CN116215907B - Vertical take-off and landing variant unmanned aerial vehicle with tilting, folding and telescopic wings - Google Patents
Vertical take-off and landing variant unmanned aerial vehicle with tilting, folding and telescopic wings Download PDFInfo
- Publication number
- CN116215907B CN116215907B CN202310379673.1A CN202310379673A CN116215907B CN 116215907 B CN116215907 B CN 116215907B CN 202310379673 A CN202310379673 A CN 202310379673A CN 116215907 B CN116215907 B CN 116215907B
- Authority
- CN
- China
- Prior art keywords
- wing
- telescopic
- unmanned aerial
- aerial vehicle
- rotary driving
- 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.)
- Active
Links
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a vertical take-off and landing variant unmanned aerial vehicle with tilting, folding and telescopic wings, which comprises a fuselage, a telescopic deformation machine wing and a tail wing, wherein the telescopic deformation machine wing and the tail wing are respectively connected with the head part and the tail part of the fuselage through folding mechanisms, and the telescopic deformation machine wing and the tail wing are respectively connected with a propeller through driving mechanisms in a rotating way. The tilting-folding-telescopic wing vertical take-off and landing variant unmanned aerial vehicle has innovative designs such as large-scale deformation wings, wing-body large-amplitude tilting and folding mechanisms and the like, and can realize full-mode conversion between fixed wings and four-rotation wings. Meanwhile, the four-rotor unmanned aerial vehicle has the advantages of being strong in cruising ability, high in loading ability, strong in maneuverability and high in flying speed. Meanwhile, the variant unmanned aerial vehicle improves the environment adaptability of the traditional tilting wing type vertical take-off and landing unmanned aerial vehicle, and provides a reference path for the design direction of the novel variant unmanned aerial vehicle in the future.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a vertical take-off and landing variant unmanned aerial vehicle with tilting, folding and telescoping wings.
Background
The vertical take-off and landing fixed-wing aircraft can take off and land vertically like a helicopter, can fly before cruising like a fixed-wing aircraft, has the remarkable advantages of high forward flight speed, long voyage and the like, and compared with the conventional fixed-wing aircraft, the vertical take-off and landing fixed-wing aircraft can take off and land and hover at fixed points, has no dependence on airport runways, and has remarkably improved task capacity.
Vertical takeoff and landing aircraft are mainly divided into three categories: lifting and pushing combined type vertical take-off and landing fixed-wing unmanned aerial vehicle, tailstock type vertical take-off and landing fixed-wing unmanned aerial vehicle, tilting rotor wing type vertical take-off and landing fixed-wing unmanned aerial vehicle. The tilting rotor wing/wing type vertical take-off and landing fixed wing unmanned aerial vehicle has the advantages of high mass efficiency of the whole aircraft, small pneumatic interference, good stability characteristics, high realizability and the like.
Along with the wider and wider application of unmanned aerial vehicles in military and civil fields in recent years, the requirements on the take-off and landing modes of the unmanned aerial vehicles are diversified, and the unmanned aerial vehicles do not need to consider the problems of life guarantee, physiological limit and the like of pilots, so that the vertical take-off and landing technology is more flexible and easier to realize in the unmanned aerial vehicle field.
For a tilt rotor type vertical take-off and landing fixed wing unmanned aerial vehicle, although the research is most in VTOL (vertical take-off and landing) aircrafts at present, the application is most mature, the coupling between a rotor and a fixed wing is serious in the tilting process, and the downward washing air flow generated by the rotor is partially blocked by the fixed wing, so that the aerodynamic efficiency is reduced.
Disclosure of Invention
1. Technical problem to be solved
The invention aims to solve the problem that in the prior art, a tilting rotor type vertical take-off and landing fixed wing unmanned aerial vehicle is serious in coupling between a rotor and the fixed wing in the tilting process, and downwash airflow generated by the rotor is partially blocked by the fixed wing, so that the pneumatic efficiency is reduced.
