CN110834727A - Fixed-wing unmanned aerial vehicle and control method - Google Patents
Fixed-wing unmanned aerial vehicle and control method Download PDFInfo
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- CN110834727A CN110834727A CN201810941930.5A CN201810941930A CN110834727A CN 110834727 A CN110834727 A CN 110834727A CN 201810941930 A CN201810941930 A CN 201810941930A CN 110834727 A CN110834727 A CN 110834727A
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- 230000004888 barrier function Effects 0.000 claims description 3
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- 238000012423 maintenance Methods 0.000 description 2
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- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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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
- B64U30/10—Wings
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
Abstract
The invention discloses a fixed-wing unmanned aerial vehicle and a control method thereof, wherein the fixed-wing unmanned aerial vehicle comprises: a body including an airflow flow device; the first propeller module is arranged on the airflow flowing device and is connected with the machine body; at least one second propeller module connected with the fuselage; the first propeller module and the second propeller module are capable of changing the fuselage state. According to the invention, the vertical landing of the unmanned aerial vehicle is realized directly through the first propeller module and the second propeller module, the vertical landing of the unmanned aerial vehicle can be realized without running on a runway, and the unmanned aerial vehicle can be operated conveniently; the invention also realizes the forward and backward movement, steering, overturning and other flight states of the unmanned aerial vehicle through the first propeller module and the second propeller module directly, does not need control surface control, and is flexible to control.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle design, in particular to a fixed-wing unmanned aerial vehicle.
Background
The fixed wing unmanned aerial vehicle is an unmanned aerial vehicle which generates forward thrust or pull force by a power device, generates lift force by fixed wings of a fuselage and flies in the air.
The existing fixed-wing uavs are usually power devices (such as propellers and the like) which are arranged on wings or bodies and generate forward and backward thrust, and the fixed-wing uavs have the following problems:
1. the lift cannot rise and fall vertically, and the lift needs to be lifted by running on a runway;
2. the change of various postures of the unmanned aerial vehicle such as steering, overturning and the like is realized by controlling a control surface on the body, and the operation is troublesome;
3. the structure is complicated, the assembly is inconvenient, and the assembly and maintenance cost is high.
Disclosure of Invention
In order to solve the problems that the existing fixed wing unmanned aerial vehicle cannot rise and fall vertically and is troublesome to operate and the like, the invention provides a fixed wing unmanned aerial vehicle, which comprises:
a body including an airflow flow device;
the first propeller module is arranged on the airflow flowing device and is connected with the machine body;
at least one second propeller module connected with the fuselage;
the first propeller module and the second propeller module are capable of changing the fuselage state.
Preferably, the first propeller module is capable of generating airflow power capable of changing the fuselage state via the airflow flow device.
Preferably, the airflow flowing device comprises an airflow channel which is arranged on the machine body, and the first propeller module is arranged on the airflow channel and connected with the machine body.
Preferably, the first propeller module is detachably connected to the main body.
Preferably, the second propeller module is detachably connected to the main body.
Preferably, the aircraft further comprises a control circuit board module, wherein the control circuit board module is installed on the aircraft body, and the first propeller module and the second propeller module are electrically connected with the control circuit board module.
Preferably, the control circuit board module is detachably connected with the body.
Preferably, the first propeller module is connected with the machine body, the second propeller module is connected with the machine body, and the control circuit board module is connected with the machine body through tool-free quick-release components.
Preferably, the tool-less quick release assembly comprises a plug-in structure and a slot structure, the plug-in structure being inserted into the slot structure for detachable connection, wherein,
the plug-in structure is mounted on the first propeller module, the slot structure is mounted on the machine body, or the plug-in structure is mounted on the machine body, and the slot structure is mounted on the first propeller module;
the plug-in structure is mounted on the second propeller module, the slot structure is mounted on the machine body, or the plug-in structure is mounted on the machine body, and the slot structure is mounted on the second propeller module;
the plug-in structure is installed on the control circuit board module, the slot structure is installed on the machine body, or the plug-in structure is installed on the machine body, and the slot structure is installed on the control circuit board module.
