CN212047873U

CN212047873U - Flying wing type rotary wing aircraft

Info

Publication number: CN212047873U
Application number: CN201920592547.3U
Authority: CN
Inventors: 殷春平; 廖峻锋; 李涛; 鄢昕烨
Original assignee: Xiamen University
Current assignee: Xiamen University
Priority date: 2019-04-28
Filing date: 2019-04-28
Publication date: 2020-12-01
Anticipated expiration: 2029-04-28

Abstract

The utility model discloses a flying wing formula rotary wing machine, rotary wing machine has fuselage and wing, and the wing setting is in the both sides of fuselage, and the wing is provided with the screw, is provided with the undercarriage on the fuselage, and the main shaft passes the fuselage, installs the bearing at the both ends of main shaft and is connected with both sides wing, and the wing passes through the wing rotation and can wind the main shaft rotation with locking device to can realize the locking after rotatory predetermined angle. The rotary wing aircraft simultaneously considers the good aerodynamic shape of the flying wing and the vertical take-off and landing function of the rotary wing aircraft, reduces the requirement on an engine during vertical take-off and landing compared with a common tilt rotor aircraft, and simultaneously provides a new idea for the development of future aircrafts.

Description

Flying wing type rotary wing aircraft

Technical Field

The utility model belongs to novel aircraft design field, concretely relates to all-wing aircraft formula rotary wing machine. The novel flying wing type rotary wing aircraft combines a rotary wing aircraft and a flying wing type aircraft.

Background

The flying wing type layout of the aircraft is a pneumatic layout form with only one integrated wing surface, and the whole aircraft has no plane tail, vertical tail, canard wing and other stabilizing surfaces, even no obvious aircraft body. The structure efficiency is higher, and larger oil carrying capacity and larger takeoff mass can be realized, which means that the range and the time of flight of the flying wing layout are necessarily larger than those of the conventional layout. The flying wing type layout has the outstanding advantages of large lift-drag ratio, high pneumatic efficiency, uniform load distribution, high structural efficiency, large effective load capacity, good stealth performance and the like. However, the flying wing type airplane also has the defects of long sliding distance, high requirement on the field and the like.

The rotary wing aircraft is a new concept aircraft, and is a combination of a rotary wing aircraft and a fixed wing aircraft. The main characteristic of the device is that a pair of rotary wings can rotate at high speed to be used as a rotor wing and can be locked to be used as fixed wings, so that the rotary wings can vertically take off and land and hover at fixed points like a helicopter and have the high-speed cruising capability of a jet-propelled fixed wing aircraft.

The technical verification machine of the X50-A dragonfly duck-shaped rotary wing (CRW) of Boeing company is a typical representation of a rotary wing, but two verification machines crash in verification flight one after another and do not complete transition flight. 7 months 2014, U.S. Dzyne technology company has designed a carbon fiber composite unmanned aerial vehicle of "pathfinder", and its wing can become 0 to 75 contained angles with the fuselage, can carry out angle adjustment according to the flight state of difference. At present, the research on the flight verification of the rotary wing is lacked in China.

Disclosure of Invention

Based on the consideration of the above problems, the combination of the flying wing type airplane and the rotary wing type airplane provides a direction and an idea for the future rotary flying wing type airplane. The flying wing type rotary wing machine adopts the wing rotating technology, so that the flying wing type rotary wing machine has the vertical take-off and landing functions and good pneumatic performance.

The utility model discloses a: the utility model provides a flying wing formula rotary wing machine, rotary wing machine has fuselage and wing, the wing sets up in the both sides of fuselage, and the wing is provided with the screw, is provided with the undercarriage on the fuselage, and the main shaft passes the fuselage, installs the bearing at the both ends of main shaft and is connected with both sides wing, the wing passes through the wing rotation and locking device can be rotatory around the main shaft to can realize the locking after rotatory predetermined angle.

Further, the wing rotating and locking device comprises a motor arranged on the body, a sliding rail arranged on the wing, and a connecting rod driven by a motor output shaft to rotate, wherein a pulley is arranged on the connecting rod, the pulley is arranged in the sliding rail, the pulley moves in the sliding rail when the motor drives the connecting rod to rotate, a locking hole is further formed in the wing, and an insertion pin is correspondingly arranged on the body (when the wing rotates to a preset angle, the insertion pin extends out of the body and is inserted into the locking hole).

Furthermore, the bearing is an axial pressure bearing, the bearing is fixed on the wing, an annular groove is formed in the contact surface of the bearing and the main shaft, an annular protrusion is correspondingly formed in the main shaft, and the groove and the protrusion are matched to enable the bearing to rotate only and not to move radially.