2. Technical proposal
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the vertical take-off and landing variant unmanned aerial vehicle with the tiltable, foldable and telescopic wings comprises a fuselage, a telescopic deformation machine wing and a tail wing, wherein the telescopic deformation machine wing and the tail wing are respectively connected with the head part and the tail part of the fuselage through folding mechanisms, and the telescopic deformation machine wing and the tail wing are respectively connected with a propeller through driving mechanisms in a rotating way;
the wing of the telescopic deformation machine comprises two main wing beams and auxiliary wing beams which are symmetrically arranged, wherein the outer parts of the two main wing beams are fixedly sleeved with a main skin, the outer parts of the two auxiliary wing beams are fixedly sleeved with auxiliary skins, the main wing beams are slidably sleeved with a plurality of main wing ribs, the auxiliary wing beams are slidably sleeved with a plurality of auxiliary wing ribs, the main wing ribs at the wing root end are fixedly connected with two first rotary driving motors, a plurality of telescopic mechanisms are arranged between the main wing ribs and the auxiliary wing ribs, and the output ends of the first rotary driving motors are connected with the telescopic mechanisms;
the folding mechanism comprises a center wheel, a gear ring, a frame, a second rotary driving motor, a third rotary driving motor and a wing connecting piece which are symmetrically arranged, wherein the center wheel is connected with the output end of the second rotary driving motor, the gear ring is rotationally meshed and linked with three planetary gears, the gear ring is fixedly connected to the machine body, one side of each planetary gear is fixedly connected with the frame, the second rotary driving motor and the third rotary driving motor are fixedly connected with the frame, the output end of the third rotary driving motor is fixedly connected with the wing connecting piece, and one end of the wing connecting piece is rotationally connected with the frame.
Preferably, a plurality of said telescopic mechanisms are arranged in a linear array.
Preferably, the telescopic mechanism comprises a first driving rod, a second driving rod, a first driven rod, a first sliding block, a second driven rod, a second sliding block, a third driven rod and a fourth driven rod; the first driving rod, the second driven rod and the fourth driven rod are connected through coaxial matching, the second driving rod, the first driven rod and the third driven rod are connected through coaxial matching, the first sliding block is in sliding sleeve joint on the first driving rod, one end of the first driven rod is in rotating connection with the first sliding block, the second sliding block is in sliding sleeve joint on the third driven rod, and one end of the second driven rod is in rotating connection with the second sliding block.
Preferably, the first driving rod, the second driving rod, the third driven rod and the fourth driven rod are fixedly connected with a connecting gear at the end far away from each other, and mounting ports corresponding to the connecting gear are formed in the main wing rib and the auxiliary wing rib.
Preferably, the first rotary driving motor, the second rotary driving motor and the third rotary driving motor are all self-locking rotary driving motors.
Preferably, a plurality of landing gears which are symmetrically arranged are rotatably connected to the bottom of the body.
3. Advantageous effects
Compared with the prior art, the invention has the advantages that:
according to the invention, the tilting-folding-telescopic wing vertical take-off and landing variant unmanned aerial vehicle has innovative designs such as large-scale deformation wings, large-scale tilting-folding mechanisms of wings and bodies, and the like, and can realize full-mode conversion between fixed wings and four-rotation wings. Meanwhile, the four-rotor unmanned aerial vehicle has the advantages of being strong in cruising ability, high in loading ability, strong in maneuverability and high in flying speed. Meanwhile, the variant unmanned aerial vehicle improves the environment adaptability of the traditional tilting wing type vertical take-off and landing unmanned aerial vehicle, and provides a reference path for the design direction of the novel variant unmanned aerial vehicle in the future.
