CN108045548A - A kind of aircraft deformation nose cone device based on space two degrees of freedom development agency - Google Patents
A kind of aircraft deformation nose cone device based on space two degrees of freedom development agency Download PDFInfo
- Publication number
- CN108045548A CN108045548A CN201711286667.2A CN201711286667A CN108045548A CN 108045548 A CN108045548 A CN 108045548A CN 201711286667 A CN201711286667 A CN 201711286667A CN 108045548 A CN108045548 A CN 108045548A
- Authority
- CN
- China
- Prior art keywords
- nose cone
- cone shell
- ball
- hinged
- groups
- Prior art date
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
- Tires In General (AREA)
Abstract
A kind of aircraft deformation nose cone device based on two degrees of freedom space development agency, including nose cone shell, nose cone shell is divided into more than three-level altogether, first order nose cone shell is cylindric for diameter maximum, intergrade nose cone housing diameter successively decreases, and be round table-like, most final stage nose cone shell outermost end has spherical crown feature, is connected between nose cone shell by extending bending linkage mechanism with auxiliary ball vice mechanism；The elongation bending leverage that elongation bending linkage mechanism is symmetrically installed by two groups on nose cone shell horizontal flange forms, each group of elongation bending leverage includes four groups of parallelogram and is driven leverage, the input of four groups of parallelogram transmission leverages is connected with the drive rod of upper level, and the output of four groups of parallelogram transmission leverages of afterbody is connected with foot piece；Totally two groups of auxiliary ball vice mechanism, on the symmetrical installation of nose cone shell vertical split, the present invention can realize it is whole freely stretch and bend, possess the advantages that deflection is big, driving is simple.
Description
Technical field
The present invention relates to field of aerospace technology, and in particular to a kind of flight based on space two degrees of freedom development agency
Device deforms nose cone device.
Background technology
For re-entry space vehicle in aerial mission, flight environment of vehicle difference is huge, thus need to the aerodynamic configuration of aircraft into
Row changes, and nose cone is the key structure for influencing air drag suffered by aircraft.From bionics angle, the required deformation of nose cone
Feature and the deformation of honeybee abdomen are quite similar, that is, realize flexible bending and dilatation, and current nose cone is mostly fixed
Structure can not realize flexible bending and dilatation.
The content of the invention
The shortcomings that in order to overcome the above-mentioned prior art, object of the present invention is to provide one kind to be based on space two degrees of freedom
The aircraft deformation nose cone device of development agency, can realize it is whole freely stretch and bend, possess that deflection is big, driving letter
Singly, the advantages of occupied space is few, reliability is high.
In order to achieve the above object, the technical solution taken of the present invention is：
A kind of aircraft deformation nose cone device based on two degrees of freedom space development agency, it is curved including nose cone shell 1, elongation
Bent linkage mechanism 2 and auxiliary ball vice mechanism 3, wherein, nose cone shell 1 is divided into more than three-level altogether, and first order nose cone shell 1A is
Maximum cylindric of diameter, intergrade nose cone housing diameter successively decreases, and is round table-like, and most final stage nose cone shell outermost end has ball
Feature is preced with, is connected between nose cone shell by extending bending linkage mechanism 2 and auxiliary ball vice mechanism 3.
The elongation that the elongation bending linkage mechanism 2 is symmetrically installed by two groups on nose cone shell horizontal flange is bent
Leverage forms, and each group of elongation bending leverage includes four groups of parallelogram and be driven leverage, and four groups of parallelogram are driven leverage
Input and drive rod 2A, the drive link 2C of upper level be hinged, the output of four groups of parallelogram transmission leverages of afterbody and
Foot piece 2D is hinged, and chopped-off head drive rod 2A is hinged in first order nose cone shell, foot piece 2D is hinged in afterbody nose cone shell.
Described parallelogram transmission leverage includes the drive rod 2A of upper level, drive rod 2A and in parallel short
Bar 2B is installed on the vertical split of nose cone shell, the installation site of other two quarter butt 2B then in drive rod 2A both sides,
One end is hinged at hole and stomidium respectively with drive rod 2A in its center, and the other end one is cut with scissors with nose cone shell at hinge base
It connects, the one side of a quarter butt 2B at nose cone shell vertical split is hinged with its one end, and drive link 2C is in quarter butt 2B one sides
And drive rod 2A one sides are hinged respectively with the two.
