CN111731466A - Aircraft with automatic folding wings - Google Patents

Aircraft with automatic folding wings Download PDF

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Publication number
CN111731466A
CN111731466A CN202010527802.3A CN202010527802A CN111731466A CN 111731466 A CN111731466 A CN 111731466A CN 202010527802 A CN202010527802 A CN 202010527802A CN 111731466 A CN111731466 A CN 111731466A
Authority
CN
China
Prior art keywords
wing
aircraft
connecting rod
driving
limiting member
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.)
Pending
Application number
CN202010527802.3A
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Chinese (zh)
Inventor
谢陵
刘十一
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Zhongshan Fukun Aviation Technology Co ltd
Original Assignee
Zhongshan Fukun Aviation Technology Co ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Zhongshan Fukun Aviation Technology Co ltd filed Critical Zhongshan Fukun Aviation Technology Co ltd
Priority to CN202010527802.3A priority Critical patent/CN111731466A/en
Publication of CN111731466A publication Critical patent/CN111731466A/en
Pending legal-status Critical Current

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    • 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
    • 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
    • B64C27/22—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
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force

Abstract

The invention discloses an aircraft with automatically folded wings, which comprises an aircraft body, wherein wing assemblies are respectively arranged on the left side and the right side of the aircraft body, and each wing assembly comprises an inner wing, an outer wing and a folding driving mechanism; the inner side of the inner wing is connected with the fuselage, and the outer side of the inner wing is connected with the inner side of the outer wing; one end of the folding driving mechanism is installed on the inner wing, the other end of the folding driving mechanism is installed on the outer wing, and the folding driving mechanism expands or folds the outer wing. In the embodiment of the invention, the aircraft can automatically expand the wings during cruising flight to increase the wing span, thereby improving the cruising flight endurance time, and meanwhile, the aircraft can automatically fold the wings during vertical take-off, landing and hovering to reduce the wing span, thereby improving the wind resistance of the aircraft during vertical take-off, landing and hovering, having good flight performance, and simultaneously reducing the take-off, landing and storage space required by the aircraft.

