CN108583912A - A kind of tail sitting posture unmanned vertical flight - Google Patents
A kind of tail sitting posture unmanned vertical flight Download PDFInfo
- Publication number
- CN108583912A CN108583912A CN201810081900.1A CN201810081900A CN108583912A CN 108583912 A CN108583912 A CN 108583912A CN 201810081900 A CN201810081900 A CN 201810081900A CN 108583912 A CN108583912 A CN 108583912A
- Authority
- CN
- China
- Prior art keywords
- propeller
- wing
- motor
- tail
- fuselage
- 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.)
- Withdrawn
Links
- 210000000988 bone and bone Anatomy 0.000 claims abstract description 21
- 230000010006 flight Effects 0.000 claims 3
- 238000012423 maintenance Methods 0.000 abstract description 3
- 230000001141 propulsive effect Effects 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 241000272517 Anseriformes Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000007373 indentation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/08—Stabilising surfaces mounted on, or supported by, wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of tail sitting posture unmanned vertical flight, including fuselage, the front of the fuselage is equipped with wing, the rear portion of the fuselage is set there are four empennage, the tail portion of the fuselage is equipped with telescopic tail bone, and the telescopic tail bone is located at the rear of four empennages, freight house is equipped in the fuselage, the wing is equipped with aileron, the present invention has higher propulsive efficiency, small, is readily disassembled maintenance, operational stability is good, and wind resistance is good.
Description
Technical field
The present invention relates to air vehicle technique fields, and in particular to a kind of tail sitting posture unmanned vertical flight.
Background technology
For unmanned plane due at low cost, safety is good, widely used, and traditional rotor class vehicle flight speeds are low, voyage
Short, single-rotor helicopter mechanical system is complicated；Although using the unmanned plane of tilted propeller or tilting rotor and tradition nobody
Machine is compared, and flying speed improves, and voyage extends, but needs complicated, bulky large torque inclining rotary mechanism, and some types need
Wing is wanted to vert together, this causes VTOL wind resistance poor, and when transition flight, wing is in advanced stall state, maneuverability
It is poor with stability；Tail sitting posture aircraft is whatsoever laid out, and propellerslip rudder is only leaned on when hovering to have the problem of maneuverability difference,
Especially normal arrangement and canard configuration are worse in VTOL stage wind resistance, and geometric dimension can be larger, and Flying-wing
In flat fly, stability is poor and trim scarce capacity.
Invention content
The purpose of the present invention is overcoming the shortcomings of in existing product, a kind of tail sitting posture unmanned vertical flight is provided.
In order to achieve the above object, the present invention is achieved by the following technical solutions：
The front of a kind of tail sitting posture unmanned vertical flight, including fuselage, the fuselage is equipped with wing, the fuselage
Rear portion set there are four empennage, the tail portion of the fuselage is equipped with telescopic tail bone, and the telescopic tail bone is located at four tails
The rear of the wing, the fuselage is interior to be equipped with freight house, and the wing is equipped with aileron, and the wing is equipped with the first power plant, described
First power plant includes propeller A, the first brshless DC motor, first motor governor, the first nothing of the propeller A connections
Brushless motor, first brshless DC motor connect first motor governor, and it is dynamic that four empennages are both provided with second
Power apparatus, second power plant include propeller B, the second brshless DC motor, the second machine governor, the propeller
B the second brshless DC motors of connection, second brshless DC motor connect the second machine governor, and propeller A is spacing paddle
Or variable-pitch propeller, propeller B is spacing paddle or folds paddle, and second brshless DC motor connects the second machine governor,
The second brshless DC motor connection propeller B, four empennage arrangements are in X-shaped, are designed on the end of four empennages
Elastic support is designed with control surface on four empennages.
The center line that aileron of the present invention extends length direction is parallel with the shaft of propeller, and the aileron extends rectangular
To center line and propeller the distance between shaft be less than propeller diameter length 1/10th.
The control surface of the present invention is located at the rear of four empennages.
Angle between two adjacent empennages of the present invention is 90 °.
The wing of the present invention is the wing of falling sea-gull.
Power plant of the present invention includes brshless DC motor, machine governor, and brshless DC motor connects machine governor.
The invention also includes spring, guide rod, the tail portion of fuselage is equipped with slot and through-hole, and spring pocket on the guide bar, is led
It is fixedly connected to one end of bar with telescopic tail bone, one end of guide rod is matched with slot, telescopic tail bone and through-hole
Interference fit.
Aileron of the present invention is located at the rear of wing.
Power plant arrangement in the power plant being arranged on wing and four empennages of the present invention is in M shape.
First power plant, the arrangement of the second power plant are in M shape.