Preferably, the first propeller module, the second propeller module and the control circuit board module are separable from the fuselage and are combined into an aircraft.
Preferably, the fuselage comprises a fuselage main body and wings arranged on the left side and the right side of the fuselage main body, and the two wings and the fuselage are integrally manufactured.
Preferably, the aircraft body is provided with two first propeller modules, and the two first propeller modules are horizontally arranged on the aircraft body side by side from left to right.
Preferably, the fuselage is provided with two second propeller modules, and the two second propeller modules are obliquely arranged on the two wings respectively.
Preferably, the second propeller arrangement is arranged at the rear end of the wing.
Preferably, the first propeller module and the second propeller module each comprise a duct, a motor base arranged in the middle of the duct, and a motor and a propeller which are installed on the motor base.
Preferably, the battery module is further included, and the battery module is mounted above or below the control circuit board module.
The invention also provides a control method of the fixed-wing unmanned aerial vehicle, the fixed-wing unmanned aerial vehicle adopts the fixed-wing unmanned aerial vehicle, the fixed-wing unmanned aerial vehicle also comprises an intelligent main control module, and the control method of the fixed-wing unmanned aerial vehicle comprises the following steps:
the control method of the fixed-wing unmanned aerial vehicle comprises the following steps:
the control circuit board module controls the first propeller module to enable the machine body to change states;
the control circuit board module controls the second propeller module to enable the machine body to change states;
or:
the control circuit board module controls the second propeller module to enable the machine body to change states;
the control circuit board module controls the first propeller module to enable the machine body to change states.
Preferably, the step of controlling the first propeller module by the control circuit board module to change the state of the main body specifically includes:
and an intelligent main control module in the control circuit board module controls the propeller on the first propeller module to rotate or simultaneously controls the propellers on the first propeller module and the second propeller module to rotate, so that the machine body can take off and land.
Preferably, the step of controlling the second propeller module by the control circuit board module to change the state of the main body specifically includes:
an intelligent main control module in the control circuit board module controls the propeller on the second propeller module to rotate in the forward direction to generate thrust to push the machine body to move;
or
And an intelligent main control module in the control circuit board module controls the propellers on the second propeller module to rotate reversely at the same time, so that reverse thrust is generated, and the machine body is pushed to move.
Preferably, the control circuit board module controlling the second propeller module to change the state of the body includes:
the two second propeller modules are arranged on the machine body, and the intelligent main control module in the control circuit board module controls the rotating speed of the propellers on the two second propeller modules to have a rotating speed difference, so that the machine body can turn.
Preferably, the intelligent main control module controls the rotating speed of the propeller on the left second propeller module to be greater than that of the propeller on the right second propeller module, so that a rotating speed difference is generated, and the function of turning to the right is realized;
preferably, the intelligent main control module controls the rotating speed of the propeller on the second propeller module on the right side to be greater than the rotating speed of the propeller on the second propeller module on the left side, so that a rotating speed difference is generated, and the function of turning to the left is achieved.
Preferably, a gyroscope is arranged on the fixed-wing unmanned aerial vehicle; the gyroscope detects the angle deviation of the fixed-wing unmanned aerial vehicle in the running process, when the angle deviation is detected, the angle deviation is fed back to the intelligent main control module, the intelligent main control module respectively controls the rotating speed difference of the propellers on the two second propeller modules according to the fed-back data to correct the course, and the effect that the fixed-wing unmanned aerial vehicle runs straight is achieved.
Preferably, the method further comprises the following steps:
the fixed wing unmanned aerial vehicle is provided with a camera device, and the control circuit board module is used for capturing images around the fuselage through the camera device, judging whether barriers exist around the fuselage and adjusting the course of the fuselage.
Preferably, the control method of the fixed-wing drone further comprises:
separating the first propeller module, the second propeller module, and the control circuit board module from the fuselage;
combining the first propeller module, the second propeller module, and the control circuit board module into an aircraft;
the aircraft can realize high-altitude flight.
