CN218703884U - Bionic flapping wing aircraft - Google Patents
Bionic flapping wing aircraft Download PDFInfo
- Publication number
- CN218703884U CN218703884U CN202222975703.9U CN202222975703U CN218703884U CN 218703884 U CN218703884 U CN 218703884U CN 202222975703 U CN202222975703 U CN 202222975703U CN 218703884 U CN218703884 U CN 218703884U
- Authority
- CN
- China
- Prior art keywords
- transmission
- driving
- rod
- wing
- hinged
- 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
Images
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a bionic flapping wing aircraft, which comprises a frame and two front wings arranged at the two sides of the frame; the front wing comprises a main wing and an aileron, one side of the main wing is respectively hinged with the frame, and the aileron is hinged with the other side of the main wing; the frame is provided with a first driving mechanism, the first driving mechanism comprises a first driving piece, a first transmission mechanism and a second transmission mechanism, the first driving piece is connected with the two main wings through the first transmission mechanism respectively and drives the two main wings to swing up and down along a hinge point between the two main wings and the frame, the second transmission mechanism is connected with the first transmission mechanism and the two ailerons respectively, the first transmission mechanism drives the second transmission mechanism to move when moving, and drives the two ailerons to swing up and down along the hinge point between the two ailerons and the main wings through the second transmission mechanism. The flapping wing aircraft can simulate and restore the flapping wing action of bird flight to the maximum extent during flight by designing the structure and the action drive of the flapping wing aircraft.
Description
Technical Field
The utility model belongs to the technical field of the aircraft, concretely relates to bionical flapping wing aircraft.
Background
With the continuous development of micro aircrafts, the aircrafts are more and more developed towards the direction of miniaturization and flexible movement. The micro aircraft is divided into a fixed wing aircraft, a rotor aircraft and a bionic flapping wing aircraft according to the difference of motion mechanisms, and from the perspective of bionics, the flapping wing aircraft has better flight performance relative to the fixed wing aircraft and the rotor aircraft under the condition of small size. Therefore, the flapping-wing air vehicle has attracted wide attention in the technical field of micro air vehicles due to the advantages of small size, portability, flexible flight, excellent concealment and the like.
The existing flapping wing air vehicle needs to simulate complex flapping wing actions, and is often complex in the aspect of structural design, so that the stability and continuity of the flapping wing air vehicle in the motion process are difficult to be ensured in practice, and the application and the use performance of the flapping wing air vehicle are limited to a certain extent.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a bionical flapping wing aircraft can solve the problem of stability, the action continuity that flapping wing aircraft exists in the motion process, can realize the bionical simulation better to the flapping wing action.
The utility model discloses a following technical scheme realizes:
the bionic flapping wing aircraft comprises a frame and two front wings arranged on two sides of the frame;
the front wing comprises a main wing and an aileron, one side of the main wing is respectively hinged with the frame, and the aileron is hinged with the other side of the main wing;
the driving mechanism comprises a first driving part, a first transmission mechanism and a second transmission mechanism, the first driving part is connected with the two main wings through the first transmission mechanism respectively and drives the two main wings to swing up and down along the hinge point between the two main wings and the frame, the second transmission mechanism is connected with the first transmission mechanism and the two ailerons respectively, the first transmission mechanism drives the second transmission mechanism to move when moving, and the second transmission mechanism drives the two ailerons to swing up and down along the hinge point between the two ailerons and the main wings.
As a further improvement to the above technical solution, the first transmission mechanism includes two sets of first transmission components respectively connected with the two main wings;
the first transmission assembly comprises a transmission assembly and a connecting rod assembly, a crank connecting rod mechanism is formed between the transmission assembly and the connecting rod assembly, the transmission assembly comprises a first transmission wheel rotatably connected with the rack and a first transmission shaft arranged on the first transmission wheel, the first transmission shaft is arranged at a position far away from the axis of the first transmission wheel, the first driving piece drives the first transmission wheel to rotate, one end of the connecting rod assembly is hinged with the first transmission shaft, the other end of the connecting rod assembly is hinged with the main wing, and the connecting end between the connecting rod assembly and the main wing is driven to reciprocate up and down when the first transmission wheel rotates;
the first transmission shaft is connected with the first transmission wheel in a sliding fit mode, so that the first transmission shaft can rotate along the axis of the first transmission shaft and can slide on the first transmission wheel along the axis direction of the first transmission shaft.