Drawings
Fig. 1 is a schematic structural diagram of a vertical take-off and landing variant unmanned aerial vehicle with a tiltable, foldable and telescopic wing;
FIG. 2 is a schematic view of the internal structure of the wing of the telescopic deformer according to the present invention;
FIG. 3 is a schematic perspective view of a wing of the telescopic deformer according to the present invention;
FIG. 4 is a schematic structural view of a telescopic mechanism according to the present invention;
FIG. 5 is a schematic view of a fully contracted configuration of a fully contracted flexible wing according to the present invention;
FIG. 6 is a schematic structural view of a fully extended, telescoping wing according to the present invention;
FIG. 7 is a schematic view of an exploded structure of a folding mechanism according to the present invention;
FIG. 8 is a schematic perspective view of a folding mechanism according to the present invention;
FIG. 9 is a schematic view of a wing tip-over Cheng in accordance with the present invention;
FIG. 10 is a schematic illustration of the degree of folding of a wing in accordance with the present invention;
FIG. 11 is a schematic view of a fixed wing flight mode according to the present invention;
figure 12 is a schematic diagram of a four-rotor flight mode according to the present invention;
FIG. 13 is a schematic view of a fixed-wing flight mode of the present invention;
fig. 14 is a schematic diagram of a flight transition of the unmanned aerial vehicle from a four-rotor mode to a fixed-wing mode according to the present invention;
fig. 15 is a schematic diagram of a flight transition of the unmanned aerial vehicle from a fixed wing mode to a four-rotor mode according to the present invention.
In the figure: 1 fuselage, 2 flexible deformation aircraft wing, 201 main spar, 202 auxiliary spar, 203 main skin, 204 auxiliary skin, 205 main wing rib, 206 auxiliary wing rib, 207 first rotary driving motor, 3 fin, 4 folding mechanism, 401 central wheel, 402 gear circle, 403 frame, 404 second rotary driving motor, 405 third rotary driving motor, 406 wing connecting piece, 407 planet wheel, 5 screw, 6 first driving rod, 7 second driving rod, 8 first driven rod, 9 first slider, 10 second driven rod, 11 second slider, 12 third driven rod, 13 fourth driven rod, 14 connecting gear, 15 undercarriage.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments.
Example 1:
referring to fig. 1, a vertical take-off and landing variant unmanned aerial vehicle with tilting, folding and telescopic wings comprises a fuselage 1, a telescopic deformation machine wing 2 and a tail wing 3, wherein a plurality of landing gears 15 which are symmetrically arranged are rotationally connected to the bottom of the fuselage 1, the telescopic deformation machine wing 2 and the tail wing 3 are respectively connected with the head and the tail of the fuselage 1 through a folding mechanism 4, and a propeller 5 is rotationally connected to the telescopic deformation machine wing 2 and the tail wing 3 through a driving mechanism;
in the invention, a telescopic deformation machine wing 2 comprises two main wing beams 201 and auxiliary wing beams 202 which are symmetrically arranged, wherein the outer parts of the two main wing beams 201 are fixedly sleeved with a main skin 203, the outer parts of the two auxiliary wing beams 202 are fixedly sleeved with auxiliary skins 204, the main wing beams 201 are slidably sleeved with a plurality of main wing ribs 205, the auxiliary wing beams 202 are slidably sleeved with a plurality of auxiliary wing ribs 206, two first rotary driving motors 207 are fixedly connected to the main wing ribs 205 at the wing root end, a plurality of telescopic mechanisms are arranged between the main wing ribs 205 and the auxiliary wing ribs 206, the output ends of the first rotary driving motors 207 are connected with the telescopic mechanisms, and the telescopic mechanisms are arranged in a linear array;
in the invention, the telescopic mechanism comprises a first driving rod 6, a second driving rod 7, a first driven rod 8, a first sliding block 9, a second driven rod 10, a second sliding block 11, a third driven rod 12 and a fourth driven rod 13; the first driving rod 6, the second driven rod 10 and the fourth driven rod 13 are connected through coaxial matching, the second driving rod 7, the first driven rod 8 and the third driven rod 12 are connected through coaxial matching, the first sliding block 9 is in sliding sleeve connection with the first driving rod 6, one end of the first driven rod 8 is in rotating connection with the first sliding block 9, the second sliding block 11 is in sliding sleeve connection with the third driven rod 12, one end of the second driven rod 10 is in rotating connection with the second sliding block 11, connecting gears 14 are fixedly connected to the ends, far away from the first driving rod 6, the second driving rod 7, the third driven rod 12 and the fourth driven rod 13, of the main wing ribs 205 and the auxiliary wing ribs 206 are provided with mounting ports corresponding to the connecting gears 14;
