CN114379779A - Universal aircraft - Google Patents
Universal aircraft Download PDFInfo
- Publication number
- CN114379779A CN114379779A CN202210026063.9A CN202210026063A CN114379779A CN 114379779 A CN114379779 A CN 114379779A CN 202210026063 A CN202210026063 A CN 202210026063A CN 114379779 A CN114379779 A CN 114379779A
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- Prior art keywords
- annular ring
- motor
- aircraft
- shell
- main
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- 241000883990 Flabellum Species 0.000 claims 1
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a universal aircraft, which comprises a hollowed-out shell, wherein a first annular ring, a second annular ring and a third annular ring are connected in the shell, the first annular ring is positioned in the shell and connected with the shell, the second annular ring is arranged in the first annular ring and rotatably connected with the first annular ring, the third annular ring is arranged in the second annular ring and rotatably connected with the second annular ring, a main connecting rod is connected in the third annular ring, a main motor is arranged on the lower half section of the main connecting rod, a main fan blade is fixedly sleeved on an output shaft of the main motor, the main motor is connected with a control system, and the control system controls the main motor to rotate. When the aircraft is used by a user, no matter how the user holds the aircraft, the aircraft can automatically adjust the right side of the aircraft to be upward, the normal flight of the aircraft is ensured, the angle of the aircraft does not need to be adjusted by the user, and the operation is simple and convenient.
Description
Technical Field
The invention relates to an aircraft, in particular to a universal aircraft.
Background
With the development of the technology, the unmanned aerial vehicle is widely applied in the civil field and the military field. Unmanned aerial vehicles are widely used for terrain reconnaissance, unmanned shooting or other entertainment. The existing unmanned aerial vehicle has some defects in the using process, for example, the blades of the unmanned aerial vehicle are exposed in the air, and when the unmanned aerial vehicle flies in the fields of jungle or underground pipeline investigation and the like, the blades collide with obstacles such as branches and cables, so that the blades are damaged. Therefore, spherical aircrafts appear on the market, and the main principle is that the paddle is wrapped by a hollow shell to achieve the purpose of protecting the paddle.
For example, the Chinese patent application with the application publication number of CN106005392A and the publication date of 2016, 10, 12 discloses a spherical aircraft, which comprises a spherical sleeve, the outer side surface of the spherical sleeve is hollow, a frame is arranged on the inner side of the spherical sleeve, a motor is vertically arranged on the frame at the spherical center of the spherical sleeve, paddles are arranged at the output end of the motor, a steering engine is arranged in the frame below the motor, two sides of the steering engine are respectively and symmetrically hinged with a rudder sheet, the spherical sleeve comprises a longitude ring and a latitude ring which are made of hard materials, the longitude ring with the same diameter is vertically and fixedly arranged at the central position of the latitude ring along the radial direction of the latitude ring, a plurality of reinforcing rings are uniformly arranged in gaps between the longitude ring and the lateral wall of the latitude ring at intervals, a flight control device is arranged in the frame, and a flight control module is arranged in the flight control device, the control end of the flight control module is connected with a motor control module and a rudder control module.
The application publication number is CN104724286A, and the publication date is 2015, 6 and 24 Chinese patent application discloses a spherical aircraft. The electric control culvert device comprises an upper hemisphere, a control panel, a camera module, a lower hemisphere, a culvert fan, an electric controller, a main circuit board, a circuit support frame and a battery, wherein the upper hemisphere and the lower hemisphere are connected to form a spherical cavity, the upper hemisphere is provided with the control panel, the camera module and an air inlet, the lower hemisphere is provided with an air outlet, the culvert fan is arranged in the air outlet, the electric controller, the main circuit board and the battery are arranged in the spherical cavity through the circuit support frame, the electric controller is connected with the main circuit board and the battery, the camera module is connected with the main circuit board, and the electric controller is connected with the culvert fan. The invention has novel structure and flexible control, and is suitable for reconnaissance of various environments.
