CN110844063A - Deformable aircraft - Google Patents
Deformable aircraft Download PDFInfo
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- CN110844063A CN110844063A CN201911298367.5A CN201911298367A CN110844063A CN 110844063 A CN110844063 A CN 110844063A CN 201911298367 A CN201911298367 A CN 201911298367A CN 110844063 A CN110844063 A CN 110844063A
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- 230000001174 ascending effect Effects 0.000 claims description 12
- 230000002146 bilateral effect Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 8
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- 230000003068 static effect Effects 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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- 238000006243 chemical reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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Abstract
The invention relates to a deformable aircraft, relates to the technical field of aircrafts, and aims to solve the technical problems that in the prior art, a vertical take-off and landing aircraft folding wing actuating mechanism is large in moment, and poor in flight reliability and safety. The morphing aircraft comprises a fuselage, fixed wings and rotating wings, wherein the fixed wings are symmetrically arranged on two sides of the fuselage, the center position of the rotating wings is connected to one end, far away from the fuselage, of the fixed wings through a rotating mechanism, and the rotating wings can rotate relative to the fixed wings by taking a connecting point as a center. The center point of the rotating wing is used as the connecting point of the rotating wing and the fixed wing, so that the static stress on two sides of the rotating mechanism is the same, the rotating moment required by the rotating wing relative to the fixed wing is smaller, the rotating wing can freely adjust the angle in the flying process of the morphing aircraft, and the reliability and the safety of the rotating wing of the morphing aircraft in the rotating process are guaranteed.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a deformable aircraft.
Background
The fixed wing aircraft for vertical take-off and landing combines the fixed wing aircraft with a rotor plane, and can realize vertical take-off and landing, hovering in the air and cruise in a fixed wing mode. The aircraft is mainly characterized in that: (1) the aircraft has the advantages of a gyroplane and a fixed-wing aircraft, can realize vertical take-off and landing and vertical hovering, can be transformed into the fixed-wing aircraft capable of flying for a long time, and can be converted between the two types of aircraft according to requirements. (2) When cruising, two rotors can rotate 90 degrees to be parallel to the longitudinal axis of the airplane, so that power is provided for cruising flight, the energy consumption is relatively low, and the two rotors have high flight speed and large flight radius. With the continuous provision of aircraft automatic control technology, the use scenes of vertical takeoff type aircraft are more and more.
The existing vertical take-off and landing aircraft comprises a tailstock type aircraft, a combined type aircraft, a tilting type aircraft and the like. The tilting power type vertical take-off and landing aircraft has the advantages that the mutual conversion from the horizontal to the vertical of the rotor wing or the jet engine is realized through the tilting mechanism, the aircraft has the defects that an additional tilting mechanism is required, the structural weight and the complexity are increased, the tilting moment is large, and the safety of the aircraft is poor.
Disclosure of Invention
The invention aims to provide a deformable aircraft to solve the technical problems that a vertical take-off and landing aircraft folding wing actuating mechanism in the prior art is large in moment and poor in flight reliability and safety.
The invention is realized by the following technical scheme: the utility model provides a morphing aircraft, includes fuselage, fixed wing and rotor, the bilateral symmetry of fuselage is installed fixed wing, rotor's central point put through slewing mechanism connect in fixed wing keeps away from the one end of fuselage, just rotor can for fixed wing uses its tie point as the center rotation.
Furthermore, in order to better implement the invention, at least one rotor is provided on each of the rotor wings.
Further, in order to better implement the present invention, the fixed wing includes a fixed section and a rotating section, the fixed section is connected to both sides of the fuselage, one end of the rotating section is connected to one end of the fixed section, which is far away from the fuselage, and the rotating section can rotate around a center line of one end of the fixed section, which is far away from the fuselage, with respect to the fixed section, the other end of the rotating section is connected to a center position of the rotating wing, and the rotating wing can rotate around an edge of one end of the rotating section, which is far away from the fixed section, as a center with respect to the rotating section.
Further, in order to better implement the present invention, the fixed section is connected to the rotating section through a first rotating device, one end of the first rotating device is provided with a power output end capable of outputting rotating power, the fixed end of the first rotating device is mounted on the fixed section, and the power output end of the first rotating device is mounted on the rotating section.
Further, in order to better realize the invention, the rotating mechanism is a folding device, the rotating section is connected with the rotating wing through the folding device, power output ends capable of outputting rotating power are arranged on two sides of the folding device, one end of the folding device is fixed on the rotating section, and the other end of the folding device is connected to the central position of the rotating wing through the output ends on the two sides.
