CN105329441A - Combined four-shaft flying-wing aircraft - Google Patents
Combined four-shaft flying-wing aircraft Download PDFInfo
- Publication number
- CN105329441A CN105329441A CN201510855528.1A CN201510855528A CN105329441A CN 105329441 A CN105329441 A CN 105329441A CN 201510855528 A CN201510855528 A CN 201510855528A CN 105329441 A CN105329441 A CN 105329441A
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- Prior art keywords
- wing
- aircraft
- wing aircraft
- flying
- fuselage
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
A combined four-shaft flying-wing aircraft comprises a central column body, wherein two aircraft wings are symmetrically arranged on the central column body in the lateral direction, and a flying wing assembly I is arranged at a wing rib of each aircraft wing; the central column body is also provided with a front vertical fin and a rear vertical fin, which are perpendicular to the aircraft wing, a flying wing assembly II is installed on each vertical fin by virtue of a supporting rod, the center distance from the flying wing assembly II to the central column body is identical to that from the flying wing assembly I to the central column body, and the flying wing assembly II and the flying wing assembly I stay on a same plane. By adopting a variable structural flight mode combining four shafts and flying wings, the weaknesses that a four-shaft aircraft is large in power consumption and low in flight speed can be overcome, and the aircraft can be directly changed from the vertical takeoff to horizontal flight. The combined four-shaft flying-wing aircraft has characteristics of stable hovering and high aerodynamic efficiency of the flying wings, has a function of changing from vertical takeoff to horizontal flight and has excellent flight performance.
Description
Technical field
The present invention relates to a kind of vehicle technology field, particularly a kind of compound type four axle all-wing aircraft aircraft.
Background technology
At the aviation field of the world today, always very popular to the research of vertical takeoff and landing or short take-off and landing (STOL) aircraft.For the aircraft of this type, the advantage that it has general helicopter and fixed-wing not to possess.Aircraft can vertical takeoff and landing or short takeoff, thus less to the requirement of flying field, the carrier-borne aircraft that such as aircraft carrier is equipped, and now popularly still launches short takeoff.But along with succeeding in developing of F-35 fighter plane, the history of carrier-borne aircraft is set up one piece of monument.In addition, can the aircraft of vertical takeoff and landing, in General Aviation, also have huge market.Such as selected areas of China achieves the opening in field, low latitude now, is exactly a chance lured especially, but it is also proposed stricter requirement to the performance of aircraft simultaneously for Private Flight device businessman.
Study vertical takeoff and landing technology how to realize, will know how heavier-than-air aircraft flies.Aircraft flight needs to overcome two kinds of power-gravity and resistance.Gravity is by pneumatic of aircraft, and the vertical lift that namely wing and empennage produce balances; Resistance is then that the horizontal thrust provided by driving engine overcomes.The take-off process of normal aircraft be exactly aircraft under the promotion of driving engine, runway overcomes resistance to advancing slip race, wing is linear translational motion in atmosphere, and the air pressure difference utilizing specific aerofoil profile and state of flight to produce obtains lift.Along with the quickening of speed, lift is also increasing, and when the lift that sliding running velocity degree is large enough to make wing produce is greater than the weight of aircraft, aircraft just can leave ground lift-off and fly.Because the resistance that flies under certain conditions is much smaller than the weight of aircraft, so the flight of aircraft can realize holding up large weight with low thrust, namely thrust-weight ratio is less than 1, is a kind of labour-saving flying method.
As can be seen from the above, aircraft wants flight must overcome gravity, and omniplane is not owing to needing sliding race, just can not produce by wing the lift overcoming gravity.How could that realize the vertical takeoff and landing in original place on earth? can only have two kinds of methods, one is jet reaction, and one utilizes aerodynamic force.Use jet reaction to realize the more famous sparrow hawk formula having Britain of the aircraft of vertical takeoff and landing, Harrier realizes vertical takeoff and landing by the jet pipe of deflection driving engine." sparrow hawk " formula aircraft adopts the sweepback high mounted wing of band inverted diherdral, " flying horse " driving engine, 4 rotatable air nozzles of 0 ° ~ 98.5 ° are had before and after fuselage, dynamic lift needed for vertical takeoff and landing (VTOL), transition flight and orthodox flight and thrust are provided, wing tip, tail and head have jet reaction nozzle, for controlling the attitude of aircraft and improving stall performance." sparrow hawk " has that low-to-medium altitude performance is good, maneuverability, decentralized configuration, can in company with features such as battle line shift rapidly.Its disadvantage be when taking off vertically voyage and radius of action is little, bullet-loading capacity is little and land use time logistics support difficulty.