The Chinese patent with the publication number of CN102358421B and publication date of 2013, 6 and 5 discloses a flying spherical robot, which comprises a reticular spherical shell, wherein a long-axis motor, a circular frame, a long axis and a long-axis rotating support sleeve are sequentially connected and arranged in the reticular spherical shell, an external counterweight is arranged around the long-axis motor, a short axis, a propeller side-swinging motor, a bent axis, a connecting shaft and a short-axis rotating support sleeve are sequentially connected and arranged in the circular frame, the propeller side-swinging motor is laterally connected with the internal counterweight, and the other direction of the propeller side-swinging motor is connected with a propeller motor with a propeller; the long shaft motor, the short shaft motor, the propeller side-swinging motor and the propeller motor are connected with a central controller arranged in the reticular spherical shell. The flying spherical robot can roll on the ground and fly in the air.
The Chinese patent with the publication number of CN103394197B and publication date of 2016, 8 and 10 discloses a ball-circling flyer and a ball-circling flying toy system. The global flyer comprises a shell, wherein the shell is composed of an upper shell, a lower shell and a shell outer ring, three or more than three wheels are arranged on the shell, the outer edges of the wheels are higher than the upper end and the lower end of the shell, so that the global flyer can normally fly no matter whether the global flyer lands on the front side or lands on the back side or lands on the side surface. In addition, the system is also provided with an electric inflator and an inflation hose, when in use, the flying object around the ball is put into the inflation ball from the balloon door to play on the wall of the flying vehicle in the ball.
The prior art has the following defects:
when the aircraft takes off, the aircraft can normally fly only by facing the aircraft upwards (namely, the blades are arranged upwards), if a user controls the spherical aircraft to take off, the aircraft cannot normally take off without facing the aircraft upwards, the user cannot pay attention to the fact that the aircraft is damaged even after taking off the hands, and the use experience is poor.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the universal aircraft, when a user uses the universal aircraft, no matter how the user holds the aircraft, the aircraft can automatically adjust the right side of the aircraft to be upward, the normal flight of the aircraft is ensured, the angle of the aircraft does not need to be adjusted by the user, and the universal aircraft is simple and convenient to operate.
The utility model provides a universal aircraft, includes the shell of fretwork, its characterized in that: a first annular ring, a second annular ring and a third annular ring are connected in the shell, the first annular ring is positioned in the shell and is connected with the shell, the second annular ring is arranged in the first annular ring and is rotationally connected with the first annular ring, the third annular ring is arranged in the second annular ring and is rotationally connected with the second annular ring, a main connecting rod is connected in the third annular ring, a main motor is arranged on the main connecting rod, the output shaft of the main motor is rotatably sleeved on the main connecting rod, the output shaft of the main motor is fixedly sleeved with the main fan blades, the output shaft of the steering control motor is rotatably sleeved on the main connecting rod, the output shaft of the steering control motor is movably connected with a balance rod, one end of the balance rod is provided with a balance ball, the other end of the balance rod is provided with a steering torque motor, and the output shaft of the steering torque motor is fixedly provided with the fan blades.
Preferably, the housing is a spherical housing.
Preferably, the first annular ring is rotatably connected with the housing through a bearing, and the specific structure is as follows: the bearing outer ring is fixedly arranged on the first annular ring, the shell is connected to the inner ring of the bearing or the bearing outer ring is fixedly arranged on the shell, the first annular ring is connected to the inner ring of the bearing or the first annular ring and the shell are both provided with a bearing, and the inner rings of the two bearings are fixed on a connecting rod.
Preferably, the second annular ring is rotatably connected with the first annular ring through a bearing, and the third annular ring is rotatably connected with the second annular ring through a bearing.