As a further improvement to the above technical solution, the link assembly includes a first driven rod connected to the first rotating shaft and a first driving rod connected to the main wing, and the first driven rod and the first driving rod are connected by a cross universal joint.
As a further improvement of the above technical solution, the second transmission mechanism includes a second connecting rod and a second transmission rod fixedly connected to the aileron, one end of the second connecting rod is hinged to the output end of the connecting rod assembly, the other end of the second connecting rod is hinged to the second transmission rod, and a four-bar linkage mechanism is formed among the second transmission rod, the second connecting rod, the main wing and the connecting rod assembly.
As a further improvement to the above technical solution, an auxiliary transmission mechanism is arranged between the main wing and the aileron, and the auxiliary transmission mechanism and the second transmission mechanism are oppositely arranged at an interval along the longitudinal direction of the frame;
the auxiliary transmission mechanism comprises an auxiliary swing rod and an auxiliary connecting rod which are hinged with the main wing, and an auxiliary transmission rod fixedly connected to the auxiliary wing, wherein two ends of the auxiliary connecting rod are respectively hinged with the auxiliary swing rod and the auxiliary transmission rod, and a four-bar mechanism is formed among the auxiliary swing rod, the auxiliary connecting rod, the auxiliary transmission rod and the main wing.
As a further improvement to the technical scheme, the first driving part adopts a double-shaft output motor, and two output shafts of the first driving part simultaneously drive two groups of first transmission assemblies to act.
As a further improvement to the technical scheme, the first driving part and the first driving wheel are connected through a third transmission mechanism respectively, the third transmission mechanism comprises a speed reduction component and a third transmission part, the speed reduction component is connected with the output shaft of the first driving part, the third transmission part is rotatably connected with the rack, the third transmission part is connected with the output shaft of the speed reduction component, and the third transmission part is connected with the first driving wheel in a meshed mode.
As a further improvement to the technical scheme, the speed reduction assembly comprises a driving wheel and a driven wheel, the driving wheel is connected with an output shaft of the first driving piece, and the driven wheel is connected with the driving wheel through a synchronous belt wheel.
As a further improvement to the above technical solution, the tail part of the frame is provided with a tail wing and a tail wing driving mechanism;
the tail wing driving mechanism comprises a pitching driving assembly and a steering driving assembly, the pitching driving assembly is used for driving the tail wing to swing up and down in the vertical direction, and the steering driving assembly is used for driving the tail wing to swing left and right.
As a further improvement to the above technical solution, the steering driving assembly includes a first steering engine disposed on the frame and a steering driving rod connected to an output end of the first steering engine;
the pitching driving assembly comprises a supporting swing rod which is hinged with the rack and can rotate in the horizontal direction, a second steering engine which is arranged on the supporting swing rod and a pitching driving rod which is connected with the output end of the second steering engine;
the steering driving rod is hinged to the output end of the first steering engine, the other end of the steering driving rod is hinged to the support swing rod, one end of the pitching driving rod is hinged to the output end of the second steering engine, the other end of the pitching driving rod is hinged to the tail wing, the tail wing is hinged to the support swing rod, and the tail wing can rotate up and down along a hinged point.
Compared with the prior art, the utility model, following advantage and beneficial effect have:
1) Through the design of the flapping wing aircraft structure and the action drive, the flapping wing aircraft can simulate and restore the flapping wing action of bird flight to the maximum extent during flight, so that the action of the aircraft in the flight process is more continuous, the maximum action efficiency can be exerted, various flight actions can be realized, and the flight control requirement of the aircraft can be met.
2) Through designing the structure of the front wing driving mechanism in the flapping wing aircraft, the structure is simpler and has better reliability and stability while realizing the bionic action of the front wing.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained from the drawings without inventive efforts.
Fig. 1 is the structure schematic diagram of the bionic flapping wing air vehicle of the utility model.
Fig. 2 is a partial schematic view of a portion a of fig. 1.
Fig. 3 is a partial schematic view of fig. 1 at B.
Fig. 4 is a front view of the bionic flapping wing aircraft structure of the utility model.
Fig. 5 is a top view of the bionic flapping wing aircraft structure of the utility model.
Figure 6 is the utility model discloses bionical flapping wing aircraft structure right side view.
Fig. 7 is a partial schematic view of fig. 6 at C.
Fig. 8 is a partial schematic view of fig. 6 at D.
Fig. 9 is the schematic view of the structure of the auxiliary transmission mechanism in the bionic flapping wing aircraft.
