阅读说明：本技术 一种减摇鳍水陆两栖飞机 (Amphibious aircraft with fin stabilizer ) 是由 武耀罡 尹文浩 刘晴 崔正阳 余昀锴 于 2021-10-08 设计创作，主要内容包括：本发明创造提供一种减摇鳍水陆两栖飞机,包括机身(1)和主机翼(2),还包括连接轴(3)和全动舵面(4),四个所述全动舵面(4)通过所述连接轴(3)安装于所述机身(1)底部的前后两侧；所述机身(1)两侧共安装有四个全动舵面(4),其中两个所述全动舵面(4)安装在所述机身(1)的前端部,另外两个所述全动舵面(4)安装在所述机身(1)的后端部。本发明创造的有益效果是：本发明将减摇鳍装置与传统机翼相结合,利用其减摇鳍装置在水面作业时可起到减摇效果,并有效提高航行速度；在飞行器巡航阶段,减摇鳍装置可以提高升力,利用飞行控制器一定程度控制飞行姿态,达到增升增稳效果,大大提升安全与实用性。(The invention provides an amphibious aircraft with fin stabilizer, which comprises an aircraft body (1), a main wing (2), a connecting shaft (3) and full-motion control surfaces (4), wherein the four full-motion control surfaces (4) are arranged on the front side and the rear side of the bottom of the aircraft body (1) through the connecting shaft (3); the novel airplane is characterized in that four full-motion control surfaces (4) are mounted on two sides of the airplane body (1), wherein two full-motion control surfaces (4) are mounted at the front end portion of the airplane body (1), and the other two full-motion control surfaces (4) are mounted at the rear end portion of the airplane body (1). The beneficial effects of the invention are as follows: the fin stabilizer device is combined with the traditional wing, and can play a role in stabilizing when the fin stabilizer device is used for operation on water, and effectively improve the navigation speed; in the cruising stage of the aircraft, the fin stabilizer device can improve the lift force, and the flight attitude is controlled to a certain degree by using the flight controller, so that the effects of increasing the lift and the stability are achieved, and the safety and the practicability are greatly improved.)

1. An amphibious aircraft with fin stabilizer comprises an aircraft body (1) and a main wing (2), and is characterized in that: the main wing (2) is installed at the top of the machine body (1) through a fixed support (5), and further comprises a connecting shaft (3) and full-motion control surfaces (4), wherein the four full-motion control surfaces (4) are installed at the front side and the rear side of the bottom of the machine body (1) through the connecting shaft (3);

the aircraft is characterized in that four full-motion control surfaces (4) are mounted on two sides of the aircraft body (1), wherein two full-motion control surfaces (4) are mounted at the front end part of the aircraft body (1), the other two full-motion control surfaces (4) are mounted at the rear end part of the aircraft body (1), and the full-motion control surfaces (4) mounted at the front end part are smaller than those mounted at the rear end part.

2. A fin stabilizer amphibious aircraft as claimed in claim 1, wherein: the fin shape of the full-motion control surface (4) positioned at the front end part of the machine body (1) is a parallelogram with an inner angle of 45 degrees; the fin shape of the full-motion control surface (4) positioned at the rear end part of the machine body (1) is rectangular.

3. A fin stabilizer amphibious aircraft as claimed in claim 1, wherein: the dihedral angle of the fully-movable control surface (4) at the front end part of the machine body (1) is 22 degrees, and the dihedral angle of the fully-movable control surface (4) at the rear end part of the machine body (1) is 33 degrees.

4. A fin stabilizer amphibious aircraft as claimed in claim 1, wherein: the area ratio of the fully-movable control surface (4) positioned at the front end part of the machine body (1) to the fully-movable control surface (4) positioned at the rear end part of the machine body (1) is 0.4.

5. A fin stabilizer amphibious aircraft as claimed in claim 1, wherein: the machine body (1) also comprises a rotating structure and a tilting steering engine placing table (10);

the rotating structure is located on the tilting steering engine placing table (10) inside the front side and the rear side of the machine body (1), the rotating structure is connected with the connecting shaft (3) and comprises a tilting steering engine (24) and a connecting piece (25), and the tilting steering engine (24) passes through the connecting piece (25) and the tail end of the connecting shaft (3) are connected.

