CN210479005U

CN210479005U - Aircraft with retractable wings

Info

Publication number: CN210479005U
Application number: CN201921430336.6U
Authority: CN
Inventors: 倪昌云
Original assignee: Wuxi Hongzhen Aviation Technology Co Ltd
Current assignee: Wuxi Hongzhen Aviation Technology Co Ltd
Priority date: 2019-08-30
Filing date: 2019-08-30
Publication date: 2020-05-08
Anticipated expiration: 2029-08-30

Abstract

The utility model discloses a wing-contained aircraft, which comprises a main body, wherein the tail part of the main body is provided with an aileron and is connected with a propeller; two sides of the main body are respectively connected with wings, the wings are provided with a first hinge point and a second hinge point, the wings are hinged with the main body through the first hinge point, the second hinge point of the wings is hinged with the tail end of a main lever, and the head end of the main lever is hinged with a main sliding block; the main sliding block slides along the length direction of the main body and drives the wings to swing around the first hinge point through the main lever. A type aircraft can be accomodate to wing, the main engine body both sides wing can be swung, area occupied when can reducing the aircraft and idle.

Description

Aircraft with retractable wings

Technical Field

The utility model relates to an aircraft especially relates to a wing type aircraft of accomodating.

Background

An aircraft is an aircraft that can fly controllably in the atmosphere. Any aircraft must generate lift greater than its own weight in order to fly. The types of aircrafts are various, and the common aircrafts mainly comprise balloons, airships, airplanes, gliders, gyroplanes, helicopters and the like. The lift of an aircraft is based on the bernoulli principle: the greater the flow rate, the lower the pressure; the smaller the flow rate, the greater the pressure. The wing of the airplane is shaped so that the flow velocity below the wing is lower than the flow velocity above the wing, thereby generating the pressure difference between the upper part and the lower part of the wing and further obtaining the lift force. Thus, the wings on both sides of the aircraft are the main components providing lift. However, the aircraft with the wing-shaped like airplane needs to occupy more space when being parked on the ground or stored in a warehouse.

Disclosure of Invention

The purpose of the invention is as follows: in order to overcome the not enough of existence among the prior art, the utility model provides a wing can accomodate type aircraft to reduce the space that the aircraft occupy when parking.

The technical scheme is as follows: in order to achieve the above object, the present invention provides a wing stowable aircraft, comprising a main fuselage and a drive device; the two sides of the main body are respectively connected with wings, the wings are provided with a first hinge point and a second hinge point, the wings are hinged with the main body through the first hinge point, the driving device is connected to the main body, the two sides of the driving device are hinged with the second hinge point, and the wings rotate around the first hinge point under the driving of the driving device.

Further, the driving device comprises a main lever and a main slider; the tail end of the main lever is hinged with a second hinge point of the wing, and the head end of the main lever is hinged with the main sliding block; the main sliding block slides along the length direction of the main body and drives the wings to rotate around the first hinge point through the main lever.

Furthermore, the driving device also comprises an auxiliary lever, the tail end of the auxiliary lever is hinged between the head end of the main lever and the tail end of the main lever, the head end of the auxiliary lever is hinged with an auxiliary sliding block, and the auxiliary sliding block slides along the sliding direction of the main sliding block.

Further, still include the master cylinder, the master cylinder stiff end is connected on fixing the girder on the main fuselage, the flexible end and the main sliding block of master cylinder are connected.

Further, be provided with main spout on the girder, main slider sliding connection is in main spout.

Further, drive arrangement still includes vice hydro-cylinder, vice hydro-cylinder stiff end is connected on fixing the girder on the main fuselage, the flexible end and the vice slider of vice hydro-cylinder are connected.

Furthermore, an auxiliary sliding groove is formed in the main beam, and the auxiliary sliding block is connected to the auxiliary sliding groove in a sliding mode.

Furthermore, a plurality of auxiliary connecting plates are arranged at intervals at the tail end of the auxiliary lever along the vertical direction, and the auxiliary connecting plates are provided with auxiliary connecting holes; a plurality of convex main connecting plates are arranged between the head end and the tail end of the main lever at intervals along the vertical direction, and the main connecting plates are provided with main connecting holes; the main connecting plates and the auxiliary connecting plates are sequentially overlapped with each other, and the main connecting holes are coaxially opposite to the auxiliary connecting holes.

