CN115230951A - Aircraft and control device thereof - Google Patents
Aircraft and control device thereof Download PDFInfo
- Publication number
- CN115230951A CN115230951A CN202110452177.5A CN202110452177A CN115230951A CN 115230951 A CN115230951 A CN 115230951A CN 202110452177 A CN202110452177 A CN 202110452177A CN 115230951 A CN115230951 A CN 115230951A
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- aircraft
- module
- propellers
- flight
- control
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- 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 14
- 238000002485 combustion reaction Methods 0.000 claims abstract description 10
- 230000000694 effects Effects 0.000 claims description 4
- 239000000446 fuel Substances 0.000 claims description 4
- 230000005484 gravity Effects 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
- 239000002131 composite material Substances 0.000 claims description 2
- 229910052751 metal Inorganic materials 0.000 claims description 2
- 239000002861 polymer material Substances 0.000 claims description 2
- 239000007769 metal material Substances 0.000 claims 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims 1
- 238000013473 artificial intelligence Methods 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000012806 monitoring device Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C17/00—Aircraft stabilisation not otherwise provided for
- B64C17/02—Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
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- 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
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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- 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
- B64D31/00—Power plant control; Arrangement thereof
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
An aircraft and a control device thereof comprise a lift force module, a control platform, a power module, a propulsion module and a flight control module, and are characterized in that the lift force module consists of 2-4 large-size propellers, the propellers are driven by an electric motor or an internal combustion engine to rotate so as to generate lift force, the control platform consists of a core control unit, the electric motor can be adjusted through an electronic speed regulator, the rotating speed of the propellers of the lift force module is controlled to adjust the flight attitude and speed of the aircraft, the power module consists of a battery or the internal combustion engine, and the control module consists of 2-20 small-size propellers, can adjust the lift force of the left side, the right side, the front side and the rear side of the aircraft, and plays roles in adjusting the flight attitude and controlling balance.
Description
The invention relates to an aircraft in the traffic field, in particular to an aircraft and a control device thereof.
Background
The vertical take-off and landing aircraft is a traffic tool which does not need a runway, can take off and land vertically and realize short distance in the air, and is an important link for constructing a future three-dimensional traffic system. Because of the rotational speed that a plurality of rotors can be through adjusting the screw, adjust the lift that every rotor is different to realize the control of flight attitude, but the aircraft of four rotors and six rotors or even more rotors is the vertical take-off and landing instrument of using the broadest at present. At present, most aerial photography aircrafts and agricultural plant protection aircrafts adopt a multi-rotor structure.
In order to achieve a greater load capacity, the size of the propeller needs to be increased, which inevitably leads to an excessive volume of the entire aircraft. Although many rotor structural design can conveniently carry out the adjustment of flight gesture, many rotor crafts's size can be very big usually, is unfavorable for goods transportation and manned flight such as realization express delivery and takeaway.
Accordingly, the present invention provides an aircraft and a control device thereof, wherein a large-sized propeller provides stable lift force for the aircraft, and a small-sized propeller provides flight attitude control. The invention solves the problems of the aircraft of large size, short flying distance, small load capacity and the like in flying attitude control, and is the aircraft with practical value.
Disclosure of Invention
The invention aims to solve the problems of the existing vehicles and provides a manned or cargo aircraft which does not need a runway, can take off and land vertically and can realize medium and short distance traffic.
In order to achieve the purpose, the technical scheme adopted by the invention comprises the following steps: an aircraft and a control device thereof comprise a lift force module, a control platform, a power module, a propulsion module and a flight control module, and are characterized in that the lift force module consists of 2-4 large-size propellers, the propellers are driven by an electric motor or an internal combustion engine to rotate so as to generate lift force, the control platform consists of a core control unit, the electric motor can be adjusted through an electronic speed regulator, the rotating speed of the propellers of the lift force module is controlled to adjust the flight attitude and speed of the aircraft, the power module consists of a battery or the internal combustion engine, and the control module consists of 2-20 small-size propellers, can adjust the lift force of the left side, the right side, the front side and the rear side of the aircraft, and plays roles in adjusting the flight attitude and controlling balance.
Specifically, the lift force module consists of 2-4 large-size propellers, the number of the propellers is 2-20, the length of the propellers is 100-2000 mm, the thickness of the propellers is 1-100 mm, the width of the propellers is 10-400 mm, and the propellers are made of carbon fibers, high polymer materials, metals or other composite materials.