Description

Aircraft with automatic folding wings
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft with automatically folded wings.
Background
In recent years, aircrafts have been continuously developed, and have the advantages of low manufacturing cost, simplicity and convenience in operation, high flexibility, capability of flying at ultra-low altitude and the like, so that the aircrafts are increasingly widely used by various industries, and most of the existing aircrafts are mainly applied to the fields of scientific research, geographic detection, agricultural irrigation, video shooting and the like.
In a conventional aircraft, in order to further improve the cruising flight endurance, the wing span needs to be increased, but the increase of the wing span affects the wind resistance of the aircraft in the vertical take-off and landing and hovering states, and brings certain negative effects on the vertical take-off and landing and hovering of the aircraft.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and provides an aircraft with automatically folded wings, wherein the aircraft can automatically unfold the wings during cruising flight, can automatically fold the wings during vertical take-off, landing and hovering, has good flight performance, and can reduce the take-off and landing place and the storage space required by the aircraft.
Correspondingly, the embodiment of the invention provides an aircraft with automatically folded wings, which comprises a fuselage, wherein wing assemblies are respectively arranged on the left side and the right side of the fuselage, and each wing assembly comprises an inner wing, an outer wing and a folding driving mechanism;
the inner side of the inner wing is connected to the fuselage, and the outer side of the inner wing is connected with the inner side of the outer wing; one end of the folding driving mechanism is installed on the inner wing, the other end of the folding driving mechanism is installed on the outer wing, and the folding driving mechanism unfolds or folds the outer wing.
In an alternative embodiment, the outer side of the inner wing and the inner side of the outer wing are connected by a hinge.
In an optional embodiment, the folding driving mechanism comprises a steering engine and a four-bar linkage;
the steering engine is arranged on the inner wing;
the four-bar linkage mechanism comprises a driving connecting bar, a middle connecting bar and a fixed connecting bar; one end of the driving connecting rod is connected with the steering engine, the other end of the driving connecting rod is hinged with one end of the middle connecting rod, the other end of the middle connecting rod is hinged with one end of the consolidation connecting rod, and the other end of the consolidation connecting rod is fixed on the outer wing.
In an optional implementation manner, the wing assembly further includes a limiting member and a fastening point mechanism, the limiting member is connected with the inner wing through a torsion spring, and the fastening point mechanism includes a slope block, a sliding block and a hook-shaped member;
the inclined plane block is fixed on the limiting piece, and a sliding shaft is arranged in the inclined plane block; the sliding block is arranged on the sliding shaft in a sliding mode; the hook-shaped piece is fixed on the sliding block, and one end of the hook-shaped piece is connected with the torsion spring;
when the outer wing is unfolded, the driving connecting rod is matched with the limiting part and drives the limiting part and the inclined plane block to move along the vertical direction, the inclined plane block is matched with the sliding block and drives the sliding block to slide along the sliding shaft, and the sliding block drives the hook-shaped piece to rotate so as to hook and fix the consolidation connecting rod.
In an optional implementation mode, one side of the inclined plane block is provided with a first inclined plane, one side of the sliding block is provided with a second inclined plane matched with the first inclined plane, and when the outer wing is unfolded, the first inclined plane of the inclined plane block is matched with the second inclined plane of the sliding block and drives the sliding block to slide along the sliding shaft.
In an optional implementation manner, the wing assembly further includes a limiting member bottom plate, the limiting member bottom plate is connected to the inner wing, a limiting member guide shaft is vertically disposed on the limiting member bottom plate, and when the outer wing is unfolded, the driving connecting rod is matched with the limiting member and drives the limiting member to move along the limiting member guide shaft.
In an optional embodiment, a vertical power device is further arranged on the machine body;
in an optional implementation mode, the vertical power device comprises a plurality of rotor arms, one end of any one of the rotor arms is fixed on the fuselage, a vertical driving motor is arranged at the other end of any one of the rotor arms, a vertical rotor is connected to the driving end of the vertical driving motor, and the vertical rotor rotates under the driving of the vertical driving motor.
In an optional embodiment, the vertical starting power device further comprises a rotor arm expansion device arranged on the fuselage, one end of each of the plurality of rotor arms is connected with the rotor arm expansion device, and the plurality of rotor arms are driven by the rotor arm expansion device to synchronously expand and contract.
The embodiment of the invention provides an aircraft with automatically folded wings, wherein the aircraft can automatically unfold the wings during cruising flight to increase the wing span so as to improve the cruising flight endurance time, and simultaneously can automatically fold the wings during vertical take-off, landing and hovering so as to reduce the wing span so as to improve the wind resistance of the aircraft during vertical take-off, landing and suspension, so that the aircraft has good flight performance, and meanwhile, the take-off, landing and storage space required by the aircraft can be reduced.
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 top view of an aircraft with an outer wing deployed in accordance with an embodiment of the present invention;
FIG. 2 is a top view of an aircraft with the outer wings folded in accordance with an embodiment of the present invention;
