CN110775262A - Tailstock type sea-air cross-domain aircraft device based on four-rotor driving mode - Google Patents
Tailstock type sea-air cross-domain aircraft device based on four-rotor driving mode Download PDFInfo
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- CN110775262A CN110775262A CN201911006438.XA CN201911006438A CN110775262A CN 110775262 A CN110775262 A CN 110775262A CN 201911006438 A CN201911006438 A CN 201911006438A CN 110775262 A CN110775262 A CN 110775262A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/008—Amphibious sea planes
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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
- B64C35/00—Flying-boats; Seaplanes
- B64C35/005—Flying-boats; Seaplanes with propellers, rudders or brakes acting in the water
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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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Abstract
The invention provides a tailstock type sea-air cross-domain aircraft device based on a four-rotor driving mode, which comprises: the device comprises an aircraft body module, an aircraft tailstock module 5, an aircraft control module 9, a posture adjustment module and a thruster module; the aircraft body module comprises: fuselage components, wing components; the fuselage part is connected with the wing part in a smooth transition mode; the aircraft tailstock module 5 can support the aircraft to take off and land vertically; the aircraft tailstock module 5 is arranged at the tail of the wing; the attitude adjusting module adjusts the attitude of the aircraft; the thruster module comprises: the main air contra-rotating propeller part and the auxiliary air contra-rotating propeller part; the main air contra-rotating paddle part and the auxiliary air contra-rotating paddle part can provide forward power for the aircraft when the aircraft sails in water and in the air; the aircraft control module 9 is connected with the attitude adjusting module and the propeller module. The invention can vertically go out of and enter water like four rotors through two pairs of air propellers, thereby realizing the cross-region flying in the sea and the air.
Description
Technical Field
The invention relates to the field of unmanned autonomous aircrafts, in particular to a tailstock type sea-air cross-domain aircraft device based on a four-rotor driving mode, and particularly relates to a tailstock type sea-air cross-domain unmanned autonomous aircraft based on a four-rotor driving mode.
Background
Currently, for the purposes of emergency quick search or military stealth and defense penetration, and the like, an unmanned autonomous aircraft capable of crossing sea and air domains needs to be designed, and the unmanned autonomous aircraft is required to meet the following purposes: when the aircraft needs to rapidly maneuver, the aircraft flies out of the water surface and rapidly moves in the air; when the underwater vehicle does not need to be maneuvered quickly, the underwater vehicle is hidden at the water bottom, the monitoring task is completed, and the underwater vehicle can be used for opportunistically attacking the enemy. Although some existing amphibious aircraft can achieve part of the functions, the capabilities of concealment, adaptability to complex environments and the like need to be further improved. The tailstock type sea-air cross-domain unmanned autonomous aircraft based on the four-rotor driving mode has the characteristics of capability of crossing two sea-air domains, vertical take-off and landing, high flexibility, high concealment, capability of hovering in the air, high wind and wave resistance and the like, and is expected to be widely applied to the fields of marine scientific investigation, sea-bottom resource exploration and development, military and the like.
Patent document CN109562821A discloses an aircraft (100) comprising a central frame (1), an antenna (3), and a horn assembly (2) connected to the central frame, the horn assembly comprising a horn (21). The antenna is arranged on the machine arm and far away from the position of the center frame. The aircraft further comprises a connecting piece (4) arranged on the horn, and the connecting piece is used for fixing the antenna on the horn. The aircraft sets up the antenna on the horn, keeps away from aircraft center frame setting and has avoided other parts to influence this antenna performance, and can make things convenient for the dismantlement of foot rest. The patent still has the space to be improved on the characteristics of cross-sea-air two-domain use, vertical take-off and landing, high flexibility, strong concealment and the like.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a tailstock type sea-air cross-domain aircraft device based on a four-rotor driving mode.