Further, an arc-shaped auxiliary body is arranged above the front part of the main body, the head end of the auxiliary body and the main body are integrally formed, and the tail end of the auxiliary body extends backwards and is opposite to the main body up and down.

The utility model has the advantages as follows: a wing stowable aircraft, the wings on both sides can be retracted: the telescopic end of the main oil cylinder extends, the telescopic end of the auxiliary oil cylinder is reduced, the main lever drives the wings to rotate around the first hinge point, the tail ends of the wings are close to the ailerons, the wings are stored, and the occupied area for parking the aircraft is reduced; the main oil cylinder is shortened, the auxiliary oil cylinder is extended, and the main lever drives the wings to rotate towards two sides and extend without affecting the normal use of the aircraft.

Drawings

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

fig. 2 is a schematic structural diagram of the connection of the main lever, the auxiliary lever, the main slider, the auxiliary slider, the main oil cylinder and the auxiliary oil cylinder;

fig. 3 is a schematic diagram of the connection between the main lever and the auxiliary lever according to the present invention.

Detailed Description

The present invention will be further described with reference to the accompanying drawings.

A wing stowable aircraft as described in figures 1 to 3, comprising a main fuselage 1 and a drive arrangement comprising two main levers 6, two auxiliary levers 8, a main slider 7, an auxiliary slider 9, a main cylinder 10 and an auxiliary cylinder 11.

The tail part of the main body 1 is provided with an aileron 2 and is connected with a propeller 18; the number of the ailerons 2 is 3, the ailerons 2 are respectively connected to the two sides and the upper part of the tail part of the main body 1, the three ailerons 2 are distributed in a triangular shape, and the propeller 18 is a three-wing propeller with the axis horizontally arranged. The both sides of main fuselage 1 are connected with wing 3 respectively, the head end of wing 3 is articulated with main fuselage 1, the tail end of wing 3 swings backward and is close to aileron 2, accomplishes accomodating of wing to area when reducing parking of aircraft. The wings 3 should be provided with a take-off and landing plate 17. The bottom of the main body 1 is provided with a lifting frame 19.

In particular, one end of the wing 3 is provided with two distinct hinge points, respectively a first hinge point 4 and a second hinge point 5. The first hinge point 4 is hinged with the main body 1, the second hinge point 5 is hinged with the tail end of the main lever 6, and the head end of the main lever 6 is hinged with the main sliding block 7; the main sliding block 7 slides along the length direction of the main body 1, and drives the wing 3 to swing around the first hinge point 4 through the main lever 6. The main slider 7 is connected with the telescopic end of the main oil cylinder 10, and the fixed end of the main oil cylinder 10 is fixedly connected to the main beam of the main body 1. In order to effectively control the motion track of the main slider 7 and reduce the shaking of the main lever 6, a main sliding groove is arranged on the main beam 1 along the length direction of the main body, so that the main slider 7 slides along the main sliding groove. And the other end of the auxiliary lever 8 is hinged with an auxiliary sliding block 9. The auxiliary sliding block 9 also slides along the length direction of the main body 1, and the sliding track of the main sliding block and the sliding track of the auxiliary sliding block 9 are the same straight line. The auxiliary sliding block 9 is connected to the telescopic end of the auxiliary oil cylinder 11, and the fixed end of the auxiliary oil cylinder 11 is connected to the main beam. Similarly, in order to ensure the sliding track of the auxiliary slider 9 and reduce the swing of the auxiliary lever, an auxiliary sliding groove is also arranged on the main beam, so that the auxiliary slider 9 slides along the auxiliary sliding groove.

A plurality of auxiliary connecting plates 12 are arranged at the tail end of the auxiliary lever 8 at intervals along the vertical direction, and auxiliary connecting holes 13 are formed in the auxiliary connecting plates 12; a plurality of convex main connecting plates 14 are arranged between the head end and the tail end of the main lever 6 at intervals along the vertical direction, and the main connecting plates 14 are provided with main connecting holes 15; the main connecting plates 14 and the auxiliary connecting plates 12 are sequentially and mutually overlapped, and the main connecting holes 15 are coaxially opposite to the auxiliary connecting holes 13.