Due to the adoption of the technical scheme, compared with the prior art, the invention has the following advantages and positive effects:
1. according to the fixed-wing unmanned aerial vehicle, the first propeller module and the second propeller module are directly matched to realize the rising and falling of the unmanned aerial vehicle in the vertical direction, the unmanned aerial vehicle can vertically rise and fall without running on a runway, and the unmanned aerial vehicle can be conveniently operated; the invention also directly realizes the forward and backward movement, steering, overturning and other flight states of the unmanned aerial vehicle through the second propeller module, omits the design of the traditional control surface, does not need control surface control and has flexible control;
2. according to the fixed-wing unmanned aerial vehicle, the first propeller module and the second propeller module are matched, and the control circuit board module and the vehicle body are detachably connected, so that modular assembly is realized, and the first propeller module and the second propeller module can be alternately used; meanwhile, the connection mode does not need structures such as screws and the like to assist in connection, and does not need auxiliary tools during disassembly and assembly, so that the disassembly and assembly are more convenient.
Drawings
The above and other features and advantages of the present invention will be more clearly understood from the following detailed description taken in conjunction with the accompanying drawings, in which:
fig. 1 is a schematic structural diagram of a fixed-wing drone provided by the present invention;
fig. 2 is a front view of a fixed wing drone provided by the present invention;
FIG. 3 is a top view of a fixed wing drone provided by the present invention;
fig. 4 is a side view of a fixed wing drone provided by the present invention.
Description of the symbols:
1-a fuselage main body, 101-a fuselage support seat, 2-wings, 3-a control circuit board module, 4, 5-a first propeller module, 6, 7-a second propeller module, and 401, 501-a motor base.
Detailed Description
The present invention will be described in more detail below with reference to the accompanying drawings, which illustrate embodiments of the invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, the size and relative sizes of layers and regions may be exaggerated for clarity.
Example 1
The invention provides a fixed-wing unmanned aerial vehicle, which comprises a vehicle body, wherein at least one first propeller module and at least one second propeller module are arranged on the vehicle body, and the first propeller module and the second propeller module are arranged on the vehicle body; the machine body also comprises an airflow flowing device, and the first propeller module is arranged on the airflow flowing device and connected with the machine body; the first propeller module and the second propeller module are capable of changing the fuselage state.
According to the fixed-wing unmanned aerial vehicle, the unmanned aerial vehicle can rise and fall in the vertical direction directly through the first propeller module and the second propeller module; specifically, the airframe is provided with the airflow flowing device, the first propeller module is arranged on the airflow flowing device, the first propeller module can generate airflow power, and the airflow flows up and down, so that the airframe can complete the vertical lifting function without running on a runway, and the unmanned aerial vehicle can be conveniently operated; the invention can also realize the flight states of other unmanned aerial vehicles such as forward and backward movement, steering and overturning of the unmanned aerial vehicle by controlling the first propeller module and the second propeller module, omits the design of the traditional control surface, does not need control surface control and has flexible control.
In this embodiment, the airflow flowing device comprises an airflow channel, the airflow channel is arranged on the machine body, and the first propeller module is arranged on the airflow channel and connected with the machine body. Of course, in other embodiments, when the fuselage is small, there is not enough space on the fuselage to provide the airflow channel, and at this time, the first propeller module may also be directly disposed on the side of the fuselage head, as long as it is ensured that the first propeller module can generate the airflow flowing up and down, and this is not limited here.
Referring to fig. 1 to 4, in the present embodiment, the fuselage includes a fuselage main body 1 and wings 2 disposed on two sides of the fuselage main body 1, and further the wings 2 are integrally formed with the fuselage main body 1 to form the fuselage of the fixed wing drone. The specific structural form of the fuselage may adopt the structural form in fig. 1, and may also be adjusted according to specific situations, and is not limited herein.
