specification, it should be appreciated by those skilled in the art,
Still can modify to the present invention or equivalent replacement, and the technical solution of the spirit and scope for not departing from invention of all and
It is improved, and is intended to be within the scope of the claims of the invention.
Claims (7)
1. a kind of folded in three wing kinetic characteristics experimental provision using steering engine, it is characterised in that：The experimental provision includes
The outer section wing (4) of firm banking (1), the folded wing inner segment wing (2), the folded wing stage casing wing (3) and folded wing, the experimental provision
To simulate the structure of folded wing；Support aluminium section bar (7), corner brace in firm banking (1) and the folded wing inner segment wing (2)
(9) it is threadedly coupled by bolt, inner segment steering engine (10) and the folded wing stage casing wing (3) of the folded wing inner segment wing (2)
Steering engine arm (20) is threadedly coupled by bolt, the outer section wing of steering engine arm (20) and folded wing of the folded wing stage casing wing (3)
(4) outer section steering engine (22) is threadedly coupled by bolt, forms folded wing model equipment.
2. a kind of folded in three wing kinetic characteristics experimental provision using steering engine according to claim 1, feature
It is：Firm banking (1) is bolted on actuating vibration table, and the folded wing inner segment wing (2) is installed on firm banking (1) one
Side；Steering engine is directly connected to folded wing model equipment, and firm banking (1) is made of multiple aluminium section bars (5), each aluminium section bar
(5) it is connected between by corner brace (6).
3. a kind of folded in three wing kinetic characteristics experimental provision using steering engine according to claim 1, feature
It is：The folded wing inner segment wing (2) by support aluminium section bar (7), inner segment carbon fiber skin (8), corner brace (9), inner segment steering engine (10),
Inner segment bending floor (11) and stainless steel fixed plate (12) composition, wherein, support aluminium section bar (7) improves whole for proof strength
Body device rigidity；Inner segment carbon fiber skin (8) is directly connected to support aluminium section bar by epoxy resin glue by bonding way
(7) on, inner segment bending floor (11) and stainless steel fixed plate (12) carry out being threaded in support aluminium section bar (7) by bolt
On；The upper surface of inner segment carbon fiber skin (8) is mounted directly vibration-testing sensor；Corner brace (9) is for two support aluminium section bars (7)
Connection, aluminium section bar (7) will be supported to be connected with corner brace (9) by bolt, wherein bolt has omitted；Inner segment steering engine (10) is lift
It rises the folded wing stage casing wing (3) and power is provided, inner segment steering engine (10) is connected by bolt with stainless steel fixed plate (12)；Inner segment
Bending floor (11) makes the outside of the folded wing inner segment wing (2) for promoting the local strength on the outside of the folded wing inner segment wing (2)
It is integral with inside shape.
4. a kind of folded in three wing kinetic characteristics experimental provision using steering engine according to claim 1, feature
It is：The folded wing stage casing wing (3) is by outer-hexagonal bolts (13), nut (14), flake bearing (15), screw rod (16), stage casing
Bending floor (18), stage casing floor (19), steering engine arm (20) and stage casing carbon fiber skin on the outside of side bending floor (17), stage casing
(21) it forms；Steering engine arm (20) comes from the power of inner segment steering engine (10) and outer section of steering engine (24) offer, steering engine arm for being driven
(20) it is threadedly coupled with stage casing floor (19) by bolt, the Foldable wing stage casing wing (3) movement；Outer-hexagonal bolts
(13), nut (14), flake bearing (15) and screw rod (16), which by its included threaded line be threadedly coupled, forms a structure,
Structure provides the intensity of the folded wing stage casing wing (3), plays the role of support；Bending floor (17) and stage casing outside on the inside of stage casing
Bending floor (18) is directly connected to by bonding way on stage casing carbon fiber skin (21) by epoxy resin glue, for carrying
The local strength of the folded wing stage casing wing (3) is risen, and makes screw rod (16) and stage casing carbon fiber skin (21) shape integral, is made outer
The flake bearing (15) of side and stage casing carbon fiber skin (21) shape are integral.