The invention provides a tailstock type sea-air cross-domain aircraft device based on a four-rotor driving mode, which comprises: the device comprises an aircraft body module, an aircraft tailstock module 5, an aircraft control module 9, a posture adjustment module and a thruster module; the aircraft body module comprises: fuselage components, wing components; the fuselage part is connected with the wing part in a smooth transition mode; therefore, the effects of reducing the resistance of the aircraft and improving the movement speed of the aircraft can be achieved. The main body part mainly provides lift force for the aircraft when moving in the air or underwater, and can increase the load capacity of the aircraft when navigating underwater; the aircraft tailstock module 5 can support the aircraft to take off and land vertically; the wing component includes: a wing tail; the aircraft tailstock module 5 is arranged at the tail of the wing; the attitude adjusting module adjusts the attitude of the aircraft by moving the position of the center of gravity; the thruster module comprises: the main air contra-rotating propeller part and the auxiliary air contra-rotating propeller part; the main air contra-rotating paddle part and the auxiliary air contra-rotating paddle part can provide forward power for the aircraft when the aircraft sails in water and in the air; the aircraft control module 9 is connected with the attitude adjusting module and the propeller module.
Preferably, the method further comprises the following steps: an aircraft steering module; the number of the auxiliary air contrarotating propeller parts is 2; the aircraft steering module can adjust 2 auxiliary air contra-rotating propeller parts to different rotating speeds when the aircraft steers.
Preferably, the method further comprises the following steps: an aircraft power module 4; the aircraft power module 4 employs a lithium lead battery.
Preferably, the primary air contra-rotating paddle component comprises: a main propeller part 1; the number of the main propeller parts 1 is 2; the main propeller part 1 includes: a left main propeller component, a right main propeller component; the wing component includes: a horizontal left wing component, a horizontal right wing component; the horizontal left wing part and the horizontal right wing part are symmetrical about the aircraft body module; the left main propeller part and the right main propeller part are symmetrically arranged on the horizontal left wing part and the horizontal right wing part.
Preferably, the main air contra-rotating paddle part further comprises: a main propeller motor 2 and a main propeller electric controller 3; the main propeller motor 2 is connected with the main propeller part 1; the main propeller electric controller 3 is connected with the main propeller motor 2; the main pitch 3 includes: the left main propeller electric controller and the right main propeller electric controller; the left main propeller electric regulator and the right main propeller electric regulator are symmetrically arranged on the horizontal left wing component and the horizontal right wing component.
Preferably, the secondary air counter-rotating paddle member comprises: a sub-propeller member 6; the number of the auxiliary propeller parts 6 is 2; the sub-propeller member 6 includes: an upper auxiliary propeller part and a lower auxiliary propeller part; the wing component further comprises: a horizontal upper wing component, a horizontal lower wing component; the horizontal upper wing part and the horizontal lower wing part are symmetrical about the aircraft body module; the upper auxiliary propeller part and the lower auxiliary propeller part are symmetrically arranged on the horizontal upper wing part and the horizontal lower wing part.
Preferably, the secondary air counter-rotating paddle component further comprises: an auxiliary paddle motor 7 and an auxiliary paddle electronic regulator 8; the auxiliary propeller motor 7 is connected with the auxiliary propeller part 6; the auxiliary paddle electricity regulator 8 is connected with an auxiliary paddle motor 7; the auxiliary pitch controller 8 comprises: the upper auxiliary paddle electric regulator and the lower auxiliary paddle electric regulator; the upper auxiliary propeller electric controller and the lower auxiliary propeller electric controller are symmetrically arranged on the horizontal upper wing part and the horizontal lower wing part.
Preferably, the aircraft control module 9 is arranged inside the fuselage section.
Preferably, the aircraft power module 4 is arranged inside the fuselage section; the fuselage component comprises: an aircraft head; the aircraft power module 4 is arranged at the head of the aircraft.
Compared with the prior art, the invention has the following beneficial effects:
1. the aircraft combines the four rotor wings and the fixed wings, adopts a wing body fusion mode, and adopts circular arc smooth transition at the joint of the wing and the aircraft body, thereby achieving the effects of reducing the resistance of the aircraft and improving the movement speed of the aircraft;
2. the invention can vertically go out and enter water like four rotors through two pairs of air propellers, thereby realizing the cross-region flying in sea and air;
3. according to the invention, the balance torque is provided through the difference of the propellers during water outlet, so that the water outlet stability of the aircraft can be improved. In addition, functions of hovering in the air at fixed points and the like can be realized.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic view of the overall structure of the aircraft according to the invention.
