CN105882961A - High-speed aircraft capable of taking off and landing vertically as well as control method of high-speed aircraft - Google Patents
High-speed aircraft capable of taking off and landing vertically as well as control method of high-speed aircraft Download PDFInfo
- Publication number
- CN105882961A CN105882961A CN201610227947.5A CN201610227947A CN105882961A CN 105882961 A CN105882961 A CN 105882961A CN 201610227947 A CN201610227947 A CN 201610227947A CN 105882961 A CN105882961 A CN 105882961A
- Authority
- CN
- China
- Prior art keywords
- wing
- aircraft
- pulling force
- fuselage
- propeller
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention provides a high-speed aircraft capable of taking off and landing vertically as well as a control method of the high-speed aircraft. The high-speed aircraft adopts wings in the form of a joined wing, a middle propeller of a fuselage is mounted in the middle of front and back wings of the joined wing, compared with aircrafts such as V22 Osprey aircrafts and the like, the high-speed aircraft has the advantages that the propeller is not mounted or fixed on the wings, downward and backward wash flows of the propeller cannot sweep the wings in the flying process, so that aerodynamic interference between the wash flows of the propeller and the wings of the aircraft in the whole flying process is greatly reduced, smooth transition from vertical taking off and landing to high-speed forward flying of the aircraft can be realized, the safety coefficient of the aircraft is increased, and the practicability of the aircraft is improved; besides, the middle propeller is surrounded in the middle of the joined wing, and the propeller can be effectively prevented from being collided by ground objects at vertical taking off and landing stages, so that the taking off and landing safety is improved.
Description
Technical field
The present invention relates to aviation aircraft technical field, a kind of can the high-speed aircraft of VTOL and control thereof
Method.
Background technology
Could realize owing to the takeoff and landing of fixed wing airplane is required for certain ground run distance, it is therefore desirable to have and compare
Open landing field and longer runway.Building of landing site is the most expensive, time-consuming, and wartime is easily destroyed.Cause
This, people wish always a kind of can be at the aviation aircraft of small space landing.Along with the birth of helicopter, people
This demand obtain a certain degree of meet.But owing to helicopter is under front flying working environment, there is rotor gas
Flowing asymmetric situation, helicopter maximum forward flight speed is separated by advancing blade comperssibility influence and retreating blade air-flow
Limiting, the maximum cruise of pure helicopter is generally at about 300 kilometers/hour.In many occasions, speed becomes
The key factor of restriction helicopter application.
For a long time, Chinese scholars is seeking new technology thinking of development always untiringly, tries hard to create one novel
Aircraft, can either keep the advantage of the VTOL of helicopter, hovering and economy, can reach again fixed wing airplane
High-speed flight performance.Through exploration for many years with create practice and define and many not only can realize VTOL but also can be high
The technological means of speed flight.The ratio V-22 " osprey " of the more typical U.S., but owing to this kind of aircraft is under transition flight state
Kinetic stability is poor, and there is aerodynamic interference between strong rotor and wing their application prospect is received perhaps
The query of many people.Multi rack V-22 " osprey " is crashed more make it make the matter worse because of this problem.And " sparrow hawk formula " and the U.S.
F-35B this kind of can VTOL aircraft, utilize its powerful motor power and thrust deflexion control technology, it is achieved that
VTOL peace fly between conversion flight, but the highest to engine calls, there is also that VTOL efficiency is low and control
The shortcomings such as complexity processed is high, cost is high, are only applicable to military fighter aircraft, are not suitable for developing into light-small aircraft and nothing
People's aircraft.So make every effort to study a kind of novel pneumatic layout can the high-speed aircraft of VTOL to avoid above-mentioned flying
The shortcoming of machine thus be widely used and become a kind of demand.
Summary of the invention
Solve the technical problem that
For solving the problem that prior art exists, it is provided that a kind of have flying of preferable place adaptability and quick-reaction capability
Machine, the present invention propose a kind of can the high-speed aircraft of VTOL and control method thereof.