Beneficial effects of the present invention are as follows：Power plant arrangement in the power plant being arranged on wing and four empennages
In M shape, propeller provides power by power plant so that aircraft has lower disk loading in VTOL, together
When in the cruising flight of wing carrying, there is higher propulsive efficiency, flying speed substantially increases；The rear portion of fuselage is equipped with
Four empennages, four empennage arrangements are in X-shaped, and the angle between adjacent two empennages is 90 °, reduces the size of aircraft so that
Structure is compacter, and number of components is few, small, is readily disassembled maintenance, and in the VTOL stage, four empennage arrangements are in
X-shaped, wind resistance is good, and the operational stability in flat winged cruise is good；The tail portion of fuselage is equipped with telescopic tail bone, in VTOL
Or ground can also take on damper leg when landing and use when parking inside indentation endpiece；It is stretched out when flat winged, ensures fuselage endpiece
Smooth transition, to reduce the pressure drag of fuselage, operational stability is good.Wing is the wing of falling sea-gull so that realizes wing or so
The barycenter that the plane that the symmetry axis of both sides propeller and the axis of shaft are constituted passes through aircraft so that hang and VTOL
When be easier so that the propeller B load on wing on propeller A and empennage tends to be equal, to be designed on the end of four empennages
Elastic support so that slow down when the contact ground of aircraft and play cushioning effect, substantially increase safety；On four empennages all
Equipped with control surface so that more stablize when taking off, assisted diversion so that turn to and more stablize；When putting down winged when cruise, using wing
Carrying flight, lift resistance ratio is big, and can reach quick cruise, small power consumption with lower power consumption.
Description of the drawings
Fig. 1 is a kind of dimensional structure diagram of state of the present invention；
Fig. 2 is the partial enlarged view at I position of Fig. 1；
Fig. 3 is the dimensional structure diagram of another state of the present invention；
Fig. 4 is the schematic cross-sectional view of the fuselage of the present invention；
Fig. 5 is the partial enlarged view at II position of Fig. 4.
Specific implementation mode
Technical scheme of the present invention is described further with reference to the accompanying drawings of the specification：
As shown in Fig. 1 to Fig. 5, a kind of tail sitting posture unmanned vertical flight, including fuselage 1, the front of the fuselage 1
Equipped with wing 2, the rear portion of the fuselage 1 is set there are four empennage 3, and the tail portion of the fuselage 1 is described equipped with telescopic tail bone 4
Telescopic tail bone 4 is located at the rear of four empennages 3, and freight house 11 is equipped in the fuselage 1, and the wing 2 is equipped with aileron 21,
The wing 2 is equipped with the first power plant, and first power plant includes propeller A5, the first brshless DC motor 6, first
Machine governor 16, the first brshless DC motor of the propeller A5 connections 6, the connection of the first brshless DC motor 6 first
Machine governor 16, four empennages 3 are both provided with the second power plant, second power plant include propeller B15,
Second brshless DC motor 26, the second machine governor 36, the second brshless DC motor of the propeller B15 connections 26 are described
Second brshless DC motor 26 connects the second machine governor 36, and propeller A5 is spacing paddle or variable-pitch propeller, propeller B15
For spacing paddle or paddle is folded, second brshless DC motor connects the second machine governor, second brshless DC motor
Propeller B15 is connected, four arrangements of empennages 3 are in X-shaped, are designed with elastic support 32 on the end of four empennages 3, and described four
Control surface 31 is designed on a empennage 3.The center line that the aileron 21 extends length direction is parallel with the shaft of propeller 5, institute
It states aileron 21 and extends the distance between the center line of length direction and the shaft of propeller 5 are less than the diameter length of propeller 5 ten
/ mono-.Two blades on the propeller 5 that the diameter of propeller 5 refers to rotate the diameter of a circle to be formed.The control surface 31
In the rear of four empennages 3.Corner dimension between two adjacent empennages 3 is 90 °.The wing 2 is the machine of falling sea-gull
The wing.The invention also includes spring 7, guide rod 8, the tail portion of the fuselage 1 is equipped with slot 12 and through-hole 13, and the spring 7 is sleeved on
On guide rod 8, one end of the guide rod 8 is fixedly connected with telescopic tail bone 4, one end and the slot 12 of the guide rod 8
It matches, the telescopic tail bone 4 is interference fitted with through-hole 13.Aileron 21 is located at the rear of wing 2.First power plant,
Second power plant sees that arrangement is in M shape from front to back.
