CN105383683B - A kind of three-stage shock resistance type unmanned plane wing - Google Patents
A kind of three-stage shock resistance type unmanned plane wing Download PDFInfo
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- CN105383683B CN105383683B CN201510807774.XA CN201510807774A CN105383683B CN 105383683 B CN105383683 B CN 105383683B CN 201510807774 A CN201510807774 A CN 201510807774A CN 105383683 B CN105383683 B CN 105383683B
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- wing
- steering wheel
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- framework
- trapezoidal sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/20—Integral or sandwich constructions
Abstract
The invention belongs to unmanned air vehicle technique field; it is related to a kind of three-stage shock resistance type unmanned plane wing; wing is constituted by wing framework, carbon fibre composite covering and foam; set protection formula can Automatic-falling structure, embedded steering wheel mounting structure on wing; embedded steering wheel mounting structure embeds steering wheel; steering wheel by steering wheel line connect protection formula can Automatic-falling structure, the downside of embedded steering wheel mounting structure sets the steering wheel connection rectangular section aileron in rectangular section aileron, embedded steering wheel mounting structure；The wing solid light structure, greatly improves the surface strength and front impact resistance of wing.Simultaneously protect formula can Automatic-falling structure one end be provided with fixed interface; the other end is provided with electrical apparatus interface; fixed interface is fixed on rectangle piece housing; airborne equipment in the electric interfaces connection fuselage of the other end, need to only take out the electric interfaces in fuselage the fixed interface that docking is fixed on rectangle piece housing when using.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, it is related to a kind of three-stage shock resistance type unmanned plane wing.
Background technology
Wing is one of important component of unmanned plane, and its main function is to produce lift.The design of wing, which is removed, need to meet machine
Outside the structural strength of the wing, construction weight is also as light as possible, and dismounting is simply readily transported.
Existing small and medium size unmanned aerial vehicles have the disadvantages that：Unmanned plane adds fiberglass covering type to design using beam, rib, wing
The fragile fragile impact resistance of heavier-weight and surface is poor；Wing electric interfaces are typically connected or self-locking electricity using screw
Gas interface, aircraft wing in rough land, which departs from, is easily damaged electric interfaces and airborne equipment.
The content of the invention
The technical problem to be solved in the present invention is to provide a kind of both Simple, lights, net collision recovery requirement can be met again, and can
It is quick to use the unmanned plane wing installed.
In order to solve the above-mentioned technical problem, technical scheme is as follows：
A kind of three-stage shock resistance type unmanned plane wing, including 2 trapezoidal sections wing housings, 2 trapezoidal sections Vierendeel girders, 2
Trapezoidal sections wing bulkhead, 2 connection units, 1 rectangle piece housing, 1 rectangular section Vierendeel girder, 1 rectangular section wing bulkhead, 2
Individual embedded steering wheel mounting structure, protection formula can Automatic-falling structure and 2 rectangular section ailerons；
Wherein, 1 trapezoidal sections wing housing, 1 trapezoidal sections Vierendeel girder, 1 trapezoidal sections wing bulkhead constitute left section of wing frame
Frame, covers one layer of carbon fibre composite covering outside left section of wing framework, in left section of wing framework lumen loading foam, left
Section wing framework, carbon fibre composite covering and foam constitute left section of wing；
1 trapezoidal sections wing housing, 1 trapezoidal sections Vierendeel girder, 1 trapezoidal sections wing bulkhead constitute right section of wing framework,
One layer of carbon fibre composite covering of covering outside right section of wing framework, in right section of wing framework lumen loading foam, right section of machine
Wing framework, carbon fibre composite covering and foam constitute right section of wing；
1 rectangle piece housing, 1 rectangular section Vierendeel girder and 1 rectangular section wing bulkhead composition stage casing wing framework, in
One layer of carbon fibre composite covering of covering outside section wing framework, in stage casing wing framework lumen loading foam, stage casing wing
Framework, carbon fibre composite covering and foam constitute stage casing wing；
Left section of wing and right section of wing connect stage casing wing by 1 connection unit respectively and constitute complete wing；
Set on rectangle piece housing protection formula can Automatic-falling structure, while the both sides of rectangle piece housing set 2 to embed
Formula steering wheel mounting structure, embedded steering wheel mounting structure embeds steering wheel, and steering wheel connects protection formula by steering wheel line can Automatic-falling
Structure, the downside of 2 embedded steering wheel mounting structures sets the steering wheel in 2 rectangular section ailerons, embedded steering wheel mounting structure
Connect rectangular section aileron；
The protection formula can Automatic-falling structure one end be provided with fixed interface, the other end be provided with electrical apparatus interface, fixed interface
It is fixed on rectangle piece housing 5, the airborne equipment in the electric interfaces connection fuselage of the other end.