FIG. 3 is a rear view of an aircraft with the outer wings folded in accordance with an embodiment of the present invention;
FIG. 4 is a schematic illustration of a wing assembly of an embodiment of the invention in an outboard wing deployment;
FIG. 5 is a schematic view of a wing assembly according to an embodiment of the invention when the outer wing is folded;
FIG. 6 is a schematic view of a first configuration of a stuck point mechanism in an embodiment of the invention;
fig. 7 is a second structural diagram of the click mechanism in the embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Fig. 1 is a plan view of an aircraft with an outer wing according to an embodiment of the present invention unfolded, fig. 2 is a plan view of an aircraft with an outer wing according to an embodiment of the present invention folded, and fig. 3 is a rear view of an aircraft with an outer wing according to an embodiment of the present invention folded.
The embodiment of the invention provides an aircraft with automatically folded wings, which comprises a fuselage 1, wherein wing assemblies 2 are respectively arranged on the left side and the right side of the fuselage 1, and an inner wing 21, an outer wing 22 and a folding driving mechanism are arranged in the wing assemblies 2;
the inner side of the inner wing 21 is connected to the fuselage 1, and the outer side of the inner wing 21 is connected with the inner side of the outer wing 22; one end of the folding driving mechanism is mounted on the inner wing 21, the other end of the folding driving mechanism is mounted on the outer wing 22, and the folding driving mechanism expands or folds the outer wing 22.
When the aircraft vertically takes off, lands and hovers, the folding driving mechanism folds the outer wing 22, and the outer wing 22 faces upwards, so that the wing span is reduced, and the wind resistance of the aircraft during vertical take off, lands and suspension can be improved simultaneously by matching with the outer wing 22 facing upwards.
When the aircraft is in cruising flight, the folding driving mechanism unfolds the outer wing 22, so that the wing span of the aircraft is increased, and the cruising flight duration of the aircraft is further improved.
In the embodiment of the present invention, the outer side of the inner wing 21 and the inner side of the outer wing 22 are connected by a hinge 4, the hinge 4 is adopted to realize the connection between the outer side of the inner wing 21 and the inner side of the outer wing 22, the outer wing 22 can be flexibly, quietly and perfectly unfolded or folded, and a good practical use effect is achieved.
Fig. 4 is a schematic structural view of a wing assembly according to an embodiment of the present invention when the outer wing is unfolded, and fig. 5 is a schematic structural view of the wing assembly according to an embodiment of the present invention when the outer wing is folded.
The folding driving mechanism can be implemented in various ways, in the embodiment of the present invention, the folding driving mechanism includes a steering engine 23 and a four-bar linkage 24, and the unfolding or folding of the outer wing 22 is realized through the steering engine 23 and the four-bar linkage 24.
The steering engine 23 is arranged on the inner wing 21.
The four-bar linkage 24 comprises a driving connecting rod 241, a middle connecting rod 242 and a fixed connecting rod 243, one end of the driving connecting rod 241 is connected with the steering engine 23, the other end of the driving connecting rod 241 is hinged with one end of the middle connecting rod 242, the other end of the middle connecting rod 242 is hinged with one end of the fixed connecting rod 243, and the other end of the fixed connecting rod 243 is fixed on the outer wing 22.
When the aircraft vertically takes off, lands and hovers, the four-bar linkage 24 moves under the driving of the steering engine 23 so as to fold the outer wing 22.
When the aircraft is in cruising flight, the four-bar linkage 24 moves under the driving of the steering engine 23 to unfold the outer wing 22.
Fig. 6 is a first structural schematic diagram of a click mechanism in an embodiment of the present invention, and fig. 7 is a second structural schematic diagram of the click mechanism in the embodiment of the present invention.
In the embodiment of the present invention, the wing assembly 2 further includes a limiting member 25 and a fastening point mechanism 26, when the outer wing 22 is completely deployed, the outer wing 22 can be fixed based on the limiting member 25 and the fastening point mechanism 26, so as to avoid the situation that the outer wing 22 swings during the cruise flight, thereby ensuring the normal cruise flight of the aircraft.
The limiting member 25 is connected to the inner wing 21 through a torsion spring 251.
The click mechanism 26 comprises a slope block 261, a sliding block 262 and a hook 263; the inclined plane block 261 is fixed on the limiting member 25, and a sliding shaft 2611 is arranged in the inclined plane block 261; the sliding block 262 is slidably disposed on the sliding shaft 2611; the hook 263 is fixed on the sliding block 262, and one end of the hook 263 is connected to the torsion spring 251.
When the aircraft is in cruising flight, the driving connecting rod 241 moves under the driving of the steering engine 23, the driving connecting rod 241 drives the middle connecting rod 242 and the fixing connecting rod 243 to move, the outer wing 22 is unfolded through the fixing connecting rod 243, in the process of unfolding the outer wing 22, the driving connecting rod 241 is matched with the limiting piece 25 and drives the limiting piece 25 and the inclined plane block 261 on the limiting piece 25 to move along the vertical direction, the inclined plane block 261 is matched with the sliding block 262 and drives the sliding block 262 to slide along the sliding shaft 2611, the sliding block 262 drives the hook-shaped piece 263 to rotate by taking the torsion spring 251 as the center, when the hook-shaped piece 263 rotates to the torque limit of the torsion spring 251, the hook-shaped piece 263 fixes the fixing connecting rod 243 in a hooking manner, so that the fixing connecting rod 243 is fixed to support the outer wing 22, fixing the outer wing 22 in this way avoids the outer wing 22 from wobbling during cruise flight, thereby ensuring normal cruise flight of the aircraft.