FIG. 2 is a side view of the present invention.
Fig. 3 is a schematic top view of the present invention.
Fig. 4 is a front view of the present invention.
Fig. 5 is a schematic view of the external structure of the present invention.
Fig. 6 is a schematic diagram of the working principle of the present invention.
In the figure:
Main propeller electric controller 3 and auxiliary propeller electric controller 8
Aircraft power module 4 aircraft control module 9
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1-6, the tailstock type sea-air cross-domain aircraft device based on the four-rotor driving mode provided by the invention has the characteristics of capability of crossing two sea-air domains, vertical take-off and landing, high flexibility, strong concealment, capability of hovering in the air, strong wind and wave resistance and the like, so that the aircraft has the capability of fast maneuvering and can conceal in water to complete various designated tasks. The method comprises the following steps: the device comprises an aircraft body module, an aircraft tailstock module 5, an aircraft control module 9, a posture adjustment module and a thruster module; the aircraft body module comprises: fuselage components, wing components; the fuselage part is connected with the wing part in a smooth transition mode; therefore, the effects of reducing the resistance of the aircraft and improving the movement speed of the aircraft can be achieved. The main body part mainly provides lift force for the aircraft when moving in the air or underwater, and can increase the load capacity of the aircraft when navigating underwater; the aircraft tailstock module 5 can support the aircraft to take off and land vertically; the wing component includes: a wing tail; the aircraft tailstock module 5 is arranged at the tail of the wing; the attitude adjusting module adjusts the attitude of the aircraft by moving the position of the center of gravity; the thruster module comprises: the main air contra-rotating propeller part and the auxiliary air contra-rotating propeller part; the main air contra-rotating paddle part and the auxiliary air contra-rotating paddle part can provide forward power for the aircraft when the aircraft sails in water and in the air; the aircraft control module 9 is connected with the attitude adjusting module and the propeller module.
Preferably, the method further comprises the following steps: an aircraft steering module; the number of the auxiliary air contrarotating propeller parts is 2; the aircraft steering module can adjust 2 auxiliary air contra-rotating propeller parts to different rotating speeds when the aircraft steers.
Preferably, the method further comprises the following steps: an aircraft power module 4; the aircraft power module 4 employs a lithium lead battery.
Preferably, the primary air contra-rotating paddle component comprises: a main propeller part 1; the number of the main propeller parts 1 is 2; the main propeller part 1 includes: a left main propeller component, a right main propeller component; the wing component includes: a horizontal left wing component, a horizontal right wing component; the horizontal left wing part and the horizontal right wing part are symmetrical about the aircraft body module; the left main propeller part and the right main propeller part are symmetrically arranged on the horizontal left wing part and the horizontal right wing part.
Preferably, the main air contra-rotating paddle part further comprises: a main propeller motor 2 and a main propeller electric controller 3; the main propeller motor 2 is connected with the main propeller part 1; the main propeller electric controller 3 is connected with the main propeller motor 2; the main pitch 3 includes: the left main propeller electric controller and the right main propeller electric controller; the left main propeller electric regulator and the right main propeller electric regulator are symmetrically arranged on the horizontal left wing component and the horizontal right wing component.
Preferably, the secondary air counter-rotating paddle member comprises: a sub-propeller member 6; the number of the auxiliary propeller parts 6 is 2; the sub-propeller member 6 includes: an upper auxiliary propeller part and a lower auxiliary propeller part; the wing component further comprises: a horizontal upper wing component, a horizontal lower wing component; the horizontal upper wing part and the horizontal lower wing part are symmetrical about the aircraft body module; the upper auxiliary propeller part and the lower auxiliary propeller part are symmetrically arranged on the horizontal upper wing part and the horizontal lower wing part.
