CN206202672U - Can tiltrotor aircraft - Google Patents

Abstract

Disclosing one kind can tiltrotor aircraft.It is described can tiltrotor aircraft include：Utricule, it has upper and lower surface, the utricule includes zone line and the neighboring area around the zone line, and the neighboring area of the utricule includes being through to from the upper surface multiple ducts of the lower surface, and the duct includes making the side wall of the utricule sealing；Support meanss, the support meanss are fixed in the duct of the utricule；Rotor, the rotor is rotated with the support meanss and is connected.This can tiltrotor aircraft utricule be filled with density less than air gas, make utricule that there is upward lift, so that during aircraft hovering, what rotor was provided is the lift reduction for maintaining aircraft balance in vertical direction, and save energy is so as to extend hovering and the cruising time of aircraft；During horizontal movement, rotor acting be completely used for for it is described can tiltrotor aircraft level is provided, make aircraft that there is faster flying speed.

Description

Can tiltrotor aircraft

Technical field

The utility model is related to aircraft field, can tiltrotor aircraft more particularly, to one kind.

Background technology

Unmanned plane during flying utensil is widely used, for example, unmanned plane during flying device is used for into city security protection border patrol, match Thing is live, intelligence is herded, amusement etc. of photographing.

The cruising time of current rotor wing unmanned aerial vehicle is far below fixed-wing unmanned plane, in order to retain the hovering function of unmanned plane, Improve its cruising time simultaneously, many people pass through the characteristics of combining rotor wing unmanned aerial vehicle with fixed-wing unmanned plane, and development can vertically rise The class fixed-wing unmanned plane of drop, for example, a kind of new of prior art can tilting rotor VTOL aircraft, horizontal movement process In its fixed-wing can provide lift to offset the deadweight of part fuselage, but during hovering, fuselage weight is mainly by propeller offer Lift is balanced, it is impossible to ensure its prolonged hovering；A kind of tool for being related in the prior art is aliped can tilting rotor Quadrotor, it be by ala during horizontal movement provide lift to extend boat when, but hovering when, also mainly according to Lift is provided by four propellers.

To sum up, even if in the prior art by combining the aircraft that rotor wing unmanned aerial vehicle and fixed-wing unmanned plane are obtained, it hangs It is still not fully up to expectations between the stopping time.

Utility model content

In view of the above problems, the purpose of this utility model is that offer one kind can tiltrotor aircraft, the rotation that can vert The hovering of rotor aircraft and cruising time are longer, and flying speed is faster.

According to the utility model provide one kind can tiltrotor aircraft, including：Utricule, the utricule have upper surface and Lower surface, including zone line and the neighboring area around the zone line, the neighboring area of the utricule are included from described Surface is through to multiple ducts of the lower surface, and the duct includes making the side wall of the utricule sealing；Support meanss, it is described Support meanss are fixed in the duct of the utricule；Rotor, the rotor is rotated with the support meanss and is connected.

Preferably, the upper surface of the utricule is the fairshaped conical surface.

Preferably, the duct cross section is circle, the length of the circular cross section diameter more than the duct of the duct.

Preferably, central shaft of the multiple duct on the utricule is arranged symmetrically.

Preferably, the support meanss are multiple tiliting axis, and each correspondence in the multiple tiliting axis is fixed on many In each in the individual duct.

Preferably, the diameter parallel arrangement of multiple tiliting axis.

Preferably, axis of the rotation axis of the rotor perpendicular to the tiliting axis.

Preferably, the rotor includes：Support, the support is rotated with the support meanss and is connected；Motor, the motor Fix on the bracket；Propeller, the propeller and the motor connection, the motor can drive the propeller to turn It is dynamic.

Preferably, it is described can tiltrotor aircraft also include：Landing pad, the landing pad is fixed under the utricule Surface.

Preferably, the landing pad includes：Plenum space, the gas inside the plenum space filled with density less than air Body；Load-bearing space, the load-bearing space is used to load device, and the device includes battery and Aerial Electronic Equipment.

According to it is of the present utility model can tiltrotor aircraft, its utricule be filled with density less than air gas, make utricule With upward lift, the lift that the utricule is provided can balance out part aircraft gross weight power so that in aircraft hovering process In, what rotor was provided is the lift reduction for maintaining aircraft to be balanced in vertical direction, and save energy is so as to extend the outstanding of aircraft Stop and cruising time.When aircraft moves horizontally, because utricule upper surface is heaved, it can be produced determines lift so that perpendicular Nogata to without rotor extra lift is provided it is ensured that balance on aircraft vertical direction, now by adjusting inclining for rotor Turn direction, the thrust for producing rotor is consistent with heading, aircraft is had faster flying speed.Capsule with duct Body causes that the propeller and motor of rotor are protected by duct, improve can tiltrotor aircraft stability.

