阅读说明：本技术 一种具有倾转旋翼的飞行器 (Aircraft with tilt rotor ) 是由 谢陵 刘十一 于 2020-06-10 设计创作，主要内容包括：本发明公开了一种具有倾转旋翼的飞行器,飞行器包括机身,机身的左右两侧分别设置有机翼,机身上还设置有垂起动力装置；机翼上设置有倾转旋翼臂,倾转旋翼臂上设置有倾转驱动装置,倾转驱动装置的驱动端连接有倾转旋翼驱动电机,倾转旋翼驱动电机的驱动端连接有倾转旋翼；倾转旋翼驱动电机和倾转旋翼在倾转驱动装置的驱动下倾转,倾转旋翼驱动电机和倾转旋翼朝向机身的前方,或倾转旋翼驱动电机和倾转旋翼朝向机身的上方；倾转旋翼在倾转旋翼驱动电机的驱动下旋转。在本发明实施例中,所述倾转旋翼在垂直起降时可以提供垂直起降的动力,增大垂直起降的升力,保证飞行器的垂直起降性能,而且可以提高垂直起降时大翼展情况下的抗风能力。(The invention discloses an aircraft with a tilt rotor wing, which comprises an aircraft body, wherein wings are respectively arranged on the left side and the right side of the aircraft body, and a vertical starting power device is also arranged on the aircraft body; a tilt rotor arm is arranged on the wing, a tilt driving device is arranged on the tilt rotor arm, the driving end of the tilt driving device is connected with a tilt rotor driving motor, and the driving end of the tilt rotor driving motor is connected with a tilt rotor; the tilt rotor driving motor and the tilt rotor tilt under the driving of the tilt driving device, and the tilt rotor driving motor and the tilt rotor face to the front of the fuselage, or the tilt rotor driving motor and the tilt rotor face to the upper part of the fuselage; the tilt rotor is driven by the tilt rotor driving motor to rotate. In the embodiment of the invention, the tilting rotor wing can provide vertical take-off and landing power during vertical take-off and landing, increase the lift force of vertical take-off and landing, ensure the vertical take-off and landing performance of an aircraft, and improve the wind resistance under the condition of large span during vertical take-off and landing.)

1. The aircraft with the tilting rotor wing is characterized by comprising a fuselage, wherein wings are arranged on the left side and the right side of the fuselage respectively, and a vertical power device is arranged on the fuselage;

a tilt rotor arm is arranged on the wing, a tilt driving device is arranged on the tilt rotor arm, the driving end of the tilt driving device is connected with a tilt rotor driving motor, and the driving end of the tilt rotor driving motor is connected with a tilt rotor;

the tilt rotor driving motor and the tilt rotor tilt under the driving of the tilt driving device, the tilt rotor driving motor and the tilt rotor face to the front of the fuselage, or the tilt rotor driving motor and the tilt rotor face to the upper part of the fuselage;

the tilt rotor is rotated under the drive of the tilt rotor driving motor.

2. The aircraft of claim 1 wherein one end of said tilt rotor arm is fixed to said wing;

the tilting driving device is arranged at the other end of the tilting rotor arm.

3. The aircraft of claim 1 wherein said tilt drive unit drive end is connected to a tilt member, said tilt member being driven by said tilt drive unit to tilt, said tilt rotor drive motor being disposed on said tilt member.

4. The aircraft of claim 1 wherein said tilt drive is a steering engine.

5. The aircraft of claim 1, wherein the droop motive power device comprises a plurality of droop rotor arms, one end of each droop rotor arm is fixed to the fuselage, the other end of each droop rotor arm is provided with a droop rotor driving motor, a drive end of the droop rotor driving motor is connected with a droop rotor, the droop rotor driving motor and the droop rotor face the upper side of the fuselage, and the droop rotor is driven by the droop rotor driving motor to rotate.

6. The aircraft of claim 5, wherein the vertical starting power device further comprises a vertical rotor arm extension device disposed on the fuselage, one end of each of the plurality of vertical rotor arms is connected to the vertical rotor arm extension device, and the plurality of vertical rotor arms are synchronously extended and retracted under the driving of the vertical rotor arm extension device.

Technical Field

The invention relates to the technical field of aircrafts, in particular to an aircraft with tilting rotors.