Further, in order to better implement the present invention, the fixed wing includes an ascending section and a descending section, the ascending section is connected to the fuselage and inclines upward by an angle c, one end of the descending section is connected to one end of the ascending section away from the fuselage, the angle of inclination of the descending section with respect to the horizontal plane is b, the other end of the descending section is connected to the center of the rotating wing, and the rotating wing can rotate with respect to the descending section around the vertical line of the descending section.
Further, in order to better implement the present invention, the rotating mechanism is a second rotating device, the descending section is connected with the rotating wing through the second rotating device, the descending section is provided with a fastener for fixing the second rotating device, a fixed end of the second rotating device is fixed on the fastener, and an output end of the second rotating device passes through the descending section and is fixedly connected to the rotating wing.
Further, in order to better realize the invention, the inclination angle of the plane of the rotary wing and the central line of the rotor wing is d, and d is more than or equal to 30 degrees and less than or equal to 45 degrees and/or b is more than or equal to 30 degrees and less than or equal to 45 degrees.
Further, in order to better implement the invention, the fixed wing is movably connected with the fuselage.
Further, in order to better implement the present invention, the bottom of the rotary wing is respectively provided with at least one landing support device.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention provides a morphing aircraft which comprises a fuselage, fixed wings and rotating wings, wherein the fixed wings are symmetrically arranged on two sides of the fuselage, the center position of the rotating wings is connected to one end, far away from the fuselage, of the fixed wings through a rotating mechanism, and the rotating wings can rotate relative to the fixed wings by taking a connecting point as a center. The center position of the rotating wing is connected to one end, far away from the fuselage, of the fixed wing, so that the rotating wing can rotate relative to the fixed wing, and the connecting point of the rotating wing and the fixed wing is the center point of the rotating wing, so that the static stress on two sides of the rotating mechanism is the same, the rotating moment required by the rotating wing relative to the fixed wing is smaller, the angle of the rotating wing can be freely adjusted in the flying process of the morphing aircraft, and the reliability and the safety of the rotating wing of the morphing aircraft in the rotating morphing process can be fully guaranteed.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural view of a morphing aircraft in embodiment 1 of the invention;
fig. 2 is a plan view of a drooping state of the morphing aircraft in embodiment 1 of the present invention;
fig. 3 is a deformation analysis diagram of the morphing aircraft in embodiment 1 of the invention;
fig. 4 is a plan view of the morphing aircraft in embodiment 1 of the invention in a flat flight state;
fig. 5 is a rear view of the morphing aircraft in flat flight state in embodiment 1 of the invention;
fig. 6 is a schematic diagram of a deformed state of the morphing aircraft in embodiment 1 of the invention;
fig. 7 is a plan view of a drooping state of the morphing aircraft in embodiment 2 of the present invention;
fig. 8 is a plan view of a flat flight state of the morphing aircraft in embodiment 2 of the invention;
fig. 9 is a plan view of a drooping state of the morphing aircraft in embodiment 3 of the present invention;
fig. 10 is a rear view of a drooping state of the morphing aircraft in embodiment 3 of the invention;
fig. 11 is a rear view of a flat flight state of the morphing aircraft in embodiment 3 of the invention;
fig. 12 is a deformation analysis diagram of the drooping state of the morphing aircraft in embodiment 3 of the invention;
fig. 13 is a schematic structural view of a connection between a rotor and a descender of a morphing aircraft according to embodiment 3 of the present invention.
In the figure: 1-a fuselage; 2-fixed wings; 21-a fixed segment; 22-a rotation section; 23-a rising section; 24-a descending section; 3-rotating the wing; 4-a rotor wing; 41-rotor one; 42-rotor two; 43-rotor three; 44-rotor four; 5-a landing support device; 6-a first rotating means; 7-a folding device; 8-a second rotating means; 9-a fastener; 10-bearing.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the examples given herein without any inventive step, are within the scope of the present invention.
