CN109383759B - Aircraft capable of adjusting flight attitude based on control surface - Google Patents
Aircraft capable of adjusting flight attitude based on control surface Download PDFInfo
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- CN109383759B CN109383759B CN201811307693.3A CN201811307693A CN109383759B CN 109383759 B CN109383759 B CN 109383759B CN 201811307693 A CN201811307693 A CN 201811307693A CN 109383759 B CN109383759 B CN 109383759B
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- rotating shaft
- rudder
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- aircraft
- pivot
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
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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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/12—Adjustable control surfaces or members, e.g. rudders surfaces of different type or function being simultaneously adjusted
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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
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/04—Aircraft characterised by the type or position of power plant of piston type
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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
- Y02T50/40—Weight reduction
Abstract
The application relates to an aircraft for adjusting the flight attitude based on a control surface, which comprises a horizontal mounting frame, a propeller, a Z-rudder, a cross horizontal support frame, an X-rudder, a Y-rudder, an oil tank and an oil-driven engine. The horizontal mounting frame is provided with a propeller driven by an oil-driven engine and a Z-rudder driven by a steering engine and capable of rotating and tilting relative to a horizontal plane; the cross horizontal support frame is arranged below the horizontal installation frame, and the X-direction positive half support and the X-direction negative half support in the cross horizontal support frame are respectively provided with an X-direction rudder which is driven by different steering engines and can rotate around an X axis, and the Y-direction positive half support and the Y-direction negative half support are respectively provided with a Y-direction rudder which is driven by different steering engines and can rotate around a Y axis. The structure combines the oil-driven energy supply mode with the unmanned aerial vehicle gesture adjustment mode by the control surface, and realizes the large load and long endurance of the unmanned aerial vehicle with a simple structure with low cost.
Description
Technical Field
The application relates to the field of aircrafts, in particular to an aircraft capable of adjusting a flight attitude based on a control surface.
Background
With the development and application of unmanned aerial vehicle technology, the performance requirements of users on unmanned aerial vehicle big load and long duration are higher and higher, but among the current unmanned aerial vehicle, common adoption electric drive's many rotor unmanned aerial vehicle, its loadability and duration are not enough, when adopting oil power drive, generally adopt the displacement screw to guarantee unmanned aerial vehicle's balance stability and adjust its gesture, but the structure of displacement screw is complicated, with high costs, the fault rate is high, the maintenance requirement is high, be difficult for wide application.
Disclosure of Invention
The application aims to solve the technical problem of providing an aircraft for adjusting the flight attitude based on a control surface, and by utilizing the device, the oil-powered energy supply mode and the unmanned aerial vehicle flight attitude adjustment mode can be combined, so that the unmanned aerial vehicle can realize large load and long endurance with a simple structure with low cost.
The technical scheme adopted by the application for solving the technical problems is as follows:
an aircraft for adjusting a flight attitude based on a control surface, comprising: the horizontal installation frame is provided with a plurality of propellers capable of rotating in a horizontal plane and a Z-direction rudder driven by a steering engine and capable of rotating and tilting relative to the horizontal plane; the X-direction positive half support and the X-direction negative half support are respectively provided with X-direction rudders which are driven by different steering engines and can rotate around an X axis, and Y-direction positive half support and Y-direction negative half support are respectively provided with Y-direction rudders which are driven by different steering engines and can rotate around a Y axis; when the oil tank is arranged to supply energy to the oil-driven engine arranged on the cross horizontal support frame, the oil-driven engine drives the propeller to rotate.
In a preferred embodiment, the horizontal mounting frame is cross-shaped and comprises an X-direction mounting frame and a Y-direction mounting frame.
In a preferred embodiment, the left side of the mounting frame is provided with a first rotating shaft, the right side of the mounting frame is provided with a second rotating shaft, the first rotating shaft and the second rotating shaft extend along the X direction and are driven by different steering engines, the Z-direction rudder fixedly connected to the first rotating shaft and the Z-direction rudder fixedly connected to the second rotating shaft are symmetrically arranged relative to the X-direction mounting frame, and the first rotating shaft and the second rotating shaft are opened and closed relatively in the process of rotating relatively reversely.
