CN105329441B - A kind of four axis all-wing aircraft aircraft of combined type - Google Patents
A kind of four axis all-wing aircraft aircraft of combined type Download PDFInfo
- Publication number
- CN105329441B CN105329441B CN201510855528.1A CN201510855528A CN105329441B CN 105329441 B CN105329441 B CN 105329441B CN 201510855528 A CN201510855528 A CN 201510855528A CN 105329441 B CN105329441 B CN 105329441B
- Authority
- CN
- China
- Prior art keywords
- wing
- aircraft
- wing aircraft
- fuselage
- newel
- 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.)
- Active
Links
Classifications
-
- 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
-
- 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
-
- 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
-
- 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
Landscapes
- 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 kind of four axis all-wing aircraft aircraft of combined type including newel fuselage, is arranged with two wings of left and right settings, all-wing aircraft assembly is equipped at the rib of described two wings on the newel fuselage；It is additionally provided with former and later two vertical fins set with wing vertical on the newel fuselage, all-wing aircraft assembly is equipped with by supporting rod on the vertical fin, the all-wing aircraft assemblyTo the centre-to-centre spacing of newel fuselage and all-wing aircraft assemblyCentre-to-centre spacing to newel fuselage is identical, and all-wing aircraft assemblyWith all-wing aircraft assemblyIn same level.The structure changes offline mode that the present invention is mixed using four axis with all-wing aircraft, compensates for the shortcomings that four-axle aircraft power consumption is big, and flying speed is low, realizes VTOL and turns flat winged.The present invention has the characteristics of aerodynamic efficiency that hovering is stablized and all-wing aircraft is higher, and having made flying instrument standby, VTOL turns to equal winged function, and have very outstanding flying quality.
Description
Technical field
The present invention relates to a kind of vehicle technology field, particularly a kind of four axis all-wing aircraft aircraft of combined type.
Background technology
Aviation field in the world today is very popular always to the research of VTOL or short take-off and landing aircraft.
For the aircraft of this type, it has the advantages of general helicopter and fixed-wing do not have.Aircraft being capable of VTOL
Or short takeoff, it is now popular so as to the requirement carrier-borne aircraft that is smaller, such as being equipped on aircraft carrier to flying field
Or ejection short takeoff.But succeeding in developing with F-35 fighter planes, set up in the history of carrier-borne aircraft one piece it is rich
Upright stone tablet.Furthermore it is possible to the aircraft of VTOL, also possesses huge market in terms of General Aviation.Such as present China Partial
Area realizes the opening in low latitude field, is exactly a chance especially lured for private aircraft businessman, but simultaneously
It also proposed tightened up requirement to the performance of aircraft.
Study VTOL technology how is realized it is necessary to knowing how heavier-than-air aircraft flies.Fly
Machine flight needs to overcome two kinds of power-gravity and resistance.Gravity is the vertical of the pneumatic face by aircraft, i.e. wing and empennage generation
Lift balance；Resistance is then that the horizontal thrust provided by engine overcomes.The take-off process of normal aircraft is exactly that aircraft exists
Under the promotion of engine, resistance is overcome on runway to advancing slip race, wing linear translational motion in air utilizes specific aerofoil profile
Lift is obtained with the air pressure difference that state of flight generates.With the quickening of speed, lift is also increasing, when running speed is enough
When being more than the weight of aircraft to the lift for generating wing greatly, aircraft can leave ground lift-off and fly.Due to certain
Under conditions of the resistance that flies be much smaller than the weight of aircraft, so the flight of aircraft can be realized holds up big weight with low thrust,
Namely thrust-weight ratio is less than 1, is a kind of labour-saving flying method.
From the above it can be seen that aircraft must pull against gravity to flight, and VTOL aircraft slides race due to not needing to,
It is impossible to be overcome by wing generation the lift of gravity.How that could realize in situ VTOL on earthCan only have
Two methods, one kind are jet reactions, and one kind is to utilize air force.VTOL is realized using jet reaction
The more famous sparrow hawk formula for having Britain of aircraft, Harrier realize VTOL by deflecting the jet pipe of engine." sparrow hawk " formula
Aircraft uses the sweepback high mounted wing with inverted diherdral, and " flying horse " engine has 4 rotatable 0 °~98.5 ° before and after fuselage
Puff prot provides dynamic lift and thrust needed for vertical rise and fall, transition flight and orthodox flight, wing tip, tail and head
There is jet reaction nozzle, for controlling the posture of aircraft and improving stall performance." sparrow hawk " has that low-to-medium altitude performance is good, motor-driven spirit
The features such as living, be distributed, can rapidly being shifted in company with battle line.Its disadvantage be when taking off vertically voyage and radius of action it is small,
Bullet-loading capacity is small and logistics support is difficult during land use.
