CN105799914A - Rotation unfolding mechanism for aircraft wing - Google Patents
Rotation unfolding mechanism for aircraft wing Download PDFInfo
- Publication number
- CN105799914A CN105799914A CN201610154124.4A CN201610154124A CN105799914A CN 105799914 A CN105799914 A CN 105799914A CN 201610154124 A CN201610154124 A CN 201610154124A CN 105799914 A CN105799914 A CN 105799914A
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- CN
- China
- Prior art keywords
- central siphon
- aircraft wing
- shaft
- rotation
- wing
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
Abstract
The invention discloses a rotation unfolding mechanism for an aircraft wing.The rotation unfolding mechanism comprises a shaft cover, the wing, an inner shaft pipe, a supporting combination, an aircraft body, a thrust spring, a shaft base, a fixing piece, a positioning block, a positioning spring, a fixed shaft, a rotating shaft, an outer shaft pipe and a guide rail groove.The rotation unfolding mechanism has the advantages that the structure is compact in connection, a combination of an elastic force device or the thrust device and a sliding mechanism is adopted to achieve rotation unfolding of the aircraft wing, the effects that running is stable, the rotation speed can be adjusted and unfolding positioning of the aircraft wing can be achieved very well are achieved, the service life is long, the potential energy of the thrust spring can be converted into the rotation kinetic energy of the fixed shaft of a maneuvering wing face within a short time so that energy consumption in the movement process can be met, the rotation unfolding mechanism of the aircraft wing is simple in structure, low in failure rate, suitable for a folding and unfolding mechanical structure of the aircraft wing and suitable for being applied and popularized and has good economic benefits and social benefits.
Description
Technical field
The present invention relates to rotary expansion mechanism, be specially a kind of rotary expansion mechanism for aircraft wing, belong to rotary expansion mechanism applied technical field.
Background technology
nullDevelopment along with social development and science and technology，Motor-driven aerofoil is a kind of controlled structure changes aerodynamic force parts，It is typically used under some particular flight state and improves the horizontal course maneuvering ability of aircraft，And at regular flight condition，Then packed up and be concealed in body，Namely motor-driven aerofoil is converted by a set of motion to duty by collapsed state is launch locking mechanism to realize，Therefore，The rotary expansion mechanism of wing has extremely important effect for the development of aircraft，Present stage aircraft，Including unmanned plane，It is widely used in military、Civil area，Along with improving constantly that aircraft survival ability and fighting efficiency are required，Have on the basis of excellent aerodynamic characteristic，Smaller volume can be realized、Lightweight，Portable，Also an important indicator of Flight Vehicle Design requirement is become，And there is a lot of weak point in the rotary expansion mechanism of current aircraft wing，For collapsible aircraft，Folding and expanding mechanism is wherein key mechanism，Existing fold mechanism is more complicated，Volume is big，Be not suitable for the aircraft of small size，Therefore，For the problems referred to above, a kind of rotary expansion mechanism for aircraft wing is proposed.
Summary of the invention
The purpose of the present invention is that provides a kind of rotary expansion mechanism for aircraft wing to solve the problems referred to above, elastic force apparatus or thrust device and slide mechanism combination is adopted to realize the rotary expansion of aircraft wing, there is simple in construction, stable, rotary speed adjustable, can well realize the effect that aircraft wing is launched.
The present invention is achieved through the following technical solutions above-mentioned purpose, a kind of rotary expansion mechanism for aircraft wing, and including outer central siphon, described outer central siphon connects interior central siphon and described outer central siphon one end connection shaft seat by support combinations；Described axle bed side arranges thrust spring and described thrust spring is positioned at inside described central siphon；Rotating shaft is set between described outer central siphon and described interior central siphon, and described rotating shaft one end connects dead axle；Described rotating shaft arranged outside fuselage；Shaft-cup and described shaft-cup arranged outside wing are installed in described interior central siphon one end；Described shaft-cup side arranges fixture, and described fixture one end connects locating piece；Described fixture internally installed location spring.
Preferably, also include guide-track groove, between described interior central siphon and described outer central siphon, be provided with guide-track groove.
Preferably, described support combinations one end is arranged on inside described interior central siphon, and described support combinations one end is arranged on inside described outer central siphon.
Preferably, described location spring is fixed on described outer central siphon side.
Preferably, described locating piece one end is connected with described interior central siphon.
Preferably, described thrust spring one end is connected with described axle bed.