in the present invention, referring to fig. 2-6, the telescopic wing extends the working process: when the external controller sends out a wing extension instruction, two rotary driving motors with self-locking functions start to work along with the wing extension instruction, and drive the driving rod 1 connected with the external controller to rotate clockwise and simultaneously with the driving rod 2, so that an included angle alpha between the driving rod 1 and the driving rod 2 is gradually reduced, the driven rod 4 coaxially matched with the driving rod 1 rotates clockwise, an included angle beta between the driving rod 1 and the driven rod 4 is gradually increased, the opposite side driving rod 2 and driven components thereof move under the same condition, and ribs connected with the driven rod 3 and the driven rod 4 are pushed to move along the wing tip directions along the two wing beams, so that the whole telescopic mechanism extends along the wing span direction. After the telescopic mechanism at the wing root is driven, because the included angle between the driven rods 3 and 4 is relatively reduced, the driving rod 1 and the driving rod 2 arranged on the adjacent side of the wing rib are driven by the gear to start rotating, so that the telescopic mechanism at the other side of the wing rib can complete the same action, the driven rod 1, the sliding block 1, the driven rod 2 and the sliding block 2 play a role in maintaining stable balance in the process, and when the auxiliary skin is completely stretched out, the two rotary driving motors stop working and are locked, and the telescopic wing is in a completely stretched state.
In the invention, the contraction working process of the telescopic wing comprises the following steps: when the external controller sends out wing contraction instructions, the two rotary driving motors with self-locking functions start to work to drive the telescopic mechanism to move. The contraction process is opposite to the movement direction of the extension process, the first driven rod 8, the first sliding block 9, the second driven rod 10 and the second sliding block 11 play a role in maintaining stable balance in the process, and when the auxiliary skin 204 is completely contracted, the two rotary driving motors stop working and are locked, and the telescopic wing is in a completely contracted state;
in the invention, the folding mechanism 4 comprises a center wheel 401, a gear ring 402, a frame 403, a second rotary driving motor 404, a third rotary driving motor 405 and a wing connecting piece 406 which are symmetrically arranged, wherein the center wheel 401 is connected with the output end of the second rotary driving motor 404, the gear ring 402 is in rotary meshing connection with three planetary gears 407, the gear ring 402 is fixedly connected on the machine body 1, one side of each planetary gear 407 is fixedly connected with the frame 403, the second rotary driving motor 404 and the third rotary driving motor 405 are both fixedly connected with the frame 403, the output end of the third rotary driving motor 405 is fixedly connected with the wing connecting piece 406, one end of the wing connecting piece 406 is in rotary connection with the frame 403, and the first rotary driving motor 207, the second rotary driving motor 404 and the third rotary driving motor 405 are all self-locking rotary driving motors.
In the present invention, referring to fig. 7-10, taking a single-side wing as an example, the wing tilting working process is as follows: when the external controller sends out a wing tilting command, the second rotary driving motor 404 with a self-locking function starts to work along with the wing tilting command, drives the central wheel 401 connected with the second rotary driving motor to start rotating, further drives the three planetary wheels 407 to start rotating, and enables the rack 403 fixedly connected with the planetary wheels 407 to start rotating, so that the wing is driven to tilt by 0-90 degrees, and when the wing is tilted by 0 degrees, namely the gamma plane is parallel to the plane of the machine body 1 or is tilted by 90 degrees, namely the gamma plane is perpendicular to the plane of the machine body 1, the second rotary driving motor 404 automatically stops working and is self-locked, and the external controller can also brake the second rotary driving motor 404 at any time, so that the wing can stop tilting at any angle of 0-90 degrees.