6. A fin stabilizer amphibious aircraft as claimed in claim 1, wherein: fuselage (1) inside evenly is provided with a plurality of bulkheads (11), and is a plurality of the stay tube (6) has been alternate in bulkheads (11), fuselage (1) outside is covered completely by waterproof board (19), upset board (7) are installed to fuselage (1) upper portion front end, upset board (7) pass through hinge (12) with waterproof board (19) and are connected.

7. A fin stabilizer amphibious aircraft as claimed in claim 1, wherein: the main wing (2) comprises an aileron (20), a connecting rod (21), a brushless motor (22) and a waterproof steering engine (23); the front edge position of the main wing (2) is controlled to place one brushless motor (22), install respectively on main wing (2) lower part both sides waterproof steering wheel (23), install on aileron (20) connecting rod (21), connecting rod (21) with waterproof steering wheel (23) are connected.

8. A fin stabilizer amphibious aircraft as claimed in claim 1, wherein: a flight controller (15), a power module BEC (14) and an electronic speed regulator ESC (14) are arranged in the machine body (1), and a flight controller device placing table (9) is arranged at the middle section part in the machine body (1);

the flight controller (15) is divided into two systems, the two systems are respectively a PIXHAWK flight controller (17) and an F3 flight controller (16), the PIXHAWK flight controller (17) is suspended above a bottom plate of the airplane body (1) through a plurality of support columns (18), and a place for placing the F3 flight controller (17) is arranged between the support columns;

the PIXHAWK flight controller (17) and the F3 flight controller (16) are respectively connected with the electronic speed regulator ESC (14), the tilting steering engine (24), the waterproof steering engine (23) and the brushless motor (22), and the PIXHAWK flight controller (17) and the F3 flight controller (16) are electrically connected to the power supply module BEC (14) for supplying power.

9. A fin stabilizer amphibious aircraft according to claim 8, characterised in that: the flight controller system (15) is fixed on the flight controller device placing table (9), and an attitude sensor is arranged in the flight controller system.

10. A fin stabilizer amphibious aircraft according to claim 6, characterised in that: the lower part of the turnover plate (7) is provided with a battery placing table (8), and a power module BEC (14) is placed on the battery placing table (8) in the machine body (1).

Technical Field

The invention belongs to the field of unmanned aerial vehicles, and particularly relates to an amphibious aircraft with fin stabilizer.

Background

In recent years, the frequency of human marine activities has increased, and industries related to marine fishery, marine exploration, and the like have become more important. The amphibious aircraft can take off and land on land and also can take off and land on the water surface, has incomparable advantages of ships such as timeliness and high speed, and can play a unique role in tasks such as ocean rescue supply, escort patrol and the like.

However, the existing amphibious aircraft has the following disadvantages: 1. the existing traditional amphibious aircraft has insufficient stability during operation on the water surface and has strict requirements on the water surface environment, and particularly, the existing amphibious aircraft cannot provide stable rolling by itself during operation in severe environments such as large storms and the like, so that safety risks exist. 2. The conventional amphibious aircraft is generally in a conventional layout, has no high-lift stability-increasing structure, is relatively small in load capacity, is relatively heavy to operate and is low in working efficiency.

Disclosure of Invention

In view of the above, the invention aims to provide a fin stabilizer amphibious aircraft capable of taking off and landing vertically and solves the problems of harsh requirements on the operation environment, poor stability, small load capacity, heavy operation and low working efficiency in the prior art.

In order to achieve the purpose, the technical scheme of the invention is realized as follows:

the fin stabilizer amphibious aircraft comprises an aircraft body (1) and main wings (2), wherein the main wings (2) are installed at the top of the aircraft body (1) through fixed supports (5), the fin stabilizer amphibious aircraft further comprises connecting shafts (3) and full-motion control surfaces (4), and the four full-motion control surfaces (4) are installed at the front side and the rear side of the bottom of the aircraft body (1) through the connecting shafts (3);

the aircraft is characterized in that four full-motion control surfaces (4) are mounted on two sides of the aircraft body (1), wherein two full-motion control surfaces (4) are mounted at the front end part of the aircraft body (1), the other two full-motion control surfaces (4) are mounted at the rear end part of the aircraft body (1), and the full-motion control surfaces (4) mounted at the front end part are smaller than those mounted at the rear end part.

