CN106585951A - Folding structure and aircraft - Google Patents
Folding structure and aircraft Download PDFInfo
- Publication number
- CN106585951A CN106585951A CN201611129120.7A CN201611129120A CN106585951A CN 106585951 A CN106585951 A CN 106585951A CN 201611129120 A CN201611129120 A CN 201611129120A CN 106585951 A CN106585951 A CN 106585951A
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- fuselage
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- symmetry
- plane
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- 230000005484 gravity Effects 0.000 claims description 3
- 230000002441 reversible effect Effects 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 208000031481 Pathologic Constriction Diseases 0.000 description 1
- 238000005194 fractionation Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 210000001215 vagina Anatomy 0.000 description 1
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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a folding structure and an aircraft. The folding structure comprises a first connecting piece, a second connecting piece and a locking piece. The first connecting piece and the second connecting piece are hinged. The first connecting piece or the second connecting piece is sleeved with a locking piece. The second connecting piece can be reversibly rotated to the unfolded state from the folded state; when the second connecting piece is in the unfolded state, the first connecting piece and the second connecting piece are coaxial and do not coincide, and at the moment, the locking piece slides to the position where the first connecting piece and the second piece are hinged and is locked so that the second connecting piece can be kept in the unfolding state.
Description
Technical field
The present invention relates to a kind of foldable structure and the aircraft with foldable structure.
Background technology
Chinese patent (CN201510450014) discloses a kind of Fixed Wing AirVehicle of many rotor VTOL, takes into account
The flight characteristics of Fixed Wing AirVehicle and multi-rotor aerocraft, such as has hovering ability, and to runway without dependence, and zero velocity rises
Fly the advantages of landing, and with higher horizontal flight speed, and there is bigger voyage.In addition, above-mentioned flight
Device has also combined the structure of Fixed Wing AirVehicle and multi-rotor aerocraft, specifically includes fuselage, wing and empennage, arranges on fuselage
There are preposition propeller or rear-mounted propeller, wherein preposition propeller is arranged on the front end of fuselage, and level drawing is produced to aircraft
Power, rear-mounted propeller is arranged on the rear end of fuselage, and produces horizontal thrust to aircraft, is additionally provided with wing or fuselage multiple
Rotor, is provided with the propeller that longitudinal force is produced to aircraft on each rotor, so far, make what the structure of aircraft became to answer
It is miscellaneous, and then the installation to aircraft and transport bring very big inconvenience.
In order to solve the above problems, existing aircraft adopts dismountable mode, such as aircraft of Double-edge type wing
In, two wings are detachably connected on respectively the both sides of fuselage by spar, and empennage is by the securing member such as bolt or latch and machine
Body is detachably connected, and rotor is detachably connected by securing member with fuselage or wing；And in the aircraft of three-stage wing, stage casing
Wing is connected with fuselage by securing member, and two outer section wings are connected to respectively the both sides of stage casing wing by spar, and rotor is removable
Unload or non-dismountable installed in stage casing wing and the junction of outer section of wing, therefore when aircraft is conveyed, can be to aircraft
Each assembly carries out fractionation transport, but in assembling, needs to find corresponding assembly and assembled, can aircraft peace
Dress is made troubles.
The content of the invention
The main object of the present invention there is provided a kind of simple structure, and install the folding structure and tool with convenient transportation
There is the aircraft of foldable structure.
To reach object above, the invention provides a kind of foldable structure, including the first connector, the second connector and lock
Tight part, first connector and second connector are hinged, the locking member be set in first connector or
On second connector, second connector can reversibly turn to deployed condition from folded state, in deployed condition,
Second connector is coaxial with first connector and misaligned setting, and now, the locking member slides into described first
The hinged place of connector and second connector is simultaneously locked, and makes second connector keep deployed condition.
Further, the locking member is set on second connector, and second connector connects with described first
One end outside that fitting is hinged is provided with the first cooperation section, and one end that first connector is hinged with second connector is prolonged
Stretching has the second cooperation section, and when second connector turns to deployed condition, the second cooperation section is fastened on described second
The outside of connector, and the second cooperation section and the first cooperation section cooperatively form external screw thread, the external screw thread with it is described
Locking member is threadedly coupled.
Further, finite place piece is arranged on first connector, the locating part is hinged with second connector, and
The locating part coordinates section adjacent with described second.
Further, first connector and second connector are pipe.