In the invention, the wing folding working process comprises the following steps: when an external controller sends out a wing folding instruction, a third rotary driving motor 405 with a self-locking function starts to work along with the wing folding instruction, and drives a wing connecting piece 406 connected with the wing folding instruction to rotate, so that the wing can be folded by-60 degrees to 60 degrees relative to a gamma plane, namely, the theta range in the figure is-60 degrees to 60 degrees (the dihedral direction is regulated to be positive). When θ is 0 °, 60 °, or-60 °, the third rotary driving motor 405 automatically stops working and is self-locking, and the external controller can also brake the third rotary driving motor 405 at any time, so that the wing can stop folding at any angle of-60 ° to 60 °.
In the present invention, referring to fig. 11-13, the drone has two modes of flight: the unmanned aerial vehicle comprises a fixed wing flight mode and a four-rotor flight mode, wherein the unmanned aerial vehicle can take off and land at a short distance in the fixed wing flight mode, the wing tilting system is enabled to deflect forwards by 45 degrees by controlling the wing-body large-amplitude tilting folding mechanism, so that the rotor wing can generate thrust and lift simultaneously, compared with a vertical take-off and landing mode, a large amount of fuel can be saved, the range is increased, in the fixed wing flight mode, the folding of the wing can be realized by controlling the wing-body large-amplitude tilting folding mechanism, the dihedral size of the V-shaped tail wing can be adjusted, the course static stability of the unmanned aerial vehicle can be adjusted, and the differential tilting of the wings at two sides can be realized by controlling the wing-body large-amplitude tilting folding mechanism, so that the rolling movement of the unmanned aerial vehicle is realized.
In the present invention, referring to fig. 14, the transition of flight from quad-rotor mode to fixed-wing mode: the unmanned aerial vehicle is in four rotor flight modes initially, when external controller sends out the transition and changes into fixed wing flight mode instruction, two folding mechanism of control flexible deformation wing and fin begin folding work simultaneously, when θ is 0 (θ in folding mechanism's wing folding work process), control the folding rotary driving motor of wing stop work and auto-lock, the wing stops folding, later wing and fin begin to incline, when wing and fin incline to 0, namely the plane that the wing is located and fin is parallel with the plane that the fuselage is located, control the third rotary driving motor 405 that wing and fin incline to stop work and auto-lock, wing and fin stop incline, flexible deformation wing's telescopic machanism begins and accomplishes the extension work thereupon, the wing reaches complete elongation state, finally, control fin folding mechanism takes place folding action, when θ is 30, control fin folding rotary driving motor stop work and auto-lock, the fin stops folding and forms V type fin, unmanned aerial vehicle transitions into fixed wing flight mode.
In the present invention, referring to fig. 15, the transition of flight from fixed wing mode to quad-rotor mode: the unmanned aerial vehicle is initially in fixed wing flight mode, when external controller sends the transition and changes four rotor flight mode instructions, folding action takes place for the folding mechanism of control fin, when θ is 0 promptly the fin place plane with the plane parallel of fuselage place, the fin stops folding, afterwards the telescopic machanism of flexible deformation wing begins and accomplishes shrink work, the wing reaches complete shrink state, two tilting folding mechanism of control flexible deformation wing and fin begin tilting work thereupon, when wing and fin tilt for 90 promptly the plane of wing place plane and fin place plane and plane parallel vertical of fuselage place, the rotary driving motor of control wing and fin tilt stops work and auto-lock, wing and fin stop tilting, finally, two folding mechanism of control flexible deformation wing and fin begin folding work simultaneously, two wings fold forward, two fins fold backward, when two planes of two wings (fin) place form the contained angle and be 60, control wing and folding rotary driving motor stop work and auto-lock, unmanned aerial vehicle transitions into four rotor flight mode.