It is therefore seen that during realizing that aircraft vertical turns flat and flies, mechanical structure and control principle are all especially complex, make
It is relatively low into system reliability, meanwhile, existing aircraft flight performance is insufficient, is not sufficiently stable safety.
Invention content
The technical problem to be solved by the present invention is in view of the deficiencies of the prior art, propose that a kind of stable safety, height are motor-driven winged
Row, can overstable landing four axis all-wing aircraft aircraft of combined type.
The technical problem to be solved by the present invention is to what is be achieved through the following technical solutions, a kind of four axis all-wing aircraft of combined type flight
Device, its main feature is that：Including newel fuselage, it is arranged with two wings of left and right settings on the newel fuselage, described two
All-wing aircraft assembly is equipped at the rib of a wing, the all-wing aircraft assemblyIt is mounted on wing by wing mount brackets；The center
It is additionally provided with former and later two vertical fins set with wing vertical on column fuselage, all-wing aircraft assembly is equipped with by supporting rod on the vertical fin, the all-wing aircraft assemblyTo the centre-to-centre spacing of newel fuselage and all-wing aircraft assemblyCentre-to-centre spacing to newel fuselage is identical, and flies
Wing assemblyWith all-wing aircraft assemblyIn same level.
The technical problem to be solved in the present invention can also realize further by the following technical programs, the all-wing aircraft assemblyIncluding wing motor and the motor-driven wing propeller of wing.
The technical problem to be solved in the present invention can also realize further by the following technical programs, the all-wing aircraft assemblyIncluding vertical fin motor and the motor-driven vertical fin propeller of vertical fin.
The technical problem to be solved in the present invention can also realize further by the following technical programs, it is described former and later two
All-wing aircraft assemblyBetween connected by running through the connecting rod of newel fuselage.
The technical problem to be solved in the present invention can also realize further by the following technical programs, the newel machine
The top of body is equipped with head.
The technical problem to be solved in the present invention can also further realize that the wing hangs down by the following technical programs
One end bottom of the tail far from newel fuselage is equipped with undercarriage.
Compared with prior art, the present invention stablizes safety, and easy to operate, reliability is very high, by all-wing aircraft assemblyMounted on machine
At the rib of the wing, meanwhile, former and later two all-wing aircraft assembliesBetween connected by running through the connecting rod of newel fuselage, using four axis with
The structure changes offline mode of all-wing aircraft mixing, compensates for the shortcomings that four-axle aircraft power consumption is big, and flying speed is low, realizes vertical
Landing turns flat and flies.The present invention has the characteristics of aerodynamic efficiency that hovering is stablized and all-wing aircraft is higher, has made flying instrument standby and has hung down
Straight landing turns to equal winged function, and have very outstanding flying quality.
Description of the drawings
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is the left view structural representation of Fig. 1；
Fig. 3 is the dimensional structure diagram of the present invention；
Fig. 4 is all-wing aircraft assemblyStructure diagram；
Fig. 5 is all-wing aircraft assemblyStructure diagram.
Specific embodiment
A kind of four axis all-wing aircraft aircraft of combined type, including newel fuselage 9, a left side is arranged on the newel fuselage 9
Two wings 1 of right setting are equipped with all-wing aircraft assembly at the rib of described two wings 1, the all-wing aircraft assemblyPacified by wing
2 are shelved to be mounted on wing 1；Be additionally provided on the newel fuselage 9 with former and later two the vertically disposed vertical fins 7 of wing 1, it is described
All-wing aircraft assembly is equipped with by supporting rod 6 on vertical fin 7, the all-wing aircraft assemblyTo the centre-to-centre spacing and all-wing aircraft of newel fuselage 9
AssemblyCentre-to-centre spacing to newel fuselage 9 is identical, and all-wing aircraft assemblyWith all-wing aircraft assemblyIn same level.In described
Stem fuselage 9 is made of side plate and partition board, and the retaining element of connecting rod is connected with two partition boards in newel fuselage 9 with glue, connecting rod
It is parallel to the ground in hang to fly control platform across retaining element, on newel fuselage 9.Rudder is housed on the wing 1 of the present invention
Machine, steering engine rocking arm are connected by connecting rod with other end with the rudder foot on rudder face.Four motors can be mixed with rudder face
Control, two rudder faces have in the same direction or incorgruous two kinds of motor patterns, adjust the winged flight attitude of hovering peace jointly with four motors, and complete
Winged flight structure transformation is put down into hanging down to playing.Under floating state, wing 1 is vertical with the paddle plane of propeller with the string of a musical instrument of vertical fin 7,
When completely flat winged, the paddle plane of four axis is perpendicular to the ground.Equipped with battery, winged control, receiver on the newel fuselage 9.Wherein
Four motors are connected respectively by four electron speed regulators with flying control, and electricity, which is adjusted to, flies control power supply.Battery is the mechanical, electrical tune of rudder, motor
Power supply.