Brief description of the drawings

By description referring to the drawings to the utility model embodiment, of the present utility model above-mentioned and other mesh , feature and advantage will be apparent from, in the accompanying drawings：

Fig. 1 show according to the utility model specific embodiment can first state of flight of tiltrotor aircraft face Figure.

Fig. 2 show according to the utility model specific embodiment can tiltrotor aircraft the first state of flight side-looking Figure.

Fig. 3 show according to the utility model specific embodiment can tiltrotor aircraft the first state of flight vertical view Figure.

Fig. 4 show according to the utility model specific embodiment can first state of flight of tiltrotor aircraft look up Figure.

Fig. 5 show according to the utility model specific embodiment can tiltrotor aircraft the first state of flight section Figure.

Fig. 6 show according to the utility model specific embodiment can second state of flight of tiltrotor aircraft face Figure.

Fig. 7 show according to the utility model specific embodiment can tiltrotor aircraft the second state of flight side-looking Figure.

Fig. 8 show according to the utility model specific embodiment can tiltrotor aircraft the second state of flight vertical view Figure.

Fig. 9 show according to the utility model specific embodiment can second state of flight of tiltrotor aircraft look up Figure.

In figure, 100, can tiltrotor aircraft；110, utricule；111, duct；120, tiliting axis；130, rotor；131, Support；132, motor；133, propeller；140, landing pad.

Specific embodiment

The utility model is more fully described hereinafter with reference to accompanying drawing.For the sake of clarity, the various pieces in accompanying drawing do not have Have drawn to scale.Furthermore, it is possible to not shown some known parts.Describe hereinafter of the present utility model many specific Details, but just as the skilled person will understand, this can not be realized according to these specific details Utility model.

It should be appreciated that in the structure of outlines device, being referred to as being located at another floor, another area when by a floor, a region When domain " above " or " top ", can refer to above another layer, another region, or its with another layer, it is another Other layers or region are also included between individual region.Also, if device overturn, this layer, a region will be positioned at another Layer, another region " below " or " lower section ".

If in order to describe located immediately at another layer, another region above scenario, herein will be using " A is directly on B Face " or the form of presentation of " A is on B and abuts therewith ".In this application, " A is in B " represents that A is located in B, and And A and B is abutted directly against.

Fig. 1 to Fig. 5 show according to the utility model specific embodiment can tiltrotor aircraft front view, side-looking Figure, top view, upward view and sectional view, wherein, the line AA in Fig. 3 shows the interception position of sectional view.The rotation of verting Rotor aircraft 100 includes utricule 110, multiple tiliting axis 120 and multiple rotors 130.

Wherein, the utricule 110 for bamboo hat-shaped revolving body, its gyration central axis perpendicular to ground level, the utricule 110 cavitys being made up of fairshaped upper surface and smooth lower surface, the utricule 110 include zone line with around should The neighboring area of zone line, the central area of the upper surface of the utricule 110 is higher than neighboring area so that the utricule 110 The upper surface is the fairshaped conical surface.The small gas of density ratio air is filled with the inside of the utricule 110, for example, hydrogen Or helium so that the utricule 110 be subject to upward buoyancy so that for it is described can tiltrotor aircraft 100 provide upward Lift, the big I of the buoyancy that the utricule 110 is provided is adjusted according to the species and amount of the gas being filled with the utricule 110 It is whole.The Design of Aerodynamic Configuration of the utricule 110, the i.e. design of the utricule 110 with streamlined cone-shaped upper surface so that the capsule Body 110 is in horizontal movement with the lift produced when being moved in atmosphere similar to fixed-wing.The material of utricule 110 is generally selected With the flexible material of high intensity, for example, from high-tenacity polyethylene fibre, polyarylate fiber etc..

The neighboring area of utricule 110 includes being through to from the upper surface multiple ducts 111 of the lower surface, wherein, The duct 111 includes the side wall for sealing the utricule 110 so that the duct 111 is upper and lower through the utricule 110 The air-tightness of the utricule 110 is not destroyed while two surfaces.Preferably, in the present embodiment can tiltrotor aircraft 100 include four ducts 111, and when four ducts 111 are located at the periphery of the utricule 110, it is on the bamboo hat-shaped capsule The central shaft of body 110 is arranged symmetrically so that the stress equalization of the utricule 110, it is easier to balance.The duct 111 axially cuts Face is circle, and the duct 111 axial length of the circular cross section diameter more than the duct 111, to install in it Rotor 130 adjust tilt angle after can expose from the upper and lower surface part of the utricule 110.It is appreciated that , the quantity of the duct 111 is not limited to four, but used as preferred embodiment, four ducts 111 can ensure institute State can the landing of tiltrotor aircraft 100, flight and carry out in the air more stable during pose adjustment.