Power plant arrangement in the power plant being arranged on wing and four empennages is in M shape, and propeller passes through dynamic
Power apparatus provides power so that aircraft has lower disk loading in VTOL, while flying in the cruise of wing carrying
It in row, is carried and is flown using empennage, lift resistance ratio is big, and there is higher propulsive efficiency, flying speed to substantially increase, can be with relatively low
Power consumption reach quick cruise, therefore small power consumption；The rear portion of fuselage is set there are four empennage, and four empennage arrangements are adjacent in X-shaped
Angle between two empennages is 90 °, reduces the size of aircraft so that structure is compacter, and number of components is few, small, easily
In demolition and maintenance, the control and stability and the center of gravity scope of application in flat winged cruise are wider；And in VTOL stage, four tails
Wing arrangement is in X-shaped, and wind resistance is good, and the operational stability in flat winged cruise is good；The tail portion of fuselage is equipped with telescopic tail bone, bullet
Spring 7 is sleeved on guide rod 8, and one end of guide rod 8 is fixedly connected with telescopic tail bone 4, one end and 12 phase of slot of guide rod 8
Cooperation, telescopic tail bone 4 are interference fitted with through-hole 13.When VTOL or ground are parked or are landed, the tail portion of tail bone 4 by
To the effect on ground so that tail bone 4 is pressed onto fuselage interior by through-hole 13, takes on damper leg use, when putting down winged, by spring
Elastic force, which acts on, makes tail bone 4 protruding, ensures fuselage endpiece smoothness transition, to reduce the pressure drag of fuselage, stable operation
Property is good.Wing is the wing of falling sea-gull so that realizes that the symmetry axis of propeller and the axis of shaft are constituted flat at left and right sides of wing
The barycenter that face passes through aircraft so that the spiral shell so that on wing on propeller A and empennage is easier when hang and VTOL
Rotation paddle B load tends to be equal so that unmanned plane stability is good；It is designed with elastic support on the end of four empennages so that aircraft
Slow down when contacting ground and play cushioning effect, substantially increases safety；It is designed with control surface on four empennages so that take off
Shi Gengjia stablizes, assisted diversion so that turns to and more stablizes；When putting down winged when cruise, being carried and flown using wing, lift resistance ratio is big,
And quick cruise, small power consumption can be reached with lower power consumption.Aileron 21 extend the center line of length direction and propeller 5 shaft it
Between distance be less than propeller 5 diameter length 1/10th, aileron can be immersed in propellerslip so that aileron is more
Effective control airflow direction and speed.Power plant also serves as lift engine and propelling motor, and wing also serves as lifting surface, behaviour
Vertical face, engine cantilever, empennage also serve as stabilization, control surface, engine cantilever and undercarriage, realize zero deadweight substantially.
It should be noted that listed above is only a kind of specific embodiment of the present invention.It is clear that the invention is not restricted to
Upper embodiment, acceptable there are many deformations.In short, those skilled in the art can directly lead from present disclosure
All deformations for going out or associating, are considered as protection scope of the present invention.
Claims (8)
1. a kind of tail sitting posture unmanned vertical flight, including fuselage (1), which is characterized in that the front of the fuselage (1) is set
There are wing (2), the rear portion of the fuselage (1) to set there are four empennage (3), the tail portion of the fuselage (1) is equipped with telescopic tail bone
(4), the telescopic tail bone (4) is located at the rear of four empennages (3), and freight house (11), the machine are equipped in the fuselage (1)
The wing (2) is equipped with aileron (21), and the wing (2) is equipped with the first power plant, and first power plant includes propeller A
(5), the first brshless DC motor (6), first motor governor (16), the propeller A (5) connect the first brshless DC motor
(6), the first brshless DC motor (6) connection first motor governor (16), four empennages (3) are both provided with second
Power plant, second power plant include propeller B (15), the second brshless DC motor (26), the second machine governor
(36), the propeller B (15) connects the second brshless DC motor (26), the second brshless DC motor (26) connection second
Machine governor (36), propeller A (5) are spacing paddle or variable-pitch propeller, and propeller B (15) is spacing paddle or folding paddle, institute
It states the second brshless DC motor and connects the second machine governor, the second brshless DC motor connection rotation paddle B (15), four tails
The wing (3) arrangement is in X-shaped, is designed with elastic support (32) on the end of four empennages (3), on four empennages (3) all
Equipped with control surface (31).
2. a kind of tail sitting posture unmanned vertical flight according to claim 1, which is characterized in that aileron (21) edge
The center line in length direction is parallel with the shaft of propeller (5), and the aileron (21) extends the center line and spiral of length direction
The distance between shaft of paddle (5) is less than 1/10th of the diameter length of propeller (5).