Furthermore, the fin shape of the full-motion control surface (4) positioned at the front end part of the machine body (1) is a parallelogram with an inner angle of 45 degrees; the fin shape of the full-motion control surface (4) positioned at the rear end part of the machine body (1) is rectangular.

Furthermore, the dihedral angle of the fully-movable control surface (4) positioned at the front end part of the machine body (1) is 22 degrees, and the dihedral angle of the fully-movable control surface (4) positioned at the rear end part of the machine body (1) is 33 degrees.

Furthermore, the area ratio of the fully-movable control surface (4) positioned at the front end part of the machine body (1) to the fully-movable control surface (4) positioned at the rear end part of the machine body (1) is 0.4.

Furthermore, the machine body (1) also comprises a rotating structure and a tilting steering engine placing table (10);

the rotating structure is located on the tilting steering engine placing table (10) inside the front side and the rear side of the machine body (1), the rotating structure is connected with the connecting shaft (3) and comprises a tilting steering engine (24) and a connecting piece (25), and the tilting steering engine (24) passes through the connecting piece (25) and the tail end of the connecting shaft (3) are connected.

Further, fuselage (1) is inside evenly to be provided with a plurality of bulkheads (11), and is a plurality of alternate in bulkheads (11) has stay tube (6), fuselage (1) outside is covered by waterproof board (19) completely, fuselage (1) upper portion front end is installed and is rolled over board (7), roll over board (7) pass through hinge (12) with waterproof board (19) and be connected.

Furthermore, the main wing (2) comprises an aileron (20), a connecting rod (21), a brushless motor (22) and a waterproof steering engine (23); the front edge position of the main wing (2) is controlled to place one brushless motor (22), install respectively on main wing (2) lower part both sides waterproof steering wheel (23), install on aileron (20) connecting rod (21), connecting rod (21) with waterproof steering wheel (23) are connected.

Furthermore, a flight controller (15), a power module BEC (14) and an electronic speed regulator ESC (14) are arranged in the machine body (1), and a flight controller device placing table (9) is arranged at the middle section part in the machine body (1);

the flight controller (15) is divided into two systems, the two systems are respectively a PIXHAWK flight controller (17) and an F3 flight controller (16), the PIXHAWK flight controller (17) is suspended above a bottom plate of the airplane body (1) through a plurality of support columns (18), and a place for placing the F3 flight controller (17) is arranged between the support columns;

the PIXHAWK flight controller (17) and the F3 flight controller (16) are respectively connected with the electronic speed regulator ESC (14), the tilting steering engine (24), the waterproof steering engine (23) and the brushless motor (22), and the PIXHAWK flight controller (17) and the F3 flight controller (16) are electrically connected to the power supply module BEC (14) for supplying power.

Further, a flight controller system (15) is fixed on the flight controller device placing table (9), and an attitude sensor is arranged in the flight controller system.

Furthermore, a battery placing table (8) is arranged at the lower part of the turnover plate (7), and a power module BEC (14) is placed on the battery placing table (8) in the machine body (1).

The invention has the advantages and positive effects that:

(1) the amphibious aircraft with the fin stabilizer can effectively reduce rolling on the water surface by using the fin stabilizer device, so that the adaptability to the water surface environment is greatly increased, and the safety risk is greatly reduced;

(2) according to the amphibious aircraft with the fin stabilizer, the fin stabilizer device is combined with the traditional wing, so that the lift force can be effectively improved, the flight attitude is controlled to a certain degree by using the flight controller, the effects of increasing lift and stability are achieved, and the safety and the practicability are greatly improved.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only the embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a schematic overall appearance of the present invention;

FIG. 2 is a schematic diagram of the overall structure of the present invention;

FIG. 3 is a structural diagram of a rotary structure and a part of a full-motion control surface in the invention;

fig. 4 is a front view of the invention.