Tiliting axis 120 is used for the connection and the support to each part on the rotor 130 of the rotor 130, and it includes Relative two ends, the relative two ends are separately fixed on the side wall in the duct 111, and the tiliting axis 120 arrange parallel to ground level.Preferably, the quantity of the multiple tiliting axis 120 corresponds to the quantity of the multiple duct, and And each tiliting axis 120 is correspondingly arranged in a duct 111, in the present embodiment, the axis phase of multiple tiliting axis 111 Mutually it is arranged in parallel.In follow-up embodiment, scheme of the present utility model is described for convenience, contained with 4 tiliting axis and 4 Road is specific example, it will be understood by those of skill in the art that for the tiliting axis and duct of other quantity, in this practicality Within new protection domain.

Rotor 130 includes：Support 131, motor 132 and propeller 133, wherein, the support 131 and the tiliting axis Connection is rotated between 120, for example, the support 131 is connected with the tiliting axis 120 by bearing, and rotation driving dress is installed additional Put so that the support 131 can be rotated or various angles of verting under the driving of the drive device around the tiliting axis 120 Degree.The motor 132 is fixed on the support 131, and the support 131 in the present embodiment is cylinder and is located at the cylinder Interior cross is combined, and the motor 132 is fixed on the cross center of the support 131.The propeller 133 with The motor 132 is connected, and the motor 132 can drive the propeller 133 to rotate.The quantity correspondence of the multiple rotor 130 In the quantity of the multiple duct 111, it is 4 for example to set quantity, and each rotor 130 correspondence is connected to a duct On the tiliting axis 120 in 111, it is preferred that axis of the rotation axis of the rotor 130 perpendicular to the tiliting axis 120.

In the present embodiment can tiltrotor aircraft 100 also include landing pad 140, the landing pad can select utricule 110 materials are made, and it includes plenum space and load-bearing space.Wherein, it is less than air filled with density inside the plenum space Gas, for example, hydrogen or helium, it is described can be during the landing of tiltrotor aircraft 100, the landing pad 140 can be played The effect of buffering, make it is described can the landing of tiltrotor aircraft 100 more stablize.The load-bearing space is used to load device, The device be, for example, including battery and Aerial Electronic Equipment, be it is described can tiltrotor aircraft 100 energy and control are provided.

It is understood that the present embodiment can be in tiltrotor aircraft 100, the tiliting axis 120 is a kind of main Connection for the rotor 130 and the support meanss to each member supporting on the rotor 130, the support meanss are not limited In the shaft-like structure using tiliting axis 120 in the present embodiment, the support meanss of other structures are can also be, for example, rigid ten Cabinet frame, tubular structure etc..

In the present embodiment can tiltrotor aircraft 100 when taking off, it is in the first state of flight, i.e., described four The rotation axis of the rotor 130 in duct 111 refer to Fig. 1 to Fig. 5 perpendicular to the state of ground level, and Fig. 1 to Fig. 5 shows Go out according to the utility model specific embodiment can the front view of the first state of flight of tiltrotor aircraft 100, side view, Line AA in top view, upward view and sectional view, wherein Fig. 3 shows the interception position of sectional view.As it was previously stated, the utricule The big I of 110 buoyancy for providing is adjusted according to the species and amount of the gas being filled with the utricule 110, in the present embodiment The lift that the low density gas gas of air (density less than) in the utricule 110 is provided substantially with it is described can tilting rotor fly The gross weight of row device 100 maintains an equal level, when taking off, by the tilt angle for adjusting the rotor 130 so that the rotation of four rotors 130 Perpendicular to ground level, the motor 132 drives the propeller 133 to rotate and the rotor 130 is inclined for described shaft axis Rotate rotor aircraft 100 provide lift, due to low density gas provide lift substantially with it is described can tiltrotor aircraft 100 Gross weight maintains an equal level, so the lift only small part that the acting of the rotor 130 is provided is used to balance fuselage gross weight, is mostly used in described Can tiltrotor aircraft 100 climb.Therefore, taking off and climbing the stage, advantageously reducing power-supply system to the defeated of motor Go out, reach the effect of energy-conservation.

In the present embodiment can tiltrotor aircraft 100 hovering when, it is still within the first state of flight, i.e., described State of the rotation axis of the rotor 130 in four ducts 111 perpendicular to ground level.Referring to figs. 1 to Fig. 5, due to described The buoyancy that utricule 110 is provided be slightly less than it is described can the gross weight of tiltrotor aircraft 100, so the rotor 130 is needed only provide for A small amount of lift come maintain it is described can the vertical direction of tiltrotor aircraft 100 balance, reduce energy consumption, improve boat so as to reach When purpose.