More preferably, when the number of the propellers of the lift module is 4, every two propellers of the 4 propellers form a pair and are arranged in parallel up and down, the rotating directions are opposite, and the function of balancing moment is achieved. The two pairs of propellers are arranged in a front-back manner, and the speed of the lifting, advancing or retreating of the aircraft can be adjusted by adjusting the rotating speed of the four propellers. By adjusting the rotational speed of the four propellers, the moment generated by each propeller will be different, thereby adjusting the rotation of the aircraft in the plane of the propellers. It is noted that when the number of lift propellers is 4, each propeller is considered to be a two-axis aircraft, even if it is fixed to the other modules of the aircraft by means of respective fixing means.
In particular, the manipulation platform may be manual or automatic. The control platform controls an electric motor or an internal combustion engine through wireless or wired electronic signals, adjusts an aircraft lift force module and a flight control device, and controls the lifting speed, the flight speed and the flight attitude of the aircraft.
In particular, the power module consists of an electric motor powered by a battery or an internal combustion engine powered by fuel. When the electric motors are used for driving, each electric motor drives one propeller to rotate, the motors are controlled by the electronic speed regulators, and the electric signals sent by the control platform are used for regulating the rotating speeds of the motors and the propellers, so that the lifting force of the propellers is regulated, and the lifting, advancing or retreating speeds of the aircraft and the rotation of the aircraft on the plane of the propellers are controlled. In order to balance the moment generated by the aircraft carrying people or transporting goods relative to the center of gravity of the aircraft, the battery or the fuel storage device can be adjusted in position relative to the center of gravity of the aircraft, so that the effect of balancing the moment of the whole aircraft is achieved.
Specifically, the flight control module consists of 2-20 small-size propellers which are positioned on the left side, the right side, the front side and the rear side of the aircraft, and the flight control module is controlled by the control platform through an electronic speed regulator and an electric motor and can adjust the lifting force on the left side, the right side, the front side and the rear side of the aircraft, so that the flight control module plays a role in adjusting the flight attitude of the aircraft and controlling balance. The diameter of the small-size propeller of the flight control module is 5% -49% of the width of the aircraft body.
More preferably, the flight control device is composed of 8 small-sized propellers which are arranged on the left and right sides and the front and rear sides of the large-sized propeller.
In particular, the propulsion module of the aircraft consists of 1-4 propellers. The number of the propeller blades is 2-20, and the diameter of the propeller is 50-2000 mm. Except that the propeller rotates to provide aircraft thrust, the propulsion module can rotate in the direction perpendicular to the rotation direction of the propeller, so that the effect of changing the thrust direction and adjusting the flight attitude of the aircraft is realized. .
More preferably, the propulsion module of the aircraft consists of 2 propellers. The number of the propeller blades is 4.
The aircraft provided by the invention can be used as a manned transportation scheme and can also be used as a solution scheme for logistics transportation such as express delivery or takeaway. As a manned transportation scheme, the aircraft provided by the invention can be designed to control the control platform manually, so as to control the take-off and landing, the flying speed and the flying attitude of the aircraft. When the steering platform is manually controlled, the balancing of the aircraft may be automatically controlled. The aircraft can be used as a manned traffic scheme and can also be automatically controlled by the control platform according to automatically set, calculated or received signals. When the aircraft is used as a logistics transportation solution, the aircraft can be automatically controlled by the control platform according to automatically set, calculated or received signals.
The aircraft provided by the invention can also realize the functions of taking off and landing, adjusting the flight attitude, adjusting the flight speed, planning the flight route and the like in an artificial intelligence mode. In order to realize the automatic control of the aircraft, the aircraft can be connected with an artificial intelligence module, a visual calculation module, a radar, a monitoring device, a global positioning system and the like so as to facilitate the automatic and safe operation of the aircraft.
In order to guarantee safety, the safety guarantee module can be added to the aircraft design scheme provided by the invention. The safety guarantee module can receive the instruction of the control platform, and can realize emergency landing or pop up a parachute when the aircraft has safety failure or other safety problems so as to guarantee the safety of personnel or articles in the aircraft.
In order to ensure comfort, the aircraft design scheme provided by the invention can be added with an air conditioner to control the temperature.
In order to guarantee safety, the aircraft design scheme provided by the invention can be additionally provided with an indicator light. The pilot lamp is located aircraft front and back left and right sides for instruct the flight direction and the state of taking off and landing of aircraft.
To provide longer flight distances, the aircraft design provided by the invention can be added with folding wings. The folding wings can be folded during taking off and landing of the aircraft, so that the aircraft can approach or fly in a smaller space. Because the folding wings can provide the lift force of the aircraft in the flying process, the lift force module is prevented from consuming more power, and therefore, the aircraft can fly for a longer time and a longer distance.
In order to increase the production convenience, the aircraft provided by the invention can be combined in a modularized mode. The lift module, the propulsion module, the control module, the cockpit and the like can be produced independently and assembled to obtain an integrated aircraft.
The aircraft design scheme provided by the invention can be additionally provided with internal display devices, sound devices and other devices for providing flight information, man-machine interaction and entertainment functions.