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
Example 1:
as shown in fig. 1 to 6, the morphing aircraft provided in this embodiment includes a fuselage 1, fixed wings 2, and rotating wings 3, where the fixed wings 2 are symmetrically installed on both sides of the fuselage 1, the center position of the rotating wings 3 is connected to one end of the fixed wings 2 far away from the fuselage 1 through a rotating mechanism, and the rotating wings 3 can rotate around their connection points with respect to the fixed wings 2. The center position of the rotating wing 3 is connected to one end, far away from the fuselage 1, of the fixed wing 2, so that the rotating wing 3 can rotate relative to the fixed wing 2, and the connecting point of the rotating wing 3 and the fixed wing 2 is the central point of the rotating wing 3, so that the static stress on two sides of the rotating mechanism is the same, the rotating moment required by the rotating wing 3 relative to the fixed wing 2 is smaller, the rotating wing 3 can freely adjust the angle in the flying process of the morphing aircraft, the change of the gravity center of the aircraft cannot be caused, and the reliability and the safety of the rotating wing 3 of the morphing aircraft in the rotating morphing process are fully guaranteed. In order to reach a certain lift force when the traditional combined type vertical take-off and landing aircraft flies flatly, the general wings are longer, and the size is larger, but the deformation aircraft of the embodiment can rotate because the rotating wings 3 are rotatable relative to the fixed wings 2, when the deformation aircraft is in a vertical state, the fixed wings are equivalently shortened, so that the occupied area of a take-off field or a storage field is reduced, and the take-off is more convenient compared with the traditional combined type vertical take-off and landing aircraft. Both traditional tilt-type and compound VTOL aircrafts require a plurality of rotor wing devices to be added on the fixed wing, but in a flat flight state, the dead weight is high because the utilization rate of the rotor propeller is low. The morphing aircraft of this embodiment, rotor are many rotor frames promptly, and after the flat flying, rotor can provide lift for morphing aircraft through rotating to being parallel with the horizontal plane or being certain contained angle, and the rotor still provides power to reduce morphing aircraft's dead weight.
As a more preferred embodiment of the present embodiment, at least one rotor 4 is provided on each of the rotor wings 3, as shown in fig. 1. Preferably, the rotor 4 is arranged at both ends of the fixed wing 2. When the morphing aircraft of this embodiment takes off vertically, as shown in fig. 2, at this time, the fuselage 1, the fixed wing 2, and the rotor wing 3 are all perpendicular to the ground, the morphing aircraft takes off under the power provided by the rotor 4 propeller, and after taking off, the pitching control of the rotor wing 4 is adjusted, as shown in fig. 3, when it is necessary to switch to the horizontal direction, the rotation speeds of the first rotor wing 41 and the third rotor wing 43 are increased, and the rotation speeds of the second rotor wing 42 and the fourth rotor wing 44 are decreased, so that the fuselage 1 and the fixed wing 2 of the morphing aircraft both start to tilt forward until the morphing aircraft gradually turns to the flat flight, and at the same time, the rotating mechanism drives the rotor wing 3 to. When the morphing aircraft is in a flat flight state, as shown in fig. 4 and 5, the rotary wing 3 is parallel to the horizontal plane, and the rotary wing 3 provides lift for the aircraft together with the fixed wing 2. As shown in fig. 6, the smaller the angle a of the rotary wing 3 with respect to the horizontal plane, the larger the lift force, and vice versa, so that the lifting height of the morphing aircraft can be adjusted by adjusting the rotation angle of the rotary wing 3 on both sides of the fuselage 1 with respect to the fixed wing 2, and the roll attitude of the morphing aircraft can also be adjusted by adjusting the rotary wing 3 on one side of the fuselage 1.
As an alternative embodiment, as shown in fig. 4, the rotating mechanism is a folding device 7, the fixed wing 2 and the rotating wing 3 are connected through the folding device 7, both sides of the folding device 7 are provided with power output ends capable of outputting rotary power, one end of the folding device 7 is fixed on the fixed wing 2, and the other end of the folding device 7 is connected to the central position of the rotating wing 3 through the output ends at both sides. This folding device 7 adopts the biax steering wheel of purchase, and the model is: the fixed end of the steering engine is fixed on the fixed wing 2, the output shaft of the steering engine is arranged in a direction parallel to the direction of the machine body 1, and the output shaft of the movable end of the steering engine is connected to the central line of the long edge of the rotating wing 3, so that the steering engine can drive the rotating wing 3 to rotate 180 degrees relative to the fixed wing 2 along the edge of one end, far away from the machine body, of the fixed wing 2 when rotating.