FIG. 5 is a top view of the present invention;

FIG. 6 is a left side view of the external structure created by the present invention;

fig. 7 is a right side view of the internal structure created by the present invention.

In the figure:

1-a fuselage; 2-main wing; 3-connecting the shaft; 4-full-motion control surface; 5, fixing a support; 6-supporting the tube; 7-turning over the board; 8-a battery placement table; 9-a flight controller device mounting table; 10-a tilting steering engine placing table; 11-a bulkhead; 12-a hinge; 13-electronic governor ESC; 14-power module BEC; 15-a flight controller; 16-F3 flight controller; 17-PIXHAWK flight controller; 18-a pillar; 19-a waterproof board; 20-ailerons; 21-a connecting rod; 22-a brushless motor; 23-a waterproof steering engine; 24-a tilt steering engine; 25-connecting piece.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by persons skilled in the art based on the embodiments in the invention without any creative effort belong to the protection scope of the invention, and the embodiments in the invention and the features in the embodiments can be combined with each other without conflict.

In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, but the present invention may be embodied in other specific forms than described herein, and it will be apparent to those skilled in the art that the present invention may be practiced without departing from the spirit and scope of the invention.

In the following detailed description of the embodiments of the present invention, the cross-sectional views illustrating the structure of the device are not enlarged partially in general scale for convenience of illustration, and the schematic drawings are only examples, which should not limit the scope of the present invention. In addition, the three-dimensional dimensions of length, width and height should be included in the actual fabrication.

In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings, which are merely for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be construed as limiting the invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.

In the description of the invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted", "connected" and "connected" are to be construed broadly, e.g. as being fixed or detachable or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.

As shown in fig. 1 to 7, the invention comprises a fuselage (1) and a main wing (2), and is characterized in that: the main wing (2) is installed on the top of the machine body (1) through a fixed support (5), and further comprises a connecting shaft (3) and full-motion control surfaces (4), wherein the four full-motion control surfaces (4) are installed on the front side and the rear side of the bottom of the machine body (1) through the connecting shaft (3);

the novel airplane is characterized in that four full-motion control surfaces (4) are mounted on two sides of the airplane body (1), wherein two full-motion control surfaces (4) are mounted at the front end portion of the airplane body (1), and the other two full-motion control surfaces (4) are mounted at the rear end portion of the airplane body (1).

The fin shape of the full-motion control surface (4) positioned at the front end part of the machine body is a parallelogram with an internal angle of 45 degrees, and a down-turned angle of 22 degrees; the fin shape of the total-motion control surface (4) positioned at the rear end part of the machine body is rectangular, and the dihedral angle is 33 degrees. The area ratio of the fully-movable control surface (4) positioned at the front end part of the machine body to the fully-movable control surface (4) positioned at the rear end part of the machine body is 0.4.

Fuselage (1) inside even framework has a plurality of bulkheads (11), alternate among a plurality of bulkheads (11) and have stay tube (6), fuselage (1) outside is covered by waterproof board (19) completely, fuselage (1) upper portion front end is installed and is turned over board (7), it is connected through hinge (12) with waterproof board (19) to turn over board (7).

The machine body (1) also comprises a rotating structure and a tilting steering engine placing table (10);

the rotating structure is located on the tilting steering engine placing table (10) inside the front side and the rear side of the machine body (1), the rotating structure is connected with the connecting shaft (3) and comprises a tilting steering engine (24) and a connecting piece (25), and the tilting steering engine (24) passes through the connecting piece (25) and the tail end of the connecting shaft (3) are connected. The four full-motion control surfaces (4) positioned on the machine body are connected with the tilting steering engine (24) through a connecting shaft (3). The tilting steering engine (24) is connected with the machine body (1) through a tilting steering engine placing platform (10), and the tilting steering engine (24) can enable the connecting shaft (3) and the full-motion control surface (4) to rotate by 120 degrees at the maximum through a connecting piece (25). The tilting steering engine can carry out linear output of 120 degrees to the maximum extent according to an input signal of the flight controller;

the main wing (2) comprises an aileron (20), a connecting rod (21), a brushless motor (22) and a waterproof steering engine (23); a brushless motor (22) is respectively placed about the leading edge position of main wing (2), waterproof steering wheel (23) are installed respectively to main wing (2) lower part both sides, install connecting rod (21) on aileron (20), connecting rod (21) are connected with waterproof steering wheel (23).