Totally two groups of the auxiliary ball vice mechanism 3, on the symmetrical installation of nose cone shell vertical split, each group auxiliary
Ball vice mechanism 3 is helped to include, and four identical auxiliary balls are secondary and an auxiliary ball pair for carrying ball pair foot piece 3D, auxiliary ball pair are wrapped
Include ball pair sphere 3A, band club 3B or ball pair foot piece 3D, ball slave connecting rod 3C and ball pair upper cover 3E, ball pair sphere 3A and dribbling
Bar 3B or ball pair foot piece 3D are connected through a screw thread, half ball groove in ball pair sphere 3A and ball pair upper cover 3E and nose cone shell 1
Feature forms ball auxiliary structure；Band club 3B or ball pair foot piece 3D and ball slave connecting rod 3C one end is hinged, the ball slave connecting rod 3C other ends
It is hinged with nose cone shell 1 at its hinge base.
Beneficial effects of the present invention are：
The present invention by corresponding telescoping collapse Gan Zu mechanisms 2 and Qiu Fu auxiliary bodies 3 formed with nose cone shell 1 two from
By spending space development agency, realize the elongation for the nose cone shell for being similar to the deformation of honeybee abdomen and curved movement, and only need
Driving above and below first order nose cone at drive rod two to be installed, controls the rotary motion of two drive rods that integrated machine can be realized
The elongation of structure and bending motion.
Motion control of the present invention is flexible, and drive form is simple, and the extended length and deflection angle of nose cone amoeboid movement are accurate
Controllably, the technology requirement of aircraft under various circumstances can be met, and occupied space is few inside nose cone, it is parallel up and down
Quadrangle is driven the back of the body web that the design reference of the auxiliary ball vice mechanism of linkage mechanism and both sides honeybee abdomen realizes deformation
The structure of connection structure and intersegmental fold, bionical is with obvious effects.
Description of the drawings
Fig. 1 is the overall structure diagram of this embodiment of the present invention.
Fig. 2 is the side view of the embodiment of the present invention.
Fig. 3 is the top view of the embodiment of the present invention.
Fig. 4 is the schematic diagram of third and fourth grade of junction of the embodiment of the present invention.
Fig. 5 is the sectional view of third and fourth grade of junction of the embodiment of the present invention.
Specific embodiment
The present invention is described in detail with reference to the accompanying drawings and examples.
With reference to Fig. 1, a kind of aircraft deformation nose cone device based on two degrees of freedom space development agency, including nose cone shell
1st, elongation bending linkage mechanism 2 and auxiliary ball vice mechanism 3, wherein, nose cone shell 1 is divided into six grades altogether, first order nose cone shell
1A is the cylindric of diameter maximum, successively decreases from the second to six grade of nose cone housing diameter, and is round table-like, the 6th grade of nose cone shell
Outermost end has spherical crown feature, is connected between nose cone shell by extending bending linkage mechanism 2 and auxiliary ball vice mechanism 3.
With reference to Fig. 2, what the elongation bending linkage mechanism 2 was symmetrically installed by two groups on nose cone shell horizontal flange
Elongation bending leverage composition, each group of elongation bending leverage include four groups of parallelogram and are driven leverage, four groups of parallelogram
The input of transmission leverage is connected with drive rod 2A, the drive link 2C of upper level, four groups of parallelogram transmission leverages of afterbody
Output connected with foot piece 2D, be connected with chopped-off head drive rod 2A in first order nose cone shell, connection in afterbody nose cone shell
There is foot piece 2D.
With reference to Fig. 2, Fig. 4 and Fig. 5, parallelogram transmission leverage includes the drive rod 2A of upper level, drive rod
2A and quarter butt 2B in parallel are installed on the vertical split of nose cone shell, the installation site of other two quarter butt 2B
Then in drive rod 2A both sides, one end is hinged at hole and stomidium respectively with drive rod 2A in its center, the other end one and nose cone
Shell is hinged at hinge base, and the one side of a quarter butt 2B at nose cone shell vertical split is hinged with its one end, transmission
Bar 2C is hinged in quarter butt 2B one sides and drive rod 2A one sides with the two respectively；
Four are stock before the drive rod 2A, are hinged respectively with first to fourth grade of nose cone shell at hinge seat,
The last one drive rod 2A is hinged for quarter butt with level V nose cone shell at hinge base, the narrow one end of foot piece 2D and afterbody head
Bore cage connection.
With reference to Fig. 3, Fig. 4 and Fig. 5, totally two groups of the auxiliary ball vice mechanism 3 is symmetrical on nose cone shell vertical split
Distributing installation, each group of auxiliary ball vice mechanism 3 includes four identical auxiliary balls pairs and one auxiliary with ball pair foot piece 3D
Ball pair is helped, auxiliary ball is secondary to include ball pair sphere 3A, band club 3B or ball pair foot piece 3D, ball slave connecting rod 3C and ball pair upper cover
3E, ball pair sphere 3A with being connected through a screw thread with club 3B or ball pair foot piece 3D, ball pair sphere 3A and ball pair upper cover 3E and
Hemisphere cavity feature in nose cone shell 1 forms ball auxiliary structure；Band club 3B or ball pair foot piece 3D is cut with scissors with ball slave connecting rod 3C one end
It connects, the ball slave connecting rod 3C other ends are hinged with nose cone shell 1 at its hinge base.