5. a kind of folded in three wing kinetic characteristics experimental provision using steering engine according to claim 1, feature
It is：The outer section wing (4) of folded wing by outer section of steering engine (22), outer section of carbon fiber floor (23), outer section of carbon fiber skin (24) and
Outer section of bending floor (25) composition；Outer section of steering engine (22) is threadedly coupled with steering engine arm (20) by bolt, is folded wing
The outer section of wing (4) movement provides power, while servo motor is driven to make outside folded wing in the section wing (4) and folded wing by pwm
Duan Yi (2) remains parallel；Outer section of carbon fiber floor (23) and outer section of bending floor (25) play a supportive role；Outer section of carbon fiber
Covering (24) is connected to by epoxy resin glue on outer section of carbon fiber floor (23) and outer section of bending floor (25).
6. a kind of folded in three wing kinetic characteristics experimental provision using steering engine according to claim 1, feature
It is：The outer section carbon fiber skin (24) of inner segment carbon fiber skin (8), stage casing carbon fiber skin (21) is used for analog machine in an experiment
The covering of the wing.
7. a kind of folded in three wing kinetic characteristics experimental provision using steering engine according to claim 1, feature
It is：The realization process of the device is as follows,
S1：Inner segment steering engine (10) and outer section of steering engine (22) is controlled to remain a constant angle in an experiment by SCM PWM,
Meanwhile make to remain parallel, folding machine with the folded wing inner segment wing (2) and with the upper surface of the section wing (4) outside folded wing
The angle working condition at 0 °, 30 °, 60 °, 90 °, 120 ° respectively between the wing inner segment wing (2) and the folded wing stage casing wing (3), is used
To simulate the static parameter of folded wing；
S2：Control inner segment steering engine (10) and outer section of steering engine (22) that a specific speed is kept to carry out in an experiment by SCM PWM
Circular motion makes between the folded wing inner segment wing (2) and the folded wing stage casing wing (3) angle that can be gradually increased to 120 ° from 0 °, then
0 ° is gradually decreased as from 120 °, while should ensure that the folded wing inner segment wing (2) and protected with the upper surface of the section wing (4) outside folded wing
Maintain an equal level row, to simulate dynamic parameter of the folded wing in wing expansion and contraction process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810363819.2A CN108267285B (en) | 2018-04-22 | 2018-04-22 | Three-section folding wing dynamic characteristic experimental device using steering engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810363819.2A CN108267285B (en) | 2018-04-22 | 2018-04-22 | Three-section folding wing dynamic characteristic experimental device using steering engine |
Publications (2)
| Publication Number | Publication Date |
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| CN108267285A true CN108267285A (en) | 2018-07-10 |
| CN108267285B CN108267285B (en) | 2020-09-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810363819.2A Expired - Fee Related CN108267285B (en) | 2018-04-22 | 2018-04-22 | Three-section folding wing dynamic characteristic experimental device using steering engine |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2739605A1 (en) * | 1995-10-04 | 1997-04-11 | Roy Janick | Multipurpose frame for light sand or ice yacht |
| CN103123293A (en) * | 2012-12-24 | 2013-05-29 | 中国航空工业空气动力研究院 | Drive-embedded dynamic folding morphing wing |
| CN104897355A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Folded wing non-linear flutter test device |
| CN105547618A (en) * | 2015-12-03 | 2016-05-04 | 北京机械设备研究所 | Modal analysis method based on folding control surface rudder system |
| CN105620721A (en) * | 2016-01-30 | 2016-06-01 | 邢永安 | Small wing face folding mechanism of unmanned aerial vehicle |
| CN106596020A (en) * | 2016-12-30 | 2017-04-26 | 北京工业大学 | Dynamic characteristic test device for foldable wing |
-
2018
- 2018-04-22 CN CN201810363819.2A patent/CN108267285B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2739605A1 (en) * | 1995-10-04 | 1997-04-11 | Roy Janick | Multipurpose frame for light sand or ice yacht |
| CN103123293A (en) * | 2012-12-24 | 2013-05-29 | 中国航空工业空气动力研究院 | Drive-embedded dynamic folding morphing wing |
| CN104897355A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Folded wing non-linear flutter test device |
| CN105547618A (en) * | 2015-12-03 | 2016-05-04 | 北京机械设备研究所 | Modal analysis method based on folding control surface rudder system |
| CN105620721A (en) * | 2016-01-30 | 2016-06-01 | 邢永安 | Small wing face folding mechanism of unmanned aerial vehicle |
| CN106596020A (en) * | 2016-12-30 | 2017-04-26 | 北京工业大学 | Dynamic characteristic test device for foldable wing |
Non-Patent Citations (1)
| Title |
|---|
| 赵江南: "折叠翼飞行器仿真与实验研究", 《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》 * |
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| CN108267285B (en) | 2020-09-25 |
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