In addition, when the aircraft vertically takes off, lands and hovers, the driving connecting rod 241 is driven by the steering engine 23 to move, the driving connecting rod 241 drives the middle connecting rod 242 and the fixed connecting rod 243 to move, the outer wing 22 is folded through the fixed connecting rod 243, at this time, the driving connecting rod 241 is not matched with the limiting part 25, the limiting part 25 resets under the action of the torsion spring 251, and the clamping point mechanism 26 is driven to reset.
In the embodiment of the present invention, one side of the inclined block 261 is provided with a first inclined surface 2612, one side of the sliding block 262 is provided with a second inclined surface 2621 engaged with the first inclined surface 2612, during the process of unfolding the outer wing 22, the first inclined surface 2612 of the inclined block 261 is engaged with the second inclined surface 2621 of the sliding block 262 and drives the sliding block 262 to slide along the sliding shaft 2611, and the inclined block 261 drives the sliding block 262 to slide along the sliding shaft 2611 in this way, which has the advantages of simple structure and reasonable design, and can drive the sliding block 262 to slide along the sliding shaft 2611 without being engaged with other mechanisms, thereby reducing the overall weight of the aircraft and further improving the cruising flight duration of the aircraft.
In the embodiment of the present invention, the wing assembly 2 further includes a limiting member base plate 27, the limiting member base plate 27 is connected to the inner wing 21, a limiting member guide shaft 271 is vertically disposed on the limiting member base plate 27, and in the process of unfolding the outer wing 22, the driving link 241 is matched with the limiting member 25 and drives the limiting member 25 to move along the limiting member guide shaft 271, so as to ensure that the limiting member 25 and the inclined plane block 261 always move along the vertical direction, and thus ensure that the inclined plane block 261 and the sliding block 262 are normally matched.
In the embodiment of the invention, a vertical tail 11 is arranged above the rear end of the machine body 1, and horizontal tails 12 are symmetrically arranged on the left side and the right side of the rear end of the machine body 1.
It should be noted that the vertical tail 11 can reduce the induced drag of the aircraft and increase the lift-to-drag ratio of the aircraft, thereby improving the flight performance of the aircraft in vertical take-off and landing and hovering; the main function of the horizontal tail 12 is to generate lift force, which not only improves the aerodynamic effect of the aircraft, but also increases the lateral stability of the aircraft, and also can well improve the flight performance of the aircraft in vertical take-off and landing and hovering.
The fuselage 1 is also provided with a power device, the power device comprises a cruise power device 31 and a vertical starting power device 32, the cruise power device 31 is used for driving the cruise flight of the aircraft, and the vertical starting power device 32 is used for driving the aircraft to vertically take off, land and hover.
The cruise power device 31 may be implemented in various ways, and in the embodiment of the present invention, the cruise power device 31 includes a cruise drive motor and a cruise rotor 311, the cruise drive motor is disposed at the tail of the fuselage 1, the cruise rotor 311 is connected to the driving end of the cruise drive motor, and the cruise rotor 311 is driven by the cruise drive motor to rotate so as to drive the aircraft to cruise.
The vertical starting power device 32 may be implemented in various manners, in an embodiment of the present invention, the vertical starting power device 32 includes a rotor arm expansion device 321 and a plurality of rotor arms 322, the rotor arm expansion device 321 is disposed in the middle of the fuselage 1, the plurality of rotor arms 322 are uniformly distributed along the same circumference, the plurality of rotor arms 322 are respectively connected to the rotor arm expansion device 321, and the plurality of rotor arms 322 are synchronously expanded and contracted under the driving of the rotor arm expansion device 321.
Wherein, the one end of arbitrary rotor arm 322 with rotor arm telescoping device 321's flexible end is connected, and the other end of arbitrary rotor arm 322 is provided with the driving motor that hangs down, it hangs down to be connected with on driving motor's the drive end and hangs down rotor 3221, it is in to hang down rotor 3221 rotatory under driving motor's the drive of hanging down to the drive aircraft VTOL and hover.
When the aircraft vertically takes off and lands and hovers, the rotor arm telescopic device 321 drives the plurality of rotor arms 322 to synchronously extend out and expand to the outside of the fuselage 1 so as to drive the aircraft to vertically take off and land and hover.
When the aircraft is cruising, the rotor arm expansion device 321 drives the plurality of rotor arms 322 to synchronously contract and retract into the fuselage 1, so that the flight resistance of the aircraft is reduced, and the cruising flight duration of the aircraft is further prolonged.
The embodiment of the invention provides an aircraft with automatically folded wings, wherein the aircraft can automatically unfold the wings during cruising flight to increase the wing span so as to improve the cruising flight endurance time, and simultaneously can automatically fold the wings during vertical take-off, landing and hovering so as to reduce the wing span so as to improve the wind resistance of the aircraft during vertical take-off, landing and suspension, so that the aircraft has good flight performance, and meanwhile, the take-off, landing and storage space required by the aircraft can be reduced.
In addition, the above detailed description is provided for the aircraft with the automatically folded wings according to the embodiments of the present invention, and specific examples are used herein to explain the principles and embodiments of the present invention, and the above descriptions of the embodiments are only used to help understanding the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.

