CN209956222U

CN209956222U - Novel vertical take-off and landing aircraft

Info

Publication number: CN209956222U
Application number: CN201920672296.XU
Authority: CN
Inventors: 丁桦; 盛国强; 邱谭平; 白思和
Original assignee: Institute of Industry Technology Guangzhou of CAS
Current assignee: Institute of Industry Technology Guangzhou of CAS
Priority date: 2019-05-10
Filing date: 2019-05-10
Publication date: 2020-01-17
Anticipated expiration: 2029-05-10

Abstract

The utility model discloses a novel VTOL aircraft, including the fuselage, still including setting up rotation axis on fuselage upper portion, the wing of setting at the rotation epaxial, wherein be equipped with in the rotation axis and be used for controlling the rotatory or fixed locking mechanism of wing, the symmetry is equipped with a two-way engine that possesses forward and reverse propulsion drivability respectively on the both ends of wing, when the two-way engine of wing both sides is forward respectively and reverse propulsion, the wing uses the rotation axis to rotate as the axle, when the two-way engine forward of wing both sides impels, the wing is locked by locking mechanism and keep with fuselage vertically state. The utility model has the advantages that: under the same takeoff weight, the aircraft has the advantages of smaller size, portability, higher cruising speed, large flying distance and low energy consumption due to no change of the pneumatic layout of the aircraft, and is favorable for prolonging the dead time.

Description

Novel vertical take-off and landing aircraft

Technical Field

The utility model belongs to the technical field of an airborne vehicle technique and specifically relates to a technique of hybrid VTOL aircraft is related to.

Background

There are three main types of aircraft that are common today: multi-rotor, fixed-wing, or hybrid with multiple rotor takeoff and landing modules added to a conventional fixed-wing aircraft. Most manned aircraft or airplanes take off and land in three ways.

Limited by airport settings, in order to improve the convenience of airplane use, the need of vertical take-off and landing has become an increasingly major need for using aircrafts, and as for the existing airplanes with three wing-shaped modes, the airplane has advantages and disadvantages: 1. for a fixed wing aircraft, although the fixed wing aircraft has fast speed, long range and little influence by weather, the fixed wing aircraft is supported by the field and is more easily limited by a take-off mode and cannot meet the requirement of vertical take-off and landing; 2. the multi-rotor aircraft has low requirements on fields, can take off and land at any time and any place, can hover in the air and is flexible, but the horizontal flight speed, the effective load, the range and the environment adaptability are limited, and the capacity of the aspects needs to be increased, the volume of the aircraft becomes extremely remarkable, and the cost performance and the use convenience of the aircraft are directly influenced; 3. the hybrid model combines together many rotors and stationary vane, is about to the rotor installs on the stationary vane, and the advantage that plays many rotor crafts VTOL and stationary vane fast cruise simultaneously, but also has the problem that it is limited to have the weight of avoiding taking off, and more importantly is when cruising, and aerodynamic configuration meets with the destruction, arouses that flight resistance increases, duration reduces etc..

Disclosure of Invention

The utility model aims at providing a can realize switching between stationary vane and rotor, small, the complete novel VTOL aircraft of the pneumatic overall arrangement that cruises.

Another object of the present invention is to provide a novel control method for a vertical take-off and landing aircraft with convenient operation and control.

The technical solution of the utility model is that: the utility model provides a novel VTOL aircraft, includes the fuselage, still is in including setting up rotation axis on fuselage upper portion, the wing of setting at the rotation epaxial, wherein be equipped with in the rotation axis and be used for controlling the rotatory or fixed locking mechanism of wing, the symmetry is equipped with a two-way engine that possesses forward and reverse propulsion drivability respectively on the both ends of wing, when the two-way engine of wing both sides is forward respectively and reverse propulsion, the wing uses the rotation axis to rotate as the axle, when the two-way engine forward propulsion of wing both sides, the wing is locked by locking mechanism and keep with fuselage vertically state.