Present invention also offers a kind of aircraft, including a fuselage, a wing and an at least rotor, the wing is arranged on
On the fuselage, the rotor includes the first motor and the first propeller, and first motor drives first propeller to turn
Longitudinal lift of the movable property life to the aircraft, first motor connects the fuselage or the wing by foldable structure,
Wherein described first connector connects the fuselage or the wing, and second connector connects first motor.
Further, the center of gravity that the fuselage has a plane of symmetry, the axis of the fuselage and the aircraft is respectively positioned on institute
State on the plane of symmetry of fuselage；
The quantity of the rotor is four, and rotor described in two of which is arranged on the first side of the fuselage plane of symmetry, separately
Two rotors are arranged on the second side of the fuselage plane of symmetry, and are arranged on two institutes of the side of the fuselage plane of symmetry first
Two rotors stated rotor and be arranged on the side of the fuselage plane of symmetry second are symmetrical arranged along the fuselage plane of symmetry, position
Two rotors in described fuselage plane of symmetry the same side are located at respectively the both sides of the wing；
Each described rotor passes through respectively foldable structure described in and connects the wing, the axle of four first connectors
Line is parallel to each other with the fuselage axis, in folded state, between second connector and first connector
Angle is 90 °, and each described second connector is towards the plane of symmetry of the fuselage.
Further, two second connectors positioned at described fuselage plane of symmetry the same side are integrated.
Further, the wing includes one first wing and two second wings, and first wing is fixed on the fuselage
On, the second wing described in two is respectively hinged at the both sides of first wing, and the second wing described in two respectively along the machine
The plane of symmetry of body is symmetrical arranged；
First wing to connect and be provided with fixture on the end face of described second wing one end, arranges on the fixture
There are two first collars, two first set ring sets are located on second connector, second wing connection described the
Revolving part is fixed with the end face of one wing one end, two second collars are provided with the revolving part, two described second set
Ring set is located on second connector；
At least one first annulus are provided with the fixture, at least one second circles are provided with the revolving part
Ring, second wing can go to folded state from deployed condition is reversible, in deployed condition, first wing and described
Two wings are coaxial and misaligned setting, and first annulus is corresponding with second annulus, is now distinguished by latch
Through first annulus and second annulus, second wing is set to keep deployed condition, in folded state, described second
Wing is located at the downside of first wing.
Further, the second motor is provided with the fuselage, the output shaft of second motor is connected with the second propeller,
Second propeller is located at the head of the fuselage；
The afterbody of the fuselage is connected with empennage by the foldable structure, wherein first connector connects the machine
Body, second connector connects the empennage, and in folded state, second connector is located at the upside of the fuselage, and
The axis of second connector is located on the fuselage plane of symmetry.
Further, the empennage is V-shaped, and opening upwards.
According to preferred embodiment, the invention provides following advantage：
(1) the first connector and the second connector of the invention are connected together all the time, effectively prevent losing for part
Lose and extend the time of part of finding, and effectively increase component efficiency.
(2) rotor of aircraft of the present invention can connect fuselage or wing by foldable structure, and empennage can pass through foldable structure
Connection fuselage, makes the volume after aircraft folded state diminish, and is readily transported and assembles.
The present invention is further illustrated below in conjunction with drawings and Examples.
Description of the drawings
Fig. 1 is the folded state structural representation of foldable structure of the present invention；
Fig. 2 is the deployed condition structural representation of foldable structure of the present invention；
Fig. 3 is the folded state structural representation of aircraft of the present invention；
Fig. 4 is the deployed condition structural representation of aircraft of the present invention；
Fig. 5 is the folded state structural representation of wing of the present invention；
Fig. 6 is the deployed condition structural representation of wing of the present invention.
Specific embodiment
Hereinafter describe for disclosing the present invention so that those skilled in the art can realize the present invention.It is excellent in below describing
Embodiment is selected to be only used as citing, it may occur to persons skilled in the art that other obvious modifications.Define in the following description
Ultimate principle of the invention can apply to other embodiments, deformation program, improvement project, equivalent and without the back of the body
From the other technologies scheme of the spirit and scope of the present invention.