In this embodiment, the fixed-wing unmanned aerial vehicle includes two first propeller modules, namely a first propeller module 4 and a first propeller module 5, wherein the first propeller module 4 and the first propeller module 5 are arranged on the main body 1 side by side from left to right; of course, in other embodiments, the number of the first propeller modules may be adjusted according to the circumstances, for example, only one first propeller module may be provided, and for example, three first propeller modules may be provided, which is not limited herein.
Further, the first propeller module 4 and the first propeller module 5 are horizontally arranged at the top of the airplane body; of course, the unmanned aerial vehicle can also be arranged at the bottom of the fuselage, and in other embodiments, the first propeller module 4 and the first propeller module 5 can also be inclined at a certain angle relative to the horizontal plane, as long as it is ensured that the airflow generated by the first propeller module 4 and the first propeller module 5 can enable the unmanned aerial vehicle to fly upwards, and the limitation is not made here.
Further, the first propeller module 4 and the first propeller module 5 both comprise a duct, a motor base arranged in the middle of the duct, a motor arranged on the motor base, and a propeller arranged on the motor. Of course, in other embodiments, the specific structural form of the first propeller module 4 and the first propeller module 5 may also be adjusted according to specific situations, and is not limited herein. Of course, in other embodiments, the specific structural forms of the first propeller module 4 and the first propeller module 5 are not limited to the above, and may be adjusted according to the specific circumstances, for example, the arrangement of the duct may be omitted.
Further, the bottom of the mounting seat on the first propeller module 4 extends downwards to form an extension 401, the bottom of the mounting seat on the first propeller module 5 extends downwards to form an extension 501, and the extension 401, the extension 501 and the fuselage support base 101 at the bottom of the fuselage main body 1 together form a landing gear of the fixed wing unmanned aerial vehicle, as shown in fig. 2.
In this embodiment, the fixed-wing drone includes two second propeller modules, which are a second propeller module 6 and a second propeller module 7, respectively; the second propeller module 6 and the second propeller module 7 are respectively arranged on the two wings 2; of course, in other embodiments, the second propeller modules may also be disposed in the middle or below the wing, and the number may also be adjusted according to specific situations, for example, only one second propeller module disposed in the middle of the rear end of the fuselage may also be included, for example, three second propeller modules disposed side by side in the rear end of the fuselage may also be included, and the like, which is not limited herein.
Further, second screw module 6, the slope of second screw module 7 are arranged on the rear end of wing 1, and this embodiment sets up second screw module 6, the slope of second screw module 7 for the thrust of the slope that fixed wing unmanned aerial vehicle second screw module 6, second screw module 7 produced when taking off, the thrust of this slope and the vertical thrust that two first screw modules produced, combined action has guaranteed unmanned aerial vehicle take off the stability in course.
Of course, in other embodiments, the second propeller modules 6 and 7 may also be vertically installed on the wing 1, as long as the second propeller modules 6 and 7 can generate the pushed airflow in the front-back direction, which is not limited herein.
Furthermore, the second propeller module 6 and the second propeller module 7 both comprise a duct, a motor base arranged in the middle of the duct, a motor arranged on the motor base, and a propeller arranged on the motor. Of course, in other embodiments, the specific structural form of the second propeller module 6 and the second propeller module 7 may also be adjusted according to specific situations, and is not limited herein.
In this embodiment, the fixed-wing unmanned aerial vehicle further includes a control circuit board module 3, and the control circuit board module 3 is electrically connected with the two first propeller modules and the two second propeller modules, and is used for respectively controlling the rotating speed and the steering direction of each first propeller module and each second propeller module; for example, the control circuit board module 3 controls the first propeller module 4 and the rotating speed of the first propeller module 5 to realize upward lifting and descending of the head of the fixed-wing drone, and for example, the control circuit board module 3 controls the second propeller module 6 and the rotating speed of the second propeller module 7 to realize forward and backward movement of the fixed-wing drone, and for example, the control circuit board module 3 controls the rotating speed difference between the second propeller module 6 and the second propeller module 7 to realize turning and the like of the fixed-wing drone, and no limitation is made here.