Technical scheme
The technical scheme is that
Technical scheme 1:
Described a kind of can the high-speed aircraft of VTOL, including fuselage, vertical tail and dynamical system；Vertical tail
It is arranged on fuselage afterbody；It is characterized in that: also include the connection wing；
The described connection wing is combined by front wing and rear wing；
Described front wing is with angle of sweep, and front wing is symmetrically mounted on fore-body both sides along the longitudinally asymmetric face of fuselage；
Described rear wing is with sweepforward angle, and rear wing is symmetrically installed along the longitudinally asymmetric face of fuselage, wherein pacifies in the middle part of rear wing
Being contained in vertical tail top, two ends of rear wing are fixed on front wing；
On the described connection wing, high lift device and rudder face are installed, vertical tail is provided with rudder face；
What described dynamical system included being arranged on waist both sides can tilted propeller and be arranged on the pitching of afterbody
Control tail-rotor；
Described can provide only pulling force upwards or pulling force forward by tilted propeller, it is also possible to provide upwards simultaneously
Pulling force and pulling force forward, it is also possible to pulling force upwards and pulling force backward are provided simultaneously；
Described pitch control tail-rotor can provide pulling force upwards or downward pulling force.
Technical scheme 2:
Described a kind of can the high-speed aircraft of VTOL, including fuselage, vertical tail and dynamical system；Vertical tail
It is arranged on fuselage afterbody；It is characterized in that: also include the connection wing；
The described connection wing is combined by front wing, rear wing and slab construction part；
Described front wing is with angle of sweep, and front wing is symmetrically mounted on fore-body both sides along the longitudinally asymmetric face of fuselage；
Described rear wing is with sweepforward angle, and rear wing is symmetrically installed along the longitudinally asymmetric face of fuselage, wherein pacifies in the middle part of rear wing
Being contained in vertical tail top, two ends of rear wing are fixed on front wing by slab construction part respectively；
On the described connection wing, high lift device and rudder face are installed, vertical tail is provided with rudder face；
What described dynamical system included being arranged on waist both sides can tilted propeller and be arranged on the pitching of afterbody
Control tail-rotor；
Described can provide only pulling force upwards or pulling force forward by tilted propeller, it is also possible to provide upwards simultaneously
Pulling force and pulling force forward, it is also possible to pulling force upwards and pulling force backward are provided simultaneously；
Described pitch control tail-rotor can provide pulling force upwards or downward pulling force.
Further preferred version, described a kind of can the high-speed aircraft of VTOL, it is characterised in that: slab construction
Part end is fixed at 50%～100% length of front wing.
Further preferred version, described a kind of can the high-speed aircraft of VTOL, it is characterised in that: rear wingtip
Portion is fixed at 50%～100% length of front wing.
Further preferred version, described a kind of can the high-speed aircraft of VTOL, it is characterised in that: couple on the wing
High lift device and rudder face are installed, vertical tail is provided with rudder face.
Further preferred version, described a kind of can the high-speed aircraft of VTOL, it is characterised in that: be arranged on machine
Can being connected by being perpendicular to the rotating shaft of longitudinally asymmetric of fuselage with fuselage by tilted propeller of both sides in the middle part of body, can vert spiral shell
Rotation oar oar face can rotate around described rotating shaft, and be provided with in rotating shaft control can tilted propeller oar face around described rotating shaft
The mechanism of the anglec of rotation.
Further preferred version, described a kind of can the high-speed aircraft of VTOL, it is characterised in that: be arranged on machine
The pitch control tail-rotor of body afterbody and fuselage are by being in longitudinally asymmetric of fuselage, and the installation parallel with fuselage datum
Pipe connects, and the oar axle of pitch control tail-rotor is perpendicular to install pipe, and is in longitudinally asymmetric of fuselage.
Further preferred version, described a kind of can the high-speed aircraft of VTOL, it is characterised in that: fuselage is in carefully
Long body, head is that low-resistance is avette, and afterbody shrinks and narrows.