The invention has the beneficial effects that:
(1) Different from the common multi-rotor aircraft, the aircraft provided by the invention adopts the combined design of the large-size propeller and the small-size propeller, so that the volume of the aircraft is greatly reduced. The aircraft is similar to a common household car in volume when serving as a manned traffic scheme, can use the existing parking space, can land in a small space, and can also directly fly into a resident building or an office building.
(2) Different from a propeller helicopter, the aircraft provided by the invention adopts a small-size propeller to carry out flight control, and plays a role in increasing the stability of the aircraft body and adjusting the flight attitude, so that the control performance of the aircraft is greatly increased.
(3) Compared with a multi-rotor aircraft, the aircraft provided by the invention has larger propeller size, the lift efficiency is greatly improved,
(4) The aircraft provided by the invention is provided with the propelling device, so that the power of horizontal flight is not required to be provided by the lift force module, and high-speed flight can be realized.
(5) The aircraft provided by the invention can be additionally provided with the folding wings, and is used for providing the lifting force of the aircraft in the flying process and realizing long-distance flight.
Therefore, the aircraft provided by the invention has the characteristics of high energy efficiency, heavy load and long range, can realize manned flight, can provide rapid transportation guarantee for express delivery, takeaway and the like, and provides a solution for medium-distance and long-distance logistics transportation.
Therefore, the aircraft design scheme provided by the invention has high practicability and industrialization prospect, and can provide a brand-new traffic, logistics and life mode.
Drawings
FIG. 1 is a schematic layout of the various modules of an aircraft.
Claims (6)
1. An aircraft and a control device thereof comprise a lift force module, a control platform, a power module, a propulsion module and a flight control module, and are characterized in that the lift force module consists of 2-4 large-size propellers, the propellers are driven to rotate by an electric motor or an internal combustion engine to generate lift force, the control platform consists of a core control unit, the electric motor can be adjusted through an electronic speed regulator, the rotating speed of the propellers of the lift force module is controlled to adjust the flight attitude and speed of the aircraft, the power module consists of a battery or the internal combustion engine, and the control module consists of 2-20 small-size propellers, can adjust the lift force of the left side, the right side, the front side and the rear side of the aircraft, and plays roles of adjusting the flight attitude and controlling balance.
2. The aircraft and its control device as claimed in claim 1, wherein said lift module is composed of 2-4 large-sized propellers. The propeller has 2-20 blades, length of 100-2000 mm, thickness of 1-100 mm and width of 10-400 mm, and is made of carbon fiber, polymer material, metal or composite material. The diameter of the propeller is 60% -100% of the width of the aircraft body.
3. The aircraft and its control device as claimed in claim 1, wherein the control platform can be manual or automatic. The control platform controls an electric motor or an internal combustion engine through wireless or wired electronic signals, adjusts an aircraft lift force module and a flight control device, and controls the lifting speed, the flight speed and the flight attitude of the aircraft.
4. The aircraft and its control device of claim 1, wherein said power module is comprised of an electric motor powered by a battery or an internal combustion engine powered by fuel. In order to balance the moment generated by the aircraft relative to the center of gravity of the aircraft when carrying people or transporting goods, the battery or the fuel storage device can be adjusted in position relative to the center of gravity of the aircraft, so that the effect of balancing the moment of the whole aircraft is achieved.
5. The aircraft and its control device as claimed in claim 1, wherein the flight control module consists of 2-20 small propellers located at the left and right and front and rear sides of the aircraft, the flight control module is controlled by the control platform through an electronic speed governor and an electric motor and can adjust the lift force at the left and right and front and rear sides of the aircraft, so as to adjust the flight attitude of the aircraft and control the balance. The diameter of the small-size propeller of the flight control module is 5% -50% of the width of the aircraft body.
6. The aircraft and its control device as claimed in claim 1, wherein the propulsion module is composed of 1-8 propellers. The number of the propeller blades is 2-20, and the diameter of the propeller is 50-2000 mm. Except that the propeller rotates to provide aircraft thrust, the propelling module can rotate in the direction perpendicular to the rotation direction of the propeller, so that the effect of changing the thrust direction and adjusting the flight attitude of the aircraft is realized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110452177.5A CN115230951A (en) | 2021-04-24 | 2021-04-24 | Aircraft and control device thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110452177.5A CN115230951A (en) | 2021-04-24 | 2021-04-24 | Aircraft and control device thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115230951A true CN115230951A (en) | 2022-10-25 |
Family
ID=83665715
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110452177.5A Pending CN115230951A (en) | 2021-04-24 | 2021-04-24 | Aircraft and control device thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115230951A (en) |
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2021
- 2021-04-24 CN CN202110452177.5A patent/CN115230951A/en active Pending
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