Further, be provided with 6 gyroscopes on the control circuit board module 3 for control first screw module 4, first screw module 5, second screw module 6, second screw module 7, thereby be convenient for realize the automatic control of unmanned aerial vehicle gesture.
In this embodiment, the first propeller module 4, the first propeller module 5, the second propeller module 6, the second propeller module 7, and the control circuit board module 3 are detachably mounted on the machine body. Install first screw module 4, first screw module 5, second screw module 6, the direct detachable of second screw module 7 on the fuselage in this embodiment, its simple structure has realized the modularization assembly, and the equipment is convenient, and assembly, maintenance cost are low.
Further, the detachable connection can be realized by adopting the tool-free quick-release assembly between the first propeller module 4, the first propeller module 5, the second propeller module 6, the second propeller module 7, the control circuit board module 3 and the fuselage, so that the assembly of the fixed-wing unmanned aerial vehicle is further facilitated.
Specifically, the tool-free quick-release assembly comprises a plug-in structure and a slot structure, and the plug-in structure is inserted into the slot structure to realize detachable connection;
the plug-in structure is arranged on the first propeller modules 4 and 5, and the slot structure is arranged on the machine body; or the plug-in structure is arranged on the machine body, and the slot structure is arranged on the first propeller module 4, 5;
the plug-in structure is arranged on the second propeller modules 6 and 7, and the slot structure is arranged on the machine body; or the plug-in structure is arranged on the machine body, and the slot structure is arranged on the second propeller modules 6 and 7;
the plug-in structure is arranged on the control circuit board module 3, and the slot structure is arranged on the machine body; or a plug-in structure is mounted on the body and a slot structure is mounted on the control circuit board module 3.
Of course, in other embodiments, the detachable connection manner between the first propeller module 4, the first propeller module 5, the second propeller module 6, the second propeller module 7, the control circuit board module 3 and the main body is not limited to the above, and may be adjusted according to specific situations.
Example 2
The invention also provides a control method of the fixed-wing unmanned aerial vehicle, the fixed-wing unmanned aerial vehicle adopts the fixed-wing unmanned aerial vehicle described in embodiment 1, the fixed-wing unmanned aerial vehicle further comprises an intelligent main control module, and the control method of the fixed-wing unmanned aerial vehicle comprises the following steps:
the control circuit board module controls the first propeller module to change the state of the machine body; the control circuit board module controls the second propeller module to change the state of the machine body;
or the control circuit board module controls the second propeller module to change the state of the machine body; the control circuit board module controls the first propeller module to change the state of the machine body;
or the circuit board module controls the first propeller module and the second propeller module simultaneously to enable the machine body to change states.
In this embodiment, the control circuit board module controls the first propeller module and the second propeller module to change the state of the main body, specifically including:
when the first propeller module is horizontally arranged and the second propeller module is vertically arranged, the intelligent main control module in the control circuit board module controls the propeller on the first propeller module to rotate, so that up-and-down airflow is generated, and the machine body is directly pushed to lift;
when the first propeller module is horizontally arranged and the second propeller module is obliquely arranged, the intelligent main control module in the control circuit board module controls propellers on the first propeller module and the second propeller module to rotate simultaneously, so that up-and-down airflow is generated together, and the machine body is directly pushed to lift;
in this embodiment, the controlling the second propeller module by the control circuit board module to change the state of the main body specifically includes: an intelligent main control module in the control circuit board module controls the propeller on the second propeller module to rotate in the forward direction to generate thrust to push the machine body to move; or the intelligent main control module in the control circuit board module controls the propellers on the second propeller module to rotate reversely at the same time, so that reverse thrust is generated, and the machine body is pushed to move.