Described a kind of can the control method of high-speed aircraft of VTOL, it is characterised in that:
Taking off and the vertical landing stage at aircraft vertical, the rolling of aircraft controls can be verted spiral by waist both sides
Oar provides different size of upwards pulling force to realize；The pitch control of aircraft is changed by the pitch control tail-rotor of afterbody
The size of pulling force and above-below direction realize；The driftage of aircraft controls can tilted propeller differential by waist both sides
Deflection realizes；
In aircraft transition stage, waist both sides can provide pulling force upwards and drawing forward by tilted propeller simultaneously
Power；The rolling of aircraft controls to provide different size of upwards pulling force by tilted propeller by waist both sides, and
Couple the control surface deflection on the wing to realize；The pitch control of aircraft changes pulling force by the pitch control tail-rotor of afterbody
Size and above-below direction, and couple the control surface deflection realization on the wing；The driftage of aircraft controls by waist both sides
Can the differential deflection of tilted propeller, and vertical tail control surface deflection realizes；
Fly the stage before aircraft, waist both sides can provide only pulling force forward by tilted propeller；The rolling of aircraft
Control to be realized by the rudder face coupling on the wing；The pitch control of aircraft realizes by coupling the control surface deflection on the wing；Aircraft
Driftage control realized by vertical tail control surface deflection.
Beneficial effect
The present invention propose a kind of can the aircraft of VTOL, compared to other open vertically taking off and landing flyer announced
For, wing centre position before and after the wing is coupled owing to using the wing coupling wing formula and waist propeller to be arranged on,
For the aircraft such as V22 " osprey ", because propeller is fitted without being fixed on wing, spiral shell in flight course
Rotation oar wash downwardly and rearwardly all will not scan on wing, thus greatly reduces propeller in whole flight course
Aerodynamic interference between wash and aircraft wing, can realize aircraft from VTOL to high speed before the smooth transition that flies, carry
The safety coefficient of high aircraft and practicality；And couple the wing and middle spiral oar is enclosed in centre, can effectively prevent
The touching to propeller of the VTOL stage ground object, thus improve landing safety.
The additional aspect of the present invention and advantage will part be given in the following description, and part will become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Accompanying drawing explanation
Above-mentioned and/or the additional aspect of the present invention and advantage are from combining the accompanying drawings below description to embodiment and will become
Substantially with easy to understand, wherein:
Fig. 1: embodiment 1 VTOL stage schematic diagram；
Stage schematic diagram is flown before Fig. 2: embodiment 1；
Fig. 3: embodiment 2 VTOL stage schematic diagram；
Stage schematic diagram is flown before Fig. 4: embodiment 2；
Fig. 5: embodiment 3 VTOL stage schematic diagram；
Stage schematic diagram is flown before Fig. 6: embodiment 3；
Fig. 7: embodiment 4 VTOL stage schematic diagram；
Stage schematic diagram is flown before Fig. 8: embodiment 4.
Wherein: 1, fuselage；2, front wing；3, slab construction part；4, can tilted propeller on the right side of waist；5、
Can tilted propeller on the left of waist；6, vertical tail；7, rear wing；8, pitch control propeller；9, turn
Axle.
Detailed description of the invention
Embodiments of the invention are described below in detail, and the example of described embodiment is shown in the drawings, the most from start to finish
Same or similar label represents same or similar element or has the element of same or like function.Below by ginseng
It is exemplary for examining the embodiment that accompanying drawing describes, it is intended to be used for explaining the present invention, and it is not intended that limit to the present invention
System.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " laterally ", " length ", " width
Degree ", " thickness ", " on ", D score, "front", "rear", "left", "right", " vertically ", " level ", " top ", " end ",
Orientation or the position relationship of the instruction such as " interior ", " outward ", " clockwise ", " counterclockwise " are based on orientation shown in the drawings or position
Put relation, be for only for ease of and describe the present invention and simplify description rather than instruction or the device of hint indication or element
Must have specific orientation, with specific azimuth configuration and operation, be therefore not considered as limiting the invention.
Example below be can the high speed unmanned proof machine design of VTOL, the design Gross Weight Takeoff of aircraft is
6kg；The conversion speed set is 500 meters as 15m/s, the flying height of transition status.
As depicted in figs. 1 and 2, design includes fuselage, vertical tail and dynamical system to embodiment 1；Fuselage cuts
Face maximum gauge is 0.2 meter, and in slender bodies, a length of 1.8m, head is that low-resistance is avette, and afterbody shrinks and narrows.
Fuselage interior includes mission payload, electrokinetic cell and flight control unit etc..