Background

In recent years, aircrafts have been continuously developed, and have the advantages of low manufacturing cost, simplicity and convenience in operation, high flexibility, capability of flying at ultra-low altitude and the like, so that the aircrafts are increasingly widely used by various industries, and most of the existing aircrafts are mainly applied to the fields of scientific research, geographic detection, agricultural irrigation, video shooting and the like.

The traditional aircraft has the problem of poor vertical take-off and landing performance, and the problem of poor wind resistance in the vertical take-off and landing process affects the actual use effect of the aircraft.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provides an aircraft with a tilting rotor wing, wherein the tilting rotor wing can provide vertical take-off and landing power during vertical take-off and landing, the lift force of vertical take-off and landing is increased, the vertical take-off and landing performance of the aircraft is ensured, and the wind resistance under the condition of large span during vertical take-off and landing can be improved.

Correspondingly, the embodiment of the invention provides an aircraft with a tilt rotor wing, which comprises a fuselage, wherein wings are respectively arranged on the left side and the right side of the fuselage, and a vertical power device is arranged on the fuselage;

a tilt rotor arm is arranged on the wing, a tilt driving device is arranged on the tilt rotor arm, the driving end of the tilt driving device is connected with a tilt rotor driving motor, and the driving end of the tilt rotor driving motor is connected with a tilt rotor;

the tilt rotor driving motor and the tilt rotor tilt under the driving of the tilt driving device, the tilt rotor driving motor and the tilt rotor face to the front of the fuselage, or the tilt rotor driving motor and the tilt rotor face to the upper part of the fuselage;

the tilt rotor is rotated under the drive of the tilt rotor driving motor.

In an alternative embodiment, one end of the tilt rotor arm is fixed to the wing;

the tilting driving device is arranged at the other end of the tilting rotor arm.

An optional implementation mode, tilting drive device's drive end is connected with the piece that verts, tilting is in tilting drive device's drive down, the rotor driving motor that verts sets up tilting is last.

In an optional embodiment, the tilting drive device is a steering engine.

Optional embodiment, the start power device that hangs down includes many rotor arms that hang down, and the one end of arbitrary rotor arm that hangs down is fixed on the fuselage, and the other end of arbitrary rotor arm that hangs down is provided with the rotor driving motor that hangs down, the drive end of rotor driving motor that hangs down is connected with the rotor that hangs down, the rotor driving motor that hangs down with the rotor orientation that hangs down the top of fuselage, the rotor that hangs down is in it is rotatory under the drive of rotor driving motor that hangs down.

In an optional implementation manner, the vertical starting power device further includes a vertical rotor arm telescoping device disposed on the fuselage, one end of each of the vertical rotor arms is connected to the vertical rotor arm telescoping device, and the vertical rotor arms are driven by the vertical rotor arm telescoping device to synchronously telescope.

The embodiment of the invention provides an aircraft with tilting rotors, wherein when the aircraft vertically takes off and lands, a driving motor of the tilting rotors and the tilting rotors face to the upper part of an airframe, the tilting rotors rotate under the driving of the driving motor of the tilting rotors, and the tilting rotors are matched with a vertical starting force device to provide vertical lifting force for the aircraft, so that the vertical taking off and the landing of the aircraft are driven, the vertical taking off and the landing performance of the aircraft are ensured, the force arm of the tilting rotors is large, and the wind resistance of the aircraft in the vertical taking off and the landing process can be improved through the tilting rotors; the aircraft finishes VTOL and gets into when the flight that cruises, the rotor driving motor that verts with the rotor orientation that verts the place ahead of fuselage, just the rotor that verts is in it is rotatory under the rotor driving motor's that verts the drive, the rotor that verts does the aircraft provides power that cruises, thereby the drive the flight that cruises of aircraft guarantees the flight performance that cruises of aircraft has fine in-service use effect.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a top view of an aircraft in cruise flight in an embodiment of the present invention;

FIG. 2 is a side view of an aircraft in cruise flight in an embodiment of the present invention;

FIG. 3 is a top view of an aircraft at vertical take-off and landing in an embodiment of the present invention;