For example, the installation mode of the second propeller is limited, forward transmission of the second propeller module is defined as forward movement of the fixed-wing unmanned aerial vehicle, and overturning of the second propeller is defined as backward movement of the fixed-wing unmanned aerial vehicle; of course, in other embodiments, forward drive of the second propeller module may be defined as backward drive of the fixed-wing drone, and reverse drive of the second propeller may be defined as forward drive of the fixed-wing drone.
In this embodiment, the controlling the second propeller module by the control circuit board module to change the state of the main body further includes: two second propeller modules are arranged on the machine body, and the intelligent main control module in the control circuit board module controls the rotating speed of the propellers on the two second propeller modules to have a rotating speed difference, so that the machine body can turn.
Furthermore, the intelligent main control module controls the rotating speed of the propeller on the second propeller module on the left side to be greater than the rotating speed of the propeller on the second propeller module on the right side, so that a rotating speed difference is generated, and the function of turning to the right is realized.
The intelligent main control module controls the rotating speed of the propeller on the second propeller module on the right side to be greater than that of the propeller on the second propeller module on the left side, and a rotating speed difference is generated, so that the function of turning to the left is achieved.
In this embodiment, the controlling the circuit board module to control the first propeller module and the second propeller module to change the state of the main body further includes: the intelligent main control module controls the rotating speeds of the two first propeller modules to generate a rotating speed difference, and controls the rotating speed between the two second propeller modules to generate a rotating speed difference, so that the fixed-wing unmanned aerial vehicle can be overturned.
In this embodiment, a gyroscope is arranged on the fixed-wing drone; the gyroscope detects the angle deviation of the fixed-wing unmanned aerial vehicle in the running process, when the angle deviation is detected, the angle deviation is fed back to the intelligent main control module, the intelligent main control module respectively controls the rotating speed difference of the propellers on the two second propeller modules according to the fed-back data to correct the course, and the effect that the fixed-wing unmanned aerial vehicle runs straight is achieved.
In this embodiment, be provided with camera device on the fixed wing unmanned aerial vehicle, the control circuit board module passes through camera device and catches the image around the fuselage, judges whether have the barrier around the fuselage and adjust fuselage course.
In this embodiment, the method for controlling a fixed-wing drone further includes: separating the first propeller module, the second propeller module and the control circuit board module from the machine body; the first propeller module, the second propeller module and the control circuit board module are combined into the aircraft, and the aircraft can fly at high altitude. This embodiment has realized the conversion between fixed wing unmanned aerial vehicle and the aircraft, has improved application scope greatly.
It will be appreciated by those skilled in the art that the invention can be embodied in many other specific forms without departing from the spirit or scope thereof. Although embodiments of the present invention have been described, it is to be understood that the present invention should not be limited to those precise embodiments, and that various changes and modifications can be effected therein by one skilled in the art without departing from the scope or spirit of the invention as defined by the appended claims.
Claims (25)
1. A fixed wing drone, comprising:
a body including an airflow flow device;
the first propeller module is arranged on the airflow flowing device and is connected with the machine body;
at least one second propeller module connected with the fuselage;
the first propeller module and the second propeller module are capable of changing the fuselage state.
2. The fixed-wing drone of claim 1, wherein the first propeller module is capable of generating airflow power capable of changing the fuselage state via the airflow flow device.
3. The fixed-wing drone of claim 1 or 2, wherein the airflow flow device includes an airflow channel disposed on the fuselage, the first propeller module being disposed in the airflow channel and connected to the fuselage.
4. The fixed-wing drone of claim 1, wherein the first propeller module is removably connected with the fuselage.
5. The fixed-wing drone of claim 1, wherein the second propeller module is removably connected with the fuselage.
6. The fixed-wing drone of claim 1, further comprising a control circuit board module, the control circuit board module being mounted on the fuselage, and the first and second propeller modules being electrically connected to the control circuit board module.
7. The fixed-wing drone of claim 6, wherein the control circuit board module is removably connected with the fuselage.
8. The fixed wing drone of claim 4, 5 or 7, wherein the first propeller module is connected to the fuselage, the second propeller module is connected to the fuselage, and the control circuit board module is connected to the fuselage using a tool-free quick release assembly.