An arc-shaped auxiliary body 16 is arranged above the front part of the main body 1, the head end of the auxiliary body 16 and the main body 1 are integrally formed, and the tail end of the auxiliary body 16 extends backwards and is opposite to the main body 1 up and down.

The specific storage method of wing do: when the aircraft needs to be stored, the main oil cylinder extends, the auxiliary oil cylinder shortens, the main lever rotates along a hinge point with the main sliding block, and meanwhile, the wing is driven to rotate around the first hinge point, so that the tail end of the wing is close to the auxiliary wing until the storage is finished; when the aircraft needs to take off, the main oil cylinder is shortened, the auxiliary oil cylinder grows, the main lever rotates along a hinge point with the main sliding block, the wing is driven to rotate around the first hinge point, and the tail end of the wing is far away from the auxiliary wing until the extension is completed.

The above description is only a preferred embodiment of the present invention, and it should be noted that: for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can be made, and these improvements and modifications should also be considered as the protection scope of the present invention.

Claims

1. The utility model provides a wing type aircraft that can accomodate which characterized in that: comprises a main body (1) and a driving device; the both sides of main fuselage (1) are connected with wing (3) respectively, wing (3) have first pin joint (4) and second pin joint (5), wing (3) are articulated through first pin joint (4) and main fuselage (1), drive arrangement connects on main fuselage (1), drive arrangement's both sides are articulated with second pin joint (5), wing (3) rotate around first pin joint (4) under drive arrangement's drive.

2. The wing stowable aircraft according to claim 1, wherein: the driving device comprises a main lever (6) and a main sliding block (7); the tail end of the main lever (6) is hinged with a second hinge point (5) of the wing (3), and the head end of the main lever (6) is hinged with a main sliding block (7); the main sliding block (7) slides along the length direction of the main body (1) and drives the wing (3) to rotate around the first hinge point (4) through the main lever (6).

3. The wing stowable aircraft according to claim 2, wherein: the driving device further comprises an auxiliary lever (8), the tail end of the auxiliary lever (8) is hinged between the head end of the main lever (6) and the tail end of the main lever (6), the head end of the auxiliary lever (8) is hinged with an auxiliary sliding block (9), and the auxiliary sliding block (9) slides along the sliding direction of the main sliding block (7).

4. The wing stowable aircraft according to claim 2, wherein: still include master cylinder (10), master cylinder (10) stiff end is connected on fixing the girder on main fuselage (1), the flexible end and the owner's slider (7) of master cylinder (10) are connected.

5. The wing stowable aircraft according to claim 4, wherein: the main beam is provided with a main sliding groove, and the main sliding block (7) is connected to the main sliding groove in a sliding mode.

6. The wing stowable aircraft according to claim 3, wherein: the driving device further comprises an auxiliary oil cylinder (11), the fixed end of the auxiliary oil cylinder (11) is connected to a main beam fixed on the main body (1), and the telescopic end of the auxiliary oil cylinder (11) is connected with the auxiliary sliding block (9).

7. The wing stowable aircraft according to claim 6, wherein: the main beam is provided with an auxiliary sliding groove, and the auxiliary sliding block (9) is connected in the auxiliary sliding groove in a sliding mode.

8. The wing stowable aircraft according to claim 3, wherein: a plurality of auxiliary connecting plates (12) are arranged at the tail end of the auxiliary lever (8) at intervals along the vertical direction, and auxiliary connecting holes (13) are formed in the auxiliary connecting plates (12); a plurality of convex main connecting plates (14) are arranged between the head end and the tail end of the main lever (6) at intervals along the vertical direction, and the main connecting plates (14) are provided with main connecting holes (15); a plurality of main connecting plates (14) and a plurality of auxiliary connecting plates (12) are mutually overlapped in sequence, and the main connecting holes (15) are coaxially opposite to the auxiliary connecting holes (13).

9. The wing stowable aircraft according to claim 1, wherein: the upper portion of the front portion of the main machine body (1) is provided with an arc-shaped auxiliary machine body (16), the head end of the auxiliary machine body (16) and the main machine body (1) are integrally formed, and the tail end of the auxiliary machine body (16) extends backwards and is opposite to the main machine body (1) from top to bottom.