As a more preferred embodiment of the present embodiment, the fixed wing 2 is movably connected with the fuselage 1. Preferably, the fixed wings 2 can be respectively connected with the fuselage 1 through hinge mechanisms, one end of each hinge mechanism is connected with the fixed wing 2, and the other end of each hinge mechanism is connected with the fuselage 1, so that the folding or unfolding state of the deformable aircraft can be adjusted, and when the deformable aircraft is in the folding and accommodating state, the fixed wings 2 can be folded on two sides of the fuselage 1, so that the size of the aircraft is reduced. And meanwhile, locking mechanisms are respectively arranged at the joints of the fixed wings 2 and the aircraft body 1, and can be buckles for keeping the stability of the folding or unfolding state of the aircraft.
As a more preferred embodiment of the present embodiment, as shown in fig. 1, the bottom of the rotor wing 3 is provided with at least one landing support 5. Landing gear supports 5 may be provided at both ends of the rotary wing 3, and the bottoms of the landing gear supports 5 contact and support the morphing aircraft on the ground when the morphing aircraft descends to the ground. Preferably, the bottom of the landing support device 5 is provided with rollers, so that the morphing aircraft can take off, land and run, and the ground can support during sliding and parking.
Example 2:
as a specific implementation manner of embodiment 1, as shown in fig. 7 to 8, the fixed wing 2 includes a fixed section 21 and a rotating section 22, the fixed section 21 is connected to two sides of the fuselage 1, one end of the rotating section 22 is connected to one end of the fixed section 21 away from the fuselage 1, the rotating section 22 can rotate around a center line of one end of the fixed section 21 away from the fuselage as a center with respect to the fixed section 21, the other end of the rotating section 22 is connected to a center position of the rotating wing 3, and the rotating wing 3 can rotate around an edge of one end of the rotating section 22 away from the fixed section 21 as a center with respect to the rotating section 22. When the morphing aircraft of this embodiment takes off vertically, as shown in fig. 7, the fixed sections 21 of the fuselage 1 and the fixed wing 2 are parallel to the ground, and the rotating section 22 of the fixed wing 2 and the rotating wing 3 are perpendicular to the ground. After the aircraft takes off, as shown in fig. 8, the rotating section 22 of the fixed wing 2 rotates to the direction parallel to the fixed section 21 until the rotating section rotates to be on the same plane with the fixed section 21, and at the same time, the rotating wing 3 rotates to be parallel to the horizontal plane in the horizontal direction. In the process of transforming the deformable aircraft from the vertical state to the flat flying state, the fuselage 1 of the deformable aircraft is kept in the horizontal state, and the flying state of the deformable aircraft is adjusted only by the rotating section 22 and the rotating wing 3. Because the connection part of the rotating section 22 of the fixed wing 2 and the rotating wing 3 is the middle position of the rotating wing 3, the static rotating moment of the rotating mechanism connecting the rotating wing 3 and the fixed wing 2 is small, and the rotating wing 3 can rotate along with the rotating section 22 of the fixed wing 2. When the two wing rotating sections 22 rotate forwards or backwards together, the pitching attitude of the aircraft can be controlled, and when the two wing rotating sections 22 rotate in opposite directions, the turning state during vertical flight or the rolling state during horizontal flight can be controlled.
As a more preferred embodiment of this embodiment, as shown in fig. 8, the fixed section 21 and the rotating section 22 are connected by the first rotating means 6, a power output end capable of outputting rotational power is provided at one end of the first rotating means 6, the fixed end of the first rotating means 6 is attached to the fixed section 21, and the power output end of the first rotating means 6 is attached to the rotating section 22. This first rotary device 6 adopts the unipolar steering wheel of purchasing, and the model is: futaba S3003, the fixed end of the steering engine is fixed on the fixed section 21, the power output shaft of the steering engine is arranged in the direction away from the machine body 1, the power output shaft of the steering engine extends out of the fixed section 21 and is connected with one end of the rotating section 22, and when the steering engine rotates, the steering engine can drive the rotating section 22 to rotate relative to the fixed section 21 by taking the central line of one end of the fixed section 21 away from the machine body as the center.
As a more preferable embodiment of this embodiment, the rotating mechanism is a folding device 7, the rotating section 22 is connected to the rotating wing 3 through the folding device 7, power output ends capable of outputting rotating power are disposed on both sides of the folding device 7, one end of the folding device 7 is fixed to the rotating section 22, and the other end of the folding device 7 is connected to the center position of the rotating wing 3 through the output ends on both sides. This folding device 7 adopts the biax steering wheel of purchase, and the model is: the fixed end of the steering engine is fixed on the rotating section 22, the output shaft of the steering engine is arranged in a direction parallel to the direction of the airframe 1, and the output shaft of the movable end of the steering engine is connected to the central line of the rotating wing 3, so that the steering engine can drive the rotating wing 3 to rotate 180 degrees relative to the rotating section 22 by taking the edge of one end, away from the fixed section 21, of the rotating section 22 as the center when rotating.