9. The fixed wing drone of claim 4, 5, or 7, wherein the tool-less quick disconnect assembly includes a plug-in structure and a socket structure, the plug-in structure being inserted into the socket structure to enable a detachable connection, wherein,
the plug-in structure is mounted on the first propeller module, the slot structure is mounted on the machine body, or the plug-in structure is mounted on the machine body, and the slot structure is mounted on the first propeller module;
the plug-in structure is mounted on the second propeller module, the slot structure is mounted on the machine body, or the plug-in structure is mounted on the machine body, and the slot structure is mounted on the second propeller module;
the plug-in structure is installed on the control circuit board module, the slot structure is installed on the machine body, or the plug-in structure is installed on the machine body, and the slot structure is installed on the control circuit board module.
10. The fixed-wing drone of claim 6, wherein the first propeller module, the second propeller module, and the control circuit board module are separable from the fuselage and combinable into an aircraft.
11. The fixed wing drone of claim 1 or 2 or 3 or 5, wherein the fuselage includes a fuselage body and wings disposed on the left and right sides of the fuselage body, and the two wings are integrally formed with the fuselage.
12. The fixed-wing drone of claim 11, wherein the fuselage is provided with two of the first propeller modules, the two first propeller modules being horizontally arranged side-by-side on the fuselage.
13. A fixed wing drone according to claim 11, wherein the fuselage is provided with two of the second propeller modules, the two second propeller modules being arranged obliquely on the two wings, respectively.
14. The fixed-wing drone of claim 13, wherein the second propeller structure is disposed at the wing aft end.
15. The fixed-wing drone of claim 1, wherein the first and second propeller modules each include a duct, a motor mount disposed in the middle of the duct, a motor and a propeller mounted on the motor mount.
16. The fixed-wing drone of claim 1, further comprising a battery module mounted above or below the control circuit board module.
17. A method of controlling a fixed-wing drone, the fixed-wing drone employing the fixed-wing drone of any one of claims 1-17, the fixed-wing drone further including an intelligent host module, the method of controlling the fixed-wing drone comprising:
the control method of the fixed-wing unmanned aerial vehicle comprises the following steps:
the control circuit board module controls the first propeller module to enable the machine body to change states;
the control circuit board module controls the second propeller module to enable the machine body to change states;
or:
the control circuit board module controls the second propeller module to enable the machine body to change states;
the control circuit board module controls the first propeller module to enable the machine body to change states.
18. The method of controlling a fixed-wing drone of claim 17, wherein the control circuit board module controlling the first propeller module to cause the fuselage to change state specifically includes:
and an intelligent main control module in the control circuit board module controls the propeller on the first propeller module to rotate or simultaneously controls the propellers on the first propeller module and the second propeller module to rotate, so that the machine body can take off and land.
19. The method of controlling a fixed-wing drone of claim 17, wherein the control circuit board module controlling the second propeller module to cause the fuselage to change state specifically includes:
an intelligent main control module in the control circuit board module controls the propeller on the second propeller module to rotate in the forward direction to generate thrust to push the machine body to move;
or
And an intelligent main control module in the control circuit board module controls the propellers on the second propeller module to rotate reversely at the same time, so that reverse thrust is generated, and the machine body is pushed to move.
20. The method of controlling a fixed-wing drone of claim 17, wherein the control circuit board module controlling the second propeller module to cause the fuselage to change state includes:
the two second propeller modules are arranged on the machine body, and the intelligent main control module in the control circuit board module controls the rotating speed of the propellers on the two second propeller modules to have a rotating speed difference, so that the machine body can turn.
21. The method of claim 20, wherein the intelligent master control module controls the rotation speed of the propeller on the left second propeller module to be greater than the rotation speed of the propeller on the right second propeller module, so as to generate a rotation speed difference, thereby realizing a function of turning to the right.