In a preferred embodiment, a third rotating shaft is arranged on the left side of the Y-direction mounting frame, a fourth rotating shaft is arranged on the right side of the Y-direction mounting frame, the third rotating shaft and the fourth rotating shaft extend along the Y direction and are driven by different steering engines, a Z-direction rudder fixedly connected to the third rotating shaft and a Z-direction rudder fixedly connected to the fourth rotating shaft are symmetrically arranged relative to the Y-direction mounting frame, and the third rotating shaft and the fourth rotating shaft are opened and closed relatively in the process of rotating reversely relative to each other.
In a preferred embodiment, the propeller mounted on the X-direction mount is located directly above the X-rudder and/or the propeller mounted on the Y-direction mount is located directly above the Y-rudder.
In a preferred embodiment, the center point of the cross-shaped horizontal mounting frame is taken as a middle point, and the plurality of propellers mounted on the X-direction mounting frame are symmetrically and uniformly distributed left and right, and/or the plurality of propellers mounted on the Y-direction mounting frame are symmetrically and uniformly distributed left and right.
In a preferred embodiment, a fifth rotating shaft extending in the X direction is arranged below the X-direction positive half section support, and an X-direction rudder rotating along with the fifth rotating shaft is fixedly connected to the fifth rotating shaft; the X-direction negative half section support comprises a first rotating shaft, a second rotating shaft, a third rotating shaft, a fourth rotating shaft, a fifth rotating shaft and a fourth rotating shaft, wherein the third rotating shaft extends in the X-direction, the fourth rotating shaft is fixedly connected with another X-direction rudder rotating along with the third rotating shaft, and the fourth rotating shaft are driven by different steering engines.
In a preferred embodiment, a seventh rotating shaft extending in the Y direction is arranged below the Y-direction positive half section support, and a Y-direction rudder rotating along with the seventh rotating shaft is fixedly connected to the seventh rotating shaft; an eighth rotating shaft extending in the Y direction is arranged below the Y-direction negative half-section support, another Y-direction rudder rotating along with the eighth rotating shaft is fixedly connected to the eighth rotating shaft, and the seventh rotating shaft and the eighth rotating shaft are driven by different steering engines.
In a preferred embodiment, the oil-driven engine is fixedly arranged at the cross center point of the cross horizontal support frame, the output end of the oil-driven engine is vertically upwards connected with a vertically arranged central rotating shaft, a transmission belt is sleeved between the central rotating shaft and the central shaft of the propeller, and the oil-driven engine drives the central rotating shaft to rotate so as to drive the propeller to rotate.
In a preferred embodiment, the horizontal mounting frame and the cross horizontal supporting frame are fixedly connected with a vertical strut arranged in the Z direction.
The beneficial effects of the application are as follows:
the horizontal mounting frame is provided with a plurality of propellers capable of rotating in a horizontal plane and a Z-direction rudder driven by a steering engine and capable of rotating and tilting relative to the horizontal plane; the cross horizontal support frame is arranged below the horizontal installation frame, a cross center point of the cross horizontal support frame is used as an origin, the cross horizontal support frame comprises an X-direction positive half-section support, an X-direction negative half-section support, a Y-direction positive half-section support and a Y-direction negative half-section support, X-direction rudders which are driven by different steering engines and can rotate around an X axis are respectively arranged below the X-direction positive half-section support and the X-direction negative half-section support, and Y-direction rudders which are driven by different steering engines and can rotate around a Y axis are respectively arranged below the Y-direction positive half-section support and the Y-direction negative half-section support; when the oil tank is arranged to supply energy to the oil engine arranged on the cross horizontal support frame, the oil engine drives the propeller to rotate. The structure combines the oil-driven energy supply mode with the unmanned aerial vehicle gesture adjustment mode by the control surface, and realizes the large load and long endurance of the unmanned aerial vehicle with a simple structure with low cost.
Drawings
The application is further described below with reference to the drawings and examples.