Refering to accompanying drawing 1 and Fig. 2, a kind of foldable structure according to the preferred embodiment of the present invention, including first are shown
Connector 1, the second connector 6 and locking member 5, the first connector 1 and the second connector 6 are hinged, and locking member 5 is set in
On the connector 6 of a connection piece 1 or second, the second connector 6 can reversibly turn to deployed condition, angle of rotation from folded state
Degree can be 0 °～180 °, in deployed condition, as shown in Fig. 2 the second connector 6 and the coaxial and misaligned setting of the first connector 1,
Now, locking member 5 slides into the hinged place of the first connector 1 and the second connector 6 and locks, and makes the holding exhibition of the second connector 6
Open state, when the second connector 6 is deformed into folded state from deployed condition, locking member 5 skids off the first connector 1 and second and connects
The hinged place of fitting 6, makes the first connector 1 and the second connector 6 by being hinged foldings, is easy to storage to transport, additionally, due to the
The connector 6 of a connection piece 1 and second is connected together all the time, effectively prevents the loss of part and extends and find part
Time, and effectively increase component efficiency.
First connector 1 and the second connector 6 are pipe, and locking member 5 is in a ring.
Locking member 5 is set on the second connector 6, and one end outside that the second connector 6 is hinged with the first connector 1 sets
The first cooperation section 4 is equipped with, the cross section of the first cooperation section 4 is C-shaped, and one end that the first connector 1 is hinged with the second connector 6 is prolonged
Stretching has the second cooperation section 3, and the cross section of the second cooperation section 3 is C-shaped, and when the second connector 6 turns to deployed condition, second matches somebody with somebody
The outside that section 3 is fastened on the second connector 6 is closed, and the second cooperation section 3 and first coordinates section 4 to cooperatively form external screw thread, the outer spiral shell
Stricture of vagina can be threadedly coupled with locking member 5.
Finite place piece 2 is arranged on first connector 1, locating part 2 is hinged with the second connector 6, and locating part 2 is matched somebody with somebody with second
Close section 3 adjacent, locating part 2 is used to stop that locking member 5 continues to screw off to the direction of the first connector 1.
With reference to Fig. 3 and Fig. 4, a kind of aircraft, including a fuselage 7, a wing and an at least rotor, wing is arranged on fuselage
On 7, rotor includes the first motor and the first propeller 12, and the first motor drives the first propeller 12 to rotate and produces to aircraft
Longitudinal lift, the first motor connects fuselage 7 or wing by foldable structure, wherein, the connection machine of the first connector 1 of foldable structure
Body 7 or wing, the second connector 6 connects the first motor.
Fuselage 7 has a plane of symmetry, and the axis of fuselage 7 and the center of gravity of aircraft are respectively positioned on the plane of symmetry of fuselage 7.
The quantity of rotor is four, and two of which rotor is arranged on the first side of the plane of symmetry of fuselage 7, and another two rotor is arranged
In the second side of the plane of symmetry of fuselage 7, and it is arranged on two rotors of the first side of the plane of symmetry of fuselage 7 and is arranged on the plane of symmetry of fuselage 7
Two rotors of the second side are symmetrical arranged along the plane of symmetry of fuselage 7, and two rotors positioned at the plane of symmetry the same side of fuselage 7 distinguish position
In the both sides of wing, each rotor connects wing by a foldable structure respectively, and the axis of four the first connectors 1 is and fuselage
7 axis are parallel to each other, and in folded state, the angle between the second connector 6 and the first connector 1 is 90 °, and each second
Connector 6 is towards the plane of symmetry of fuselage 7.
Two the second connectors 6 positioned at the plane of symmetry the same side of fuselage 7 are integrated.
With reference to Fig. 3 to Fig. 6, wing includes one first wing 8 and two second wings 9, and the first wing 8 is fixed on fuselage 7,
Two second wings 9 are respectively hinged at the both sides of the first wing 8, and two second wings 9 symmetrically set respectively along the plane of symmetry of fuselage 7
Put.Fixture 15 is provided with the end face of connection the second wing 9 of the first wing 8 one end, the second wing 9 connects the first wing 8 one
Revolving part 16 is fixed with the end face at end, fixture 15 and revolving part 16 are hinged, and on fixture 15 at least one is provided with
First annulus 17, is provided with least one second annulus 18 on revolving part 16, the second wing 9 can go to from deployed condition is reversible
Folded state, in deployed condition, the first wing 8 and the coaxial and misaligned setting of the second wing 9, and the first annulus 17 and the second circle
Ring 18 is corresponding, is now each passed through the first annulus 17 and the second annulus 18 by latch 14, makes the second wing 9 keep launching
State, now the axis of latch 14 can be mutually perpendicular to the axis of fuselage 7, and the axis of latch 14 is mutually put down with the plane of symmetry of fuselage 7
OK, in folded state, the second wing 9 is located at the downside of the first wing 8, and now rotational angle can be 180 °.