Vertical tail is arranged on fuselage afterbody, acts primarily as shipping-direction stability effect；Vertical fin area 0.06m2, wing root chord
Long 0.43m, wingtip chord length 0.27m, high 0.17m, leading edge sweep 33 °, torsion angle is 0 °, vertical tail afterbody
Rudder is installed.
The wing section of design uses and couples the wing, and the described connection wing is by front wing, rear wing and slab construction part
Combine.Described front wing is with angle of sweep, and front wing is symmetrically mounted on fore-body two along the longitudinally asymmetric face of fuselage
Side-lower.Described rear wing is with sweepforward angle, and rear wing is symmetrically installed along the longitudinally asymmetric face of fuselage, wherein in rear wing
Portion is arranged on vertical tail top, and two ends of rear wing are fixed on front wing by slab construction part respectively, flat
Component one end of hardening is connected with rear wing end, and the slab construction part other end is slightly connected with the front wing wing.In this embodiment,
Front wing area is 0.28m2, length is 1.44m, a length of 0.27m of wing root chord, and slightly root ratio is 0.45, leading-edge sweep
Angle is 25 °, and rear leading edge of a wing sweepforward angle is 17 °.On front wing and rear wing, high lift device and aileron are installed.
What this design medium power system included being arranged on waist both sides can tilted propeller and be arranged on fuselage tail
The pitch control tail-rotor in portion.In the present embodiment, propeller and tail-rotor all use motor-driven.
It is arranged on can connecting by being perpendicular to the rotating shaft of longitudinally asymmetric of fuselage by tilted propeller of waist both sides with fuselage
Connecing, and can rotate around described rotating shaft in tilted propeller oar face, being provided with control in rotating shaft can tilted propeller
Oar face is around the mechanism of the described rotating shaft anglec of rotation.According to flight requirement, can control can tilted propeller oar face around described
The anglec of rotation of rotating shaft, it is achieved pulling force upwards or pulling force forward can be provided only by tilted propeller, it is possible to realize simultaneously
Pulling force upwards and pulling force forward are provided, or pulling force upwards and pulling force backward are provided simultaneously.
The pitch control tail-rotor being arranged on afterbody is by being in longitudinally asymmetric of fuselage and vertical with fuselage with fuselage
The installation pipe connection that axle is parallel, the oar axle of pitch control tail-rotor is perpendicular to install pipe, and is in longitudinally asymmetric of fuselage.
According to flight requirement, pitch control propeller can be controlled and provide only pulling force upwards or downward pulling force.
Utilizing said structure, the control mode of the present embodiment is:
Take off and the vertical landing stage at aircraft vertical, if aircraft does not has a yawing rotation requirement, then waist both sides
Can provide only pulling force upwards by tilted propeller, the rolling of aircraft controls can be verted spiral by regulation waist both sides
The rotating speed of oar or pitch, thus provide different size of upwards pulling force and then formation rolling moment to realize；Bowing of aircraft
Face upward the pitch controlled by regulating afterbody pitch control tail-rotor, thus change pulling force size and above-below direction, and then
The pitching moment changing relative CG realizes；If aircraft has yawing rotation requirement, then can be inclined by waist both sides
The differential deflection of rotating propeller, i.e. waist side can provide pulling force upwards and drawing forward by tilted propeller simultaneously
Power, opposite side can provide pulling force upwards and pulling force backward by tilted propeller simultaneously, and then form yawing realization
Driftage controls.
In aircraft transition stage, waist both sides can provide pulling force upwards and drawing forward by tilted propeller simultaneously
Power；The rolling of aircraft control by regulation waist both sides can the rotating speed of tilted propeller or pitch, thus provide not
With upwards pulling force and then the formation rolling moment of size, simultaneously also by the control surface deflection coupled on the wing, produce rolling power
Square realizes；The pitch control of aircraft is by the pitch of the pitch control tail-rotor of regulation afterbody, thus changes pulling force
Size and Orientation, and then change the pitching moment of relative CG, simultaneously also by the control surface deflection coupled on the wing, produce
Raw pitching moment realizes；The driftage of aircraft controls to deflect generation by the differential of tilted propeller by waist both sides
Yawing, the most also produces yawing also by vertical tail control surface deflection and realizes.