Further, the composition structure of the trapezoidal sections Vierendeel girder and rectangular section Vierendeel girder be carbon composite shell+
Wood materials sandwich+carbon composite shell.
Further, the connection unit is composed of by latch with guide, and latch is plinth, itself and rectangle segment frames
Beam is fixedly connected, and guide is fixedly connected with trapezoidal sections wing bulkhead, and latch is provided with a groove, groove mounting O-shaped rings.
The present invention is by wing framework (including left section of wing framework, right section of wing framework and stage casing wing framework), carbon fiber
The wing that composite material skin and foam are constituted is solid light structure, greatly improves surface strength and the front of wing
Impact resistance；Simultaneously protection formula can one end of Automatic-falling structure be fixed on rectangular section housing lower surface, the other end uses easy
Depart from the airborne equipment in quick grafting electric interfaces connection fuselage, the electric interfaces in fuselage need to only be taken out during use
To dock the fixed interface being fixed on rectangle piece housing.Very convenient and dependable performance, aircraft landing is by collision opportunity
The wing departs from, and electric interfaces can automatically be disengaged, wing, electric interfaces and airborne equipment protected, it is ensured that the said equipment will not
Damage is caused by impact.
Brief description of the drawings
Fig. 1 is the structural representation of three-stage shock resistance type unmanned plane wing of the present invention；
Fig. 2 is the Structure explosion diagram of three-stage shock resistance type unmanned plane wing of the present invention；
Fig. 3 is the diagrammatic cross-section of left section of wing of the invention；
Fig. 4 is left section of wing of the present invention and the structural representation of right section of wing junction；
Fig. 5 is the structural representation of connection unit of the present invention.
Specific embodiment
The present invention is described further below in conjunction with the accompanying drawings.
A kind of three-stage shock resistance type unmanned plane wing, as depicted in figs. 1 and 2, including 2 trapezoidal sections wing housings 1,2
Trapezoidal sections Vierendeel girder 2,2 trapezoidal sections wing bulkheads 3,2 connection units 4,1 rectangle piece housing 5,1 rectangular section Vierendeel girder
6th, 1 rectangular section wing bulkhead 7,2 embedded steering wheel mounting structures 8, protection formula can Automatic-falling structure 9 and 2 rectangular sections
Aileron 11；
Wherein, 1 trapezoidal sections wing housing 1,1 serve the trapezoidal sections Vierendeel girder 2 of main stress, 1 play a supportive role
Trapezoidal sections wing bulkhead 3 constitutes left section of wing framework, is answered as shown in figure 3, covering one layer of carbon fiber outside left section of wing framework
Condensation material covering 12, in left section of wing framework lumen loading foam 10, left section of wing framework, the and of carbon fibre composite covering 12
Foam 10 constitutes left section of wing；
1 trapezoidal sections wing housing 1,1 play the trapezoidal sections Vierendeel girder 2 of main stress, 1 trapezoidal sections for playing a supportive role
Wing bulkhead 3 constitutes right section of wing framework, one layer of carbon fibre composite covering 12 is covered outside right section of wing framework, on the right side
Section wing framework lumen loading foam 10, right section of wing framework, carbon fibre composite covering 12 and foam 10 constitute right section of machine
The wing；
1 rectangle piece housing 5,1 play main stress rectangular section Vierendeel girder 6 and 1 rectangular section played a supportive role
Wing bulkhead 7 constitutes stage casing wing framework, one layer of carbon fibre composite covering 12 is covered outside the wing framework of stage casing, in
Section wing framework lumen loading foam 10, stage casing wing framework, carbon fibre composite covering 12 and foam 10 constitute stage casing machine
The wing；
Left section of wing and right section of wing connect stage casing wing by 1 connection unit 4 respectively and constitute complete wing；
Because carbon fibre composite has the advantages that axial strength and modulus are high, density is low and fatigue performance is good, carbon
Fibrous composite covering strong shock resistance and lightweight.
Therefore, wing framework (including left section of wing framework, right section of wing framework and stage casing wing framework), carbon fiber are combined
The wing that material covering 12 and foam 10 are constituted is solid light structure, greatly improves surface strength and the front of wing
Impact resistance.