Wherein:
11. the main wing 12, the ailerons 13, the tail wing 14, the frame 15 and the power supply cabin;
201. the device comprises a first driving part 202, a first driving wheel 203, a first transmission shaft 204, a first driven rod 205, a first driving rod 206, a cross universal joint 207, a second connecting rod 208, a second transmission rod 209, an auxiliary swing rod 210, an auxiliary connecting rod 211, an auxiliary transmission rod 212, a third transmission part 213, a driving wheel 214, a driven wheel 215, a synchronous belt wheel 216, a first steering engine 217, a rotation driving rod 218, a support swing rod 219, a second steering engine 220 and a pitch driving rod.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention.
Referring to fig. 1, 4 and 5, the bionic ornithopter in this embodiment includes a frame 14 and two front wings disposed at two sides of the frame 14, where the front wings include a main wing 11 and an auxiliary wing 12, the two main wings 11 are respectively hinged to the frame at one side, the auxiliary wing 12 is respectively disposed at the outer side of the main wing 11 and is hinged to the other side of the main wing, so as to form a front wing structure in which the main wing can swing up and down relative to the frame along a hinge point between the main wing and the frame, and the auxiliary wing can swing up and down relative to the main wing along a hinge point between the auxiliary wing and the main wing.
A first driving mechanism is disposed on the frame 14, and the first driving mechanism used in this embodiment includes a first driving member 201, a first transmission mechanism, and a second transmission mechanism.
The first driving member 201 is connected to the two main wings 11 through a first transmission mechanism, and drives the two main wings to swing up and down along a hinge point between the two main wings and the frame through the first transmission mechanism.
As a specific practical structure, the first transmission mechanism comprises two groups of first transmission assemblies respectively connected with the two main wings, each first transmission assembly comprises a transmission assembly and a connecting rod assembly, and a crank connecting rod mechanism is formed between the transmission assembly and the connecting rod assembly; as shown in fig. 2 and 4, the transmission assembly includes a first transmission wheel 202 rotatably connected to the frame and a first transmission shaft 203 disposed on the first transmission wheel, the first transmission shaft 203 is disposed at a position away from the axis of the first transmission wheel, and when the first transmission wheel rotates, the first transmission shaft is driven to rotate, so as to form a crank driving structure; the first driving member 201 is connected with the first driving wheel 202 and drives the first driving wheel 202 to rotate; one end of the connecting rod component is hinged with the first transmission shaft, and the other end of the connecting rod component is hinged with the main wing; when the first driving wheel rotates, the connecting end between the connecting rod assembly and the main wing is driven by the connecting rod assembly to do up-and-down reciprocating motion, so that the up-and-down reciprocating swing action of the main wing is driven.
Because the distance between the connecting end position between the connecting rod assembly and the main wing and the rack can be changed actually when the main wing swings up and down, the first transmission shaft 203 and the first transmission wheel 202 are connected in a sliding fit manner, so that the first transmission shaft 203 can slide on the first transmission wheel along the axial direction while rotating along the axis, and the connecting position between the connecting rod assembly and the first transmission shaft can move along the axial direction of the first transmission shaft to meet the requirement of up-and-down swinging of the main wing. Or the first transmission shaft 203 is fixedly arranged on the first transmission wheel 202, and the connection between the connecting rod assembly and the first rotating shaft is arranged to be in sliding fit connection, that is, the connecting rod assembly can slide on the first transmission shaft along the first transmission shaft while being in hinged rotation connection on the first transmission shaft, so as to realize the same functions.
The connecting rod assembly comprises a first driven rod 204 connected with the first transmission shaft and a first driving rod 205 connected with the main wing, and the first driven rod 204 and the first driving rod 205 are connected through a universal joint cross 206 so as to adapt to the realization of complex actions in the driving process of the main wing.
A frame structure may be disposed at the connection position between the first driving rod 201 and the main wing 11 to increase the stability of the connection and movement between the first driving rod and the main wing.
The second transmission mechanism is respectively connected with the first transmission mechanism and the two ailerons, the first transmission mechanism drives the second transmission mechanism to act when acting, the two ailerons are driven to swing up and down along the hinged point between the ailerons and the main wing through the second transmission mechanism, the swinging direction of the main wing is just opposite to the swinging direction of the ailerons at the same moment, and the bionic simulation of the flapping wing action is realized.
As a specific practical structure, as shown in fig. 2 and 4, the second transmission mechanism includes a second link 207 and a second transmission rod 208 fixedly connected to the flap, wherein one end of the second link 207 is connected to the first driving rod 205 of the link assembly and is hinged to the first driving rod 205, the other end of the second link 207 is hinged to one end of the second transmission rod 208, and a four-bar linkage is formed between the second transmission rod 208, the second link 207, the main flap 11 and the first driving rod 205 of the link assembly. When the first driving rod reciprocates up and down, the second connecting rod is driven to act, the second driving rod is driven to act under the action of the second connecting rod, and the ailerons are driven to swing up and down along the hinged point between the ailerons and the main wing through the second driving rod. The second transmission rod is connected and arranged at the position of the hinge point of the aileron and the main wing so as to better facilitate the driving of the aileron.
In order to improve the stability of the action of the ailerons, an auxiliary transmission mechanism is arranged between the main wing and the ailerons, the auxiliary transmission mechanism and a second transmission mechanism are oppositely arranged at intervals along the longitudinal direction of the frame, namely the second transmission mechanism is arranged at the position close to the front end of the aileron, the auxiliary transmission mechanism is arranged at the position close to the rear end of the aileron on the frame, and the two groups of auxiliary transmission mechanisms jointly form transmission and support for the ailerons.
As shown in fig. 9, the auxiliary transmission mechanism includes an auxiliary swing link 209 hinged to the main wing, an auxiliary link 210 and an auxiliary transmission rod 211 fixedly connected to the auxiliary wing, a connection position between the auxiliary swing link and the main wing and a connection position between the first driving rod and the main wing are located at substantially the same corresponding position on the main wing along the longitudinal direction of the frame, two ends of the auxiliary link 210 are respectively hinged to the auxiliary swing link 209 and the auxiliary transmission rod 211, and a four-bar linkage is formed between the auxiliary swing link 209, the auxiliary link 210, the auxiliary transmission rod 211 and the main wing 11, so as to realize stable support of the auxiliary wing and simultaneously avoid interference between the main wing and the auxiliary transmission mechanism during the swing process.
Here, the first driving member 201 adopts a dual-shaft output motor, and two output shafts of the first driving member 201 simultaneously drive two sets of first transmission assemblies to act, so that the front wings on both sides are simultaneously driven, and the synchronism of the actions of the front wings on both sides is ensured.
As shown in fig. 6 and 7, the first driving member 201 is connected to the first driving wheel 202 in the first driving assembly through a third transmission mechanism, so as to drive the first driving wheel, the third transmission mechanism includes a speed reducing assembly connected to the output shaft of the first driving member and a third transmission member 212, the third transmission member 212 is rotatably connected to the frame 14, and the third transmission member 212 is connected to the output shaft of the speed reducing assembly, that is, the first driving member drives the third transmission member to rotate through the speed reducing assembly, and the third transmission member is engaged with the first driving wheel, so as to drive the first driving wheel.
The speed reduction assembly comprises a driving wheel 213 and a driven wheel 214, wherein the driving wheel 213 is connected with an output shaft of the first driving part 201, the driven wheel 214 is rotatably connected with the rack 14, the driven wheel 214 is connected with the driving wheel 213 through a synchronous belt pulley 215, and flexible transmission between the first driving part and the first driving wheel is realized while speed reduction is carried out, so that a better action bionic simulation effect is achieved.
The tail part of the frame 14 is provided with a tail wing 13 and a tail wing driving mechanism; the tail wing driving mechanism is used for driving the tail wing to move so as to control the turning and other actions of the aircraft, and comprises a pitching driving assembly and a turning driving assembly, wherein the pitching driving assembly is used for driving the tail wing to swing up and down in the vertical direction, and the turning driving assembly is used for driving the tail wing to swing left and right.
Specifically, as shown in fig. 3 and 8, the steering driving assembly includes a first steering engine 216 disposed on the frame and a steering driving rod 217 connected to an output end of the first steering engine.
The pitching driving component comprises a supporting swing rod 218 which is connected with the frame through a hinge and can rotate in the horizontal direction, a second steering engine 219 arranged on the supporting swing rod, and a pitching driving rod 220 connected with the output end of the second steering engine.
The rotating driving rod 217 is hinged with the output end of the first steering engine 216, the other end of the rotating driving rod is hinged with the supporting swing rod 218, and the supporting swing rod can be driven to swing left and right in the horizontal direction when the first steering engine acts; one end of the pitching driving rod 220 is hinged with the output end of the second steering engine 219, the other end of the pitching driving rod is hinged with the empennage 13, the empennage 13 is hinged with the supporting swing rod 218 and can rotate up and down along a hinged point, and the empennage can be driven to swing up and down when the second steering engine acts, so that the flying direction of the aircraft can be controlled.
A power supply bin 15 used for setting a power supply is arranged at the tail of the rack 14, and the power supply is arranged in the power supply bin 15 and provides electric energy required by work for the first driving piece, the first steering engine and the second steering engine. The power supply bin is arranged at the tail of the rack and used for balancing the front weight and the rear weight of the aircraft, so that the gravity center of the aircraft is located at a position close to the middle part, and the flying stability is guaranteed.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like, which are used herein, refer to the orientation or positional relationship shown in the drawings, or the orientation or positional relationship that the product of the present invention is usually placed when in use, and are only used for convenience of description, and are not intended to indicate or imply that the device or element to which the term refers must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "horizontal", "vertical" and the like when used in the description of the present invention do not require that the components be absolutely horizontal or hanging, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed," "mounted," "connected," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The above is only the preferred embodiment of the present invention, not to the limitation of the present invention in any form, all the technical matters of the present invention all fall into the protection scope of the present invention to any simple modification and equivalent change of the above embodiments.
Claims (10)
1. The bionic flapping wing aircraft is characterized by comprising a rack and two front wings arranged on two sides of the rack;
the front wing comprises a main wing and an aileron, one side of the main wing is respectively hinged with the frame, and the aileron is hinged with the other side of the main wing;
the driving mechanism comprises a first driving part, a first transmission mechanism and a second transmission mechanism, the first driving part is connected with the two main wings through the first transmission mechanism respectively and drives the two main wings to swing up and down along the hinge point between the two main wings and the frame, the second transmission mechanism is connected with the first transmission mechanism and the two ailerons respectively, the first transmission mechanism drives the second transmission mechanism to move when moving, and the second transmission mechanism drives the two ailerons to swing up and down along the hinge point between the two ailerons and the main wings.
2. The bionic ornithopter as claimed in claim 1, wherein the first transmission mechanism comprises two sets of first transmission components connected to the two main wings respectively;
the first transmission assembly comprises a transmission assembly and a connecting rod assembly, a crank connecting rod mechanism is formed between the transmission assembly and the connecting rod assembly, the transmission assembly comprises a first transmission wheel rotatably connected with the rack and a first transmission shaft arranged on the first transmission wheel, the first transmission shaft is arranged at a position far away from the axis of the first transmission wheel, the first driving piece drives the first transmission wheel to rotate, one end of the connecting rod assembly is hinged with the first transmission shaft, the other end of the connecting rod assembly is hinged with the main wing, and the connecting end between the connecting rod assembly and the main wing is driven to reciprocate up and down when the first transmission wheel rotates;
the first transmission shaft is connected with the first transmission wheel in a sliding fit mode, so that the first transmission shaft can rotate along the axis of the first transmission shaft and can slide on the first transmission wheel along the axis direction of the first transmission shaft.
3. The bionic ornithopter as claimed in claim 2, wherein the linkage assembly comprises a first driven rod connected with the first rotating shaft and a first driving rod connected with the main wing, and the first driven rod and the first driving rod are connected through a cross universal joint.
4. The bionic ornithopter as claimed in claim 2 or 3, wherein the second transmission mechanism comprises a second connecting rod and a second transmission rod fixedly connected to the aileron, one end of the second connecting rod is hinged to the output end of the connecting rod assembly, the other end of the second connecting rod is hinged to the second transmission rod, and a four-bar linkage mechanism is formed among the second transmission rod, the second connecting rod, the main wing and the connecting rod assembly.
5. The bionic ornithopter as claimed in claim 4, wherein an auxiliary transmission mechanism is arranged between the main wing and the aileron, and the auxiliary transmission mechanism and the second transmission mechanism are oppositely arranged at intervals along the longitudinal direction of the frame;
the auxiliary transmission mechanism comprises an auxiliary swing rod and an auxiliary connecting rod which are hinged with the main wing, and an auxiliary transmission rod fixedly connected to the auxiliary wing, wherein two ends of the auxiliary connecting rod are respectively hinged with the auxiliary swing rod and the auxiliary transmission rod, and a four-bar mechanism is formed among the auxiliary swing rod, the auxiliary connecting rod, the auxiliary transmission rod and the main wing.
6. The bionic ornithopter as claimed in claim 2, wherein the first driving member is a two-shaft output motor, and two output shafts of the first driving member simultaneously drive the two sets of first transmission assemblies to move.
7. The bionic flapping wing aircraft of claim 1, wherein the first driving member and the first driving wheel are connected through a third transmission mechanism respectively, the third transmission mechanism comprises a speed reducing component connected with the output shaft of the first driving member and a third transmission member, the third transmission member is rotatably connected with the frame, the third transmission member is connected with the output shaft of the speed reducing component, and the third transmission member is meshed with the first driving wheel.
8. The bionic ornithopter as claimed in claim 7, wherein the speed reduction assembly comprises a driving wheel and a driven wheel, the driving wheel is connected with the output shaft of the first driving member, and the driven wheel is connected with the driving wheel through a synchronous pulley.
9. The bionic ornithopter as claimed in claim 1, wherein the tail part of the frame is provided with a tail and a tail driving mechanism;
the tail wing driving mechanism comprises a pitching driving assembly and a steering driving assembly, the pitching driving assembly is used for driving the tail wing to swing up and down in the vertical direction, and the steering driving assembly is used for driving the tail wing to swing left and right.
10. The bionic ornithopter as claimed in claim 9, wherein the steering driving assembly comprises a first steering engine arranged on the frame and a steering driving rod connected with an output end of the first steering engine;
the pitching driving assembly comprises a supporting swing rod which is hinged with the rack and can rotate in the horizontal direction, a second steering engine which is arranged on the supporting swing rod and a pitching driving rod which is connected with the output end of the second steering engine;
the steering driving rod is hinged to the first steering engine output end, the other end of the steering driving rod is hinged to the support swing rod, one end of the pitching driving rod is hinged to the second steering engine output end, the other end of the pitching driving rod is hinged to the tail wing, and the tail wing is hinged to the support swing rod and can rotate up and down along a hinged point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222975703.9U CN218703884U (en) | 2022-11-09 | 2022-11-09 | Bionic flapping wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222975703.9U CN218703884U (en) | 2022-11-09 | 2022-11-09 | Bionic flapping wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218703884U true CN218703884U (en) | 2023-03-24 |
Family
ID=85610997
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222975703.9U Active CN218703884U (en) | 2022-11-09 | 2022-11-09 | Bionic flapping wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218703884U (en) |
-
2022
- 2022-11-09 CN CN202222975703.9U patent/CN218703884U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108945430B (en) | Bionic flapping-folding-active torsion hybrid-driven flapping wing aircraft | |
| CN103241379B (en) | A kind of flapping wing device realizing wing flapping wing and aerofoil active twist | |
| CN110065630B (en) | Bionic flapping wing flying robot | |
| CN204323687U (en) | A kind of four wing flapping-wing modal | |
| US6824094B2 (en) | Power assembly for ornicopter | |
| CN110466755B (en) | Chord length self-adaptive telescopic flapping wing suitable for active torsion flapping mechanism and flapping wing machine | |
| CN106672204A (en) | Tilting mechanism for tilting rotor wing airplane | |
| CN212401546U (en) | Bionic aircraft | |
| CN114802745A (en) | Bionic flapping wing aircraft with variable body posture | |
| CN103569360B (en) | Translation flapping wing mechanism and flapping-wing aircraft and the aerodone with translation flapping wing mechanism | |
| CN115027670A (en) | Insect-imitating double-wing mechanical flapping wing aircraft with variable flapping amplitude | |
| CN108706100B (en) | Bird-like flapping-wing aircraft | |
| CN109911197A (en) | A kind of four-degree-of-freedom flapping wing aircraft device | |
| CN218703884U (en) | Bionic flapping wing aircraft | |
| CN110816827B (en) | Bionic butterfly flapping-wing aircraft | |
| CN112141332A (en) | Five pole flapping wing aircraft in space based on just gentle coupling | |
| CN114435590B (en) | Variable-incidence-angle ornithopter with wing rotation function | |
| CN109502019B (en) | Large bionic flapping wing aircraft | |
| CN115973414A (en) | Miniature flapping wing aircraft based on cross tail control | |
| CN115837977A (en) | Flapping folding movement mechanism for flapping wing aircraft | |
| CN112078791B (en) | Flapping wing aircraft | |
| CN210503181U (en) | 8-shaped wing tip track micro bionic ornithopter | |
| CN210479022U (en) | Multi-degree-of-freedom flapping wing mechanism of simulated hummingbird flapping wing aircraft | |
| CN214325372U (en) | Mechanical bird | |
| CN217396808U (en) | Bionic flapping wing aircraft with variable body posture |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |