CN214296446U

CN214296446U - Novel variant aircraft

Info

Publication number: CN214296446U
Application number: CN202023146473.2U
Authority: CN
Inventors: 蒋维安; 纪鑫东
Original assignee: Civil Aviation Flight University of China
Current assignee: Civil Aviation Flight University of China
Priority date: 2020-12-23
Filing date: 2020-12-23
Publication date: 2021-09-28
Anticipated expiration: 2030-12-23

Abstract

The utility model discloses a novel variant aircraft belongs to aircraft technical field, including the fuselage frame, the fuselage frame attach has two at least drive assembly, every drive assembly has the support arm through first pivot swing joint, drive assembly is used for driving the support arm rotatory, every fixedly connected with driving motor on the support arm, the last rotor that is connected with of driving motor. The supporting arm 4 can be rotated above the frame of the machine body by arranging the driving assembly so as to reduce the size of the whole machine, prevent the rotor wing from being damaged by collision, and facilitate flying in a narrow space and carrying and transportation; when the aircraft flies in an open space, the aerodynamic interference among the rotors and between the rotors and the aircraft body is reduced through the variants, the resistance is reduced, the speed is improved, the electric energy is saved, and the attitude control precision and the response speed are improved. The frame of the machine body can be in any shape such as polygon, rectangle, rhombus, circle or ellipse, triangle, straight line and the like.

Description

Novel variant aircraft

Technical Field

The utility model belongs to the technical field of the aircraft, concretely relates to novel variant aircraft.

Background

The multi-rotor aircraft is a special aircraft with two or more rotor shafts, and the rotor shafts are rotated by rotor motors on each shaft to drive rotors so as to generate lift force. With the continuous development of science and technology, the simple and easy-to-use characteristics of the multi-rotor aircraft enable the multi-rotor aircraft to be applied to more and more fields. However, the support arms of existing rotorcraft are generally fixed to the fuselage during flight, and if the distance between the centers of the rotors of the aircraft is small, the flexibility of the aircraft increases and the stability decreases, so that the aircraft is generally relatively large in size. This makes it difficult for these aircraft to pass through complex environments where space is small or of varying sizes (e.g., delivering couriers to designated household balconies or rooms within a residential neighborhood); at the same time, because the size cannot be adjusted during the flight, it is difficult to adjust the optimal configuration with space or environment (such as high risk areas with dense buildings or trees) or weight (such as after loading and unloading); in addition, the parking device occupies a large space and is inconvenient to park or limited in carrying quantity.

Disclosure of Invention

The utility model aims at providing a novel variant aircraft, which solves the problems that the size can not be adjusted in the flying process in the prior art, and the optimal configuration is difficult to be adjusted along with the space, the environment or the weight; in addition, the parking device occupies a large space and is inconvenient to park or has a limited carrying quantity.

The utility model provides a novel variant aircraft, including the fuselage frame, the fuselage frame attach has two at least drive assembly, every drive assembly has the support arm through first pivot swing joint, drive assembly is used for driving the support arm rotatory, every fixedly connected with driving motor on the support arm, the last rotor that is connected with of driving motor.

The working principle is as follows: when the position of the rotor wing needs to be adjusted or the size of the aircraft needs to be changed, the driving assembly is opened and drives the supporting arm to rotate, the supporting arm rotates to drive the rotor wing to move to the needed position, then the driving motor is started, and the driving motor drives the rotor wing to rotate to fly. The support arm can be rotated in the air while remaining stable during flight of the aircraft. The driving assembly 2 can rotate clockwise 360 degrees or counterclockwise 360 degrees after receiving the current. Through setting up drive assembly, can drive the support arm and carry out the rotation of 360 interior arbitrary angles, can rotate the support arm to the fuselage frame top as required with this width that reduces the complete machine, be convenient for fly in narrow and small space, and avoid the rotor to be damaged by the collision, conveniently carry and transport when not using, through the variant when open space flight, reduce the aerodynamic disturbance between each rotor, reduce the aerodynamic disturbance between knob air current and the organism, not only reduce the resistance that the rotor air current produced and the resistance that the organism received and then improve the airspeed and practice thrift the electric energy, and improved attitude control precision and response speed, more stable, fast, energy-conservation.

Further, the driving assembly is a driving assembly with speed reduction and self-locking capacity. Such as worm gear reducer, large gear ratio reducer, angular displacement servo system, etc.

Through setting up drive assembly for taking the speed reduction and have the auto-lock drive assembly of auto-lock ability, can slow down the rotatory speed of support arm, the accurate regulation of the support arm position of being convenient for to utilize the auto-lock characteristic that has, guarantee that its support arm of aircraft after the variant reconsitution can remain stable.

Furthermore, the number of the driving assemblies is even, and the driving assemblies are arranged oppositely.

By setting the number of the driving assemblies to be even and enabling the driving assemblies to be oppositely arranged, the two opposite driving assemblies can work simultaneously to change the position of the supporting arm, interference torque is reduced, and hovering or flying stability in the air is kept.

Furthermore, the number of the driving assemblies is four, and the four driving assemblies are oppositely arranged on the machine body frame.

Through setting up four drive assembly, can make two relative drive assembly work simultaneously and change the position of support arm, two drive assembly can not work in addition, keep the aircraft stable hovering in the air, can change the size of this aircraft through rotatory support arm according to the size of the space that needs pass through to guarantee its trafficability characteristic under various space conditions. For example, objects such as express delivery can be delivered to a balcony or platform or indoor space with a smaller size; in another example, necessary equipment may be carried to shuttle searches in a forest or inside a building.

Further, the fuselage frame is fixedly connected with at least two fixed arms, and every be connected with respectively on the fixed arm driving motor, driving motor is connected with the rotor.

Through setting up two at least fixed arms, can keep the suspension state when the aircraft flies, then start drive assembly, rotate the support arm, accomplish the reconsitution of aircraft in the air.

Further, the machine body frame is of a hollow structure.

Through setting up the fuselage frame into hollow out construction, can lighten weight, reduce the lift loss, improve the flight ability of aircraft.

Furthermore, the machine body frame is a movable frame, a lifting body is arranged at the center part of the machine body frame through a second rotating shaft, and the gravity center of the lifting body is arranged at a position lower than the axis of the second rotating shaft.

The fuselage frame is movably arranged, so that the fuselage frame can follow the flying airflow direction to reduce the resistance and lift loss.

The utility model has the advantages that:

1. the driving component is arranged, so that the supporting arm can be driven to rotate by 360 degrees, and the supporting arm can be rotated above the frame of the machine body, so that the width of the whole machine is reduced, and the carrying and the transportation are convenient;

2. the driving assembly is a self-locking driving assembly with speed reduction, so that the rotation speed of the supporting arm can be reduced, the accurate adjustment of the position of the supporting arm is facilitated, and the reconstructed supporting arm can be kept stable by utilizing the self-locking characteristic of the supporting arm;

3. the frame of the aircraft body is of a hollow structure, so that the weight can be reduced, and the flight capacity of the aircraft can be improved;

4. by arranging at least two fixed arms, the aircraft can keep a suspension state during flying, then a driving assembly is started to rotate the supporting arms, and the reconstruction of the aircraft in the air is completed;

5. through setting up four drive assembly, can make two relative drive assembly work simultaneously and change the position of support arm, two drive assembly are out of work in addition, keep hovering in the sky stably, can change the size of this aircraft through rotatory support arm according to the size of the space that needs pass through to guarantee its trafficability characteristic under various space conditions, guarantee high stability, rapidity, the energy-conservation nature in open space.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is a schematic view of the aircraft of the present invention;

FIG. 2 is a schematic view of an aircraft according to another embodiment of the present invention;

FIG. 3 is a schematic view of an aircraft according to another embodiment of the present invention;

fig. 4 is a schematic view of a flight state of an aircraft according to another embodiment of the present invention.

In the figure: 1-a fuselage frame, 2-a driving component, 3-a first rotating shaft, 4-a supporting arm, 5-a driving motor, 6-a rotor wing, 7-a second rotating shaft and 8-a lifting body.

Detailed Description

To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the drawings of the embodiments of the present invention are combined to clearly and completely describe the technical solutions of the embodiments of the present invention, and obviously, the described embodiments are some embodiments of the present invention, not all embodiments. The components of the embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work all belong to the protection scope of the present invention.

In the present invention, the embodiments and the features of the embodiments may be combined with each other without conflict.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", and the like indicate the directions or positional relationships based on the directions or positional relationships shown in the drawings, or the directions or positional relationships that the products of the present invention are usually placed when used, or the directions or positional relationships that the persons skilled in the art usually understand, and are only for the convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements to be referred to must have specific directions, be constructed and operated in specific directions, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be mechanically coupled, directly coupled, indirectly coupled through intervening media, or may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Example 1

The embodiment of the utility model provides a novel variant aircraft, concrete structure is as shown in fig. 1, including fuselage frame 1, fuselage frame 1 is connected with 4 drive assembly 2, and every drive assembly 2 has support arm 4 through 3 swing joint of first pivot, and drive assembly 2 is used for driving support arm 4 rotatory, and fixedly connected with driving motor 5 is gone up to every support arm 4, is connected with rotor 6 on the driving motor 5.

The working principle is as follows: when 6 positions of rotor wing need to be adjusted or the aircraft size is changed, drive assembly 2 is opened, drive assembly 2 drives support arm 4 and rotates, and support arm 4 is rotatory to be driven rotor wing 6 and is removed the position that needs, then starts driving motor 5, and driving motor 5 drives rotor wing 6 and rotates and fly. During the flight of the aircraft, the support arm 4 can be rotated in the air while remaining stable. The driving assembly 2 can rotate clockwise or counterclockwise when receiving the current. Through setting up drive assembly 2, can drive support arm 4 and carry out 360 rotations, can rotate support arm 4 to the width that reduces the complete machine with this above fuselage frame 1, be convenient for fly in narrow and small space to avoid rotor 6 to be damaged by the collision, conveniently carry and transport when not using.

Example 2

As a preferred embodiment of the present invention, the specific structure of the present invention is shown in fig. 1, and the following improvement is disclosed on the basis of embodiment 1, in which the driving assembly 2 is a driving assembly with self-locking capability.

Through setting up drive assembly 2 for the drive assembly who has the auto-lock ability that takes the speed reduction, can slow down the speed that support arm 4 is rotatory, the accurate regulation of the support arm 4 position of being convenient for to owing to have the auto-lock characteristic, support arm 4 after guaranteeing the reconsitution can remain stable.

Example 3

As a preferred embodiment of the present invention, the present invention discloses the following improvement on the basis of embodiment 1, wherein the number of the driving assemblies 2 is 6, and the driving assemblies 2 are arranged oppositely.

By arranging the driving assemblies 2 to be 6 and arranging the driving assemblies 2 oppositely, the two opposite driving assemblies 2 can work simultaneously to change the position of the supporting arm 4, reduce interference moment and keep stable hovering or flying in the air.

Example 4

In this embodiment, as a preferred embodiment of the present invention, the specific structure is as shown in fig. 1 or fig. 2, and the following improvement is disclosed on the basis of embodiment 1, in which the body frame 1 is a hollow structure.

Through setting up fuselage frame 1 to hollow out construction, can guarantee to lighten weight, reduce the lift loss under the prerequisite of fuselage frame intensity and rigidity requirement to improve aircraft's flight ability.

Example 5

As a preferred embodiment of the present invention, the specific structure is as shown in fig. 3 and fig. 4, which discloses the following improvement on the basis of embodiment 1, the body frame 1 is a partial movable structure, the central portion of the body frame 1 is provided with the lifting body 8 through the second rotating shaft 7, the lifting body 8 is a disc structure, and the center of gravity of the lifting body 8 is disposed at a position lower than the axis of the second rotating shaft 7.

Through the focus setting with the body of lift 8 being less than the axis of second pivot 7 for body of lift 8 is automatic around second pivot 7 deflection under gravity moment and aerodynamic moment combined action fuselage frame central part's body of lift 8 when flying before, thereby the area of upwind when flying before reducing reduces flight resistance, can also come the weight reduction through producing certain ascending lift, thereby the power consumption of the moment of resistance and the motor of reduction rotor.

The present invention is not limited to the above-mentioned optional embodiments, and any other products in various forms can be obtained by anyone under the teaching of the present invention, and any changes in the shape or structure thereof, all the technical solutions falling within the scope of the present invention, are within the protection scope of the present invention.

Claims

1. The utility model provides a novel variant aircraft, includes fuselage frame (1), its characterized in that, fuselage frame connected has drive assembly (2), every drive assembly has support arm (4) through first pivot (3) swing joint, drive assembly is used for driving support arm (4) rotatory, every fixedly connected with driving motor (5) on support arm (4), the last rotor (6) that is connected with of driving motor.

2. The new type of morphing aircraft of claim 1, characterized in that the drive assembly (2) is a drive assembly with deceleration and with self-locking capability.

3. The new morphing aircraft of claim 1 or 2, wherein the number of drive assemblies (2) is even and the drive assemblies (2) are arranged opposite each other.

4. A new morphing aircraft according to claim 3, characterized in that the number of drive assemblies (2) is four.

5. The new type of morphing aircraft according to claim 4, characterized in that at least two fixed arms are fixedly connected to the fuselage frame (1), each fixed arm is connected to the drive motor (5), the drive motor (5) is connected to the rotor (6).

6. A new morphing aircraft according to claim 1, characterized in that the fuselage frame (1) is of hollow construction.

7. The new type of morphing aircraft according to claim 1, characterized in that the fuselage frame (1) is a movable frame, the central part of the fuselage frame (1) is installed with a lifting body (8) through a second rotating shaft (7), the gravity center of the lifting body (8) is set at a position lower than the axis of the second rotating shaft (7).