FIG. 4 is a side view of an aircraft at vertical take-off and landing in an embodiment of the present invention;

figure 5 is a side view of an embodiment of the present invention with the tiltrotor facing forward of the fuselage;

figure 6 is a top view of an embodiment of the present invention with the tiltrotor facing forward of the fuselage;

figure 7 is a side view of an embodiment of the present invention with the tiltrotor rotors facing up the fuselage;

figure 8 is a top view of an embodiment of the present invention with the tiltrotor facing up the fuselage.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

FIG. 1 is a plan view of an aircraft in cruise flight according to an embodiment of the present invention, FIG. 2 is a side view of an aircraft in cruise flight according to an embodiment of the present invention, FIG. 3 is a plan view of an aircraft in VTOL according to an embodiment of the present invention, and FIG. 4 is a side view of an aircraft in VTOL according to an embodiment of the present invention.

The embodiment of the invention provides an aircraft with tilting rotors, which can be an airplane, an unmanned aerial vehicle and the like, and comprises an airframe 1, wherein wings 2 are respectively arranged on the left side and the right side of the airframe 1.

Fig. 5 is a side view of an embodiment of the invention with tiltrotors facing forward of the fuselage, fig. 6 is a top view of an embodiment of the invention with tiltrotors facing forward of the fuselage, fig. 7 is a side view of an embodiment of the invention with tiltrotors facing upward of the fuselage, and fig. 8 is a top view of an embodiment of the invention with tiltrotors facing upward of the fuselage.

Be provided with tilting rotor arm 31 on wing 2, be provided with tilting drive arrangement 32 on tilting rotor arm 31, tilting drive arrangement 32's drive end is connected with tilting rotor driving motor 33, tilting rotor driving motor 33's drive end is connected with tilting rotor 34.

Tilt rotor driving motor 33 with tilt rotor 34 is in tilt drive device 32's drive is down tilted, tilt rotor driving motor 33 with tilt rotor 34 orientation the place ahead of fuselage 1, or tilt rotor driving motor 33 with tilt rotor 34 orientation the top of fuselage 1.

The tilt rotors 34 are driven by the tilt rotor drive motor 33 to rotate.

The aircraft is when VTOL, tilt rotor driving motor 33 with tilt rotor 34 orientation the top of fuselage 1, just tilt rotor 34 is in it is rotatory under tilt rotor driving motor's 33 drive, this moment tilt rotor 34's the plane of rotation is parallel with ground, tilt rotor 34 does the aircraft provides the lift that hangs down to the drive the VTOL of aircraft.

In addition, still be provided with on the fuselage 1 and hang down motive power device 4, the rotor 34 that verts can be alone for the aircraft provides the lift that hangs down, also can cooperate the lift motive power device 4 that hangs down is together for the aircraft provides the lift that hangs down, thereby guarantees the VTOL performance of aircraft.

Moreover, because tilt rotor 34 is far away from the focus of aircraft, consequently tilt rotor 34's the arm of force is great, tilt rotor 34 can improve the anti-wind ability of aircraft at the in-process of VTOL has improved the actual use effect of aircraft.

When the aircraft finishes the VTOL and gets into the flight of cruising, tilt rotor driving motor 33 with tilt rotor 34 is in tilt under the drive of tilt driving device 32, tilt rotor driving motor 33 with tilt rotor 34 orientation the place ahead of fuselage 1, just tilt rotor 34 is in it is rotatory under the drive of tilt rotor driving motor 33, this moment tilt rotor 34's rotation plane perpendicular to ground, tilt rotor 34 does the aircraft provides power of cruising, thereby the drive the flight of cruising of aircraft.

Specifically, the one end of tilting rotor arm 31 is fixed on the wing, tilting drive device 32 sets up tilting rotor arm 31's the other end, tilting drive device 32's setting enables tilting drive device 32 is last tilting rotor driving motor 33 with tilting rotor 34 keeps away from as far as possible the focus of the aircraft makes tilting rotor 34's the arm of force is bigger, improves better the anti-wind ability of aircraft at the in-process of VTOL.

Specifically, the drive end of tilting drive device 32 is connected with tilting piece 321, tilting piece 321 is in tilting drive device 32's drive down tilts, tilting rotor driving motor 33 sets up tilting on piece 321, tilting piece 321's setting is convenient for tilting rotor driving motor 33 with be connected between tilting drive device 32's the drive end.