The wings are arranged on the rotating shaft, when the propelling directions of the two-way engines at two sides of the wings are opposite, the wings can rotate to generate a vertical upward lift force, when the output power of the two-way engine reversely propelled at one side is reduced, the aircraft can generate a forward speed due to unequal propelling forces at two sides of the wings, when the reverse thrust of the two-way engine reversely propelled at one side is zero, the wings rotate to be vertical to the aircraft body, the wings are fixed through the locking mechanism, then the two-way engine at one side is restarted and adjusted to be positively propelled, at the moment, the aircraft can be converted from a spiral state to a linear cruise state, so that the take-off of the rotor wing and the cruise of the fixed wing are realized, the aerodynamic performance of the whole aircraft body is not changed at all, the area of the wings is much larger than that of a common rotor wing, under the same volume, the obtained take-, the pneumatic layout and the cruising resistance are consistent with those of a fixed-wing airplane, and the cruising speed is higher.

The vertical section of the wing is in a flat plate shape or an airfoil shape. Different lift effects can be achieved at take-off and cruise.

The horizontal attack angle of two sides of the wing can be adjusted through the rotating shaft respectively. The aerodynamic layout of both sides can be respectively adjusted when the wing rotates, so that the lift force and the balance moment are improved, and the control reliability is improved.

The wing comprises a skin and an adjusting mechanism arranged in the skin and used for adjusting the windward surface shape of the wing. The aerodynamic layout of the wings on two sides can be respectively adjusted when the wings rotate, so that the lift force and the balance moment are improved.

The adjusting mechanism comprises a longitudinal connecting rod arranged along the length direction of the wing, and a plurality of groups of adjusting connecting rod groups arranged on the longitudinal connecting rod in parallel, wherein each adjusting connecting rod group comprises a transverse connecting rod fixed on the longitudinal connecting rod, a first diamond connecting rod group, a second diamond connecting rod group, a third diamond connecting rod group, a first sliding block and a second sliding block which are respectively sleeved on the transverse connecting rod and can slide along the transverse connecting rod, two symmetrical ends of the first diamond connecting rod group are respectively hinged with an upper skin and a lower skin, the other two symmetrical ends are respectively hinged with one end of the transverse connecting rod and the first sliding block, two symmetrical ends of the second diamond connecting rod group are respectively hinged with the upper skin and the lower skins of the wing, the other two symmetrical ends are respectively hinged with the first sliding block and the second sliding block, and two symmetrical ends of the third diamond connecting rod group are respectively hinged with the upper skin and the lower skin of the, the other two symmetrical ends are respectively hinged with the second sliding block and the other end of the transverse connecting rod. When the first sliding block and the second sliding block slide back and forth along the transverse connecting rod, the upper height and the lower height of the three groups of diamond connecting rod groups can be respectively adjusted, so that the distance between skins above and below the wing is adjusted, the windward shape of the wing is adjusted, and the windward state of the wing is adjusted to adapt to different states of the fixed wing and the rotor wing.

And a short wing rotating along with the rotating shaft is arranged on the rotating shaft below the wing, and when the wing is vertically fixed with the fuselage, the short wing is fixed with the fuselage in parallel. The short wing can rotate along with the rotating shaft, can provide additional lift force in the vertical take-off and landing stage and is used for balancing the lifting moment on two sides of the wing.

The utility model has the advantages that: under the same takeoff weight, the aircraft has the advantages of smaller size, portability, higher cruising speed, large flying distance and low energy consumption due to no change of the pneumatic layout of the aircraft, and is favorable for prolonging the dead time.