Furthermore, the undercarriage consists of 6 bent supports, and the three supports are respectively arranged in front of and behind the body and are symmetrically arranged with the main shaft.

Furthermore, a plurality of insertion pins are correspondingly arranged on a path of the locking hole rotating around the main shaft, the motor rotates for a certain angle according to the control signal, the insertion pins corresponding to the locking hole are bounced and extended out after the motor rotates, and are inserted into the locking hole, and locking at a certain angle is achieved.

Furthermore, a protruding rail is arranged on the sliding rail along the direction of the sliding rail, and a groove is axially arranged on the pulley.

The utility model aims at: the novel aircraft is based on the flying wing type layout, and the flying wing type aircraft and the rotary wing type aircraft are improved in the take-off mode through the wing rotating mechanism, so that the requirement on the field is reduced.

The technical solution of the utility model is as follows: based on the setting of the double aircraft, the rotation of the wings is realized through the wing rotating mechanism, so that the lift force required by the aircraft during takeoff comes from the engine pulling force and the lift force generated by the wings. After the height of the plane flight is reached, the wings are gradually laid flat and finally locked, and the plane flight from vertical flight to horizontal flight is realized.

The utility model has the advantages that: the rotary wing aircraft simultaneously considers the good aerodynamic shape of the flying wing and the vertical take-off and landing function of the rotary wing aircraft, reduces the requirement on an engine during vertical take-off and landing compared with a common tilt rotor aircraft, and simultaneously provides a new idea for the development of future aircrafts.

Drawings

Fig. 1 is a front view of the whole rotary wing aircraft wing of the present invention when locked.

Fig. 2 is a schematic view of a rotating section of a right wing of a rotary wing aircraft about a shaft in the process of taking off or landing, namely a left side view.

FIG. 3 is a schematic view of the left wing of the rotary wing aircraft in the process of taking off or landing, namely, a right side view of the rotary wing aircraft

FIG. 4 is a top view of the whole aircraft when the axis of the fuselage of the rotary wing aircraft of the present invention rotates

FIG. 5 is a magnified view of the rotating and locking portion of the wing of the present invention

Fig. 6 the detailed structure of the connecting rod with pulley of the present invention

In the figure, a fuselage 100, wings 200, a propeller 1, an undercarriage 2, a main shaft 3, a bearing 4 (a bearing installed in the wings), a position 5 where the wings are located when the wings are locked with the fuselage, a position 6 where the wings form a certain attack angle after the wings rotate, a wing rotating and locking device 7, a slide rail 8, a locking hole 9, a connecting rod 10 and a motor 11 (a motor installed on the fuselage and driving the wings to rotate) are shown.

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. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms "center", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "circumferential", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

In the present invention, unless otherwise expressly stated or limited, the terms "disposed," "mounted," "connected," and "fixed" are to be construed broadly, e.g., as meaning either a fixed connection or a removable connection; may be a mechanical connection; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

The utility model discloses a concrete scheme as follows: the utility model provides a wing-type rotary wing machine, rotary wing machine has fuselage 100 and wing 200, wing 200 sets up in the both sides of fuselage 100, and wing 200 is provided with screw 1, is provided with undercarriage 2 on the fuselage 100, and main shaft 3 passes fuselage 100, installs bearing 4 and is connected with both sides wing 200 at the both ends of main shaft 3, wing 200 can be rotatory around main shaft 3 through wing rotation and locking device 7 to can realize the locking after rotatory predetermined angle. The wing rotating and locking device 7 comprises a motor 11 arranged on the fuselage 100, a sliding rail 8 arranged on the wing 200, and a connecting rod 10 driven by an output shaft of the motor 11 to rotate, wherein a pulley is arranged on the connecting rod 10, the pulley is arranged in the sliding rail 8, the pulley moves in the sliding rail 8 when the motor 11 drives the connecting rod 10 to rotate, a locking hole 9 is further arranged on the wing 200, and an insertion pin corresponds to the fuselage 100 (when the wing 200 rotates to a preset angle, the insertion pin extends out of the fuselage 100 and is inserted into the locking hole 9). The bearing 4 is an axial pressure bearing, the bearing 4 is fixed on the wing 200, an annular groove is arranged at the contact surface of the bearing 4 and the main shaft 3, an annular bulge is correspondingly arranged on the main shaft 3, and the groove and the bulge are matched to realize that the bearing can only rotate and cannot move radially. The undercarriage 2 consists of 6 bent supports, and the front part and the rear part of the body 100 are respectively three and are symmetrically arranged with the main shaft 3. The plurality of insertion pins are correspondingly arranged on a path of the locking hole 9 rotating around the main shaft, the motor 11 rotates for a certain angle according to a control signal, and after the motor 11 rotates, the insertion pins corresponding to the locking hole 9 are bounced and extended out and inserted into the locking hole 9, so that locking at a certain angle is realized.