Find out thus, turn flat and fly in journey realizing aircraft vertical, physical construction and control principle are complicated all especially, cause system reliability lower, and meanwhile, existing aircraft flight performance is not enough, inadequate stability and safety.
Summary of the invention
The technical problem to be solved in the present invention is for the deficiencies in the prior art, proposes a kind of stability and safety, high maneuvering flight, can the compound type four axle all-wing aircraft aircraft of overstable landing.
The technical problem to be solved in the present invention is achieved through the following technical solutions, a kind of compound type four axle all-wing aircraft aircraft, be characterized in: comprise center mast fuselage, described center mast fuselage is arranged with two wings that left and right is arranged, the rib place of described two wings is provided with all-wing aircraft assembly
, described all-wing aircraft assembly
be arranged on wing by wing mount brackets; Described center mast fuselage is also provided with former and later two vertical fins arranged with wing vertical, described vertical fin is provided with all-wing aircraft assembly by strut bar
, described all-wing aircraft assembly
to width between centers and the all-wing aircraft assembly of center mast fuselage
width between centers to center mast fuselage is identical, and all-wing aircraft assembly
with all-wing aircraft assembly
be in same level.
The technical problem to be solved in the present invention can also be come to realize further by the following technical programs, described all-wing aircraft assembly
comprise wing motor and the motor-driven wing screw propeller of wing.
The technical problem to be solved in the present invention can also be come to realize further by the following technical programs, described all-wing aircraft assembly
comprise vertical fin motor and the motor-driven vertical fin screw propeller of vertical fin.
The technical problem to be solved in the present invention can also be come to realize further by the following technical programs, former and later two all-wing aircraft assemblies described
between connected by the connecting rod running through center mast fuselage.
The technical problem to be solved in the present invention can also be come to realize further by the following technical programs, and the top of described center mast fuselage is provided with head.
The technical problem to be solved in the present invention can also be come to realize further by the following technical programs, and described wing, vertical fin are equipped with alighting gear bottom the one end away from center mast fuselage.
Compared with prior art, stability and safety of the present invention, easy and simple to handle, reliability is very high, by all-wing aircraft assembly
be arranged on the rib place of wing, meanwhile, former and later two all-wing aircraft assemblies
between connected by the connecting rod running through center mast fuselage, adopt the structure changes offline mode that four axles mix with all-wing aircraft, compensate for four-axle aircraft consumption of current large, the shortcoming that flying speed is low, achieve vertical takeoff and landing and turn flat and fly.The present invention possesses the feature of the aerodynamic efficiency that hovering is stable and all-wing aircraft is higher, and vertical takeoff and landing turns the flat function flown to have made flying instrument standby, and has very outstanding airworthiness.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is the left TV structure schematic diagram of Fig. 1;
Fig. 3 is perspective view of the present invention;
Fig. 4 is all-wing aircraft assembly
structural representation;
Fig. 5 is all-wing aircraft assembly
structural representation.
Detailed description of the invention
A kind of compound type four axle all-wing aircraft aircraft, comprise center mast fuselage 9, described center mast fuselage 9 is arranged with two wings 1 that left and right is arranged, the rib place of described two wings 1 is provided with all-wing aircraft assembly
, described all-wing aircraft assembly
be arranged on wing 1 by wing mount brackets 2; Described center mast fuselage 9 is also provided with former and later two vertical fins 7 vertically disposed with wing 1, described vertical fin 7 is provided with all-wing aircraft assembly by strut bar 6
, described all-wing aircraft assembly
to width between centers and the all-wing aircraft assembly of center mast fuselage 9
width between centers to center mast fuselage 9 is identical, and all-wing aircraft assembly
with all-wing aircraft assembly
be in same level.Described center mast fuselage 9 is made up of side plate and dividing plate, and the retaining element of connecting rod is connected with glue with two dividing plates in center mast fuselage 9, and connecting rod, through retaining element, center mast fuselage 9 flies control platform parallel to the ground when hang.Wing 1 of the present invention is equipped with steering wheel, and steering wheel rocking arm is connected with the rudder pin on rudder face with other end by pipe link.Described four motors and rudder face can carry out mixing, and two rudder faces have in the same way or incorgruous two kinds of mode of motioies, jointly adjust with four motors the peaceful flight attitude flown that hovers, and complete the flight structure conversion of hanging down and playing and putting down and fly.Under floating state, wing 1 and the string of a musical instrument of vertical fin 7 and the oar plane orthogonal of screw propeller, put down when flying completely, the oar plane of four axles is perpendicular to the ground.Described center mast fuselage 9 is equipped with battery, flies control, receiver.Wherein four motors are connected with flying to control respectively by four electronic governors, and electricity is adjusted to and flies control power supply.Battery is the mechanical, electrical tune of rudder, feeding electric motors.