According to the invention, the tilting-folding-telescopic wing vertical take-off and landing variant unmanned aerial vehicle has innovative designs such as large-scale deformation wings, large-scale tilting-folding mechanisms of wings and bodies, and the like, and can realize full-mode conversion between fixed wings and four-rotation wings. Meanwhile, the four-rotor unmanned aerial vehicle has the advantages of being strong in cruising ability, high in loading ability, strong in maneuverability and high in flying speed. Meanwhile, the variant unmanned aerial vehicle improves the environment adaptability of the traditional tilting wing type vertical take-off and landing unmanned aerial vehicle, and provides a reference path for the design direction of the novel variant unmanned aerial vehicle in the future.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should make equivalent substitutions or modifications according to the technical scheme of the present invention and the inventive concept thereof, and should be covered by the scope of the present invention.
Claims (6)
1. The vertical take-off and landing variant unmanned aerial vehicle with the tilting, folding and telescopic wings comprises a fuselage (1), a telescopic deformation machine wing (2) and a tail wing (3), and is characterized in that the telescopic deformation machine wing (2) and the tail wing (3) are respectively connected with the head part and the tail part of the fuselage (1) through a folding mechanism (4), and the telescopic deformation machine wing (2) and the tail wing (3) are both rotatably connected with a propeller (5) through driving mechanisms;
the telescopic deformation wing (2) comprises two main wing beams (201) and auxiliary wing beams (202) which are symmetrically arranged, wherein a main skin (203) is fixedly sleeved outside the two main wing beams (201), an auxiliary skin (204) is fixedly sleeved outside the two auxiliary wing beams (202), a plurality of main wing ribs (205) are slidably sleeved on the main wing beams (201), a plurality of auxiliary wing ribs (206) are slidably sleeved on the auxiliary wing beams (202), two first rotary driving motors (207) are fixedly connected on the main wing ribs (205) at the wing root end, a plurality of telescopic mechanisms are arranged between the main wing ribs (205) and the auxiliary wing ribs (206), and the output ends of the first rotary driving motors (207) are connected with the telescopic mechanisms;
folding mechanism (4) are including center wheel (401), gear circle (402), frame (403), second rotary driving motor (404), third rotary driving motor (405) and wing connecting piece (406) that the symmetry set up, center wheel (401) are connected with the output of second rotary driving motor (404), gear circle (402) rotate meshing and link have three planet wheel (407), gear circle (402) fixed connection on fuselage (1), one side and frame (403) fixed connection of planet wheel (407), second rotary driving motor (404) and third rotary driving motor (405) all with frame (403) fixed connection, the output of third rotary driving motor (405) and wing connecting piece (406) fixed connection, wing connecting piece (406) one end and frame (403) rotate to be connected.
2. The unmanned aerial vehicle of claim 1, wherein a plurality of the telescoping mechanisms are arranged in a linear array.
3. A wing tiltable, foldable and telescopic vertical take-off and landing variant unmanned aerial vehicle according to claim 2, wherein the telescopic mechanism comprises a first driving lever (6), a second driving lever (7), a first driven lever (8), a first slider (9), a second driven lever (10), a second slider (11), a third driven lever (12) and a fourth driven lever (13); the novel automatic transmission device is characterized in that the first driving rod (6), the second driven rod (10) and the fourth driven rod (13) are connected through coaxial matching, the second driving rod (7), the first driven rod (8) and the third driven rod (12) are connected through coaxial matching, the first sliding block (9) is in sliding sleeve joint with the first driving rod (6), one end of the first driven rod (8) is in rotating connection with the first sliding block (9), the second sliding block (11) is in sliding sleeve joint with the third driven rod (12), and one end of the second driven rod (10) is in rotating connection with the second sliding block (11).
4. The unmanned aerial vehicle with the tilting, folding and telescopic vertical lifting wings according to claim 3, wherein the connecting gears (14) are fixedly connected to the ends, far away from the first driving rod (6), the second driving rod (7), the third driven rod (12) and the fourth driven rod (13), of the main wing rib (205) and the auxiliary wing rib (206) respectively, and mounting ports corresponding to the connecting gears (14) are formed in the main wing rib and the auxiliary wing rib.
5. The unmanned aerial vehicle with tilting, folding and telescopic vertical take-off and landing wing according to claim 1, wherein the first rotary driving motor (207), the second rotary driving motor (404) and the third rotary driving motor (405) are all self-locking rotary driving motors.