In the present embodiment can tiltrotor aircraft 100 in horizontal movement, it is in the second state of flight, i.e., described The rotation axis of the rotor 130 in four ducts 111 refer to Fig. 6 to Fig. 9, Fig. 6 to figure parallel to the state of ground level 9 show according to the utility model specific embodiment can tiltrotor aircraft 100 the second state of flight front view, side-looking Figure, top view and upward view.It is described can 100 horizontal movement of tiltrotor aircraft when, the type face that its utricule 110 has sets Be calculated as its and aerodynamic lift be provided, the buoyancy provided in vertical direction and utricule 110 jointly with it is described can tiltrotor aircraft 100 Gross weight is balanced.Now, the tilt angle of the rotor 130 is adjusted so that the rotor 130 is from the upper surface of the utricule 110 Expose with bottom surface section, and preferably, the rotation axis of four rotors 130 is parallel to ground level so that the rotation The wing 130 for it is described can tiltrotor aircraft 100 horizontal thrust is provided, in the vertical direction, it is described can tiltrotor aircraft 100 no longer need the rotor 130 to provide lift, four rotors 130 acting can be completely used for for it is described can tilting rotor Aircraft 100 provide horizontal movement thrust so that it is described can tiltrotor aircraft 100 flying speed faster, during continuation of the journey Between it is longer.

In the present embodiment can tiltrotor aircraft 100 need to gesture in motion process adjustment when, can adjust The tilt angle and rotating speed of four rotors 130, so as to the adjustment of attitude such as realize turning to, roll.

In the present embodiment can tiltrotor aircraft 100 landing when, it is changed into the first state of flight again, i.e., described four The rotation axis of the rotor 130 in individual duct 111 can adjust institute perpendicular to the state of ground level according to landing needs State four rotating speeds of rotor 130, make can the gross weight of tiltrotor aircraft 100 more than the buoyancy and described that the utricule 110 is provided The lift sum that rotor 130 is produced, thus realize it is described can tiltrotor aircraft 100 landing.

It should be noted that herein, such as first and second or the like relational terms are used merely to a reality Body or operation make a distinction with another entity or operation, and not necessarily require or imply these entities or deposited between operating In any this actual relation or order.And, term " including ", "comprising" or its any other variant be intended to Nonexcludability is included, so that process, method, article or equipment including a series of key elements not only will including those Element, but also other key elements including being not expressly set out, or also include being this process, method, article or equipment Intrinsic key element.In the absence of more restrictions, the key element limited by sentence "including a ...", it is not excluded that Also there is other identical element in process, method, article or equipment including the key element.

According to embodiment of the present utility model as described above, these embodiments do not have all of details of detailed descriptionthe, Also it is only described specific embodiment not limit the utility model.Obviously, as described above, many modifications and change can be made Change.This specification is chosen and specifically describes these embodiments, is to preferably explain that principle of the present utility model and reality should With so that skilled artisan can repairing using the utility model and on the basis of the utility model well Change and use.The utility model is only limited by claims and its four corner and equivalent.

Claims (10)

1. one kind can tiltrotor aircraft, it is characterised in that including：

Utricule, the utricule has upper and lower surface, and the utricule includes zone line and the week around the zone line Border area domain, the neighboring area of the utricule includes being through to from the upper surface multiple ducts of the lower surface, the duct Side wall including making the utricule sealing；

Support meanss, the support meanss are fixed in the duct of the utricule；

Rotor, the rotor is rotated with the support meanss and is connected.

2. according to claim 1 can tiltrotor aircraft, it is characterised in that the upper surface of the utricule is stream The conical surface of line style.

3. according to claim 1 can tiltrotor aircraft, it is characterised in that the duct cross section is circle, institute State the length of the circular cross section with diameter greater than the duct of duct.

4. according to claim 1 can tiltrotor aircraft, it is characterised in that the multiple duct is on the utricule Central shaft be arranged symmetrically.

5. according to claim 4 can tiltrotor aircraft, it is characterised in that the support meanss are verted for multiple Axle, each correspondence in the multiple tiliting axis is fixed in each in multiple ducts.

6. according to claim 5 can tiltrotor aircraft, it is characterised in that the diameter parallel of multiple tiliting axis Arrangement.

7. according to claim 6 can tiltrotor aircraft, it is characterised in that the rotation axis of the rotor perpendicular to The axis of the tiliting axis.

8. according to claim 1 can tiltrotor aircraft, it is characterised in that the rotor includes：

Support, the support is rotated with the support meanss and is connected；

Motor, the motor is fixed on the bracket；

Propeller, the propeller and the motor connection, the motor can drive the propeller rotational.

9. according to claim 1 can tiltrotor aircraft, it is characterised in that also include：

Landing pad, the landing pad is fixed on the lower surface of the utricule.

10. according to claim 9 can tiltrotor aircraft, it is characterised in that the landing pad includes：

Plenum space, the gas inside the plenum space filled with density less than air；

Load-bearing space, the load-bearing space is used to load device, and the device includes battery and Aerial Electronic Equipment.