A protruding rail is arranged on the sliding rail 8 along the direction of the sliding rail 8, and a groove is axially arranged on the pulley.

As shown in fig. 1, during take-off, the whole aircraft is vertically placed on the ground and supported by an undercarriage 2, which is composed of 6 curved supports. At the moment, the engine drives the propeller 1 to start rotating, meanwhile, the motor arranged in the fuselage pulls the wings to start rotating around the main shaft 3, the main shaft 3 penetrates through the whole fuselage to be connected with the left wing and the right wing, and the main shaft is provided with an axial pressure bearing to be connected with the wings. Taking the right wing as an example, as shown in fig. 2, when the wing is locked with the fuselage by rotating around the main shaft 3, the wing rotates from the position 5 where the wing is located when the wing is locked with the fuselage to the position 6 where the wing forms a certain angle of attack after rotating around the shaft, similarly, when the left wing is as shown in fig. 3, when the wing is locked with the fuselage, the wing rotates from the position 5 where the wing is located when the wing is locked with the fuselage to the position 6 where the wing forms a certain angle of attack after rotating around the shaft, and the rotating directions of the wings on the two sides are opposite, the motor 11 drives the connecting rod 10 with the pulley to move in the sliding rail 8, after the wing is driven to rotate to a proper position, the bolt preset in the fuselage is inserted into the locking hole 9 to lock the wing, and the. As the engine starts to work, because the directions of the two propellers 1 are opposite, a part of pulling force generated by the propellers 1 pulls the wings to rotate around the axis of the airplane, so that the wings rotate at a certain attack angle to generate lifting force, and the lifting force and an upward component force generated by the other part of propellers 1 overcome the gravity together, and the vertical takeoff is realized. After reaching a certain height, the wing rotates around the main shaft 3 to return to a position 5 where the wing is located when the wing and the fuselage are locked, at the moment, the wing and the fuselage are locked, the wing and the fuselage are changed into a horizontal flight state, and finally the vertical flight is changed into the horizontal flight.

The vertical take-off and landing of the flying wing type airplane can be realized by applying the flying wing type airplane with the rotary wing take-off and landing mode, and the requirements on an airplane engine can be reduced.

The device of application this patent production has not only kept the good aerodynamic performance of wing aircraft formula aircraft, has also reduced the requirement to the place of aircraft landing simultaneously. And reduces its requirements for the engine relative to typical tiltrotor aircraft.

Claims

1. The utility model provides a flying wing formula rotary wing machine, rotary wing machine has fuselage (100) and wing (200), wing (200) set up in the both sides of fuselage (100), and wing (200) are provided with screw (1), are provided with undercarriage (2) on fuselage (100), its characterized in that: the main shaft (3) penetrates through the fuselage (100), bearings (4) are mounted at two ends of the main shaft (3) and connected with wings (200) on two sides, and the wings (200) can rotate around the main shaft (3) through wing rotating and locking devices (7) and can be locked after rotating for a preset angle;

the wing rotating and locking device (7) comprises a motor (11) arranged on the body (100), a sliding rail (8) arranged on the wing (200), and a connecting rod (10) driven by an output shaft of the motor (11) to rotate, wherein a pulley is arranged on the connecting rod (10), the pulley is arranged in the sliding rail (8), the pulley moves in the sliding rail (8) when the motor (11) drives the connecting rod (10) to rotate, a locking hole (9) is further formed in the wing (200), and an inserting pin is correspondingly arranged on the body (100);

the bearing (4) is an axial pressure bearing, the bearing (4) is fixed on the wing (200), an annular groove is formed in the contact surface of the bearing (4) and the main shaft (3), an annular bulge is correspondingly formed in the main shaft (3), and the bearing can only rotate and cannot move radially due to the matching of the groove and the bulge; the undercarriage (2) consists of 6 bent supports, and the front part and the rear part of the undercarriage body (100) are respectively three and are symmetrically arranged with the main shaft (3);

the insertion pins are correspondingly arranged on a path of the locking hole (9) rotating around the main shaft, the motor (11) rotates for a certain angle according to a control signal, the insertion pins corresponding to the locking hole (9) are bounced and extended out after the motor (11) rotates, and are inserted into the locking hole (9), so that locking at a certain angle is realized; the sliding rail (8) is provided with a convex rail along the direction of the sliding rail (8), and the pulley is axially provided with a groove.