Drawings

Fig. 1 is a schematic structural diagram of embodiment 1 of the present invention;

fig. 2 is another angle structure diagram of embodiment 1 of the present invention;

FIG. 3 is a flight state diagram of the embodiment 1 of the present invention during vertical take-off and landing;

fig. 4 is a flight state diagram of embodiment 1 of the present invention in cruise state;

fig. 5 is another flight state diagram of embodiment 1 of the present invention in cruise state;

fig. 6 is a schematic view of an internal overlooking structure of a wing according to embodiment 1 of the present invention;

FIG. 7 is a schematic view of the structure of FIG. 6 taken along line A-A;

fig. 8 is a schematic structural diagram of embodiment 2 of the present invention;

1. the airplane comprises a fuselage, 2, wings, 3, a rotating shaft, 4, a bidirectional engine, 5, a bidirectional engine, 6, a skin, 7, a longitudinal connecting rod, 8, a transverse connecting rod, 9, a first diamond-shaped connecting rod group, 10, a second diamond-shaped connecting rod group, 11, a third diamond-shaped connecting rod group, 12, a first sliding block, 13, a second sliding block, 14 and a short wing.

Detailed Description

Example 1:

referring to fig. 1-2, a novel vertical take-off and landing aircraft comprises an aircraft body 1, a rotating shaft 3 arranged on the upper portion of the aircraft body 1, and wings 2 arranged on the rotating shaft 3, wherein a locking mechanism for controlling the rotation or fixation of the wings 2 is arranged in the rotating shaft 3, two bidirectional engines 4 and two bidirectional engines 5 with forward and reverse propulsion driving capability are symmetrically arranged at two ends of the wings 2, when the bidirectional engines 4 at two sides of the wings 2 are positively propelled and the bidirectional engines 5 are reversely propelled, the wings 2 rotate by taking the rotating shaft 3 as a shaft, and when the

bidirectional engines

4 and 5 at two sides of the wings 2 are both positively propelled, the wings 2 are locked by the locking mechanism and are kept in a state perpendicular to the aircraft body 1.

The wing 2 is arranged on the rotating shaft 3, when the propelling directions of the two-

way engines

4 and 5 at two sides of the wing 2 are opposite, the wing 2 can be rotated to generate a vertical upward lift force, when the output power of the two-way engine 5 with one side being reversely propelled is reduced, the aircraft can generate a forward speed due to unequal propelling forces at two sides of the wing 2, when the reverse thrust of the two-way engine 5 with one side being reversely propelled is zero, the wing 2 is fixed to be vertical to the aircraft body 1 through the locking mechanism, the two-way engine 5 with one side is restarted and adjusted to be in a forward propulsion state, at the moment, the aircraft can be converted from a spiral state to a linear cruise state, so that the cruise of the rotor wing and the fixed wing is realized, the aerodynamic performance of the whole aircraft body is not changed at all, the wing area is much larger than that of a common rotor, the obtained weight is larger under the, the aircraft has flexible takeoff, and the aerodynamic layout and cruising resistance are consistent with those of fixed-wing aircrafts due to the fact that the aircraft body has no additional structure, so that the speed during cruising is higher.

The vertical section of the wing 2 is flat plate-shaped or wing-shaped. The horizontal incidence angles of the two sides of the wing 2 can be respectively adjusted through the rotating shaft 3. The wing 2 comprises a skin 6 and an adjusting mechanism arranged in the skin 6 and used for adjusting the windward shape of the wing 2. The aerodynamic layout of both sides can be respectively adjusted when the wing 2 rotates, so that the lift force and the balance moment are improved, and the control reliability is improved.