Claims (9)

1. The aircraft with the automatically folded wings is characterized by comprising an aircraft body, wherein wing assemblies are respectively arranged on the left side and the right side of the aircraft body, and each wing assembly comprises an inner wing, an outer wing and a folding driving mechanism;
the inner side of the inner wing is connected to the fuselage, and the outer side of the inner wing is connected with the inner side of the outer wing; one end of the folding driving mechanism is installed on the inner wing, the other end of the folding driving mechanism is installed on the outer wing, and the folding driving mechanism unfolds or folds the outer wing.
2. The aircraft of claim 1 wherein the outer side of the inner wing is hingedly connected to the inner side of the outer wing.
3. The aircraft of claim 1, wherein the folding drive mechanism comprises a steering engine and a four-bar linkage;
the steering engine is arranged on the inner wing;
the four-bar linkage mechanism comprises a driving connecting bar, a middle connecting bar and a fixed connecting bar; one end of the driving connecting rod is connected with the steering engine, the other end of the driving connecting rod is hinged with one end of the middle connecting rod, the other end of the middle connecting rod is hinged with one end of the consolidation connecting rod, and the other end of the consolidation connecting rod is fixed on the outer wing.
4. The aircraft of claim 3, wherein the wing assembly further comprises a limiting member and a click mechanism, the limiting member is connected with the inner wing by a torsion spring, and the click mechanism comprises a ramp block, a sliding block and a hook-shaped member;
the inclined plane block is fixed on the limiting piece, and a sliding shaft is arranged in the inclined plane block; the sliding block is arranged on the sliding shaft in a sliding mode; the hook-shaped piece is fixed on the sliding block, and one end of the hook-shaped piece is connected with the torsion spring;
when the outer wing is unfolded, the driving connecting rod is matched with the limiting part and drives the limiting part and the inclined plane block to move along the vertical direction, the inclined plane block is matched with the sliding block and drives the sliding block to slide along the sliding shaft, and the sliding block drives the hook-shaped piece to rotate so as to hook and fix the consolidation connecting rod.
5. The aircraft of claim 4, wherein a first bevel is disposed on one side of the bevel block, a second bevel engaged with the first bevel is disposed on one side of the sliding block, and when the outer wing is deployed, the first bevel of the bevel block engages with the second bevel of the sliding block and drives the sliding block to slide along the sliding shaft.
6. The aircraft of claim 4, wherein the wing assembly further comprises a limiting member base plate, the limiting member base plate is connected to the inner wing, a limiting member guide shaft is vertically disposed on the limiting member base plate, and when the outer wing is unfolded, the driving link is engaged with the limiting member and drives the limiting member to move along the limiting member guide shaft.
7. The aircraft of claim 1, wherein a vertical power device is further provided on the fuselage.
8. The aircraft of claim 7, wherein the droop-starting power device comprises a plurality of rotor arms, one end of each rotor arm is fixed on the fuselage, the other end of each rotor arm is provided with a droop-driving motor, a droop rotor is connected to the driving end of the droop-driving motor, and the droop rotor is driven by the droop-driving motor to rotate.
9. The aircraft of claim 8 wherein the vertical starting power assembly further comprises a rotor arm retraction mechanism disposed on the fuselage, one end of each of the plurality of rotor arms being coupled to the rotor arm retraction mechanism, the plurality of rotor arms being synchronously retractable upon actuation of the rotor arm retraction mechanism.
CN202010527802.3A 2020-06-10 2020-06-10 Aircraft with automatic folding wings Pending CN111731466A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202010527802.3A CN111731466A (en) 2020-06-10 2020-06-10 Aircraft with automatic folding wings

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202010527802.3A CN111731466A (en) 2020-06-10 2020-06-10 Aircraft with automatic folding wings

Publications (1)

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CN111731466A true CN111731466A (en) 2020-10-02

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CN202010527802.3A Pending CN111731466A (en) 2020-06-10 2020-06-10 Aircraft with automatic folding wings

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114104263A (en) * 2021-12-09 2022-03-01 中航金城无人系统有限公司 Wing folding mechanism and unmanned aerial vehicle
CN114313217A (en) * 2022-01-13 2022-04-12 南京航空航天大学 Wing capable of folding and unfolding along unfolding direction variant
DE102020007836A1 (en) 2020-12-21 2022-06-23 BAAZ GmbH Aircraft with wings and operating procedures

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102020007836A1 (en) 2020-12-21 2022-06-23 BAAZ GmbH Aircraft with wings and operating procedures
CN114104263A (en) * 2021-12-09 2022-03-01 中航金城无人系统有限公司 Wing folding mechanism and unmanned aerial vehicle
CN114313217A (en) * 2022-01-13 2022-04-12 南京航空航天大学 Wing capable of folding and unfolding along unfolding direction variant
CN114313217B (en) * 2022-01-13 2023-09-29 南京航空航天大学 Wing capable of being folded and unfolded along unfolding direction variation

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