The all-wing aircraft assemblyThe wing propeller 10 driven including wing motor 3 and wing motor 3.The all-wing aircraft assemblyThe vertical fin propeller 11 driven including vertical fin motor 5 and vertical fin motor 5.The wing motor 3, vertical fin motor 5 are identical
Brushless motor, be distributed in symmetrical structure, to four axis centers apart from identical.The rotating speed of four motors can be differential.Motor is existing
There is a product T-MOTORMT2206, two wing mount brackets 2 are connected with motor with self threading pin on wing 1,7 two motors of top of vertical fin
Frame is connected with motor rack connecting rod with glue, and motor rack connecting rod passes through the connecting rod retaining element in fuselage and realizes fixation.Four
Motor is identical to 9 centre distance of newel fuselage.Four propellers of four axis mechanisms are 7 cun of three leaf paddle of existing product, are divided into two
A positive paddle and two anti-paddles.Diagonal two propeller rotation directions are identical, and two neighboring propeller is oppositely oriented.
Former and later two described all-wing aircraft assembliesBetween connected by running through the connecting rod of newel fuselage 9.The vertical fin electricity
Machine 5 is by passing through two connecting rods of fuselage to be connected, and two connecting rods are simultaneously by two supporting rods 6 and newel machine on vertical fin 7
Body 9 supports jointly.The top of the newel fuselage 9 is equipped with head 4.The wing 1, vertical fin 7 far from newel fuselage 9 one
End bottom is equipped with undercarriage 8.
The aircraft can be divided into the stage of taking off vertically, flat winged stage, hovering stage, landing period four at work
A stage：It takes off vertically the stage：During standby for takeoff, whole equipment is horizontal positioned, paddle plane is parallel to the ground.By opening simultaneously
Four motors are moved, driving blade is rotated with certain speed, and two neighboring propeller is oppositely oriented.Then control throttle steering engine makes
The electricity supply amount of four engines is constant, and engine is made to be in belt speed state, controls four motor speeds basically identical at this time,
Entire aerial reconnaissance machine people is made to keep equilibrium state；Increase the electricity supply amount of engine eventually by control throttle steering engine,
Engine speed is improved, aircraft is made to leave ground, completes taking off for aircraft.
Mission phase：During having hung down and turning flat and fly, pass through the rotating speed for controlling four rotors, realize aerial reconnaissance machine
The pose adjustment of people into flat winged state, and can realize the pitching, rolling, yaw of equipment.Concrete mode is：Enable four rotors
It is respectively rotor A, rotor B, rotor C and rotor D clockwise from the top；When control rotor A, rotor B, rotor C and rotation
When wing D keeps constant speed rotation, aircraft is in flat winged state；As control rotor A and C constant speed rotations, rotor B speedups, rotor D subtracts
When fast, aircraft verts to rotor D directions, realizes yaw.As control rotor B and rotor D constant speed rotations, rotor A（C）Increase
Speed, rotor C（A）Slow down, while all-wing aircraft rudder face is downward simultaneously（On）It verts, aircraft completion is bowed（It faces upward）Action.When control is revolved
Wing A speedups together with C, when rotor B slows down differential together with rotor D, while all-wing aircraft rudder face is deflected to different directions, entire to fly
Device completes rolling maneuver.
The hovering stage：It puts down during flying to hovering conversion, keeps rotor B and rotor D rotating speeds constant, rotor C
Speedup, rotor A slows down, while all-wing aircraft rudder face verts upwards, completes the flat switching for flying to floating state.
Landing phases：During landing, aircraft completes the flat state switching for flying to hovering first, controls 4 rotations
The wing keeps constant speed rotation, and aerial reconnaissance machine people is made to keep equilibrium state；Then control throttle steering engine continuously decreases the confession of motor
Electricity is gradually reduced the rotating speed of engine, until undercarriage 8 contacts to earth, aircraft lands.