22. The method as claimed in claim 20 or 21, wherein the intelligent master control module controls the rotation speed of the propeller on the second propeller module on the right side to be greater than the rotation speed of the propeller on the second propeller module on the left side, so as to generate a rotation speed difference, thereby realizing a function of turning to the left.
23. The method of controlling a fixed-wing drone of claim 17, wherein a gyroscope is provided on the fixed-wing drone; the gyroscope detects the angle deviation of the fixed-wing unmanned aerial vehicle in the running process, when the angle deviation is detected, the angle deviation is fed back to the intelligent main control module, the intelligent main control module respectively controls the rotating speed difference of the propellers on the two second propeller modules according to the fed-back data to correct the course, and the effect that the fixed-wing unmanned aerial vehicle runs straight is achieved.
24. The method of controlling a fixed-wing drone of claim 17, further comprising:
the fixed wing unmanned aerial vehicle is provided with a camera device, and the control circuit board module is used for capturing images around the fuselage through the camera device, judging whether barriers exist around the fuselage and adjusting the course of the fuselage.
25. The method of controlling a fixed-wing drone of claim 17, further comprising:
separating the first propeller module, the second propeller module, and the control circuit board module from the fuselage;
combining the first propeller module, the second propeller module, and the control circuit board module into an aircraft;
the aircraft can realize high-altitude flight.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115402509A (en) * | 2022-11-01 | 2022-11-29 | 上海飞机制造有限公司 | Vertical take-off and landing aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7874513B1 (en) * | 2005-10-18 | 2011-01-25 | Smith Frick A | Apparatus and method for vertical take-off and landing aircraft |
| KR20160116736A (en) * | 2015-03-31 | 2016-10-10 | 주식회사 샘코 | Convertible Wing Type Hybrid UAV |
| CN205661655U (en) * | 2016-06-03 | 2016-10-26 | 南京奇蛙智能科技有限公司 | Many rotor unmanned aerial vehicle of modularization combination formula |
| CN106586001A (en) * | 2016-11-30 | 2017-04-26 | 中国电子科技集团公司第三十八研究所 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
| CN108082466A (en) * | 2017-11-23 | 2018-05-29 | 北京航空航天大学 | A kind of tilting duct connection wing layout vertically taking off and landing flyer |
| CN209454990U (en) * | 2018-08-17 | 2019-10-01 | 昆山合朗电子有限公司 | A kind of fixed-wing unmanned plane |
-
2018
- 2018-08-17 CN CN201810941930.5A patent/CN110834727A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7874513B1 (en) * | 2005-10-18 | 2011-01-25 | Smith Frick A | Apparatus and method for vertical take-off and landing aircraft |
| KR20160116736A (en) * | 2015-03-31 | 2016-10-10 | 주식회사 샘코 | Convertible Wing Type Hybrid UAV |
| CN205661655U (en) * | 2016-06-03 | 2016-10-26 | 南京奇蛙智能科技有限公司 | Many rotor unmanned aerial vehicle of modularization combination formula |
| CN106586001A (en) * | 2016-11-30 | 2017-04-26 | 中国电子科技集团公司第三十八研究所 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
| CN108082466A (en) * | 2017-11-23 | 2018-05-29 | 北京航空航天大学 | A kind of tilting duct connection wing layout vertically taking off and landing flyer |
| CN209454990U (en) * | 2018-08-17 | 2019-10-01 | 昆山合朗电子有限公司 | A kind of fixed-wing unmanned plane |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115402509A (en) * | 2022-11-01 | 2022-11-29 | 上海飞机制造有限公司 | Vertical take-off and landing aircraft |
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Address after: Room No. 388, Zhengwei East Road, Jinxi Town, Kunshan City, Suzhou City, Jiangsu Province, 215324 Applicant after: Kunshan Helang Aviation Technology Co.,Ltd. Address before: Room No. 388, Zhengwei East Road, Jinxi Town, Kunshan City, Suzhou City, Jiangsu Province, 215324 Applicant before: KUNSHAN HELANG ELECTRONICS Co.,Ltd. |