Preferably, tilting drive device 32 is the steering wheel, and the steering wheel is the servo driver in a position (angle), is applicable to the control system that needs the angle constantly to change and can keep, adopts the steering wheel as tilting drive device 32 can drive tilting rotor driving motor 33 with tilting rotor 34 verts according to predetermineeing the angle, does better do the aircraft provides lift of hanging down or power of cruising to guarantee steadily the actual use effect of aircraft.

The vertical starting power device 4 may be implemented in various manners, in an embodiment of the present invention, the vertical starting power device 4 includes a plurality of vertical rotor arms 41, the plurality of vertical rotor arms 41 are uniformly distributed along the same circumference, one end of any one of the vertical rotor arms 41 is fixed on the airframe 1, the other end of any one of the vertical rotor arms 41 is provided with a vertical rotor driving motor 42, a vertical rotor driving end 43 is connected to the vertical rotor driving motor 42, the vertical rotor driving motor 42 and the vertical rotor 43 face the upper side of the airframe 1, and the vertical rotor 43 is driven by the vertical rotor driving motor 42 to rotate so as to drive the vertical ascent and descent of the aircraft.

In particular, in the embodiment of the present invention, the vertical starting power device 4 further includes a vertical rotor arm telescoping device 5 disposed on the fuselage 1, one end of each of the plurality of vertical rotor arms 41 is connected to the vertical rotor arm telescoping device 5, and the plurality of vertical rotor arms 41 are driven by the vertical rotor arm telescoping device 5 to synchronously telescope, and the embodiment of the vertical rotor arm telescoping device 5 may be various as long as the synchronous telescoping of the plurality of vertical rotor arms 41 is achieved, and is not particularly limited in the embodiment of the present invention.

When the aircraft vertically takes off and lands, the vertical rotor arm telescopic device 5 drives the multiple vertical rotor arms 41 to synchronously extend out and expand to the outside of the aircraft body 1 so as to drive the aircraft to vertically take off and land.

When the aircraft finishes vertical take-off and landing and enters cruise flight, the vertical rotor arm telescopic device 5 drives the multiple vertical rotor arms 41 to synchronously contract and take in the fuselage 1, so that the flight resistance of the aircraft is reduced, and the cruise flight performance of the aircraft is improved.

Specifically, a vertical tail 11 is arranged at the rear end of the body 1, and horizontal tails 12 are symmetrically arranged on the left side and the right side of the rear end of the body 1.

It should be noted that the vertical tail 11 can reduce the induced drag of the aircraft and increase the lift-to-drag ratio of the aircraft, thereby improving the flight performance of the aircraft; the main function of the horizontal rear wing 12 is to generate lift, which not only improves the aerodynamic effect of the aircraft, but also increases the lateral stability of the aircraft, and also improves the flight performance of the aircraft.

Specifically, the head of the aircraft body 1 and the tail of the aircraft body are both arranged to be pointed ends, so that the aerodynamic effect of the aircraft can be improved, and the flight performance of the aircraft can be improved.

The embodiment of the invention provides an aircraft with tilt rotors, when the aircraft vertically takes off and lands, the tilt rotor driving motor 33 and the tilt rotor 34 face the upper part of the fuselage 1, the tilt rotor 34 is driven by the tilt rotor driving motor 33 to rotate, the tilt rotor 34 is matched with the vertical starting power device 4 to provide vertical lifting force for the aircraft, so that the vertical taking off and landing of the aircraft are driven, the vertical taking off and landing performance of the aircraft is ensured, the force arm of the tilt rotor 34 is large, and the wind resistance of the aircraft in the vertical taking off and landing process can be improved by the tilt rotor 34; when the aircraft finishes VTOL and gets into the flight that cruises, tilt rotor driving motor 33 with tilt rotor 34 orientation the place ahead of fuselage 1, just tilt rotor 34 is in it is rotatory under tilt rotor driving motor 33's the drive, tilt rotor 34 does the aircraft provides power that cruises, thereby the drive the flight that cruises of aircraft guarantees the flight performance that cruises of aircraft has fine in-service use effect.

In addition, the above detailed description is provided for an aircraft with tilt rotors according to the embodiments of the present invention, and the principle and the embodiments of the present invention shall be explained herein by using specific examples, and the above descriptions of the embodiments are only used to help understanding the method of the present invention and the core idea thereof; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.