The invention has the beneficial effects as follows: this structure connects compact, elastic force apparatus or thrust device and slide mechanism combination is adopted to realize the rotary expansion of aircraft wing, there is simple in construction, stable, rotary speed adjustable, can well realize aircraft wing and launch the effect of location, and service life is of a specified duration, there are good economic benefit and social benefit, are suitable for promoting the use of.
Accompanying drawing explanation
Fig. 1 is overall structure schematic diagram of the present invention；
Fig. 2 is overall structure side view of the present invention；
Fig. 3 is internal structure schematic diagram of the present invention；
Fig. 4 is B place of the present invention structural representation；
Fig. 5 is guide-track groove structural representation of the present invention；
In figure: 1, shaft-cup, 2, wing, 3, interior central siphon, 4, support combinations, 5, fuselage, 6, thrust spring, 7, axle bed, 8, fixture, 9, locating piece, 10, location spring, 11, dead axle, 12, rotating shaft, 13, outer central siphon, 31, guide-track groove.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is only a part of embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of protection of the invention.
Referring to Fig. 1-5, a kind of rotary expansion mechanism for aircraft wing, including outer central siphon 13, described outer central siphon 13 connects interior central siphon 3 and described outer central siphon 13 one end connection shaft seat 7 by support combinations 4；Described axle bed 7 side arranges thrust spring 6 and described thrust spring 6 is positioned at described central siphon 3 inside；Rotating shaft 12 is set between described outer central siphon 13 and described interior central siphon 3, and described rotating shaft 12 one end connects dead axle 11；Described rotating shaft 11 arranged outside fuselage 5；Shaft-cup 1 and described shaft-cup 1 arranged outside wing 2 are installed in described interior central siphon 3 one end；Described shaft-cup 1 side arranges fixture 8, and described fixture 8 one end connects locating piece 9；Described fixture 8 internally installed location spring 10.
A kind of technical optimization scheme as the present invention, also including guide-track groove 31, be provided with guide-track groove 31 between described interior central siphon 3 and described outer central siphon 13, described guide-track groove 31 can change guide into, suiting between central siphon 3 and outer central siphon 13 in convenient, make whole device compacter.
As a kind of technical optimization scheme of the present invention, it is internal that described support combinations 4 one end is arranged on described interior central siphon 3, and described support combinations 4 one end is arranged on described outer central siphon 13 inside, for the stress guiding function of thrust spring or thrust device.
As a kind of technical optimization scheme of the present invention, described location spring 10 is fixed on described outer central siphon side；Described locating piece 9 one end is connected with described interior central siphon 3, and during outer central siphon motion certain position, locating piece 9 plays the effect of central siphon 3 in location.
As a kind of technical optimization scheme of the present invention, described thrust spring 6 one end is connected with described axle bed 7, the stretching, extension of central siphon 3 and outer central siphon 13 in convenient.
The present invention is in use, described outer central siphon 13, support combinations 4 and interior central siphon 3 are by dead axle 11, runner 12 links together, thrust spring 6 gives support combinations 4 power, the rail groove that interior central siphon 3 is arranged in outer central siphon is allowed to move, fixture 8, locating piece 9, location spring 10 is fixed on outer central siphon, during outer central siphon motion certain position, locating piece 9 plays the effect of central siphon 3 in location, thrust spring 6 is under compression, discharge internal central siphon 3 stress, after interior central siphon 3 stress, wing 2 is driven to run along guide-track groove 31, reach the purpose of rotary expansion, can be widely used for the folding device of various aircraft, realize aircraft wing is launched.
It is obvious to a person skilled in the art that the invention is not restricted to the details of above-mentioned one exemplary embodiment, and when without departing substantially from the spirit of the present invention or basic feature, it is possible to realize the present invention in other specific forms.Therefore, no matter from which point, embodiment all should be regarded as exemplary, and be nonrestrictive, the scope of the invention rather than described above limits, it is intended that all changes in the implication of the equivalency dropping on claim and scope included in the present invention.Any accompanying drawing labelling in claim should be considered as the claim that restriction is involved.
In addition, it is to be understood that, although this specification is been described by according to embodiment, but not each embodiment only comprises an independent technical scheme, this narrating mode of description is only for clarity sake, description should be made as a whole by those skilled in the art, and the technical scheme in each embodiment through appropriately combined, can also form other embodiments that it will be appreciated by those skilled in the art that.