FIG. 1 is a schematic view of the composition of an embodiment of the present application;
FIG. 2 is a schematic view of an embodiment of the present application with the horizontal mount removed;
fig. 3 is a partial enlarged view of a portion a of the embodiment of fig. 2.
Detailed Description
The conception, specific structure, and technical effects produced by the present application will be clearly and completely described below with reference to the embodiments and the drawings to fully understand the objects, aspects, and effects of the present application. It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other.
It should be noted that, unless otherwise specified, when a feature is referred to as being "fixed" or "connected" to another feature, it may be directly or indirectly fixed or connected to the other feature. Further, the descriptions of the upper, lower, left, right, etc. used in the present application are merely with respect to the mutual positional relationship of the constituent elements of the present application in the drawings unless otherwise specified.
Furthermore, unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used in the description presented herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The term "and/or" as used herein includes any combination of one or more of the associated listed items.
FIG. 1 is a schematic view of the composition of an embodiment of the present application, FIG. 2 is a schematic view of an embodiment of the present application with the horizontal mounting frame removed, and FIG. 3 is an enlarged partial view of portion A of the embodiment of FIG. 2; referring to fig. 1 to 3, the aircraft for adjusting a flight attitude based on a control surface includes:
the device comprises a horizontal mounting frame 1, a propeller 2, a Z-rudder 3, a cross horizontal support frame 4, an X-rudder 5, a Y-rudder 6, an oil tank 7, an oil-driven engine 8, a first rotating shaft 9, a second rotating shaft 10, a fifth rotating shaft 11, a sixth rotating shaft 12, a seventh rotating shaft 13, an eighth rotating shaft 14, a central rotating shaft 15, a propeller central shaft 16, a transmission belt 17 and a vertical strut 18.
Also shown in fig. 2 is a generally rectangular spatial coordinate system including an X-axis, a Y-axis, and a Z-axis, and labeled in the X-direction, the Y-direction, and the Z-direction.
In the application, a plurality of propellers 2 which can rotate in a horizontal plane are arranged on a horizontal mounting frame 1, and a Z-direction rudder 3 which is driven by a steering engine (not shown in the figure) and can be rotated and inclined to form a certain angle with the horizontal plane is also arranged; a cross horizontal support frame 4 is arranged below the horizontal installation frame 1.
Taking the cross center point of the cross horizontal support frame 4 as an origin, the cross horizontal support frame 4 comprises an X-direction positive half-section support 4a, an X-direction negative half-section support 4b, a Y-direction positive half-section support 4c and a Y-direction negative half-section support 4d; an X-rudder 5 which is driven by different steering engines (not shown in the figure) and can rotate around the X-axis by a certain angle is arranged below the X-direction positive half support 4a and the X-direction negative half support 4b, and a Y-rudder 6 which is driven by different steering engines (not shown in the figure) and can rotate around the Y-axis by a certain angle is arranged below the Y-direction positive half support 4c and the Y-direction negative half support 4 d.
The cross horizontal support frame 4 is fixedly provided with an oil-driven engine 8, and when the oil tank 7 supplies energy to the oil-driven engine 8, the oil-driven engine 8 drives the propeller 2 to rotate. Here, it is preferred that the oil tank is located at the center of gravity of the whole aircraft, and when a plurality of oil tanks are provided, the plurality of oil tanks are symmetrically distributed with respect to the center of gravity of the aircraft to optimize the balance performance of the whole aircraft.
In the structure, the aircraft adopts the mode of adjusting the flight attitude of the aircraft by the cooperation of the Z-rudder 3, the X-rudder 5 and the Y-rudder 6, and the adjusting mode is matched with the oil-driven energy supply mode, so that the unmanned aerial vehicle has the advantages of large load and long endurance, simple and reliable structure and low production and maintenance cost.
As shown in the embodiment of fig. 1 to 2, the horizontal mounting frame 1 is in a cross shape, including an X-direction mounting frame 1a and a Y-direction mounting frame 1b, which increases the area where the propeller 2 can be mounted, and when there are a plurality of propellers 2, the layout forms of the relative positions thereof are various.