Preferably, the output shaft of the main motor is rotatably sleeved on the main connecting rod through a bearing, so that the purpose that the output shaft of the main motor rotates around the main connecting rod is achieved; the output shaft of the steering control motor is rotatably sleeved on the main connecting rod through a bearing, so that the purpose that the output shaft of the steering control motor rotates around the main connecting rod is achieved, the output shaft of the steering control motor is connected with the balance rod through the bearing, and the purpose that the balance rod swings up and down around the output shaft of the steering control motor is achieved.
Preferably, the main motor, the steering control motor and the steering torque motor are respectively provided with a control system for respectively controlling the main motor, the steering control motor and the steering torque motor.
Preferably, the main motor, the steering control motor and the steering torque motor are all connected with a control system, and the control system realizes control over the main motor, the steering control motor and the steering torque motor.
Preferably, the main motor and the steering control motor are sequentially mounted on the main connecting rod from top to bottom, the main fan blade is located above the main motor, and the balance rod is located above the steering control motor.
The invention has the beneficial effects that:
the invention is characterized in that a first annular ring, a second annular ring and a third annular ring are connected in a shell, the first annular ring is positioned in the shell, the first annular ring is rotatably connected with the shell, the second annular ring is arranged in the first annular ring, the second annular ring is rotatably connected with the first annular ring, the third annular ring is arranged in the second annular ring, the third annular ring is rotatably connected with the second annular ring, a main connecting rod is connected in the third annular ring, and a main motor is arranged on the main connecting rod, the output shaft of the main motor is rotatably sleeved on the main connecting rod, the output shaft of the main motor is fixedly sleeved with the main fan blades, the output shaft of the steering control motor is rotatably sleeved on the main connecting rod, the output shaft of the steering control motor is movably connected with a balance rod, one end of the balance rod is provided with a balance ball, the other end of the balance rod is provided with a steering torque motor, and the output shaft of the steering torque motor is fixedly provided with the fan blades. The main motor and the steering control motor form a balance weight, no matter how the user holds the shell, under the effect of the balance weight, the first annular ring, the second annular ring and the third annular ring can automatically rotate and adjust, the main fan blade is ensured to be arranged on the upper portion, namely, the front face of the aircraft is ensured to be arranged upwards, the aircraft can normally take off after the user takes off the hand, the manual adjustment of the user is not needed, the front face of the aircraft is ensured to be arranged upwards, and the operation is simple and convenient for the user, and the damage of the aircraft caused by the fact that the aircraft does not take off the hand upwards is avoided.
Drawings
In order to more clearly illustrate the detailed description of the invention or the technical solutions in the prior art, the drawings that are needed in the detailed description of the invention or the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
FIG. 1 is a schematic view of the present invention with the outer shell removed;
fig. 2 is a schematic view of the structure of the housing of the present invention.
In the attached drawing, the device comprises a shell 1, a shell 2, a first annular ring 3, a second annular ring 4, a third annular ring 5, a main connecting rod 6, a main motor 7, a steering control motor 8, a main fan blade 9, a balancing rod 10, a balancing ball 11, a steering torque motor 12 and fan blades.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.
It is to be noted that, unless otherwise specified, technical or scientific terms used herein shall have the ordinary meaning as understood by those skilled in the art to which the invention pertains.
In order to ensure that the aircraft always faces upwards, three annular rings, namely a first annular ring 2, a second annular ring 3 and a third annular ring 4, are additionally arranged in a spherical hollowed-out shell 1 of the aircraft, and the diameters of the three annular rings are sequentially from large to small. The second annular ring 3 is housed inside the first annular ring 2, the third annular ring 4 is housed inside the second annular ring 3, and the first annular ring is connected inside the casing 1. The first annular ring 2 has two connecting points with the shell, and a straight line formed by connecting the two connecting points and the hemispherical surface of the shell are on the same plane. The second annular ring 3 and the first annular ring 2 have two connecting points, and the straight line formed by the connection of the two connecting points is the diameter line of the first annular ring. The third annular ring 4 and the second annular ring 3 have two connecting points, and the straight line formed by the two connecting points is the diameter line of the second annular ring 3. The front face of the aircraft is ensured to face upwards all the time, the first annular ring 2 is rotated or fixedly installed on the inner side of the shell through two connecting points, the second annular ring 3 is rotatably installed on the inner side of the first annular ring 2 through the two connecting points, and the third annular ring 4 is rotatably installed on the inner side of the second annular ring 3 through the two connecting points.