Example 3:
as a specific implementation manner of embodiment 1, as shown in fig. 9-12, the fixed wing 2 includes an ascending section 23 and a descending section 24, the ascending section 23 is connected to the fuselage 1 and inclines upwards by an angle c, one end of the descending section 24 is connected to one end of the ascending section 23 away from the fuselage, an inclination angle of the descending section 24 with respect to a horizontal plane is b, the other end of the descending section 24 is connected to a central position of the rotary wing 3, and the rotary wing 3 can rotate with respect to the descending section 24 by taking a vertical line of the descending section 24 as a center. When the morphing aircraft in this embodiment takes off vertically, as shown in fig. 12, the angle b between the descending section 24 and the horizontal plane, and the angle d between the plane of the rotor wing 3 and the center line of the rotor wing 4 are also inclined, so that b + d is equal to or approximately equal to 90 °, thereby ensuring that the center line of the rotor wing 4 on the rotor wing 3 is perpendicular or substantially perpendicular to the horizontal plane when the aircraft takes off vertically, and ensuring that the rotor wing 4 can provide an upward vertical lift for the morphing aircraft. After the morphing aircraft takes off, as shown in fig. 11, the rotor 3 rotates forward until the long axis of the rotor 3 is consistent with the inclination angle of the descending segment 24, so that the rotor 3 can provide a certain lift force for the morphing aircraft, and the morphing aircraft gradually changes into horizontal flight. In the process of the transformation from the vertical state to the flat flying state of the morphing aircraft of the embodiment, the fuselage 1 is kept in the horizontal state, and the flying state is changed only by adjusting the direction of the rotary wing 3. As shown in fig. 11, since the descending section 24 of the fixed wing 2 is inclined downward, when the rotary wing 3 rotates forward, the inclination angle of the rotary wing 3 is the same as that of the descending section 24, the rotary wing 3 can provide partial lift for the morphing aircraft when being in a non-vertical state on the horizontal plane, and since the plane of the rotary wing 3 has a certain angle with the rotary wing 4 arranged thereon, the rotary wing 4 can provide forward power while keeping partial upward power during flat flight.
As a more preferable embodiment of this embodiment, as shown in fig. 9 and 13, the rotating mechanism of this embodiment is a second rotating device 8, the descending section 24 is connected with the rotating wing 3 through the second rotating device 8, the descending section 24 is provided with clamping pieces 9 for fixing the second rotating device 8, a through hole is provided on the descending section 24 between the clamping pieces 9, a bearing 10 is provided in the through hole, the fixed end of the second rotating device 8 is fixed on the clamping pieces 9, and the output end of the second rotating device 8 passes through the descending section 24 and is fixedly connected to the rotating wing 3. This second rotary device 8 adopts the unipolar steering wheel of purchasing, and the model is: the fixed end of the steering engine is fixed on the clamping piece 9 of the descending section 24, the output shaft of the steering engine penetrates through the bearing 10 on the descending section 24 to be fixedly connected with the rotating wing 3, the fixed connection can be welding, and when the steering engine rotates, the steering engine can drive the rotating wing 3 to rotate 180 degrees relative to the descending section 24 along the vertical line of the plane of the descending section 24.
As a more preferred embodiment of the present embodiment, the plane of the rotor wing 3 is inclined at an angle d with respect to the center line of the rotor 4, and d is greater than or equal to 30 degrees and less than or equal to 45 degrees and/or b is greater than or equal to 30 degrees and less than or equal to 45 degrees. As shown in fig. 12, the inclination angle b of the descending section 24 relative to the horizontal plane is 30-45 °, when the inclination angle is larger, the projection length of the rotating wing 3 on the horizontal plane is reduced after the morphing aircraft turns to fly horizontally, and the provided lift force is reduced; when the inclination angle is smaller, the morphing aircraft can not vertically face upwards when rotating, so that the upward lift force provided by the rotor 4 is reduced. When the inclination angle b of the descending section 24 relative to the horizontal plane is 30-45 degrees, the deformation aircraft can be enabled to be in a vertical state, the rotor 4 can provide ascending force, and meanwhile, when the aircraft flies flatly, the rotatable wing 3 can provide a flatly flying lift force. The size of the inclination angle c of the ascending section 23 to the horizontal plane depends on the length of the ascending section 23, and the larger the length, the smaller the inclination angle c is, so that the center of gravity of the deformed aircraft and the power line are on the same horizontal plane as much as possible.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a morphing aircraft, its characterized in that, includes fuselage, fixed wing and rotor, the bilateral symmetry of fuselage is installed fixed wing, rotor's central point put through slewing mechanism connect in fixed wing keeps away from the one end of fuselage, just rotor can for fixed wing uses its tie point as the center rotation.
