阅读说明：本技术 一种具有可折叠伸缩式固定机翼的旋翼飞机 (Rotorcraft with foldable telescopic fixed wings ) 是由 史智勇 于 2020-08-12 设计创作，主要内容包括：本发明公开了一种具有可折叠伸缩式固定机翼的旋翼飞机,主要解决了现有技术旋翼飞机飞行速度较低,升力较小,载重量较小问题,包括旋翼飞机本体、若干对机翼、用于使所述机翼垂直或水平摆放的第一关节电机以及用于使所述机翼沿水平轴向转动的第二关节电机,所述机翼与飞机本体之间通过第一关节电机和第二关节电机连接。本发明所述旋翼飞机结构简单,制造难度低,能让旋翼飞机获得额外的垂直升力,提高了旋翼式飞机的载重量,通过增大飞机旋翼与水平方向的倾角,获得更大的前进推力,有效提高了飞行速度。(The invention discloses a rotorcraft with foldable telescopic fixed wings, which mainly solves the problems of low flying speed, low lifting force and low load capacity of the rotorcraft in the prior art. The rotary wing aircraft provided by the invention has the advantages that the structure is simple, the manufacturing difficulty is low, the rotary wing aircraft can obtain extra vertical lift force, the load capacity of the rotary wing aircraft is improved, larger forward thrust is obtained by increasing the inclination angle of the aircraft rotor wing and the horizontal direction, and the flying speed is effectively improved.)

1. The utility model provides a gyroplane with collapsible telescopic fixed wing, includes the gyroplane body, characterized by, include a plurality of pairs of wings, be used for making the first joint motor that the wing was put perpendicularly or level and be used for making the wing is along horizontal axial pivoted second joint motor, connect through first joint motor and second joint motor between wing and the aircraft body.

2. A rotorcraft having collapsible, telescoping fixed wings as claimed in claim 1, wherein the wings include a telescoping mechanism and a wing housing, the telescoping mechanism being disposed within the wing housing.

3. A rotorcraft having collapsible, retractable fixed wings as claimed in claim 2, wherein the wing shells are assembled from a plurality of outer skins of the same cross-sectional shape and sequentially reduced size.

4. A rotorcraft having collapsible fixed wings as claimed in claim 2, wherein said telescoping mechanism is formed by a combination of a plurality of hydraulic cylinders that are nested one within the other.

5. A rotorcraft having collapsible, retractable fixed wings, as claimed in claim 3 or claim 4, wherein the outer skins are correspondingly provided with a hydraulic cylinder to enable each wing to be retracted except near the body of the aircraft.

6. A rotorcraft having collapsible, retractable fixed wings as claimed in claim 3, wherein the wings are symmetrically disposed on either side of the aircraft body or on the lower part of the aircraft body.

7. A rotorcraft having collapsible, telescoping fixed wings as claimed in claim 6, wherein the wings are flat and convex in cross-section.

Technical Field

The invention relates to the field of airplanes, in particular to a rotary wing airplane with foldable telescopic fixed wings.

Background

The existing rotor aircraft can directly take off and land without runways, has lower requirements on a shutdown warehouse and an airport, and is convenient to use. However, in order to maintain vertical lift force during flight, the existing rotorcraft only needs to reduce horizontal thrust force, so that the defects of low flight speed, low lift force, low load capacity and the like are caused.

Disclosure of Invention

The invention mainly solves the problems of low flying speed, low lifting force and low load capacity of the rotorcraft in the prior art, and provides the rotorcraft with the foldable telescopic fixed wings.

The technical problem of the invention is mainly solved by the following technical scheme: the utility model provides a gyroplane with collapsible telescopic fixed wing, includes gyroplane body, a plurality of to the wing, is used for making the first joint motor that the wing was put perpendicularly or level and be used for making the wing is along horizontal axial pivoted second joint motor, connect through first joint motor and second joint motor between wing and the aircraft body.

The invention relates to a rotor-wing aircraft with foldable telescopic fixed wings, wherein the wings are in a contracted state and are vertically arranged when the rotor-wing aircraft is in a vertical lifting and stopping state. When the rotor plane flies flatly, the wings are extended through the telescopic mechanism, the wings are placed in a horizontal state through the first joint motor, and the wings rotate around the horizontal axial direction through the second joint motor, so that the flying actions such as climbing, steering, decelerating and the like are realized. The wings are extended when in a flat flying state, so that the aircraft can obtain vertical lift force additionally, the load capacity of the rotor type aircraft is improved, the inclination angle between the rotor wing of the aircraft and the horizontal direction is increased through axial rotation, larger forward thrust can be obtained, and the flying speed is improved.

As a preferred scheme, the wing comprises a telescopic mechanism and a wing shell, and the telescopic mechanism is arranged in the wing shell.

As a preferable scheme, the wing shell is formed by combining a plurality of outer skins which have the same cross section shape and sequentially reduced sizes.

As a preferred scheme, the telescopic mechanism is formed by combining a plurality of hydraulic cylinders which are sequentially nested in size.

As a preferable scheme, the outer skin is correspondingly provided with a hydraulic cylinder, so that the outer skin of each wing except the outer skin close to the airplane body can stretch, the stretching of the outer skin is driven by the stretching of the hydraulic cylinder, and the stretching of the wing is realized.

Preferably, the wings are symmetrically arranged on two sides of the airplane body or on the lower portion of the airplane body, and balance and stability are achieved.

As a preferable scheme, the cross section of the wing is flat at the bottom and convex at the top, so that a larger lifting force can be obtained in the flying process of the airplane.

Therefore, the invention has the advantages that: simple structure and low manufacturing difficulty. The rotary wing aircraft can obtain extra vertical lift force, the load capacity of the rotary wing aircraft is improved, larger forward thrust is obtained by increasing the inclination angle between the rotary wing of the aircraft and the horizontal direction, and the flying speed is effectively improved.

Drawings

FIG. 1 is a state diagram of the aircraft during takeoff and landing according to the present invention;

FIG. 2 is a state diagram of the aircraft of the present invention in flight;

fig. 3 is a schematic view of the internal structure of the present invention.

1-a rotorcraft body 2-wings 3-a first joint motor 4-a second joint motor 5-a hydraulic cylinder 6-an outer skin.

Detailed Description

The technical scheme of the invention is further specifically described by the following embodiments and the accompanying drawings.