The present invention operation principle be：
The present invention there are two whole driving, is promoted in first order nose cone shell by hydraulic push rod driving device respectively altogether
Two drive rod 2A up and down at first order nose cone shell are rotated, according to nose cone shell, elongation bending linkage mechanism and auxiliary
The motion principle of the two degrees of freedom space development agency of ball vice mechanism composition, when two drive rod 2A are identical from initial position rotation
During angle, nose cone shell 1 will realize the movement of elongation under the promotion of the leverage of linkage.If two drive rod 2A differential outputs,
Then rotating different angles along identical or different direction in symmetrical POS INT can realize that the elongation of nose cone entirety is curved
Bending motion bent, contraction is bent or length is constant, the direction of bending motion can upwardly or downwardly, this is depended primarily upon
The postrotational relative positions of drive rod 2A at first order nose cone shell.Due to extending the distance for the promotion for bending leverage up and down not
Together, nose cone can realize curved movement, i.e. nose cone integrally realizes the movement of rotation around ball pair in vertical plane.
Drive system of the present invention is simple, and integrated model motion stabilization is reliable.Calculating discovery is carried out according to mechanical motion principle,
Present invention deformation nose cone device can realize various deformation mode, can be with by adjusting different drive rod Differential Driving parameters
The different distortion of nose cone device is obtained as a result, stretching motion can both be implemented separately, can also only be realized on the basis of elongation
Bending motion can also realize stretching motion and bending motion simultaneously.
Claims (3)
1. a kind of aircraft deformation nose cone device based on two degrees of freedom space development agency, it is characterised in that：Outside including nose cone
Shell (1), elongation bending linkage mechanism (2) and auxiliary ball vice mechanism (3), wherein, nose cone shell (1) is divided into more than three-level altogether,
First order nose cone shell (1A) is cylindric for diameter maximum, and intergrade nose cone housing diameter successively decreases, and is round table-like, most end
Grade nose cone shell outermost end has spherical crown feature, passes through elongation bending linkage mechanism (2) and auxiliary ball vice mechanism between nose cone shell
(3) connect；
The elongation bent stick that the elongation bending linkage mechanism (2) is symmetrically installed by two groups on nose cone shell horizontal flange
It is composition, each group of elongation bending leverage includes four groups of parallelogram and be driven leverages, and four groups of parallelogram are driven leverage
The drive rod (2A) of input and upper level, (2C) are hinged, the output of four groups of parallelogram transmission leverages of afterbody and foot piece
(2D) is hinged, and chopped-off head drive rod (2A) is hinged in first order nose cone shell, foot piece is hinged in afterbody nose cone shell
(2D)。
2. a kind of aircraft deformation nose cone device based on two degrees of freedom space development agency according to claim 1,
It is characterized in that：Described parallelogram transmission leverage includes the drive rod (2A) of upper level, drive rod (2A) and is put down with it
Capable quarter butt (2B) is installed on the vertical split of nose cone shell, and the installation site of other two quarter butt (2B) is then in stock
(2A) both sides, one end is distinguished to be hinged at hole in its center and stomidium with drive rod (2A), and the other end one exists with nose cone shell
It is hinged at hinge base, the one side of a quarter butt (2B) at nose cone shell vertical split is hinged with its one end, drive link
(2C) is hinged in quarter butt (2B) one side and drive rod (2A) one side with the two respectively.