The equal diameters of the diameter of the first annulus 17 and the second annulus 18, and it is 4mm.
The quantity of the first annulus 17 is two, and the quantity of the second annulus 18 is two, and each first annulus 17 can be right
Second annulus 18 is answered, i.e., needs to be fixed by two latch 14 between the first wing 8 and one second wing 9, make second
Wing 9 keeps deployed condition.
In other embodiments, the second wing 9 is located at the upside of the first wing 8.
Two first collars 19 are provided with fixture 15, two second collars 20, first set are provided with revolving part 16
The collar 20 of ring 19 and second is coaxially disposed, and first collar 19 and second collar 20 are respectively sleeved at the outside of the second connector 6,
Realize the first wing 8 and the second wing 9 is hinged, and the second wing 9 can be rotated around the axis of the second connector 6.
With reference to Fig. 3 and Fig. 4, the second motor is provided with fuselage 7, the output shaft of the second motor is connected with the second propeller
11, the second propeller 11 is located at the head of fuselage 7, and the second motor drives the second propeller 11 to rotate the level produced to aircraft
Pulling force, the afterbody of fuselage 7 is connected with empennage 13 by foldable structure, wherein, the connection fuselage 7 of the first connector 1 of foldable structure,
Second connector 6 connects empennage 13, and in folded state, the axis of the second connector 6 is located on the plane of symmetry of fuselage 7, and second connects
Fitting 6 is located at the upside of fuselage 7, and now rotational angle is 180 °.
Empennage 13 is V-shaped, and opening upwards, and in folded state, fuselage 7 is located in V-shaped empennage 13.
In other embodiments, the second connector 6 is located at the downside of fuselage 7.
With reference to Fig. 3, the downside of fuselage 1 is provided with photoelectric nacelle 10, photoelectric nacelle 10 and is provided with photographic head.
Embodiment described above is merely to illustrate the technological thought and feature of the present invention, its object is to make in the art
Technical staff will appreciate that present disclosure and implement according to this, it is impossible to only limited with the present embodiment the present invention patent model
Employing, i.e., all equal changes made according to disclosed spirit or modification are enclosed, is still fallen in the scope of the claims of the present invention.
Claims (10)
1. a kind of foldable structure, it is characterised in that described including the first connector (1), the second connector (6) and locking member (5)
First connector (1) and second connector (6) are hinged, and the locking member (5) is set in first connector (1)
Or on second connector (6), second connector (6) can reversibly turn to deployed condition from folded state,
Deployed condition, second connector (6) is coaxial with first connector (1) and misaligned setting, now, the locking member
(5) slide into the hinged place of first connector (1) and second connector (6) and lock, make second connector
(6) deployed condition is kept.
2. foldable structure as claimed in claim 1, it is characterised in that the locking member (5) is set in second connector
(6) on, and one end outside that second connector (6) is hinged with first connector (1) is provided with the first cooperation section
(4) one end that, first connector (1) is hinged with second connector (6) is extended with the second cooperation section (3), when described
When second connector (6) turns to deployed condition, second cooperation section (3) is fastened on the outside of second connector (6),
And second cooperation section (3) and first cooperation section (4) cooperatively form external screw thread, the external screw thread and the locking member
(5) it is threadedly coupled.
3. foldable structure as claimed in claim 2, it is characterised in that be arranged finite place piece on first connector (1)
(2), the locating part (2) is hinged with second connector (6), and the locating part (2) coordinates section (3) phase with described second
It is adjacent.
4. foldable structure as claimed in claim 1, it is characterised in that first connector (1) and second connector
(6) it is pipe.
5. a kind of aircraft, an including fuselage (7), a wing and an at least rotor, the wing is arranged on the fuselage (7)
On, the rotor includes the first motor and the first propeller (12), and first motor drives first propeller (12) to turn
Longitudinal lift of the movable property life to the aircraft, it is characterised in that first motor is by such as any one of Claims 1-4
Described foldable structure connects the fuselage (7) or the wing, wherein first connector (1) connects the fuselage (7)
Or the wing, second connector (6) connects first motor.