As shown in figure 4, set on rectangle piece housing 5 protection formula can Automatic-falling structure 9, while the two of rectangle piece housing 5
Side sets 2 embedded steering wheel mounting structures 8, and embedded steering wheel mounting structure 8 embeds steering wheel, and steering wheel is connected by steering wheel line and protected
Shield formula can 9,2 embedded steering wheel mounting structures 8 of Automatic-falling structure downside set 2 rectangular section ailerons 11, embedded rudder
Steering wheel connection rectangular section aileron 11 in machine mounting structure 8；The protection formula can the one end of Automatic-falling structure 9 provided with fixation connect
Mouthful, the other end is provided with electrical apparatus interface, and fixed interface is fixed on rectangle piece housing 5, in the electric interfaces connection fuselage of the other end
Airborne equipment.
Protection formula can one end of Automatic-falling structure 9 be fixed on the lower surface of rectangle piece housing 5, the other end is using easily departing from fast
Electric interfaces in fuselage need to only be taken out docking by the airborne equipment in fast grafting electric interfaces connection fuselage during use
It is fixed on the fixed interface on rectangle piece housing 5.It is not only efficient and convenient, and dependable performance；Aircraft landing is by collision opportunity
The wing departs from, and electric interfaces can automatically be disengaged, wing, electric interfaces and airborne equipment protected, it is ensured that the said equipment will not
Damage is caused by impact, it is adaptable to wipe ground way of recycling.
Rectangular section aileron 11 is arranged on the rectangle piece housing 5 of rectangular section wing (i.e. stage casing wing) so that need not be
The electric interfaces of docking are installed on trapezoidal sections wing (left section and right section of wing), trapezoidal sections wing and rectangular section wing pair is reduced
The electric interfaces connect.Need to set electric interfaces in joint during compared to the design of existing aileron rudder face on trapezoidal sections wing,
It is hardly damaged when simple and storage is installed.
As shown in figure 5, the connection unit 4 is composed of by latch 42 with guide 41, latch 42 is plinth, its with
Rectangular section Vierendeel girder 6 is fixedly connected, and guide 41 is fixedly connected with trapezoidal sections wing bulkhead 3, and latch 42 is provided with a groove, groove
Mounting O-shaped rings 13.Plinth is easy to be connected with rectangular section Vierendeel girder 6, its groove mounting O-shaped rings 13, with guide 41
Compare fastening during docking.Fast Installation mode is that latch 42 is directly inserted along guide 41, fastens and eliminates pair by O-ring 13
Gap after connecing.It is many compared to the splicing of existing wing to add screw to fix this mode using latch, install simple and save the time.
Preferably, the composition structure of the trapezoidal sections Vierendeel girder 2 and rectangular section Vierendeel girder 6 is carbon composite shell
+ wood materials sandwich+carbon composite shell, its lightweight rigidity is big, improves the rigidity and intensity of wing, simultaneously weight
Amount is very light.
Claims (3)
1. a kind of three-stage shock resistance type unmanned plane wing, the unmanned plane wing includes：2 trapezoidal sections wing housings (1), 2
Connection unit (4), 1 rectangle piece housing (5), 1 rectangular section Vierendeel girder (6), it is characterised in that the unmanned plane wing is also wrapped
Include：2 trapezoidal sections Vierendeel girders (2), 2 trapezoidal sections wing bulkheads (3), 1 rectangular section wing bulkhead (7), 2 embedded steering wheels
Mounting structure (8), protection formula can Automatic-falling structure (9) and 2 rectangular section ailerons (11)；
Wherein, 1 trapezoidal sections wing housing (1), 1 trapezoidal sections Vierendeel girder (2), 1 trapezoidal sections wing bulkhead (3) constitute left section of machine
Wing framework, one layer of carbon fibre composite covering (12) is covered outside left section of wing framework, is filled out left section of wing framework inner chamber
Fill foam (10), left section of wing framework, carbon fibre composite covering (12) and foam (10) constitute left section of wing；
1 trapezoidal sections wing housing (1), 1 trapezoidal sections Vierendeel girder (2), 1 trapezoidal sections wing bulkhead (3) constitute right section of wing frame
Frame, covers one layer of carbon fibre composite covering (12) outside right section of wing framework, in right section of wing framework lumen loading bubble
Foam (10), right section of wing framework, carbon fibre composite covering (12) and foam (10) constitute right section of wing；
1 rectangle piece housing (5), 1 rectangular section Vierendeel girder (6) and 1 rectangular section wing bulkhead (7) composition stage casing wing frame
Frame, covers one layer of carbon fibre composite covering (12) outside the wing framework of stage casing, and in stage casing, wing framework lumen loading steeps
Foam (10), stage casing wing framework, carbon fibre composite covering (12) and foam (10) constitute stage casing wing；
Left section of wing and right section of wing connect stage casing wing by 1 connection unit (4) respectively and constitute complete wing；
Set on rectangle piece housing (5) protection formula can Automatic-falling structure (9), while the both sides of rectangle piece housing (5) set 2
Embedded steering wheel mounting structure (8), embedded steering wheel mounting structure (8) embeds steering wheel, and steering wheel connects protection formula by steering wheel line
Can Automatic-falling structure (9), the downside of 2 embedded steering wheel mounting structures (8) sets 2 rectangular section ailerons (11), embedded
Steering wheel connection rectangular section aileron (11) in steering wheel mounting structure (8)；
The protection formula can Automatic-falling structure (9) one end be provided with fixed interface, the other end is provided with electrical apparatus interface, and fixed interface is solid
It is scheduled on rectangle piece housing (5), the airborne equipment in the electric interfaces connection fuselage of the other end.