6. A wing tiltable, foldable and telescopic vertical take-off and landing variant unmanned aerial vehicle according to claim 1, wherein the bottom of the fuselage (1) is rotatably connected with a plurality of landing gear (15) symmetrically arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310379673.1A CN116215907B (en) | 2023-04-11 | 2023-04-11 | Vertical take-off and landing variant unmanned aerial vehicle with tilting, folding and telescopic wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310379673.1A CN116215907B (en) | 2023-04-11 | 2023-04-11 | Vertical take-off and landing variant unmanned aerial vehicle with tilting, folding and telescopic wings |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116215907A CN116215907A (en) | 2023-06-06 |
| CN116215907B true CN116215907B (en) | 2023-08-04 |
Family
ID=86571518
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310379673.1A Active CN116215907B (en) | 2023-04-11 | 2023-04-11 | Vertical take-off and landing variant unmanned aerial vehicle with tilting, folding and telescopic wings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116215907B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117985216B (en) * | 2024-04-03 | 2024-05-28 | 中国科学院工程热物理研究所 | Quick-detachable and foldable wing or tail wing spar structure of airplane and method |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104163A (en) * | 2019-04-28 | 2019-08-09 | 厦门大学 | One kind can hang down flying wing type unmanned plane |
| CN110271659A (en) * | 2019-07-03 | 2019-09-24 | 北京航空航天大学 | A kind of small drone fold concertina-wise wing based on paper folding principle |
| CN110341951A (en) * | 2019-07-22 | 2019-10-18 | 中北大学 | A kind of unmanned vehicle of folding wing and tilting rotor |
| CN111645848A (en) * | 2020-06-03 | 2020-09-11 | 西安交通大学 | Skeleton structure of telescopic wing |
| CN113353243A (en) * | 2021-07-30 | 2021-09-07 | 郑州航空工业管理学院 | From multi-functional unmanned aerial vehicle commodity circulation car of becoming wing |
| CN113415406A (en) * | 2021-06-29 | 2021-09-21 | 中国科学院长春光学精密机械与物理研究所 | Wing interval adjusting module, aircraft comprising same and aircraft control method |
| CN113525678A (en) * | 2021-09-17 | 2021-10-22 | 北京航空航天大学 | Traction-propulsion type manned aircraft with tilting wings for vertical take-off and landing |
| CN114771819A (en) * | 2022-04-07 | 2022-07-22 | 上海电气集团股份有限公司 | Vertical take-off and landing's deformation wing unmanned aerial vehicle |
| CN114987752A (en) * | 2022-06-20 | 2022-09-02 | 南京航空航天大学 | Wing for tilt rotor aircraft, tilt rotor aircraft and tilt method thereof |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150136898A1 (en) * | 2013-10-28 | 2015-05-21 | Jeremiah Benjamin Bowe McCoy | Telescopic Wing and Rack System for Automotive Airplane |
| US9522725B2 (en) * | 2014-02-13 | 2016-12-20 | Northrup Grumman Systems Corporation | Stowable and deployable unmanned aerial vehicle |
| IL241201B (en) * | 2015-09-06 | 2019-11-28 | Uvision Air Ltd | Foldable wings for an unmanned air vehicle |
| US20180297698A1 (en) * | 2017-04-13 | 2018-10-18 | Sanjay Dhall | Aircraft Having Telescopic Wings and Tilting Motor Assemblies |
| US11691713B2 (en) * | 2019-03-17 | 2023-07-04 | Behrang Mehrgan | VTOL having retractable wings |
-
2023
- 2023-04-11 CN CN202310379673.1A patent/CN116215907B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110104163A (en) * | 2019-04-28 | 2019-08-09 | 厦门大学 | One kind can hang down flying wing type unmanned plane |
| CN110271659A (en) * | 2019-07-03 | 2019-09-24 | 北京航空航天大学 | A kind of small drone fold concertina-wise wing based on paper folding principle |