A main connecting rod 5 is connected in the third annular ring 4, the length of the main connecting rod 5 is the diameter of the third annular ring 4, two ends of the main connecting rod 5 can be fixedly connected to the third annular ring in a welding or bolt connection mode, then a main motor 6 and a steering control motor 7 are installed on the main connecting rod 5, and the main motor 6 and the steering control motor 7 are installed on the lower half section of the main connecting rod. The main fan blade 8 is installed on the output shaft of the main motor 6, and the main motor 6 drives the main fan blade 8 to rotate, so that the ascending motion of the aircraft is realized. In order to reduce the vibration of the aircraft caused by the eccentric installation of the main fan blade on the main connecting rod 5 during rotation, a motor is sleeved on the main connecting rod 5, and an output shaft of a main motor 6 is installed on the main connecting rod 5 through a bearing. Similarly, the steering control motor 7 is also sleeved on the main connecting rod 5, and an output shaft of the steering control motor 7 is also arranged on the connecting rod 5 through a bearing. The output shaft of the steering control motor 7 is connected with a balance rod 9, one end of the balance rod 9 is provided with a balance ball 10, the other end of the balance rod is provided with a steering torque motor 11, and the output shaft of the steering torque motor 11 is fixedly provided with fan blades 12. The steering control motor 7 rotates to drive the balance rod 9 to rotate, so that the steering of the aircraft is controlled, the direction control of the aircraft is realized, the steering torque motor 11 rotates to control the fan blades 12 to rotate, the adjustment of the vertical angle of the aircraft is realized, the flight angle of the aircraft is controlled, and the actions such as lateral flight are realized. In order to realize the control of the main motor, the steering control motor and the steering torque motor, a control system can be respectively arranged on each motor to respectively control the main motor and the steering control motor. A control system can be arranged on the main connecting rod to realize the unified control of the main motor, the steering control motor and the steering torque motor. The main motor, the steering control motor, the steering torque motor, the control system and the balance rod are arranged on the lower half section of the main connecting rod, and then the balance rod can be used as a balance weight of the aircraft. Because the invention designs three annular rings, the invention realizes the left-right rotation action, the up-down rotation action and the front-back rotation action, and can ensure that the front surface of the aircraft faces upwards under the action of the counterweight. No matter the user holds the spherical aircraft in any position, three annular rings in the shell ensure that the aircraft faces upwards under the action of the counterweight force. Specifically, the first annular ring can be arranged to rotate left and right around a connection point with the shell, the second annular ring can rotate back and forth around the connection point with the first annular ring, and the third annular ring can rotate up and down around the connection point with the second annular ring. As to how to realize the rotational connection between the first annular ring and the housing, the second annular ring and the first annular ring, and the third annular ring and the second annular ring, the connection manner is various, and for example, the connection manner can be realized by a bearing connection manner.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.
Claims (8)
1. The utility model provides a universal aircraft, includes the shell of fretwork, its characterized in that: the fan comprises a shell, and is characterized in that a first annular ring, a second annular ring and a third annular ring are connected in the shell, the first annular ring is positioned in the shell and connected with the shell, the second annular ring is arranged in the first annular ring and rotatably connected with the first annular ring, the third annular ring is arranged in the second annular ring and rotatably connected with the second annular ring, a main connecting rod is connected in the third annular ring, a main motor is arranged on the lower half section of the main connecting rod, a main fan blade is fixedly sleeved on an output shaft of the main motor, the main motor is connected with a control system, and the control system controls the main motor to rotate.