2. The morphing aircraft of claim 1, wherein each of said rotor wings has at least one rotor.
3. The morphing aircraft of claim 2, wherein the fixed wing includes a fixed section and a rotating section, the fixed section is connected to both sides of the fuselage, one end of the rotating section is connected to the end of the fixed section away from the fuselage, and the rotating section can rotate around a center line of the end of the fixed section away from the fuselage, the other end of the rotating section is connected to a center position of the rotating wing, and the rotating wing can rotate around a side of the end of the rotating section away from the fixed section as a center.
4. The morphing aircraft of claim 3, wherein the fixed section is connected to the rotating section via a first rotating device, one end of the first rotating device is provided with a power output end capable of outputting rotating power, the fixed end of the first rotating device is mounted on the fixed section, and the power output end of the first rotating device is mounted on the rotating section.
5. The morphing aircraft of claim 3, wherein the rotating mechanism is a folding device, the rotating section is connected to the rotating wing through the folding device, two sides of the folding device are provided with power output ends capable of outputting rotating power, one end of the folding device is fixed to the rotating section, and the other end of the folding device is connected to the center position of the rotating wing through the output ends at two sides.
6. The morphing aircraft of claim 2, wherein the fixed wing includes an ascending section and a descending section, the ascending section is connected to the fuselage and is inclined upward by an angle c, one end of the descending section is connected to an end of the ascending section remote from the fuselage, and the descending section is inclined at an angle b with respect to a horizontal plane, the other end of the descending section is connected to a center position of the rotating wing, and the rotating wing is rotatable with respect to the descending section with a vertical line of the descending section as a center.
7. The morphing aircraft of claim 6, wherein the rotating mechanism is a second rotating device, the descender is connected to the rotor via the second rotating device, the descender is provided with a fastener for fixing the second rotating device, a fixed end of the second rotating device is fixed to the fastener, and an output end of the second rotating device passes through the descender and is fixedly connected to the rotor.
8. The morphing aircraft of claim 7, wherein the plane of the rotor wing is inclined at an angle d from the rotor centerline of 30 ° ≦ d ≦ 45 ° and/or 30 ° ≦ b ≦ 45 °.
9. The morphing aircraft of any one of claims 1 to 8, wherein the fixed wing is movably connected to the fuselage.
10. The morphing aircraft of any one of claims 1 to 8, wherein the base of the rotor wing is provided with at least one landing gear support means respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911298367.5A CN110844063A (en) | 2019-12-17 | 2019-12-17 | Deformable aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911298367.5A CN110844063A (en) | 2019-12-17 | 2019-12-17 | Deformable aircraft |
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| CN110844063A true CN110844063A (en) | 2020-02-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911298367.5A Pending CN110844063A (en) | 2019-12-17 | 2019-12-17 | Deformable aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113022848A (en) * | 2021-04-18 | 2021-06-25 | 上海尚实能源科技有限公司 | Wing passenger plane |
| CN113879527A (en) * | 2021-10-22 | 2022-01-04 | 浙江大学湖州研究院 | Vertical take-off and landing fixed-wing aircraft |
| WO2024065917A1 (en) * | 2022-09-27 | 2024-04-04 | 浙江天骥博特智能科技有限公司 | Reconfigurable blended wing vertical take-off and landing aircraft |
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| CN113879527A (en) * | 2021-10-22 | 2022-01-04 | 浙江大学湖州研究院 | Vertical take-off and landing fixed-wing aircraft |
| WO2024065917A1 (en) * | 2022-09-27 | 2024-04-04 | 浙江天骥博特智能科技有限公司 | Reconfigurable blended wing vertical take-off and landing aircraft |
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