In the embodiment 1 as shown in fig. 1 to 2, a first rotating shaft 9 is disposed on the left side of an X-direction mounting frame 1a, a second rotating shaft 10 is disposed on the right side of the X-direction mounting frame 1a, the first rotating shaft 9 and the second rotating shaft 10 extend along the X-direction and are driven by different steering engines (not shown in the drawings), the Z-rudder 3 fixedly connected to the first rotating shaft 9 and the Z-rudder 3 fixedly connected to the second rotating shaft 10 are symmetrically distributed relative to the X-direction mounting frame 1a, and the first rotating shaft 9 and the second rotating shaft 10 are relatively opened and closed in the process of relatively reversely rotating so as to change the airflow acting force borne by the Z-rudder 3 on the first rotating shaft 9 and the Z-rudder 3 on the second rotating shaft 10, and further change the airflow acting force borne by the whole aircraft in the vertical direction.
In embodiment 2 (not shown), a third rotating shaft is disposed on the left side of the mounting frame, a fourth rotating shaft is disposed on the right side of the mounting frame, the third rotating shaft and the fourth rotating shaft extend along the Y direction and are driven by different steering engines, the Z-rudder fixedly connected to the third rotating shaft and the Z-rudder fixedly connected to the fourth rotating shaft are symmetrically distributed relative to the Y-direction mounting frame, and the Z-rudder is opened and closed relatively in the process of relative reverse rotation of the third rotating shaft and the fourth rotating shaft, so that the airflow acting force borne by the Z-rudder on the third rotating shaft and the Z-rudder on the fourth rotating shaft can be changed, and the airflow acting force borne by the whole aircraft in the vertical direction is further changed. The structures described in embodiment 1 and embodiment 2 may be present at the same time or may be present in only one of the structures described in the embodiments.
As in the embodiment shown in fig. 1-2, the propeller 2 mounted on the X-direction mounting 1a is located directly above the X-rudder 5 and/or the propeller 2 mounted on the Y-direction mounting 1b is located directly above the Y-rudder 6, so that the air flow generated by the propeller 2 can flow directly to the X-rudder 5 and/or the Y-rudder 6 to exert a force on it.
In the embodiment shown in fig. 1 and fig. 2, the center point of the cross-shaped horizontal mounting frame 1 is taken as the midpoint, a plurality of propellers 2 mounted on the X-direction mounting frame 1a are symmetrically and uniformly distributed left and right, and/or a plurality of propellers 2 mounted on the Y-direction mounting frame 1b are symmetrically and uniformly distributed left and right, so that the overall balance of the aircraft is improved.
As shown in the embodiment of fig. 1 and 2, a fifth rotating shaft 11 extending in the X direction is arranged below the positive half-section support 4a, and the fifth rotating shaft 11 is fixedly connected with an X rudder 5 rotating along with the fifth rotating shaft 11; a sixth rotating shaft 12 extending in the X direction is arranged below the negative X-direction half-section support 4b, another X-direction rudder 5 rotating along with the sixth rotating shaft 12 is fixedly connected to the sixth rotating shaft 12, and the fifth rotating shaft 11 and the sixth rotating shaft 12 are driven by different steering engines (not shown in the figure) and can rotate independently.
As shown in the embodiment of fig. 1 and 2, a seventh rotating shaft 13 extending in the Y direction is arranged below the Y-direction positive half section support 4c, and the seventh rotating shaft 13 is fixedly connected with a Y-rudder 6 rotating along with the seventh rotating shaft 13; an eighth rotating shaft 14 extending in the Y direction is arranged below the negative half-section support 4d, another Y rudder 6 rotating along with the eighth rotating shaft 14 is fixedly connected to the eighth rotating shaft 14, and the seventh rotating shaft 13 and the eighth rotating shaft 14 are driven by different steering engines (not shown in the figure) and can rotate independently.