Preferably, the secondary air counter-rotating paddle component further comprises: an auxiliary paddle motor 7 and an auxiliary paddle electronic regulator 8; the auxiliary propeller motor 7 is connected with the auxiliary propeller part 6; the auxiliary paddle electricity regulator 8 is connected with an auxiliary paddle motor 7; the auxiliary pitch controller 8 comprises: the upper auxiliary paddle electric regulator and the lower auxiliary paddle electric regulator; the upper auxiliary propeller electric controller and the lower auxiliary propeller electric controller are symmetrically arranged on the horizontal upper wing part and the horizontal lower wing part.
Preferably, the aircraft control module 9 is arranged inside the fuselage section.
Preferably, the aircraft power module 4 is arranged inside the fuselage section; the fuselage component comprises: an aircraft head; the aircraft power module 4 is arranged at the head of the aircraft.
Specifically, in one embodiment, as shown in fig. 1 to 5, a tailstock-type sea-air cross-region unmanned autonomous aircraft based on a quad-rotor driving mode combines a quad-rotor and a fixed wing, and a wing body fusion mode is adopted for a main body part, and a circular arc smooth transition mode is adopted at a joint of a wing and a fuselage, so that the effects of reducing aircraft resistance and increasing the moving speed of the aircraft can be achieved. Compared with the existing unmanned autonomous aircraft, the aircraft mainly vertically goes out of water and enters water through two pairs of air propellers like four rotors, so that the cross-region flight in the sea and the air can be realized. The most advantages are as follows: when water flows out, the propellers differentially provide balanced torque, and the water outlet stability of the aircraft can be improved. In addition, functions of hovering in the air at fixed points and the like can be realized.
As shown in fig. 6, when a task needs to be performed, the aircraft can take off vertically on a ship, and after taking off, the aircraft can fly in the air in different motion modes by adjusting the posture. If underwater reconnaissance needs to be performed or underwater needs to be entered into water for the purpose of concealment, the vehicle can vertically enter the water by adjusting the posture, and underwater motion can be realized in different motion modes after the vehicle enters the water. When water needs to be discharged again, the aircraft can vertically discharge water by adjusting the posture. When the aerial mission is completed and the preparation and recovery are carried out, the aerial mission can be returned to the land or the ship in a vertical landing mode by adjusting the posture. When the aircraft vertically goes out of water and goes into water, the aircraft is balanced and stable by means of the four propellers during vertical movement. When the aircraft is required to turn, the aircraft is turned by changing the rotating speed of the pair of auxiliary air propellers. When the aircraft is to be changed from a vertical motion attitude to a horizontal flight attitude, the aircraft is subjected to attitude adjustment by adjusting the position of the center of gravity and the rotating speed of the pair of auxiliary air propellers. In horizontal flight attitude, the aircraft can be regarded as a normal horizontal flight aircraft, and the arrangement of the gravity center and the aerodynamic focus can be set by reference to the aircraft. In addition, when the aircraft needs to be suspended in the air (or underwater) at a fixed point for a certain task, the aircraft is adjusted from a horizontal flight attitude (or other attitude) to a vertical state through attitude adjustment, and the fixed rotating speeds of the two pairs of propellers are respectively given, so that the aircraft can realize the air (or underwater) fixed-point suspension.
The aircraft combines the four rotor wings and the fixed wings, adopts a wing body fusion mode, and adopts circular arc smooth transition at the joint of the wing and the aircraft body, thereby achieving the effects of reducing the resistance of the aircraft and improving the movement speed of the aircraft; the invention can vertically go out and enter water like four rotors through two pairs of air propellers, thereby realizing the cross-region flying in sea and air; according to the invention, the balance torque is provided through the difference of the propellers during water outlet, so that the water outlet stability of the aircraft can be improved. In addition, functions of hovering in the air at fixed points and the like can be realized.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. The utility model provides a tailstock formula sea air is aircraft device of striding territory based on four rotor drive modes which characterized in that includes: the device comprises an aircraft body module, an aircraft tailstock module (5), an aircraft control module (9), a posture adjusting module and a thruster module;
the aircraft body module comprises: fuselage components, wing components;
the fuselage part is connected with the wing part in a smooth transition mode;
the aircraft tailstock module (5) can support the aircraft to take off and land vertically;
the wing component includes: a wing tail;
the aircraft tailstock module (5) is arranged at the tail of the wing;
the attitude adjusting module adjusts the attitude of the aircraft;
the thruster module comprises: the main air contra-rotating propeller part and the auxiliary air contra-rotating propeller part;
the main air contra-rotating paddle part and the auxiliary air contra-rotating paddle part can provide forward power for the aircraft when the aircraft sails in water and in the air;
the aircraft control module (9) is connected with the attitude adjusting module and the propeller module.