Claims (6)
1. the rotary expansion mechanism for aircraft wing, including outer central siphon (13), it is characterized in that: described outer central siphon (13) connects interior central siphon (3) and described outer central siphon (13) one end connection shaft seat (7) by support combinations (4)；Described axle bed (7) side arranges thrust spring (6) and described thrust spring (6) is positioned at described central siphon (3) inside；Rotating shaft (12) is set between described outer central siphon (13) and described interior central siphon (3), and described rotating shaft (12) one end connects dead axle (11)；Described rotating shaft (11) arranged outside fuselage (5)；Shaft-cup (1) and described shaft-cup (1) arranged outside wing (2) are installed in described interior central siphon (3) one end；Described shaft-cup (1) side arranges fixture (8), and described fixture (8) one end connects locating piece (9)；Described fixture (8) internally installed location spring (10).
2. a kind of rotary expansion mechanism for aircraft wing according to claim 1, it is characterized in that: also include guide-track groove (31), between described interior central siphon (3) and described outer central siphon (13), be provided with guide-track groove (31).
3. a kind of rotary expansion mechanism for aircraft wing according to claim 1 and 2, it is characterized in that: it is internal that described support combinations (4) one end is arranged on described interior central siphon (3), and described support combinations (4) one end is arranged on described outer central siphon (13) inside.
4. a kind of rotary expansion mechanism for aircraft wing according to claim 3, it is characterised in that: described location spring (10) is fixed on described outer central siphon (13) side.
5. a kind of rotary expansion mechanism for aircraft wing according to claim 1 or 4, it is characterised in that: described locating piece (9) one end is connected with described interior central siphon (3).
6. a kind of rotary expansion mechanism for aircraft wing according to claim 5, it is characterised in that: described thrust spring (6) one end is connected with described axle bed (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610154124.4A CN105799914A (en) | 2016-03-17 | 2016-03-17 | Rotation unfolding mechanism for aircraft wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610154124.4A CN105799914A (en) | 2016-03-17 | 2016-03-17 | Rotation unfolding mechanism for aircraft wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105799914A true CN105799914A (en) | 2016-07-27 |
Family
ID=56453284
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610154124.4A Pending CN105799914A (en) | 2016-03-17 | 2016-03-17 | Rotation unfolding mechanism for aircraft wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105799914A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107776870A (en) * | 2017-10-27 | 2018-03-09 | 成都云鼎智控科技有限公司 | A kind of wing-folding locked component and unmanned plane |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2141534A (en) * | 1936-10-09 | 1938-12-27 | Hudson Richard John Harrington | Folding structural arrangement of aircraft |
| US5820072A (en) * | 1995-12-09 | 1998-10-13 | Agency For Defense Development | Apparatus for unfolding and fixing missile fins |
| CN102351045A (en) * | 2011-07-29 | 2012-02-15 | 哈尔滨工业大学 | Wing folding mechanism suitable for folding wing at any angle |
| CN103963958A (en) * | 2014-04-21 | 2014-08-06 | 西工大常熟研究院有限公司 | Wing folding mechanism for unmanned plane |
| US8894004B1 (en) * | 2013-06-11 | 2014-11-25 | The United States Of America As Represented By The Secretary Of The Navy | Folding articulating wing mechanism |
| CN204775993U (en) * | 2015-04-29 | 2015-11-18 | 北京威标至远科技发展有限公司 | Wing device is folded to aircraft |
-
2016
- 2016-03-17 CN CN201610154124.4A patent/CN105799914A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2141534A (en) * | 1936-10-09 | 1938-12-27 | Hudson Richard John Harrington | Folding structural arrangement of aircraft |
| US5820072A (en) * | 1995-12-09 | 1998-10-13 | Agency For Defense Development | Apparatus for unfolding and fixing missile fins |
| CN102351045A (en) * | 2011-07-29 | 2012-02-15 | 哈尔滨工业大学 | Wing folding mechanism suitable for folding wing at any angle |
| US8894004B1 (en) * | 2013-06-11 | 2014-11-25 | The United States Of America As Represented By The Secretary Of The Navy | Folding articulating wing mechanism |
| CN103963958A (en) * | 2014-04-21 | 2014-08-06 | 西工大常熟研究院有限公司 | Wing folding mechanism for unmanned plane |
| CN204775993U (en) * | 2015-04-29 | 2015-11-18 | 北京威标至远科技发展有限公司 | Wing device is folded to aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107776870A (en) * | 2017-10-27 | 2018-03-09 | 成都云鼎智控科技有限公司 | A kind of wing-folding locked component and unmanned plane |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| AD01 | Patent right deemed abandoned | ||
| AD01 | Patent right deemed abandoned |
Effective date of abandoning: 20180629 |