As shown in fig. 2 and 3, in the embodiment, an oil engine 8 is fixedly arranged at the cross center point of the cross horizontal support frame 4, so as to improve the balance of the aircraft, the output end of the oil engine 8 is vertically upwards connected with a vertically arranged central rotating shaft 15, a transmission belt 17 is sleeved between the central rotating shaft 15 and a central shaft 16 of the propeller, and the oil engine 8 drives the propeller 2 to rotate in the process of driving the central rotating shaft 15 to rotate.
Here, taking the cross center point of the cross horizontal mounting frame 1 as the midpoint, a transmission belt 17 is sleeved between a propeller central shaft 16 nearest to the central rotating shaft 15 and the central rotating shaft 15 on the negative half shaft section of the X-direction mounting frame; on the positive semi-axis section of the X-direction mounting frame, a sub-rotating shaft 15b adjacent to the central rotating shaft 15 is arranged, a sub-rotating shaft gear 15c sleeved on the sub-rotating shaft 15b is meshed with a central shaft gear 15a sleeved on the central rotating shaft 15, and a transmission belt 17 is sleeved between the sub-rotating shaft 15b and a propeller central shaft 16 arranged on the positive semi-axis section of the X-direction mounting frame.
Similarly, a transmission belt 17 is sleeved between a central shaft 16 of the propeller nearest to the central rotating shaft 15 and the central rotating shaft 15 on the positive half shaft section of the Y-direction mounting frame; on the negative half shaft section of the Y-direction installation frame, a sub-rotating shaft 15d adjacent to the central rotating shaft 15 is arranged, a sub-rotating shaft gear 15e sleeved on the sub-rotating shaft 15d is meshed with a central shaft gear 15a sleeved on the central rotating shaft 15, a transmission belt 17 is sleeved between the sub-rotating shaft 15d and the nearest adjacent screw central shaft 16 on the negative half shaft section of the Y-direction installation frame, and a transmission belt 17 is sleeved between the adjacent screw central shafts 16 on the same positive half shaft section or the same negative half shaft section on the Y-direction installation frame.
The oil-driven engine 8 drives the sub-rotating shafts 15b and 15d to rotate through gear engagement in the process of driving the central rotating shaft 15 to rotate, and then drives the propeller 2 to rotate through the transmission belt 17, and at the moment, the gear engagement changes the rotation direction, so that the rotation direction of the propeller 2 mounted on the positive half shaft section and the negative half shaft section of the X-direction mounting frame 1a is opposite, and the rotation direction of the propeller 2 mounted on the positive half shaft section and the negative half shaft section of the Y-direction mounting frame 1b is opposite. Here, the inside of the horizontal mounting frame 1 may be provided with a cavity, and the cavity is wrapped to accommodate the central shaft gear 15a, the sub-rotating shaft 15b, the sub-rotating shaft 15d, the sub-rotating shaft gear 15c, the sub-rotating shaft gear 15e, the propeller central shaft 16 and the driving belt 17, so as to play roles in protecting the structure and improving the structural cleanliness.
In the embodiment shown in fig. 1, preferably, a vertical strut 18 arranged in the Z direction is fixedly connected between the horizontal mounting frame 1 and the cross horizontal supporting frame 4, so that the structural strength is improved.
In the embodiment shown in fig. 1 and 2, the flight process of the aircraft is as follows:
in the vertical take-off process of the aircraft, the oil tank 7 supplies energy, the oil motor 8 drives the propeller 6 to rotate, and when the lift force generated by the propeller 2 is greater than the self weight of the aircraft, the aircraft takes off vertically; the rotating directions of the propellers 2 symmetrically arranged along the X direction and the Y direction on the horizontal mounting frame 1 are opposite, and the propellers are used for counteracting the moment of the whole machine in the X direction.