Described all-wing aircraft assembly
comprise the wing screw propeller 10 of wing motor 3 and wing motor 3 driving.Described all-wing aircraft assembly
comprise the vertical fin screw propeller 11 of vertical fin motor 5 and vertical fin motor 5 driving.Described wing motor 3, vertical fin motor 5 are identical brushless motor, symmetrically structure distribution, identical to four axle centre distances.The rotating speed of four motors can be differential.Motor is existing product T-MOTORMT2206, and on wing 1, two wing mount brackets 2 are connected with self threading pin with motor, and above vertical fin 7, two motor racks are connected with glue with motor rack connecting rod, and motor rack pipe link is through the pipe link retaining element in fuselage and realization is fixing.Four motors are identical to center mast fuselage 9 centre distance.Four screw propellers of four axis mechanisms are existing product 7 cun of three leaf oar, are divided into two positive oars and two anti-oars.Two, diagonal angle screw propeller rotation direction is identical, and adjacent two screw propeller rotation directions are contrary.
Former and later two all-wing aircraft assemblies described
between connected by the connecting rod running through center mast fuselage 9.Described vertical fin motor 5 is connected by two pipe links through fuselage, and two pipe links are simultaneously by two strut bars 6 on vertical fin 7 and center mast fuselage 9 common support.The top of described center mast fuselage 9 is provided with head 4.Described wing 1, vertical fin 7 are equipped with alighting gear 8 bottom the one end away from center mast fuselage 9.
Described aircraft operationally can be divided into the stage of taking off vertically, flat fly stage, hovering stage, landing period four-stage: take off vertically the stage: during standby for takeoff, placed by whole equipment level, oar plane is parallel to the ground.By starting four motors simultaneously, drive blade to rotate with certain speed, adjacent two screw propeller rotation directions are contrary.Controlling throttle steering wheel subsequently makes the electricity delivery volume of four driving engines constant, makes driving engine be in belt speed state, now controls four motor speeds basically identical, makes whole aerial reconnaissance machine people keep state of equilibrium; Eventually through the electricity delivery volume controlling throttle steering wheel increase driving engine, improve engine speed, make aircraft leave ground, complete taking off of aircraft.
Mission phase: running up in the flat process flown hanging down, by controlling the rotating speed of four rotors, realizing the pose adjustment of aerial reconnaissance machine people, enters and flatly flies state, and can realize the pitching of equipment, rolling, driftage.Concrete mode is: make four rotors be respectively rotor A, rotor B, rotor C and rotor D from the top clockwise direction; When controlling rotor A, rotor B, rotor C and rotor D and keeping constant speed rotation, aircraft is in put down and flies state; When control rotor A and C constant speed rotation, rotor B speedup, when rotor D slows down, aircraft verts to rotor D direction, realizes driftage.When control rotor B and rotor D constant speed rotation, rotor A(C) speedup, rotor C(A) slow down, simultaneously all-wing aircraft rudder face simultaneously downward (on) vert, aircraft completes (facing upward) action of bowing.When control rotor A and C together speedup, when rotor B and rotor D together slows down differential, all-wing aircraft rudder face deflects to different directions simultaneously, and whole aircraft completes rolling maneuver.
In the hovering stage: flat fly in the process of hovering conversion, keep rotor B and rotor D rotating speed constant, rotor C speedup, rotor A slows down, while all-wing aircraft rudder face upwards vert, complete the switching put down and fly to floating state.
Landing phases: in the process of landing, first aircraft completes the flat state flying to hovering and switches, and controls 4 rotors and keeps constant speed rotation, make aerial reconnaissance machine people keep state of equilibrium; Control the delivery that throttle steering wheel reduces motor gradually subsequently, the rotating speed of driving engine is declined gradually, until alighting gear 8 contacts to earth, aircraft lands.
Claims (6)
1. a compound type four axle all-wing aircraft aircraft, is characterized in that: comprise center mast fuselage, and described center mast fuselage is arranged with two wings that left and right is arranged, the rib place of described two wings is provided with all-wing aircraft assembly
, described all-wing aircraft assembly
be arranged on wing by wing mount brackets; Described center mast fuselage is also provided with former and later two vertical fins arranged with wing vertical, described vertical fin is provided with all-wing aircraft assembly by strut bar
, described all-wing aircraft assembly
to width between centers and the all-wing aircraft assembly of center mast fuselage
width between centers to center mast fuselage is identical, and all-wing aircraft assembly
with all-wing aircraft assembly
be in same level.