2. The quad-rotor-drive-based tailstock-type sea-air cross-domain aircraft device according to claim 1, further comprising: an aircraft steering module;
the number of the auxiliary air contrarotating propeller parts is 2;
the aircraft steering module can adjust 2 auxiliary air contra-rotating propeller parts to different rotating speeds when the aircraft steers.
3. The quad-rotor-drive-based tailstock-type sea-air cross-domain aircraft device according to claim 1, further comprising: an aircraft power module (4);
the aircraft power module (4) adopts a lithium lead battery.
4. The quad-rotor-drive-based tailstock-type sea-air cross-domain aircraft device according to claim 1, wherein the main air contra-rotating propeller part comprises: a main propeller part (1);
the number of the main propeller parts (1) is 2;
the main propeller part (1) comprises: a left main propeller component, a right main propeller component;
the wing component includes: a horizontal left wing component, a horizontal right wing component;
the horizontal left wing part and the horizontal right wing part are symmetrical about the aircraft body module;
the left main propeller part and the right main propeller part are symmetrically arranged on the horizontal left wing part and the horizontal right wing part.
5. The quad-rotor-drive-based tailstock-type sea-air cross-domain aircraft device according to claim 4, wherein the main air-to-rotor component further comprises: a main propeller motor (2) and a main propeller electric controller (3);
the main propeller motor (2) is connected with the main propeller part (1);
the main propeller electric controller (3) is connected with the main propeller motor (2);
the main propeller pitch (3) comprises: the left main propeller electric controller and the right main propeller electric controller;
the left main propeller electric regulator and the right main propeller electric regulator are symmetrically arranged on the horizontal left wing component and the horizontal right wing component.
6. The tailstock-type sea-air cross-domain aircraft device based on a four-rotor driving mode according to claim 1,
the secondary air counter-rotating paddle component comprises: a sub-propeller member (6);
the number of the auxiliary propeller parts (6) is 2;
the auxiliary propeller member (6) includes: an upper auxiliary propeller part and a lower auxiliary propeller part;
the wing component further comprises: a horizontal upper wing component, a horizontal lower wing component;
the horizontal upper wing part and the horizontal lower wing part are symmetrical about the aircraft body module;
the upper auxiliary propeller part and the lower auxiliary propeller part are symmetrically arranged on the horizontal upper wing part and the horizontal lower wing part.
7. The quad-rotor-drive-based tailstock-type air-sea cross-domain aircraft device according to claim 6, wherein the secondary air-to-rotor component further comprises: an auxiliary paddle motor (7) and an auxiliary paddle electric regulator (8);
the auxiliary propeller motor (7) is connected with the auxiliary propeller part (6);
the auxiliary paddle electricity regulator (8) is connected with an auxiliary paddle motor (7);
the auxiliary pitch (8) comprises: the upper auxiliary paddle electric regulator and the lower auxiliary paddle electric regulator;
the upper auxiliary propeller electric controller and the lower auxiliary propeller electric controller are symmetrically arranged on the horizontal upper wing part and the horizontal lower wing part.
8. The quad-rotor-drive-based tailstock-type air-sea cross-domain aircraft device according to claim 1, characterized in that the aircraft control module (9) is arranged inside a fuselage component.
9. The tailstock-type sea-air cross-domain aircraft device based on a four-rotor driving mode according to claim 1, is characterized in that an aircraft power module (4) is arranged inside a fuselage component;
the fuselage component comprises: an aircraft head;
the aircraft power module (4) is arranged at the head of the aircraft.