When the lift force generated by the propeller 2 is equal to the dead weight of the aircraft, the aircraft hovers, at the moment, two Y-rudders 6 respectively arranged on a seventh rotating shaft 13 and an eighth rotating shaft 14 rotate in the same direction around the Y axis, so that the rotation balance of the whole machine around the Y axis is realized, and the two Y-rudders 6 rotate in different directions around the Y axis, so that the rotation balance of the whole machine around the Z axis is realized; two X rudders 5 respectively arranged on the fifth rotating shaft 11 and the sixth rotating shaft 12 rotate in the same direction around the X axis, so that the rotation balance of the whole machine around the X axis is realized; the entire equilibrium stabilization process is regulated by the control 19, preferably the control 19 is located in the position of the center of gravity of the aircraft.
When the aircraft moves along the positive direction of the X axis, the Y rudder 6 rotates in the same direction around the Y axis, the rotating direction is anticlockwise seen from the positive direction of the Y axis, at the moment, the whole aircraft is subjected to clockwise torque seen from the positive direction of the Y axis, the aircraft tilts, the lifting force generated by the propeller 2 can generate a component force in the positive direction of the X axis, and the aircraft is driven to move along the positive direction of the X axis; the same applies to the movement of the aircraft in the negative X-axis direction.
When the aircraft moves along the positive direction of the Y axis, the X rudder 5 rotates around the X axis in the same direction; the rotating direction is anticlockwise seen from the positive direction of the X axis, at the moment, the whole aircraft is subjected to clockwise torque seen from the positive direction of the X axis, the aircraft is inclined, and the lifting force generated by the propeller 2 can generate a component force in the positive direction of the Y axis to drive the aircraft to move in the positive direction of the Y axis; the same applies to the movement of the aircraft in the negative Y-axis direction.
When the aircraft is to vertically land, the opposite opening angles of the Z-rudders 3 respectively arranged on the first rotating shaft 9 and the second rotating shaft 10 are increased, and/or the opposite opening angles of the Z-rudders 3 respectively arranged on the third rotating shaft and the fourth rotating shaft are increased, so that the air flow generated by the propeller 2 is blocked, the thrust of the air flow in the vertical direction is reduced, and the vertical landing of the aircraft is realized.
While the preferred embodiment of the present application has been described in detail, the present application is not limited to the embodiments, and those skilled in the art can make various equivalent modifications or substitutions without departing from the spirit of the present application, and the equivalent modifications or substitutions are included in the scope of the present application as defined in the appended claims.
Claims (8)
1. An aircraft for adjusting a flight attitude based on a control surface, comprising: the horizontal installation frame is provided with a plurality of propellers capable of rotating in a horizontal plane and a Z-direction rudder driven by a steering engine and capable of rotating and tilting relative to the horizontal plane; the X-direction positive half support and the X-direction negative half support are respectively provided with X-direction rudders which are driven by different steering engines and can rotate around an X axis, and Y-direction positive half support and Y-direction negative half support are respectively provided with Y-direction rudders which are driven by different steering engines and can rotate around a Y axis; when an oil tank is arranged to supply energy to an oil-driven engine arranged on the cross horizontal support frame, the oil-driven engine drives the propeller to rotate;
the horizontal mounting frame is cross-shaped and comprises an X-direction mounting frame and a Y-direction mounting frame; the left side of X to the mounting bracket sets up first pivot, right side sets up the second pivot, first pivot with the second pivot is along X to extending and receiving different steering wheel drive, fixed connection is in first epaxial Z is to rudder and fixed connection is in the epaxial Z of second is to the relative X is to the mounting bracket bilateral symmetry setting first pivot with the relative reverse pivoted in-process of second pivot opens and shuts relatively, works as when the aircraft is about to descend perpendicularly, the increase sets up respectively first pivot with the epaxial Z opens the angle relatively of rudder of second, stops the air current that the screw produced to reduce the thrust of air current on vertical direction, realize the aircraft descends perpendicularly.
2. The aircraft for adjusting a flight attitude based on a control surface according to claim 1, wherein: the Y sets up the third pivot to the left side of mounting bracket, the right side sets up the fourth pivot, the third pivot with the fourth pivot extends and receives different steering wheel drive along Y to the extension, fixed connection is in on the third pivot Z rudder and fixed connection are in the epaxial Z rudder of fourth is relative Y is to the mounting bracket bilateral symmetry setting the third pivot with the relative reverse pivoted in-process of fourth pivot opens and shuts relatively.