Fly the stage before aircraft, waist both sides can provide only pulling force forward by tilted propeller；The rolling of aircraft
Control to produce rolling moment by the control surface deflection coupling on the wing to realize；The pitch control of aircraft is by coupling the rudder on the wing
Deflecting facet produces pitching moment and realizes；The driftage of aircraft controls to produce yawing by vertical tail control surface deflection and realizes.
In the present embodiment, the flight course of aircraft is: when taking off, and waist both sides can go to oar by tilted propeller
Planar horizontal position, starts propeller and makes aircraft vertical take off；When aircraft is liftoff reach safe altitude after, both sides, middle part
Can gradually tilt forward by tilted propeller, aircraft starts flight forward；Along with the continuous increase of propeller tilt angle,
Aircraft constantly accelerates, and couples the lift increase that the wing produces；When aircraft accelerates to reach conversion speed, now middle spiral oar
Verting to oar plane and fuselage datum upright position, coupling the wing provides flight required all lift；Along with airscrew thrust
Continuous increase, aircraft can realize high-speed flight；Here conversion speed is the velocity amplitude set when airplane design,
The whole lift needed for aircraft controllable flight and control power can have been produced at this flight speed lower link wing.At aircraft landing
Time, aircraft flight speed reduces, and waist both sides propeller gradually verts back oar planar horizontal position, aircraft entrance
Vertical landing pattern.
Embodiment 2 as shown in Figure 3 and Figure 4, the difference of this design and embodiment 1 be slab construction part another
End is connected at 50% length of front wing.
As shown in Figure 5 and Figure 6, the connection wing structure of this design is different from embodiment 1 for embodiment 3, the most flat
Harden component, but two ends of rear wing are directly slightly connected with the front wing wing, and rear wing has bigger inverted diherdral.
As shown in Figure 7 and Figure 8, the difference with embodiment 3 of this design is two of rear wing to embodiment 4
End is directly connected at 50% length of front wing.
In above-mentioned 4 embodiments, propeller is arranged between before and after's aerofoil, and in flight course, propeller is downwardly and rearwardly
Wash all will not scan on wing, thus substantially reduce the aerodynamic disturbance between propeller wash and wing.
Although above it has been shown and described that embodiments of the invention, it is to be understood that above-described embodiment is example
Property, it is impossible to be interpreted as limitation of the present invention, those of ordinary skill in the art without departing from the present invention principle and
Above-described embodiment can be changed within the scope of the invention in the case of objective, revise, replace and modification.
Claims (9)
1. can the high-speed aircraft of VTOL, including fuselage, vertical tail and dynamical system；Vertical tail is installed
At fuselage afterbody；It is characterized in that: also include the connection wing；
The described connection wing is combined by front wing and rear wing；
Described front wing is with angle of sweep, and front wing is symmetrically mounted on fore-body both sides along the longitudinally asymmetric face of fuselage；
Described rear wing is with sweepforward angle, and rear wing is symmetrically installed along the longitudinally asymmetric face of fuselage, wherein pacifies in the middle part of rear wing
Being contained in vertical tail top, two ends of rear wing are fixed on front wing；
On the described connection wing, high lift device and rudder face are installed, vertical tail is provided with rudder face；
What described dynamical system included being arranged on waist both sides can tilted propeller and be arranged on the pitching of afterbody
Control propeller；
Described can provide only pulling force upwards or pulling force forward by tilted propeller, it is also possible to provide upwards simultaneously
Pulling force and pulling force forward, it is also possible to pulling force upwards and pulling force backward are provided simultaneously；
Described pitch control propeller can provide pulling force upwards or downward pulling force.
2. can the high-speed aircraft of VTOL, including fuselage, vertical tail and dynamical system；Vertical tail is installed
At fuselage afterbody；It is characterized in that: also include the connection wing；
The described connection wing is combined by front wing, rear wing and slab construction part；
Described front wing is with angle of sweep, and front wing is symmetrically mounted on fore-body both sides along the longitudinally asymmetric face of fuselage；
Described rear wing is with sweepforward angle, and rear wing is symmetrically installed along the longitudinally asymmetric face of fuselage, wherein pacifies in the middle part of rear wing
Being contained in vertical tail top, two ends of rear wing are fixed on front wing by slab construction part respectively；
On the described connection wing, high lift device and rudder face are installed, vertical tail is provided with rudder face；
What described dynamical system included being arranged on waist both sides can tilted propeller and be arranged on the pitching of afterbody
Control propeller；
Described can provide only pulling force upwards or pulling force forward by tilted propeller, it is also possible to provide upwards simultaneously
Pulling force and pulling force forward, it is also possible to pulling force upwards and pulling force backward are provided simultaneously；
Described pitch control propeller can provide pulling force upwards or downward pulling force.
A kind of can the high-speed aircraft of VTOL, it is characterised in that: slab construction part end
Portion is fixed at 50%～100% length of front wing.
A kind of can the high-speed aircraft of VTOL, it is characterised in that: rear wing end is solid
It is scheduled at 50%～100% length of front wing.
5. according to Claims 1 to 4 arbitrary described a kind of can the high-speed aircraft of VTOL, it is characterised in that: couple the wing
On high lift device and rudder face are installed, vertical tail is provided with rudder face.
A kind of can the high-speed aircraft of VTOL, it is characterised in that: be arranged in fuselage
Can being connected by being perpendicular to the rotating shaft of longitudinally asymmetric of fuselage with fuselage by tilted propeller of both sides, portion, can vert spiral shell
Rotation oar oar face can rotate around described rotating shaft, and be provided with in rotating shaft control can tilted propeller oar face around described
The mechanism of the rotating shaft anglec of rotation.
A kind of can the high-speed aircraft of VTOL, it is characterised in that: be arranged on fuselage tail
The pitch control tail-rotor in portion and fuselage are by being in longitudinally asymmetric of fuselage, and the installation parallel with fuselage datum
Pipe connects, and the oar axle of pitch control tail-rotor is perpendicular to install pipe, and is in longitudinally asymmetric of fuselage.
8. according to Claims 1 to 4 arbitrary described a kind of can the high-speed aircraft of VTOL, it is characterised in that: fuselage in
Slender bodies, head is that low-resistance is avette, and afterbody shrinks and narrows.
9. one kind as claimed in claim 5 can the control method of high-speed aircraft of VTOL, it is characterised in that:
Taking off and the vertical landing stage at aircraft vertical, the rolling of aircraft controls can be verted spiral by waist both sides
Oar provides different size of upwards pulling force to realize；The pitch control of aircraft is changed by the pitch control tail-rotor of afterbody
The size of pulling force and above-below direction realize；The driftage of aircraft controls can tilted propeller differential by waist both sides
Deflection realizes；
In aircraft transition stage, waist both sides can provide pulling force upwards and drawing forward by tilted propeller simultaneously
Power；The rolling of aircraft controls to provide different size of upwards pulling force by tilted propeller by waist both sides, and
Couple the control surface deflection on the wing to realize；The pitch control of aircraft changes pulling force by the pitch control tail-rotor of afterbody
Size and above-below direction, and couple the control surface deflection realization on the wing；The driftage of aircraft controls by waist both sides
Can the differential deflection of tilted propeller, and vertical tail control surface deflection realizes；
Fly the stage before aircraft, waist both sides can provide only pulling force forward by tilted propeller；The rolling of aircraft
Control to be realized by the rudder face coupling on the wing；The pitch control of aircraft realizes by coupling the control surface deflection on the wing；Aircraft
Driftage control realized by vertical tail control surface deflection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610227947.5A CN105882961A (en) | 2016-04-13 | 2016-04-13 | High-speed aircraft capable of taking off and landing vertically as well as control method of high-speed aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610227947.5A CN105882961A (en) | 2016-04-13 | 2016-04-13 | High-speed aircraft capable of taking off and landing vertically as well as control method of high-speed aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105882961A true CN105882961A (en) | 2016-08-24 |
Family
ID=57013057
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610227947.5A Pending CN105882961A (en) | 2016-04-13 | 2016-04-13 | High-speed aircraft capable of taking off and landing vertically as well as control method of high-speed aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105882961A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106586001A (en) * | 2016-11-30 | 2017-04-26 | 中国电子科技集团公司第三十八研究所 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
| CN106828915A (en) * | 2017-03-15 | 2017-06-13 | 西北工业大学 | A kind of tilted propeller can VTOL high-speed aircraft and its flight control method |
| CN107010218A (en) * | 2017-06-01 | 2017-08-04 | 北京天宇新超航空科技有限公司 | A kind of Flying-wing's vertically taking off and landing flyer |
| CN108045575A (en) * | 2017-12-18 | 2018-05-18 | 刘行伟 | A kind of short takeoff vertical landing aircraft |
| CN108082466A (en) * | 2017-11-23 | 2018-05-29 | 北京航空航天大学 | A kind of tilting duct connection wing layout vertically taking off and landing flyer |
| CN111225853A (en) * | 2017-09-22 | 2020-06-02 | 艾姆索创新私人有限公司 | Wing tilt actuation system for electric vertical take-off and landing (VTOL) aircraft |
| CN111315655A (en) * | 2017-11-02 | 2020-06-19 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for air, water, land or space vehicles |
| CN112623186A (en) * | 2020-12-24 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Lift type statically stable airplane |
| CN113460297A (en) * | 2021-07-21 | 2021-10-01 | 成都纵横大鹏无人机科技有限公司 | Tilting power structure and system and aircraft |
| CN113859527A (en) * | 2021-09-06 | 2021-12-31 | 上海新云彩航空科技有限责任公司 | Box-type wing aircraft |
| CN116573179A (en) * | 2023-05-31 | 2023-08-11 | 北京航空航天大学云南创新研究院 | Box-type layout tilting rotor miniature unmanned aerial vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5503352A (en) * | 1991-11-27 | 1996-04-02 | Eger; Vladimir S. | Light-duty box-wing aeroplane |
| RU2082651C1 (en) * | 1995-08-09 | 1997-06-27 | Владимир Сергеевич Егер | Light flying vehicle |
| US5899410A (en) * | 1996-12-13 | 1999-05-04 | Mcdonnell Douglas Corporation | Aerodynamic body having coplanar joined wings |
| RU141669U1 (en) * | 2014-01-24 | 2014-06-10 | Закрытое Акционерное Общество "Транзас" | VERTICAL TAKEOFF AND LANDING FLIGHT |
| CN204264444U (en) * | 2014-11-05 | 2015-04-15 | 刘行伟 | Joined wing configuration aircraft during high lift length boat |
| WO2015200345A1 (en) * | 2014-06-24 | 2015-12-30 | Oliver Garreau | Five-wing aircraft to permit smooth transitions between vertical and horizontal flight |
-
2016
- 2016-04-13 CN CN201610227947.5A patent/CN105882961A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5503352A (en) * | 1991-11-27 | 1996-04-02 | Eger; Vladimir S. | Light-duty box-wing aeroplane |
| RU2082651C1 (en) * | 1995-08-09 | 1997-06-27 | Владимир Сергеевич Егер | Light flying vehicle |
| US5899410A (en) * | 1996-12-13 | 1999-05-04 | Mcdonnell Douglas Corporation | Aerodynamic body having coplanar joined wings |
| RU141669U1 (en) * | 2014-01-24 | 2014-06-10 | Закрытое Акционерное Общество "Транзас" | VERTICAL TAKEOFF AND LANDING FLIGHT |
| WO2015200345A1 (en) * | 2014-06-24 | 2015-12-30 | Oliver Garreau | Five-wing aircraft to permit smooth transitions between vertical and horizontal flight |
| CN204264444U (en) * | 2014-11-05 | 2015-04-15 | 刘行伟 | Joined wing configuration aircraft during high lift length boat |
Non-Patent Citations (1)
| Title |
|---|
| 温杰: "连载兰利研究中心的创新历程(之二) 追求高效率的连翼飞机", 《国际航空》 * |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106586001A (en) * | 2016-11-30 | 2017-04-26 | 中国电子科技集团公司第三十八研究所 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
| CN106828915B (en) * | 2017-03-15 | 2023-02-28 | 西北工业大学 | Control method of high-speed aircraft with tilting propeller capable of vertically taking off and landing |
| CN106828915A (en) * | 2017-03-15 | 2017-06-13 | 西北工业大学 | A kind of tilted propeller can VTOL high-speed aircraft and its flight control method |
| CN107010218A (en) * | 2017-06-01 | 2017-08-04 | 北京天宇新超航空科技有限公司 | A kind of Flying-wing's vertically taking off and landing flyer |
| CN111225853B (en) * | 2017-09-22 | 2024-04-05 | 艾姆索创新私人有限公司 | Wing pitch actuation system for an electric vertical take-off and landing (VTOL) aircraft |
| CN111225853A (en) * | 2017-09-22 | 2020-06-02 | 艾姆索创新私人有限公司 | Wing tilt actuation system for electric vertical take-off and landing (VTOL) aircraft |
| CN111315655A (en) * | 2017-11-02 | 2020-06-19 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for air, water, land or space vehicles |
| CN111315655B (en) * | 2017-11-02 | 2023-10-27 | 卡洛斯·塞萨尔·曼特罗拉·奥托内洛 | Assembly of three composite wings for an air, water, land or space vehicle |
| CN108082466A (en) * | 2017-11-23 | 2018-05-29 | 北京航空航天大学 | A kind of tilting duct connection wing layout vertically taking off and landing flyer |
| CN108045575B (en) * | 2017-12-18 | 2024-03-19 | 刘行伟 | Short-distance take-off vertical landing aircraft |
| CN108045575A (en) * | 2017-12-18 | 2018-05-18 | 刘行伟 | A kind of short takeoff vertical landing aircraft |
| CN112623186A (en) * | 2020-12-24 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Lift type statically stable airplane |
| CN113460297A (en) * | 2021-07-21 | 2021-10-01 | 成都纵横大鹏无人机科技有限公司 | Tilting power structure and system and aircraft |
| CN113859527A (en) * | 2021-09-06 | 2021-12-31 | 上海新云彩航空科技有限责任公司 | Box-type wing aircraft |
| CN113859527B (en) * | 2021-09-06 | 2024-04-23 | 上海新云彩航空科技有限责任公司 | Box type wing aircraft |
| CN116573179A (en) * | 2023-05-31 | 2023-08-11 | 北京航空航天大学云南创新研究院 | Box-type layout tilting rotor miniature unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105882961A (en) | High-speed aircraft capable of taking off and landing vertically as well as control method of high-speed aircraft | |
| US20200407060A1 (en) | Novel aircraft design using tandem wings and a distributed propulsion system | |
| CN105882959B (en) | It is capable of the flight equipment of VTOL | |
| CN205854492U (en) | A kind of dismountable tailstock formula VUAV | |
| CN201923320U (en) | Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle | |
| US4116405A (en) | Airplane | |
| CN205440867U (en) | But tilting wing aircraft | |
| US11673643B2 (en) | Low stall or minimum control speed aircraft | |
| CN101795939B (en) | Oblique blended wing body aircraft | |
| CN103448910A (en) | Aircraft capable of vertically taking off and landing at high speed | |
| CN102336267B (en) | Rotor blade airplane with variable flight mode | |
| CN104085532B (en) | A kind of control method of tilting rotor transport plane | |
| CN106892102A (en) | A kind of VUAV and its control method | |
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| CN107140179B (en) | A kind of tailstock formula tandem chord endurance aerodynamic configuration of aircraft | |
| CN105775117A (en) | Helicopter taking off and landing vertically and flying horizontally and application thereof | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN205022861U (en) | VTOL fixed wing aircraft | |
| CN103863563A (en) | Canard-configuration aircraft with vertical/short take-off and landing | |
| CN106628162A (en) | Composite unmanned aerial vehicle | |
| CN105818980A (en) | Novel large-lift-force vertical take-off and landing aircraft | |
| CN108045575A (en) | A kind of short takeoff vertical landing aircraft | |
| CN105346715A (en) | Vertical take-off and landing unmanned plane | |
| CN205738073U (en) | A kind of helicopter of VTOL horizontal flight | |
| CN105460215A (en) | Fixed-wing air vehicle achieving vertical or short-distance take-off and landing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160824 |
|
| WD01 | Invention patent application deemed withdrawn after publication |