| CN110341951A (en) * | 2019-07-22 | 2019-10-18 | 中北大学 | A kind of unmanned vehicle of folding wing and tilting rotor |
| CN111645848A (en) * | 2020-06-03 | 2020-09-11 | 西安交通大学 | Skeleton structure of telescopic wing |
| CN113415406A (en) * | 2021-06-29 | 2021-09-21 | 中国科学院长春光学精密机械与物理研究所 | Wing interval adjusting module, aircraft comprising same and aircraft control method |
| CN113353243A (en) * | 2021-07-30 | 2021-09-07 | 郑州航空工业管理学院 | From multi-functional unmanned aerial vehicle commodity circulation car of becoming wing |
| CN113525678A (en) * | 2021-09-17 | 2021-10-22 | 北京航空航天大学 | Traction-propulsion type manned aircraft with tilting wings for vertical take-off and landing |
| CN114771819A (en) * | 2022-04-07 | 2022-07-22 | 上海电气集团股份有限公司 | Vertical take-off and landing's deformation wing unmanned aerial vehicle |
| CN114987752A (en) * | 2022-06-20 | 2022-09-02 | 南京航空航天大学 | Wing for tilt rotor aircraft, tilt rotor aircraft and tilt method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 伸缩机翼变体飞机气动布局初步研究;李士途;艾俊强;李军府;马泽孟;;航空科学技术(01);第25-28页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116215907A (en) | 2023-06-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10293928B2 (en) | Devices and methods for in flight transition VTOL/fixed wing hybrid aircraft structures and flight modes | |
| CN108528692B (en) | Folding wing dual-rotor aircraft and control method thereof | |
| JP2001213397A (en) | Improvement of aircraft | |
| CN113212753A (en) | Imitative dragonfly multi-mode conversion microminiature unmanned aerial vehicle of upset airfoil | |
| CN112238939B (en) | Novel-configuration tilt rotor aircraft and flight control method thereof | |
| US11603191B1 (en) | Stowable lift rotors for VTOL aircraft | |
| CN116215907B (en) | Vertical take-off and landing variant unmanned aerial vehicle with tilting, folding and telescopic wings | |
| CN113753229A (en) | Foldable fixed-wing four-rotor composite unmanned aerial vehicle and control method thereof | |
| CN113212752A (en) | Multi-mode switching micro unmanned aerial vehicle | |
| CN109896002B (en) | Deformable four-rotor aircraft | |
| CN116101524B (en) | Fixed wing rotor wing dual-mode tailstock type vertical take-off and landing unmanned aerial vehicle and working method | |
| CN113443134B (en) | Vertical take-off and landing aircraft with lift force blades capable of being folded and unfolded variably and with tail seat | |
| CN112124589B (en) | Two rotor vector unmanned aerial vehicle that verts | |
| CN113232830A (en) | Vertical take-off and landing unmanned aerial vehicle with foldable wings and control method thereof | |
| CN209956209U (en) | Unmanned aerial vehicle for vertical take-off and landing of morphing wing | |
| CN214451835U (en) | Detachable tilting four-rotor aircraft | |
| CN113104195B (en) | Double-duct composite wing aircraft | |
| CN219406885U (en) | Tilting four-duct aircraft with double-wing layout | |
| CN213832115U (en) | Wing body integrated unmanned aerial vehicle capable of vertically taking off and landing | |
| CN220448123U (en) | Fixed wing aircraft capable of changing sweepback wing to vertically take off and land | |
| CN211618083U (en) | Four-duct rotor fixed wing aircraft capable of taking off and landing vertically | |
| CN113148138B (en) | Tailstock type unmanned aerial vehicle and control method | |
| CN111776194B (en) | Aircraft suitable for long-term endurance, vertical take-off and landing and portable loading | |
| CN211618084U (en) | Double-duct rotor wing fixed wing aircraft capable of taking off and landing vertically | |
| CN114802703A (en) | Wing body flip structure, wing, unmanned aerial vehicle |
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 |