2. compound type four axle all-wing aircraft aircraft according to claim 1, is characterized in that: described all-wing aircraft assembly
comprise wing motor and the motor-driven wing screw propeller of wing.
3. compound type four axle all-wing aircraft aircraft according to claim 1, is characterized in that: described all-wing aircraft assembly
comprise vertical fin motor and the motor-driven vertical fin screw propeller of vertical fin.
4. compound type four axle all-wing aircraft aircraft according to claim 1, is characterized in that: former and later two all-wing aircraft assemblies described
between connected by the connecting rod running through center mast fuselage.
5. compound type four axle all-wing aircraft aircraft according to claim 1, is characterized in that: the top of described center mast fuselage is provided with head.
6. compound type four axle all-wing aircraft aircraft according to claim 1, is characterized in that: described wing, vertical fin are equipped with alighting gear bottom the one end away from center mast fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510855528.1A CN105329441B (en) | 2015-11-30 | 2015-11-30 | A kind of four axis all-wing aircraft aircraft of combined type |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510855528.1A CN105329441B (en) | 2015-11-30 | 2015-11-30 | A kind of four axis all-wing aircraft aircraft of combined type |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105329441A true CN105329441A (en) | 2016-02-17 |
| CN105329441B CN105329441B (en) | 2018-07-10 |
Family
ID=55280277
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510855528.1A Active CN105329441B (en) | 2015-11-30 | 2015-11-30 | A kind of four axis all-wing aircraft aircraft of combined type |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105329441B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043686A (en) * | 2016-07-18 | 2016-10-26 | 四川傲势乐翼科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| WO2018145355A1 (en) * | 2017-02-13 | 2018-08-16 | 深圳市龙云创新航空科技有限公司 | Vertical take-off and landing aircraft having fixed wings |
| CN108423167A (en) * | 2018-05-14 | 2018-08-21 | 南方科技大学 | Double-control system aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5516060A (en) * | 1993-03-29 | 1996-05-14 | Mcdonnell; William R. | Vertical take off and landing and horizontal flight aircraft |
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| CN203306226U (en) * | 2013-05-15 | 2013-11-27 | 曹建良 | Single-soldier vertical take-off and landing aircraft |
| CN205150230U (en) * | 2015-11-30 | 2016-04-13 | 保定维特瑞交通设施工程有限责任公司 | Modular four -axis all -wing aircraft aircraft |
-
2015
- 2015-11-30 CN CN201510855528.1A patent/CN105329441B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5516060A (en) * | 1993-03-29 | 1996-05-14 | Mcdonnell; William R. | Vertical take off and landing and horizontal flight aircraft |
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| CN203306226U (en) * | 2013-05-15 | 2013-11-27 | 曹建良 | Single-soldier vertical take-off and landing aircraft |
| CN205150230U (en) * | 2015-11-30 | 2016-04-13 | 保定维特瑞交通设施工程有限责任公司 | Modular four -axis all -wing aircraft aircraft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043686A (en) * | 2016-07-18 | 2016-10-26 | 四川傲势乐翼科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| WO2018145355A1 (en) * | 2017-02-13 | 2018-08-16 | 深圳市龙云创新航空科技有限公司 | Vertical take-off and landing aircraft having fixed wings |
| CN108423167A (en) * | 2018-05-14 | 2018-08-21 | 南方科技大学 | Double-control system aircraft |
| CN108423167B (en) * | 2018-05-14 | 2024-02-27 | 南方科技大学 | Dual control system aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105329441B (en) | 2018-07-10 |
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Address after: No. 893 Tengfei Road, Baoding Industrial Park, Baoding City, Hebei Province, 071000 Patentee after: Viterra Traffic Technology Co., Ltd. Address before: No. 893 Tengfei Road, Baoding Industrial Park, Baoding City, Hebei Province, 071000 Patentee before: Weichiduan Traffic Facility Engineering Co., Ltd., Baoding |
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Address after: 071899 room 323, building S5, No. 001, north of Baojing Road, Xiong County, Baoding City, Hebei Province Patentee after: Viterra Traffic Technology Co.,Ltd. Address before: No. 893 Tengfei Road, Baoding Industrial Park, Baoding City, Hebei Province, 071000 Patentee before: Viterra Traffic Technology Co.,Ltd. |
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