2. a kind of three-stage shock resistance type unmanned plane wing according to claim 1, it is characterised in that the trapezoidal sections frame
Set a roof beam in place (2) and the composition structure of rectangular section Vierendeel girder (6) is multiple for carbon composite shell+wood materials sandwich+carbon fiber
Condensation material shell.
3. a kind of three-stage shock resistance type unmanned plane wing according to claim 1, it is characterised in that the connection unit
(4) it is composed of by latch (42) with guide (41), latch (42) is plinth, itself and rectangular section Vierendeel girder (6) are fixed and connected
Connect, guide (41) is fixedly connected with trapezoidal sections wing bulkhead (3), latch (42) is provided with a groove, groove mounting O-shaped rings
(13)。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510807774.XA CN105383683B (en) | 2015-11-12 | 2015-11-12 | A kind of three-stage shock resistance type unmanned plane wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510807774.XA CN105383683B (en) | 2015-11-12 | 2015-11-12 | A kind of three-stage shock resistance type unmanned plane wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105383683A CN105383683A (en) | 2016-03-09 |
| CN105383683B true CN105383683B (en) | 2017-08-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510807774.XA Active CN105383683B (en) | 2015-11-12 | 2015-11-12 | A kind of three-stage shock resistance type unmanned plane wing |
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| Country | Link |
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| CN (1) | CN105383683B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105836102B (en) * | 2016-06-07 | 2018-06-08 | 广州天海翔航空科技有限公司 | A kind of high performance mini plateau scounting aeroplane |
| CN106043660A (en) * | 2016-06-07 | 2016-10-26 | 广州天海翔航空科技有限公司 | High-performance unmanned aerial vehicle applicable to seaside salt mist area |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2550146A1 (en) * | 2002-12-09 | 2004-07-22 | University Of Florida | Bendable wing for micro air vehicle |
| EP1666356A1 (en) * | 2003-08-25 | 2006-06-07 | Kawada Industries, Inc. | Small unmanned aircraft |
| CN201800914U (en) * | 2010-09-07 | 2011-04-20 | 西安翔宇航空科技股份有限公司 | Unmanned aerial vehicle platform wing |
| CN102858630A (en) * | 2010-04-19 | 2013-01-02 | 加特温股份有限公司 | A wing for an unmanned aircraft |
| CN204527611U (en) * | 2015-03-12 | 2015-08-05 | 江苏艾锐泰克无人飞行器科技有限公司 | A kind of quick release installs fixed-wing unmanned vehicle |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7377832B2 (en) * | 2003-01-09 | 2008-05-27 | Mark Spencer Chamberlain | Electric powered flying wing toy |
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2015
- 2015-11-12 CN CN201510807774.XA patent/CN105383683B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2550146A1 (en) * | 2002-12-09 | 2004-07-22 | University Of Florida | Bendable wing for micro air vehicle |
| EP1666356A1 (en) * | 2003-08-25 | 2006-06-07 | Kawada Industries, Inc. | Small unmanned aircraft |
| CN102858630A (en) * | 2010-04-19 | 2013-01-02 | 加特温股份有限公司 | A wing for an unmanned aircraft |
| CN201800914U (en) * | 2010-09-07 | 2011-04-20 | 西安翔宇航空科技股份有限公司 | Unmanned aerial vehicle platform wing |
| CN204527611U (en) * | 2015-03-12 | 2015-08-05 | 江苏艾锐泰克无人飞行器科技有限公司 | A kind of quick release installs fixed-wing unmanned vehicle |
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| Publication number | Publication date |
|---|---|
| CN105383683A (en) | 2016-03-09 |
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