10. The utility model provides a tailstock formula sea air is aircraft device of striding territory based on four rotor drive modes which characterized in that includes: the device comprises an aircraft body module, an aircraft tailstock module (5), an aircraft control module (9), a posture adjusting module and a thruster module;
the aircraft body module comprises: fuselage components, wing components;
the fuselage part is connected with the wing part in a smooth transition mode;
the aircraft tailstock module (5) can support the aircraft to take off and land vertically;
the wing component includes: a wing tail;
the aircraft tailstock module (5) is arranged at the tail of the wing;
the attitude adjusting module adjusts the attitude of the aircraft;
the thruster module comprises: the main air contra-rotating propeller part and the auxiliary air contra-rotating propeller part;
the main air contra-rotating paddle part and the auxiliary air contra-rotating paddle part can provide forward power for the aircraft when the aircraft sails in water and in the air;
the aircraft control module (9) is connected with the attitude adjusting module and the propeller module;
further comprising: an aircraft steering module;
the number of the auxiliary air contrarotating propeller parts is 2;
the aircraft steering module can adjust 2 auxiliary air contra-rotating propeller components to different rotating speeds when the aircraft steers;
further comprising: an aircraft power module (4);
the aircraft power module (4) adopts a lithium lead battery;
the main air contra-rotating propeller part comprises: a main propeller part (1);
the number of the main propeller parts (1) is 2;
the main propeller part (1) comprises: a left main propeller component, a right main propeller component;
the wing component includes: a horizontal left wing component, a horizontal right wing component;
the horizontal left wing part and the horizontal right wing part are symmetrical about the aircraft body module;
the left main propeller part and the right main propeller part are symmetrically arranged on the horizontal left wing part and the horizontal right wing part;
the main air counter-rotating paddle part further comprises: a main propeller motor (2) and a main propeller electric controller (3);
the main propeller motor (2) is connected with the main propeller part (1);
the main propeller electric controller (3) is connected with the main propeller motor (2);
the main propeller pitch (3) comprises: the left main propeller electric controller and the right main propeller electric controller;
the left main propeller electric regulator and the right main propeller electric regulator are symmetrically arranged on the horizontal left wing part and the horizontal right wing part;
the secondary air counter-rotating paddle component comprises: a sub-propeller member (6);
the number of the auxiliary propeller parts (6) is 2;
the auxiliary propeller member (6) includes: an upper auxiliary propeller part and a lower auxiliary propeller part;
the wing component further comprises: a horizontal upper wing component, a horizontal lower wing component;
the horizontal upper wing part and the horizontal lower wing part are symmetrical about the aircraft body module;
the upper auxiliary propeller part and the lower auxiliary propeller part are symmetrically arranged on the horizontal upper wing part and the horizontal lower wing part;
the secondary air counter-rotating paddle component further comprises: an auxiliary paddle motor (7) and an auxiliary paddle electric regulator (8);
the auxiliary propeller motor (7) is connected with the auxiliary propeller part (6);
the auxiliary paddle electricity regulator (8) is connected with an auxiliary paddle motor (7);
the auxiliary pitch (8) comprises: the upper auxiliary paddle electric regulator and the lower auxiliary paddle electric regulator;
the upper auxiliary propeller electric controller and the lower auxiliary propeller electric controller are symmetrically arranged on the horizontal upper wing part and the horizontal lower wing part;
the aircraft control module (9) is arranged inside a fuselage component;
the aircraft power module (4) is arranged inside the fuselage component;
the fuselage component comprises: an aircraft head;
the aircraft power module (4) is arranged at the head of the aircraft.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911006438.XA CN110775262B (en) | 2019-10-22 | 2019-10-22 | Tailstock type sea-air cross-domain aircraft device based on four-rotor driving mode |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911006438.XA CN110775262B (en) | 2019-10-22 | 2019-10-22 | Tailstock type sea-air cross-domain aircraft device based on four-rotor driving mode |
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| CN110775262B CN110775262B (en) | 2022-11-18 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113580860A (en) * | 2021-08-10 | 2021-11-02 | 上海交通大学 | High-speed large-load combined propulsion type sea-air cross-domain flight detection platform |
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| CN110775262B (en) | 2022-11-18 |
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