2. The gimbaled aircraft of claim 1, wherein: still install the steering control motor on the second section of main connecting rod, the steering control motor is located main motor below, and the swivelling joint has the balancing pole on the output shaft of steering control motor, and the steering control motor drives the balancing pole and rotates, and the balancing pole can rotate from top to bottom around the output shaft of steering control motor, and balancing pole one end is provided with the balancing ball, and the other end is provided with steering torque motor, and fixed mounting has the flabellum on steering torque motor's the output shaft.
3. The gimbaled aircraft of claim 2, wherein: the steering control motor is connected with a steering control motor control system, and the steering torque motor is connected with a steering torque motor control system; or the steering control motor and the steering torque motor are both connected with the control system, and the control system controls the steering control motor and the steering torque motor to rotate.
4. The gimbaled aircraft of claim 2, wherein: the output shaft of the main motor is rotatably sleeved on the main connecting rod, and the output shaft of the steering control motor is rotatably sleeved on the main connecting rod.
5. The gimbaled aircraft of claim 1, wherein: the shell is a spherical shell.
6. The gimbaled aircraft of claim 1, wherein: first annular ring passes through the bearing and the shell rotates to be connected, and concrete structure is: the bearing outer ring is fixedly arranged on the first annular ring, the shell is connected to the inner ring of the bearing or the bearing outer ring is fixedly arranged on the shell, the first annular ring is connected to the inner ring of the bearing or the first annular ring and the shell are both provided with a bearing, and the inner rings of the two bearings are fixed on a connecting rod.
7. The gimbaled aircraft of claim 6, wherein: the second annular ring is rotatably connected with the first annular ring through a bearing, and the third annular ring is rotatably connected with the second annular ring through a bearing.
8. The gimbaled aircraft of claim 4, wherein: the output shaft of the main motor is rotatably sleeved on the main connecting rod through a bearing, the output shaft of the steering control motor is rotatably sleeved on the main connecting rod through a bearing, and the output shaft of the steering control motor is connected with the balance rod through a bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210026063.9A CN114379779A (en) | 2022-01-11 | 2022-01-11 | Universal aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210026063.9A CN114379779A (en) | 2022-01-11 | 2022-01-11 | Universal aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114379779A true CN114379779A (en) | 2022-04-22 |
Family
ID=81202124
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210026063.9A Pending CN114379779A (en) | 2022-01-11 | 2022-01-11 | Universal aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114379779A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1997044240A1 (en) * | 1994-11-24 | 1997-11-27 | Tom Kusic | Vertical take-off aircraft |
| US6227933B1 (en) * | 1999-06-15 | 2001-05-08 | Universite De Sherbrooke | Robot ball |
| KR20030062005A (en) * | 2002-01-15 | 2003-07-23 | 하영균 | Running control system for spherical object |
| CN107352022A (en) * | 2017-06-08 | 2017-11-17 | 国蓉科技有限公司 | A kind of spherical UAS of rotor of impact resistant four |
| CN112607005A (en) * | 2020-12-23 | 2021-04-06 | 武汉量宇智能科技有限公司 | Attitude control mechanism of aircraft without control surface |
-
2022
- 2022-01-11 CN CN202210026063.9A patent/CN114379779A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1997044240A1 (en) * | 1994-11-24 | 1997-11-27 | Tom Kusic | Vertical take-off aircraft |
| US6227933B1 (en) * | 1999-06-15 | 2001-05-08 | Universite De Sherbrooke | Robot ball |
| KR20030062005A (en) * | 2002-01-15 | 2003-07-23 | 하영균 | Running control system for spherical object |
| CN107352022A (en) * | 2017-06-08 | 2017-11-17 | 国蓉科技有限公司 | A kind of spherical UAS of rotor of impact resistant four |
| CN112607005A (en) * | 2020-12-23 | 2021-04-06 | 武汉量宇智能科技有限公司 | Attitude control mechanism of aircraft without control surface |
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