3. The aircraft for adjusting a flight attitude based on a control surface according to claim 1, wherein: the propeller arranged on the X-direction mounting frame is positioned right above the X-direction rudder, and/or the propeller arranged on the Y-direction mounting frame is positioned right above the Y-direction rudder.
4. The aircraft for adjusting a flight attitude based on a control surface according to claim 1, wherein: the cross center point of the cross-shaped horizontal installation frame is taken as a midpoint, a plurality of propellers installed on the X-direction installation frame are symmetrically distributed left and right and uniformly, and/or a plurality of propellers installed on the Y-direction installation frame are symmetrically distributed left and right and uniformly.
5. The aircraft for adjusting a flight attitude based on control surfaces according to any one of claims 1, 3, and 4, wherein: a fifth rotating shaft extending in the X direction is arranged below the X-direction positive half section support, and an X-direction rudder rotating along with the fifth rotating shaft is fixedly connected to the fifth rotating shaft; the X-direction negative half section support comprises a first rotating shaft, a second rotating shaft, a third rotating shaft, a fourth rotating shaft, a fifth rotating shaft and a fourth rotating shaft, wherein the third rotating shaft extends in the X-direction, the fourth rotating shaft is fixedly connected with another X-direction rudder rotating along with the third rotating shaft, and the fourth rotating shaft are driven by different steering engines.
6. The aircraft for adjusting a flight attitude based on control surfaces according to any one of claims 1, 3, and 4, wherein: a seventh rotating shaft extending in the Y direction is arranged below the Y-direction positive half section support, and a Y-direction rudder rotating along with the seventh rotating shaft is fixedly connected to the seventh rotating shaft; an eighth rotating shaft extending in the Y direction is arranged below the Y-direction negative half-section support, another Y-direction rudder rotating along with the eighth rotating shaft is fixedly connected to the eighth rotating shaft, and the seventh rotating shaft and the eighth rotating shaft are driven by different steering engines.
7. The aircraft for adjusting a flight attitude based on a control surface according to claim 1, wherein: the oil-driven engine is fixedly arranged at the cross center point of the cross horizontal support frame, the output end of the oil-driven engine is vertically upwards connected with a vertically arranged center rotating shaft, a transmission belt is sleeved between the center rotating shaft and a propeller center shaft of the propeller, and the oil-driven engine drives the center rotating shaft to rotate so as to drive the propeller to rotate.
8. The aircraft for adjusting a flight attitude based on control surfaces according to any one of claims 1, 4, and 7, wherein: the horizontal mounting frame is fixedly connected with a vertical strut arranged in the Z direction between the cross horizontal supporting frames.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811307693.3A CN109383759B (en) | 2018-11-05 | 2018-11-05 | Aircraft capable of adjusting flight attitude based on control surface |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811307693.3A CN109383759B (en) | 2018-11-05 | 2018-11-05 | Aircraft capable of adjusting flight attitude based on control surface |
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| Publication Number | Publication Date |
|---|---|
| CN109383759A CN109383759A (en) | 2019-02-26 |
| CN109383759B true CN109383759B (en) | 2023-08-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811307693.3A Active CN109383759B (en) | 2018-11-05 | 2018-11-05 | Aircraft capable of adjusting flight attitude based on control surface |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112550742B (en) * | 2020-12-10 | 2022-04-15 | 国网浙江省电力有限公司江山市供电公司 | Rotary unmanned aerial vehicle electroscope |
| CN112550708B (en) * | 2020-12-10 | 2022-04-15 | 国网浙江省电力有限公司江山市供电公司 | Unmanned aerial vehicle tests electrical equipment |
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| CN108423167A (en) * | 2018-05-14 | 2018-08-21 | 南方科技大学 | A kind of double control system aircraft |
| CN209567073U (en) * | 2018-11-05 | 2019-11-01 | 南方科技大学 | A kind of aircraft adjusting flight attitude based on rudder face |
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