The adjusting mechanism comprises a longitudinal connecting rod 7 arranged along the length direction of the wing 2, a plurality of groups of adjusting connecting rod groups arranged on the longitudinal connecting rod 7 in parallel, wherein each adjusting connecting rod group comprises a transverse connecting rod 8 fixed on the longitudinal connecting rod 7, a first diamond-shaped connecting rod group 9, a second diamond-shaped connecting rod group 10, a third diamond-shaped connecting rod group 11, a first sliding block 12 and a second sliding block 13 which are respectively sleeved on the transverse connecting rod 8 and can slide along the transverse connecting rod 8, two symmetrical ends of the first diamond-shaped connecting rod group 9 are respectively hinged with skins 6 on and under the wing 2, the other two symmetrical ends are respectively hinged with one end of the transverse connecting rod 8 and the first sliding block 12, two symmetrical ends of the second diamond-shaped connecting rod group 10 are respectively hinged with the skins 6 on and under the wing 2, the other two symmetrical ends are respectively hinged with the first sliding block 12 and the second sliding block 13, and two symmetrical ends of the third diamond-shaped connecting rod group 11 are respectively, The other two symmetrical ends of the lower skin 6 are respectively hinged with the second sliding block 13 and the other end of the transverse connecting rod 8. When the first sliding block 12 and the second sliding block 13 slide back and forth along the transverse connecting rod 8, the upper and lower heights of the three groups of diamond connecting rod groups can be respectively adjusted, so that the distance between the skins 6 on the upper and lower parts of the wing 2 is adjusted, the windward shape of the wing 2 is adjusted, and the windward state can be adjusted according to different states of the fixed wing and the rotor wing.

Referring to fig. 3 to 5, the method for controlling a novel vertical take-off and landing aircraft according to embodiment 1 of the present invention includes the following steps:

① vertical takeoff stage, controlling the bidirectional engines 4 at two sides of the wing 2 to propel forward, and the bidirectional engines 5 to propel reversely, so that the wing 2 rotates around the rotating shaft 3, and the airplane takes off vertically;

②, during the cruising stage, the bidirectional engine 5 reversely propelled at one side of the wing 2 gradually reduces the output power, the bidirectional engine 4 positively propelled at the other side of the wing keeps the output power unchanged, the airplane ascends spirally, when the power of the bidirectional engine 5 reversely propelled is reduced to zero, the wing 2 is adjusted to be vertical to the airplane body 1, the wing 2 is fixed through the locking mechanism, the stopped bidirectional engine 5 is restarted and is changed into positive propulsion, the thrust of the engines at two sides is adjusted, and the airplane flies out along the tangential direction of the spiral line to enter the cruising state;

③, in the vertical landing stage, the locking mechanism releases the wing 2, gradually reduces the output power of the bidirectional engine 5 which is pushed forward at one side of the wing 2, and restarts and changes the bidirectional engine into reverse pushing after the output power is reduced to zero, so that the wing 2 rotates around the rotating shaft 3.

Two-way engine through both sides provides forward and reverse thrust, make 2 rotations of wing produce lift, be used for taking off and descending, through reducing reverse propulsive thrust, make the propulsive force of wing both sides unequal, produce forward speed, the aircraft can spiral rising, standby wing 2 is fixed and when making two-way engine of both sides be forward propulsion, the tangential direction that the aircraft can follow spiral flight changes the entering cruise, only need change the thrust direction of wing both sides engine, alright with the switching of realizing fixed wing and rotor state, control simply, high durability and convenient use, flight control is easy and reliable.

In addition, the method also comprises a step of adjusting the horizontal attack angle of the wings 2, wherein the attack angles of the wings 2 on both sides of the rotating shaft 3 are adjusted to be opposite in the vertical takeoff and landing stage, and the attack angles of the wings 2 on both sides of the rotating shaft 3 are adjusted to be the same in the cruising stage when the wings 2 are vertical to the fuselage 1. In the vertical take-off and landing and cruising stages, the attack angle directions of the two sides of the wing are respectively adjusted, so that the moments of the two sides of the wing are more balanced, and the control is more reliable.

The method also comprises the step of adjusting the shape of the skin 6 of the wing 2, wherein in the vertical takeoff and landing stage, the windward sides of the wings 2 on both sides of the rotating shaft 3 are opposite through an adjusting mechanism in the skin 6 of the wing 2, and in the cruising stage, the windward sides of the wings 2 on both sides of the rotating shaft 3 are identical through the adjusting mechanism in the skin 6 of the wing 2. In the vertical take-off and landing and cruising stages, the attack angle directions of the two sides of the wing are respectively adjusted, so that the moments of the two sides of the wing are more balanced, and the control is more reliable.