3. a kind of aircraft deformation nose cone device based on two degrees of freedom space development agency according to claim 1,
It is characterized in that：Totally two groups of the auxiliary ball vice mechanism (3), it is each on the symmetrical installation of nose cone shell vertical split
Group auxiliary ball vice mechanism (3) includes four identical auxiliary balls pairs and an auxiliary ball pair for carrying ball pair foot piece (3D), auxiliary
Help ball is secondary to include ball pair sphere (3A), band club (3B) or ball pair foot piece (3D), ball slave connecting rod (3C) and ball pair upper cover
(3E), ball pair sphere (3A) with club (3B) or ball pair foot piece (3D) with being connected through a screw thread, ball pair sphere (3A) and ball pair
Hemisphere cavity feature in upper cover (3E) and nose cone shell (1) forms ball auxiliary structure；Band club (3B) or ball pair foot piece (3D)
Hinged with ball slave connecting rod (3C) one end, ball slave connecting rod (3C) other end is hinged with nose cone shell (1) at its hinge base.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711286667.2A CN108045548B (en) | 2017-12-07 | 2017-12-07 | Aircraft deformation nose cone device based on space two-degree-of-freedom extensible mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711286667.2A CN108045548B (en) | 2017-12-07 | 2017-12-07 | Aircraft deformation nose cone device based on space two-degree-of-freedom extensible mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108045548A true CN108045548A (en) | 2018-05-18 |
| CN108045548B CN108045548B (en) | 2020-07-14 |
Family
ID=62123249
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711286667.2A Active CN108045548B (en) | 2017-12-07 | 2017-12-07 | Aircraft deformation nose cone device based on space two-degree-of-freedom extensible mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108045548B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114313216A (en) * | 2022-02-18 | 2022-04-12 | 上海力鸿航空科技有限公司 | Bending and twisting movement mechanism based on bidirectional bending scissor rod mechanism |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101870352A (en) * | 2010-06-29 | 2010-10-27 | 北京邮电大学 | Deformation mechanism for underwater robots |
| CN102490878A (en) * | 2011-11-25 | 2012-06-13 | 北京航空航天大学 | Single-degree-of-freedom symmetrical type swing-driven underwater robot recovery device with large expansion ratio |
| CN106275368A (en) * | 2016-10-28 | 2017-01-04 | 清华大学 | A kind of bionic Aircraft deformation nose cone device driven based on marmem |
| CN106741822A (en) * | 2016-11-04 | 2017-05-31 | 清华大学 | Aircraft deformation nose cone containing parallel institution |
-
2017
- 2017-12-07 CN CN201711286667.2A patent/CN108045548B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101870352A (en) * | 2010-06-29 | 2010-10-27 | 北京邮电大学 | Deformation mechanism for underwater robots |
| CN102490878A (en) * | 2011-11-25 | 2012-06-13 | 北京航空航天大学 | Single-degree-of-freedom symmetrical type swing-driven underwater robot recovery device with large expansion ratio |
| CN106275368A (en) * | 2016-10-28 | 2017-01-04 | 清华大学 | A kind of bionic Aircraft deformation nose cone device driven based on marmem |
| CN106741822A (en) * | 2016-11-04 | 2017-05-31 | 清华大学 | Aircraft deformation nose cone containing parallel institution |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114313216A (en) * | 2022-02-18 | 2022-04-12 | 上海力鸿航空科技有限公司 | Bending and twisting movement mechanism based on bidirectional bending scissor rod mechanism |
| CN114313216B (en) * | 2022-02-18 | 2023-12-15 | 上海力鸿航空科技有限公司 | Bending and twisting movement mechanism based on bidirectional bending scissor rod mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108045548B (en) | 2020-07-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106976550A (en) | A kind of aircraft gas rudder and airvane link gear | |
| CN102616376B (en) | Composite rotors | |
| CN104828245B (en) | Aircraft | |
| CN106184826B (en) | Satellite and the rocket spring separator | |
| CN108313268A (en) | A kind of light aerocraft Aileron control system | |
| CN104290902A (en) | Rocking arm-type undercarriage | |
| CN108045548A (en) | A kind of aircraft deformation nose cone device based on space two degrees of freedom development agency | |
| CN109153440A (en) | Aircraft with the wing elements for reducing load | |
| CN105947185A (en) | Low-friction spring load mechanism | |
| CN108773473B (en) | Aircraft variant nose cone based on multi-ring closed-chain space deployable mechanism | |
| CN203473238U (en) | Missile aileron control mechanism | |
| US20140353433A1 (en) | Rotorcraft flight control stick tiltably mounted on a support by a flexible rod with a fixed end | |
| US10590911B2 (en) | Hybrid rolling bridle system for distributing load while permitting freedom of rotation | |
| CN107902069B (en) | Single-drive multi-stage linkage bionic variant aircraft nose cone device | |
| GB183023A (en) | Improvements in aeroplanes | |
| CN205548103U (en) | Adjustable bed | |
| CN108910011A (en) | It is a kind of containing can the aircraft that can open up of space of nested merogenesis shell deform nose cone | |
| US1656492A (en) | Flying machine | |
| US1334707A (en) | Aerodynamic stabilizer | |
| CN106516105A (en) | Aircraft propeller surface regulating mechanism | |
| CN106938707B (en) | A kind of unmanned helicopter subtest and assisting in flying facility for study | |
| CN206331994U (en) | The mounting bracket of fuse switch | |
| KR20150106989A (en) | Variable span morphing wing | |
| CN205049312U (en) | Control surface torgue measurement structure | |
| US7244162B2 (en) | Model stick plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |