CN114248917A - Lever transmission flapping wing aircraft - Google Patents
Lever transmission flapping wing aircraft Download PDFInfo
- Publication number
- CN114248917A CN114248917A CN202011508976.1A CN202011508976A CN114248917A CN 114248917 A CN114248917 A CN 114248917A CN 202011508976 A CN202011508976 A CN 202011508976A CN 114248917 A CN114248917 A CN 114248917A
- Authority
- CN
- China
- Prior art keywords
- wing
- point
- wings
- transmission rod
- flapping
- 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
Links
- 230000005540 biological transmission Effects 0.000 title claims abstract description 58
- 230000007246 mechanism Effects 0.000 claims abstract description 50
- 230000033001 locomotion Effects 0.000 claims abstract description 7
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 6
- 230000009471 action Effects 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 6
- 230000008602 contraction Effects 0.000 claims description 4
- 230000005484 gravity Effects 0.000 claims description 3
- 241000203475 Neopanax arboreus Species 0.000 claims description 2
- 230000000694 effects Effects 0.000 claims description 2
- 230000008569 process Effects 0.000 claims description 2
- 230000003068 static effect Effects 0.000 claims description 2
- 208000032370 Secondary transmission Diseases 0.000 claims 1
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 239000000725 suspension Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000009191 jumping Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
A lever transmission flapping wing aircraft is characterized in that reciprocating motion is converted into up-and-down flapping motion of double wings of the aircraft through a lever principle, the structure of the lever transmission flapping wing aircraft comprises a supporting frame mechanism, a lever transmission mechanism, a flight bearing mechanism and a flight control mechanism, the supporting frame mechanism comprises wheels and a supporting frame, the lever transmission mechanism comprises a handle 11, a pedal 12, a track 13, a main transmission rod 141, an auxiliary transmission rod 142, a two-wing transmission rod 143, a fixed hinged point 144 and a movable hinged point 145, the flight bearing mechanism comprises a front wing and a tail wing 25, the front wing comprises a shoulder wing 21, a middle wing 22, a side wing 23 and a side wing 24, and the flight control mechanism comprises a front wing control mechanism, a tail wing control mechanism and a glide control mechanism.
Description
Technical Field
The invention belongs to the fields of sports fitness, entertainment supplies and air transportation, and particularly relates to a lever transmission flapping wing aircraft.
Background
The existing flapping wing air vehicle transmission forms are mostly pedal chain transmission and suspension dead weight transmission, and through retrieval, the prior art which is closer to the invention mainly comprises the following steps: the manpower flapping wing aircraft with the application number of CN00254985.9, the manpower flapping wing flight parachute with the application number of CN201710447152.X, the flapping wing mechanism with the application number of CN201910037530.6 and the manpower flapping wing aircraft with the left wing and the right wing capable of automatically changing the elevation angle.
The manpower flapping wing aircraft with application number of CN00254985.9 adopts pedal chain transmission, has low transmission efficiency and large energy loss, and can not exert the maximum force of human body, the manpower flapping wing flight parachute with application number of CN201710447152.X bears the weight of human body by a suspension part, the leg pedaling and the pull rod action adopt a suspension dead weight transmission mode, the flight parachute is actually a paraglider, the transmission mode is unreasonable, the flapping on the wings is realized by the dead weight of human body, the rising potential energy generated by the flapping of the wings is offset, the flapping wing mechanism and the manpower flapping wing aircraft with application number of CN201910037530.6, the left and right wings can automatically change the elevation angle, the human body stands on the pedals, the human body squats by the human body to perform periodic pedaling motion, the flapping on the wings is generated by the resilience force of a spring when the human body squats, the human body stands to generate effective power required by downward flapping wing by overcoming the self gravity and the rear force of the spring, the working efficiency is low, the energy loss is large, the maximum force of the human body cannot be exerted.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a lever transmission flapping wing aircraft, which is characterized in that reciprocating motion is converted into vertical flapping of two wings of the aircraft through a lever principle, the structure of the lever transmission flapping wing aircraft comprises a supporting frame mechanism, a lever transmission mechanism, a flight bearing mechanism and a flight control mechanism, the supporting frame mechanism comprises wheels and a supporting frame, the lever transmission mechanism comprises a handle 11, a pedal 12, a track 13, a main transmission rod 141, an auxiliary transmission rod 142, a two-wing transmission rod 143, a fixed hinge point 144 and a movable hinge point 145, the flight bearing mechanism comprises a front wing and a tail wing 25, the front wing comprises a shoulder wing 21, a middle wing 22, a side wing 23 and an auxiliary wing 24, and the flight control mechanism comprises a front wing control mechanism, a tail wing control mechanism and a gliding control mechanism.
The part of the 141 main transmission rod connected with the 11 handle and the 12 pedal is designed to be telescopic, so that the 11 handle and the 12 pedal can reciprocate linearly back and forth along the 13 track under the action of manpower or mechanical force, and then the 141 main transmission rod and the 144 fixed hinge point drive the 145 movable hinge point, the 142 auxiliary transmission rod and the 143 two-wing transmission rod to move up and down, thereby realizing the up and down flapping of the two wings.
The two-wing transmission rod of the 21 shoulder wing and the 143 are rigidly and fixedly connected, the connecting point D is fixedly hinged with the frame, the connecting point B of the two-wing transmission rod of the 21 shoulder wing and the 143 can reciprocate between the point B and the point C of the frame, so that the effect can be realized, the connecting point B of the two-wing transmission rod of the 21 shoulder wing and the 143 is driven by the simultaneous contraction of the two legs and the two arms to drive the 145 movable hinge point at the inner side of the 143 to move downwards, the connecting point B of the two-wing transmission rod of the 21 shoulder wing and the 143 is driven to move downwards by the downward pulling force to the point C of the frame, the point A is separated from the frame and upwarps, the two wings are lifted upwards by a certain angle when flapping, the two wings form windward surfaces, the flapping resistance on the two wings can be reduced, the lifting force of the two wings can be increased in the flying process, the two legs and the two arms simultaneously pedal and extend to drive the 145 movable hinge point at the inner side of the two-wing transmission rod of the 143 to move upwards, the connecting point B of the 21 shoulder wing and the two-wing transmission rod of the 143 is driven to move upwards to the point B of the frame, the point A is overlapped with the frame, the double wings are in a horizontal state when flapping downwards, and generate the maximum thrust. The E point between the 21 shoulder wing and the 22 middle wing is connected by a universal joint, the 21 shoulder wing can move downwards and backwards at a certain angle around the E point by adopting proper limit measures, but the upward relative movement cannot exceed 180 degrees, the F point is a movable hinge point, can rotate downwards by more than 90 degrees, but can not rotate upwards by more than 180 degrees, the point G is a movable hinge point, can rotate upwards by more than 90 degrees, but can not rotate downwards by more than 180 degrees, in addition, the 22 middle wing and the 23 side wing, the 21 shoulder wing, the 22 middle wing, the 23 side wing and the 24 aileron are hinged in a certain downward angle range, the middle wing and the side wings are folded and retracted towards the back and the lower part under the action of gravity, so that the resistance and the weight of the upward flapping wings are reduced, when the flapping wings are downward, the two wings can be completely unfolded under the action of air resistance, and the effective area of the downward flapping wings is not reduced.
The front wing control mechanism is controlled by a mechanism similar to a bicycle cable, the binding handle is fixed on the handle, the distance between the point B of the frame and the point C of the connecting point B of the two wing transmission rods 21 and 143 can be controlled by retracting and releasing the binding handle, and the elevation angles of the two front wings can be respectively controlled while the handle reciprocates so as to adjust the flying attitude and decelerate before landing.
The control mode of the tail wing control mechanism is the same as the control principle and method of the front wing control mechanism.
The control mode of the glide control mechanism is similar to the control principle and method of the front wing control mechanism, the tail end of the binding wire is controlled, 3-4 telescopic rod pieces are respectively arranged at two sides of the joint of the 143 two-wing transmission rod and the 142 auxiliary transmission rod, when the two wings flap, the rod pieces are in a contraction state, the rod pieces extend out and are mutually overlapped in a gliding state, and the two wings can keep a nearly horizontal static state like palm five-finger crossing.
The lift-off assisting power can adopt electric rail accelerating power or strong spring vertical ejection power to lift off.
The human body is approximately horizontally prostrate at the bottom of the supporting frame mechanism, the two legs and the two arms simultaneously bend and extend to generate force, the lever transmission mechanism drives the two wings to flap, the maximum human body force is converted into the force of air flapping downwards by the minimum transmission loss, and the human body jumping motion vertically upwards is realized by means of the lever transmission mechanism and the two wings.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Drawings
FIG. 1 is a schematic view of a lever-actuated ornithopter with its wings fully deployed horizontally in a gliding position.
FIG. 2 is a schematic diagram of a lever-driven flapping wing aircraft with two wings retracted backwards and upwards and flapping upwards.
FIG. 3 is a schematic diagram of a lever-actuated flapping wing aircraft with the wings fully extended and flapping downward.
Claims (7)
1. A lever transmission flapping wing aircraft is characterized in that: the structure of the device comprises a supporting frame mechanism, a lever transmission mechanism, a flight bearing mechanism and a flight control mechanism, wherein the supporting frame mechanism comprises wheels and a supporting frame, the lever transmission mechanism comprises a handle 11, a pedal 12, a track 13, a main transmission rod 141, a secondary transmission rod 142, a two-wing transmission rod 143, a fixed hinge point 144 and a movable hinge point 145, the flight bearing mechanism comprises a front wing and a tail wing 25, the front wing comprises a shoulder wing 21, a middle wing 22, a side wing 23 and an aileron 24, and the flight control mechanism comprises a front wing control mechanism, a tail wing control mechanism and a glide control mechanism.
2. The lever-actuated ornithopter of claim 1, wherein: the part of the 141 main transmission rod connected with the 11 handle and the 12 pedal is designed to be telescopic, so that the 11 handle and the 12 pedal can reciprocate linearly back and forth along the 13 track under the action of manpower or mechanical force, and then the 141 main transmission rod and the 144 fixed hinge point drive the 145 movable hinge point, the 142 auxiliary transmission rod and the 143 two-wing transmission rod to move up and down, thereby realizing the up and down flapping of the two wings.
3. The lever-actuated ornithopter of claim 1, wherein: the two-wing transmission rod of the 21 shoulder wing and the 143 are rigidly and fixedly connected, the connecting point D is fixedly hinged with the frame, the connecting point B of the two-wing transmission rod of the 21 shoulder wing and the 143 can reciprocate between the point B and the point C of the frame, so that the effect can be realized, the connecting point B of the two-wing transmission rod of the 21 shoulder wing and the 143 is driven by the simultaneous contraction of the two legs and the two arms to drive the 145 movable hinge point at the inner side of the 143 to move downwards, the connecting point B of the two-wing transmission rod of the 21 shoulder wing and the 143 is driven to move downwards by the downward pulling force to the point C of the frame, the point A is separated from the frame and upwarps, the two wings are lifted upwards by a certain angle when flapping, the two wings form windward surfaces, the flapping resistance on the two wings can be reduced, the lifting force of the two wings can be increased in the flying process, the two legs and the two arms simultaneously pedal and extend to drive the 145 movable hinge point at the inner side of the two-wing transmission rod of the 143 to move upwards, the connecting point B of the 21 shoulder wing and the two-wing transmission rod of the 143 is driven to move upwards to the point B of the frame, the point A is overlapped with the frame, the double wings are in a horizontal state when flapping downwards, and generate the maximum thrust.
4.E point between the shoulder wing 21 and the middle wing 22 adopts universal joint connection, by adopting proper limit measures, the shoulder wing 21 can move downwards and backwards at a certain angle around the E point, but the upward relative movement can not exceed 180 degrees, the F point is a movable hinge point, can rotate downwards by more than 90 degrees, but can not rotate upwards by more than 180 degrees, the point G is a movable hinge point, can rotate upwards by more than 90 degrees, but can not rotate downwards by more than 180 degrees, in addition, the 22 middle wing and the 23 side wing, the 21 shoulder wing, the 22 middle wing, the 23 side wing and the 24 aileron are hinged in a certain downward angle range, the middle wing and the side wings are folded and retracted towards the back and the lower part under the action of gravity, so that the resistance and the weight of the upward flapping wings are reduced, when the flapping wings are downward, under the action of air resistance, the two wings can be completely unfolded, and the effective area of the downward flapping wings is not reduced.
5. The lever-actuated ornithopter of claim 1, wherein: the front wing control mechanism is controlled by a mechanism similar to a bicycle cable, the binding handle is fixed on the handle, the distance between the point B of the frame and the point C of the connecting point B of the two wing transmission rods 21 and 143 can be controlled by retracting and releasing the binding handle, and the elevation angles of the two front wings can be respectively controlled while the handle reciprocates so as to adjust the flying attitude and decelerate before landing.
6. The lever-actuated ornithopter of claim 1, wherein: the control mode of the tail wing control mechanism is the same as the control principle and method of the front wing control mechanism.
7. The lever-actuated ornithopter of claim 1, wherein: the control mode of the glide control mechanism is similar to the control principle and method of the front wing control mechanism, the tail end of the binding wire is controlled, 3-4 telescopic rod pieces are respectively arranged at two sides of the joint of the 143 two-wing transmission rod and the 142 auxiliary transmission rod, when the two wings flap, the rod pieces are in a contraction state, the rod pieces extend out and are mutually overlapped in a gliding state, and the two wings can keep a nearly horizontal static state like palm five-finger crossing.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2020109910101 | 2020-09-25 | ||
| CN202010991010 | 2020-09-25 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114248917A true CN114248917A (en) | 2022-03-29 |
Family
ID=80789604
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011508976.1A Pending CN114248917A (en) | 2020-09-25 | 2020-12-19 | Lever transmission flapping wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114248917A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023217282A1 (en) * | 2022-05-12 | 2023-11-16 | 盛阳 | Ornithopter |
-
2020
- 2020-12-19 CN CN202011508976.1A patent/CN114248917A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023217282A1 (en) * | 2022-05-12 | 2023-11-16 | 盛阳 | Ornithopter |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108945431B (en) | Bird and bat imitating foldable wing of ornithopter | |
| CN108995804B (en) | Bionic aircraft for realizing flight mode conversion between flapping rotor wing and flapping wing based on deformable wing | |
| CN203854858U (en) | Ornithopter | |
| JP5490717B2 (en) | Muscle-driven airplane with flapping wings | |
| CN114455071B (en) | Wing-like dragon carrying robot | |
| CN114248917A (en) | Lever transmission flapping wing aircraft | |
| CN102649477B (en) | Flapping wing airplane | |
| CN108706100B (en) | Bird-like flapping-wing aircraft | |
| CN220764682U (en) | Manpower ornithopter | |
| CN106864727B (en) | Inflatable glider unmanned aerial vehicle | |
| CN105438466B (en) | A kind of manpower driving fixed wing aircraft | |
| CN202124117U (en) | Balloon-assisted and human-powered flying system | |
| US2757886A (en) | Manually sustained glider type aircraft | |
| CN216374999U (en) | Copying ornithopter | |
| CN107352031B (en) | Flapping wing aircraft capable of controlling flying action by sensing human body action | |
| CN201012291Y (en) | Kite | |
| CN115837977A (en) | Flapping folding movement mechanism for flapping wing aircraft | |
| CN212047880U (en) | Tile type six-connecting-rod flapping mechanism | |
| CN208593490U (en) | Rudder plane controlling mechanism and model plane | |
| CN107472525B (en) | Full-motion type flapping-wing manpower flight device | |
| KR200417261Y1 (en) | Air gate wing aircraft, | |
| CN101700808A (en) | Forward and backward double-rotor type single-person aircraft | |
| CN201045077Y (en) | Manpower flying assistant | |
| CN201520409U (en) | Backward-forward dual-rotor one-man aerobat | |
| RU2009072C1 (en) | Airship |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20220329 |