Claims (5)
1. a kind of four axis all-wing aircraft aircraft of combined type, it is characterised in that：Including newel fuselage, it is equipped in the newel fuselage
Battery flies control, receiver, and two wings of left and right settings are arranged on the newel fuselage, rudder is housed on the wing
Machine, steering engine rocking arm are connected by connecting rod with other end with the rudder foot on rudder face, and all-wing aircraft is equipped at the rib of described two wings
Assembly I, the all-wing aircraft assembly I are mounted on by wing mount brackets on wing；It is additionally provided on the newel fuselage and hangs down with wing
Former and later two vertical fins directly set are equipped with all-wing aircraft assembly II on the vertical fin by supporting rod, and the all-wing aircraft assembly II is in
The centre-to-centre spacing of stem fuselage is identical with the centre-to-centre spacing of all-wing aircraft assembly I to newel fuselage, and at all-wing aircraft assembly II and all-wing aircraft assembly I
In in same level, connected between former and later two all-wing aircraft assemblies II by running through the connecting rod of newel fuselage.
2. four axis all-wing aircraft aircraft of combined type according to claim 1, it is characterised in that：The all-wing aircraft assembly I includes machine
Wing motor and the motor-driven wing propeller of wing.
3. four axis all-wing aircraft aircraft of combined type according to claim 1, it is characterised in that：The all-wing aircraft assembly II includes hanging down
Tail motor and the motor-driven vertical fin propeller of vertical fin.
4. four axis all-wing aircraft aircraft of combined type according to claim 1, it is characterised in that：The top of the newel fuselage
Equipped with head.
5. four axis all-wing aircraft aircraft of combined type according to claim 1, it is characterised in that：The wing, vertical fin are far from
One end bottom of stem fuselage is equipped with undercarriage.
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 CN105329441A (en) | 2016-02-17 |
| CN105329441B true 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) |
Families Citing this family (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 |
| CN206511122U (en) * | 2017-02-13 | 2017-09-22 | 深圳市龙云创新航空科技有限公司 | A kind of VTOL Fixed Wing AirVehicle |
| CN108423167B (en) * | 2018-05-14 | 2024-02-27 | 南方科技大学 | Dual control system aircraft |
Citations (3)
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
-
2015
- 2015-11-30 CN CN201510855528.1A patent/CN105329441B/en active Active
Patent Citations (3)
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105329441A (en) | 2016-02-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201923320U (en) | Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle | |
| US20200010182A1 (en) | Pivoting wing system for vtol aircraft | |
| JP2019517412A (en) | Vertical take-off and landing winged aircraft with complementary angled rotors | |
| CN108382579A (en) | A kind of new and effective tilting rotor unmanned vehicle | |
| CN106043696A (en) | Flying system for unmanned aerial vehicle | |
| CN106864746A (en) | It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula three | |
| CN204674831U (en) | Many fan arms aircraft | |
| CN103129737A (en) | Inclined fixed wing unmanned plane | |
| CN204998771U (en) | Aircraft of VTOL | |
| CN203332392U (en) | Tiltable-rotation type fixed-wing unmanned aerial vehicle | |
| CN106915459A (en) | A kind of hybrid tilting rotor wing unmanned aerial vehicle | |
| CN105083551A (en) | Tilt rotary-wing aircraft and control method thereof | |
| CN106938701A (en) | It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula four | |
| CN106927040A (en) | It is a kind of can VTOL the rotor tailless configuration aircraft of tailstock formula four | |
| CN106828918B (en) | Three-wing-surface vertical take-off and landing aircraft | |
| CN108791874A (en) | A kind of tilting duct power unmanned vehicle | |
| CN205998126U (en) | A kind of unmanned plane during flying system | |
| CN105329441B (en) | A kind of four axis all-wing aircraft aircraft of combined type | |
| CN107352029A (en) | A kind of electronic multiaxis tilting rotor wing unmanned aerial vehicle system | |
| CN109263932A (en) | A kind of multi-rotor aerocraft being vertically moved up or down | |
| CN105173076B (en) | A kind of vertical take-off and landing drone | |
| CN206187340U (en) | Aircraft | |
| CN106428524B (en) | A kind of multi-rotor aerocraft with the free wing | |
| CN106828919A (en) | It is a kind of can VTOL the coaxial Fan Jiang tailless configurations aircraft of tailstock formula | |
| CN205150230U (en) | Modular four -axis all -wing aircraft aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
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 |
|
| CP01 | Change in the name or title of a patent holder | ||
| CP02 | Change in the address of a patent holder |
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. |
|
| CP02 | Change in the address of a patent holder |