6. aircraft as claimed in claim 5, it is characterised in that the fuselage (7) is with a plane of symmetry, the fuselage (7)
Axis and the center of gravity of the aircraft be respectively positioned on the plane of symmetry of the fuselage (7)；
The quantity of the rotor is four, and rotor described in two of which is arranged on the first side of the fuselage (7) plane of symmetry, another two
The individual rotor is arranged on the second side of the fuselage (7) plane of symmetry, and is arranged on the two of the first side of the fuselage (7) plane of symmetry
The individual rotor and two rotors of the second side of the fuselage (7) plane of symmetry are arranged on along the fuselage (7) plane of symmetry
It is symmetrical arranged, two rotors positioned at the fuselage (7) plane of symmetry the same side are respectively positioned at the both sides of the wing；
Each described rotor passes through respectively foldable structure described in and connects the wing, the axle of four first connectors (1)
Line is parallel to each other with the fuselage (7) axis, in folded state, second connector (6) and first connector
(1) angle between is 90 °, and each described second connector (6) is towards the plane of symmetry of the fuselage (7).
7. aircraft as claimed in claim 6, it is characterised in that positioned at two institutes of the fuselage (7) plane of symmetry the same side
State the second connector (6) to be integrated.
8. aircraft as claimed in claim 7, it is characterised in that the wing includes one first wing (8) and two second machines
The wing (9), first wing (8) is fixed on the fuselage (7), and second wing (9) is respectively hinged at described first described in two
The both sides of wing (8), and second wing (9) is symmetrical arranged respectively along the plane of symmetry of the fuselage (7) described in two；
First wing (8) to connect and be provided with fixture (15), the fixture on the end face of described second wing (9) one end
(15) two first collars (19) are provided with, two first collars (19) are set on second connector (6), institute
Revolving part (16) is fixed with the end face for stating described first wing (8) one end of the second wing (9) connection, on the revolving part (16)
Two second collars (20) are provided with, two second collars (20) are set on second connector (6)；
At least one first annulus (17) are provided with the fixture (15), on the revolving part (16) at least one is provided with
Second annulus (18), second wing (9) can go to folded state from deployed condition is reversible, in deployed condition, described
One wing (8) and second wing (9) is coaxial and misaligned setting, and first annulus (17) and second annulus
(18) it is corresponding, now first annulus (17) and second annulus (18) are each passed through by latch (14), make institute
State the second wing (9) and keep deployed condition, in folded state, second wing (9) is under first wing (8)
Side.
9. aircraft as claimed in claim 5, it is characterised in that be provided with the second motor on the fuselage (7), described second
The output shaft of motor is connected with the second propeller (11), head of second propeller (11) positioned at the fuselage (7)；
The afterbody of the fuselage (7) is connected with empennage (13) by the foldable structure, wherein first connector (1) connection
The fuselage (7), second connector (6) connects the empennage (13), in folded state, the second connector (6) position
It is located on the fuselage (7) plane of symmetry in the upside of the fuselage (7), and the axis of second connector (6).
10. aircraft as claimed in claim 9, it is characterised in that the empennage (13) is V-shaped, and opening upwards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611129120.7A CN106585951A (en) | 2016-12-09 | 2016-12-09 | Folding structure and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611129120.7A CN106585951A (en) | 2016-12-09 | 2016-12-09 | Folding structure and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106585951A true CN106585951A (en) | 2017-04-26 |
Family
ID=58597924
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611129120.7A Pending CN106585951A (en) | 2016-12-09 | 2016-12-09 | Folding structure and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106585951A (en) |
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| CN107082113A (en) * | 2017-06-09 | 2017-08-22 | 四川雷神空天科技有限公司 | Foldable attachment means and the unmanned vehicle applied |
| CN107618651A (en) * | 2017-09-14 | 2018-01-23 | 上海电力学院 | A kind of multi-rotor unmanned aerial vehicle horn is remotely controlled draw off gear |
| CN108438204A (en) * | 2018-05-21 | 2018-08-24 | 中宇航通（北京）科技有限公司 | Vertical take-off and landing drone rotor foldable structure and its folding and method of deploying |
| CN108438203A (en) * | 2018-05-21 | 2018-08-24 | 中宇航通（北京）科技有限公司 | For the self-locking mechanism of unmanned plane foldable structure and self-locking, unlocking method |
| CN112770971A (en) * | 2020-06-08 | 2021-05-07 | 深圳市大疆创新科技有限公司 | Retaining member and unmanned aerial vehicle |
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| CN112770971A (en) * | 2020-06-08 | 2021-05-07 | 深圳市大疆创新科技有限公司 | Retaining member and unmanned aerial vehicle |
| WO2021248278A1 (en) * | 2020-06-08 | 2021-12-16 | 深圳市大疆创新科技有限公司 | Locking member and unmanned aerial vehicle |
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Application publication date: 20170426 |