The aircraft of the embodiment can be a manned aircraft or an unmanned aerial vehicle.

Example 2:

referring to fig. 7, for the utility model discloses another novel VTOL aircraft, including fuselage 1, set up rotation axis 3 on fuselage 1 upper portion, set up wing 2 and stub wing 14 on rotation axis 3, wherein stub wing 14 sets up below wing 2 and can rotate along with rotation axis 3. The locking mechanism for controlling the rotation or fixation of the wing 2 and the short wing 14 is arranged in the rotating shaft 3, two bidirectional engines 4 and two bidirectional engines 5 with forward and reverse propulsion driving capability are symmetrically arranged at two ends of the wing 2, when the bidirectional engines 4 at two sides of the wing 2 are positively propelled and the bidirectional engines 5 are reversely propelled, the wing 2 rotates by taking the rotating shaft 3 as a shaft, when the

bidirectional engines

4 and 5 at two sides of the wing 2 are positively propelled, the wing 2 is locked by the locking mechanism and is kept in a state perpendicular to the fuselage 1, and at the moment, the short wing 14 is kept in a state parallel to the fuselage 1. Other technical features are the same as those of embodiment 1, and are not repeated herein.

Claims

1. The utility model provides a novel VTOL aircraft, includes the fuselage, its characterized in that: the aircraft wing structure is characterized by further comprising a rotating shaft arranged on the upper portion of the aircraft body and wings arranged on the rotating shaft, wherein locking mechanisms used for controlling the wings to rotate or be fixed are arranged in the rotating shaft, two-way engines with forward and reverse propulsion driving capabilities are symmetrically arranged at two ends of the wings respectively, the wings rotate by taking the rotating shaft as a shaft when the two-way engines on two sides of the wings are respectively propelled in the forward direction and the reverse direction, and the wings are locked by the locking mechanisms and are kept in a state perpendicular to the aircraft body when the two-way engines on two sides of the wings are propelled in the forward direction.

2. The novel VTOL aircraft of claim 1, wherein: the vertical section of the wing is in a flat plate shape or an airfoil shape.

3. The novel VTOL aircraft of claim 2, wherein: the horizontal attack angle of two sides of the wing can be adjusted through the rotating shaft respectively.

4. A novel VTOL aircraft according to claim 1, 2 or 3, characterized in that: the wing comprises a skin and an adjusting mechanism arranged in the skin and used for adjusting the windward surface shape of the wing.

5. The novel VTOL aircraft of claim 4, wherein: the adjusting mechanism comprises a longitudinal connecting rod arranged along the length direction of the wing, and a plurality of groups of adjusting connecting rod groups arranged on the longitudinal connecting rod in parallel, wherein each adjusting connecting rod group comprises a transverse connecting rod fixed on the longitudinal connecting rod, a first diamond connecting rod group, a second diamond connecting rod group, a third diamond connecting rod group, a first sliding block and a second sliding block which are respectively sleeved on the transverse connecting rod and can slide along the transverse connecting rod, two symmetrical ends of the first diamond connecting rod group are respectively hinged with an upper skin and a lower skin, the other two symmetrical ends are respectively hinged with one end of the transverse connecting rod and the first sliding block, two symmetrical ends of the second diamond connecting rod group are respectively hinged with the upper skin and the lower skins of the wing, the other two symmetrical ends are respectively hinged with the first sliding block and the second sliding block, and two symmetrical ends of the third diamond connecting rod group are respectively hinged with the upper skin and the lower skin of the, the other two symmetrical ends are respectively hinged with the second sliding block and the other end of the transverse connecting rod.

6. The novel VTOL aircraft of claim 4, wherein: and a short wing rotating along with the rotating shaft is arranged on the rotating shaft below the wing, and when the wing is vertically fixed with the fuselage, the short wing is fixed with the fuselage in parallel.