A flight controller (15), a power module BEC (14) and an electronic speed regulator ESC (14) are arranged in the machine body (1), a flight controller device placing table (9) is arranged at the middle section part in the machine body (1),

the flight controller (15) is divided into two systems, the two systems are respectively a PIXHAWK flight controller (17) and an F3 flight controller (16), the PIXHAWK flight controller (17) is suspended above a bottom plate of the airplane body (1) through a plurality of support columns (18), and a place for placing the F3 flight controller (17) is arranged between the support columns.

Each flight controller (15) is respectively connected with the electronic speed regulator ESC (14), the tilting steering engine (24), the waterproof steering engine (23) and the brushless motor (22), and each flight controller (15) is electrically connected to the power module BEC (14) for supplying power.

The flight controller system (15) is fixed on the flight controller device placing table (9), and a posture sensor is arranged in the flight controller system, so that the posture of the airplane body can be acquired in real time.

The lower part of the turnover plate (7) is provided with a battery placing table (8), and the power module BEC (14) is placed on the battery placing table (8) in the machine body (1).

When the device is lifted and landed on the water surface, the F3 flight controller (16) controls the waterproof steering engine (23) arranged at the lower end of the main wing (2) to drive the ailerons (20) to rotate downwards by a certain angle.

When the device works on the water surface, the PIXHAWK flight controller (17) stops working, the attitude sensor transmits the acquired attitude information to the F3 flight controller (16), and the F3 flight controller (16) can calculate the rotating angle of the four full-motion control surfaces (4) and the rotating speed of the brushless motor (22) to be controlled for keeping the balance of the machine body according to the acquired attitude information. Similarly, when the device flies in the air, the F3 flight controller (16) stops working, the PIXHAWK flight controller (17) acquires attitude information in real time and sends out commands to control the rotation angle of the full-motion control surface (4) and the rotation speed of the brushless motor (22) in time.

The device is provided with six receiver channels: wherein, the power system which is arranged on the device and consists of a brushless motor (22) and an electronic governor ESC (13) occupies a receiver channel; the two-side main wing ailerons (20) controlled by the waterproof steering engine (23) occupy one receiver channel; four full-motion control surfaces (4) occupy four receiver channels. The six receiver channels are controlled by six channels of a remote controller or a flight controller.

When the device takes off and lands on the water surface, the brushless motor (22) on the main wing is used as main power to accelerate the aircraft, after the device starts to slide, the ailerons (20) are controlled to tilt downwards for a certain angle to increase the lift force of the aircraft and shorten the take-off distance of the aircraft, in the process, the F3 flight controller (16) starts to work, the attitude sensor arranged in the flight controller senses relevant information and parameters of the aircraft in real time, and the processor arranged in the F3 flight controller (16) controls the four full-motion control surfaces (4) to rotate in time to enable the aircraft to take off stably.

In the process of flying, the F3 flight controller (16) stops working, the PIXHAWK flight controller (17) starts working, and in the process, the PIXHAWK flight controller (17) acquires the airplane attitude information through a built-in attitude sensor and controls the ailerons (20) and the full-motion control surface (4) to enable the airplane to fly stably.

The fin stabilizer device is combined with the traditional wing, and can play a role in stabilizing when the fin stabilizer device is used for operation on water, and effectively improve the navigation speed; in the cruising stage of the aircraft, the fin stabilizer device can improve the lift force, and the flight attitude is controlled to a certain degree by using the flight controller, so that the effects of increasing the lift and the stability are achieved, and the safety and the practicability are greatly improved.

The embodiments of the present invention have been described in detail, but the description is only for the preferred embodiments of the present invention and should not be construed as limiting the scope of the present invention. All equivalent changes and modifications made within the scope of the invention shall fall within the scope of the patent coverage of the invention.