3. a kind of tail sitting posture unmanned vertical flight according to claim 1, which is characterized in that the control surface (31)
Positioned at the rear of four empennages (3).
4. a kind of tail sitting posture unmanned vertical flight according to claim 1, which is characterized in that described adjacent two
Angle between empennage (3) is 90 °.
5. a kind of tail sitting posture unmanned vertical flight according to claim 1, which is characterized in that the wing (2) is
The wing of falling sea-gull.
6. a kind of more rotor tail sitting posture unmanned vertical flights according to claim 1, which is characterized in that further include bullet
The tail portion of spring (7), guide rod (8), the fuselage (1) is equipped with slot (12) and through-hole (13), and the spring (7) is sleeved on guide rod
(8) on, one end of the guide rod (8) is fixedly connected with telescopic tail bone (4), one end of the guide rod (8) and slot
(12) it matches, the telescopic tail bone (4) is interference fitted with through-hole (13).
7. a kind of more rotor tail sitting posture unmanned vertical flights according to claim 1, which is characterized in that the aileron
(21) it is located at the rear of wing (2).
8. a kind of more rotor tail sitting posture unmanned vertical flights according to claim 1, which is characterized in that described first
Power plant, the arrangement of the second power plant are in M shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810081900.1A CN108583912A (en) | 2018-01-29 | 2018-01-29 | A kind of tail sitting posture unmanned vertical flight |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810081900.1A CN108583912A (en) | 2018-01-29 | 2018-01-29 | A kind of tail sitting posture unmanned vertical flight |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108583912A true CN108583912A (en) | 2018-09-28 |
Family
ID=63608379
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810081900.1A Withdrawn CN108583912A (en) | 2018-01-29 | 2018-01-29 | A kind of tail sitting posture unmanned vertical flight |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108583912A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5289994A (en) * | 1989-10-10 | 1994-03-01 | Juan Del Campo Aguilera | Equipment carrying remote controlled aircraft |
| CN101353084A (en) * | 2008-09-05 | 2009-01-28 | 龙川 | Light aerobat capable of landing or taking-off vertically |
| US20120248259A1 (en) * | 2011-03-24 | 2012-10-04 | Mark Allan Page | Long endurance vertical takeoff and landing aircraft |
| CN204473127U (en) * | 2015-02-11 | 2015-07-15 | 浙江华东测绘地理信息有限公司 | Rear bikini aerial survey fixed-wing unmanned plane tail-pulley device |
| WO2017042291A1 (en) * | 2015-09-08 | 2017-03-16 | Swiss Aerobotics Ag | Aircraft for transport and delivery of payloads |
| CN106671402A (en) * | 2017-03-09 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Novel unmanned aerial vehicle (UAV) manufacturing method based on 3D printing technology |
| CN106864747A (en) * | 2017-03-03 | 2017-06-20 | 北京航空航天大学 | A kind of variant efficient small VUAV using distributed hybrid power |
| CN107521661A (en) * | 2017-09-03 | 2017-12-29 | 佛山市龙远科技有限公司 | A kind of rotatable more amphibious unmanned planes of power VTOL of wing |
| RU2641952C1 (en) * | 2016-09-12 | 2018-01-23 | Николай Павлович Сохи | Vertical take-off and landing aircraft |
-
2018
- 2018-01-29 CN CN201810081900.1A patent/CN108583912A/en not_active Withdrawn
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5289994A (en) * | 1989-10-10 | 1994-03-01 | Juan Del Campo Aguilera | Equipment carrying remote controlled aircraft |
| CN101353084A (en) * | 2008-09-05 | 2009-01-28 | 龙川 | Light aerobat capable of landing or taking-off vertically |
| US20120248259A1 (en) * | 2011-03-24 | 2012-10-04 | Mark Allan Page | Long endurance vertical takeoff and landing aircraft |
| CN204473127U (en) * | 2015-02-11 | 2015-07-15 | 浙江华东测绘地理信息有限公司 | Rear bikini aerial survey fixed-wing unmanned plane tail-pulley device |
| WO2017042291A1 (en) * | 2015-09-08 | 2017-03-16 | Swiss Aerobotics Ag | Aircraft for transport and delivery of payloads |
| RU2641952C1 (en) * | 2016-09-12 | 2018-01-23 | Николай Павлович Сохи | Vertical take-off and landing aircraft |
| CN106864747A (en) * | 2017-03-03 | 2017-06-20 | 北京航空航天大学 | A kind of variant efficient small VUAV using distributed hybrid power |
| CN106671402A (en) * | 2017-03-09 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Novel unmanned aerial vehicle (UAV) manufacturing method based on 3D printing technology |
| CN107521661A (en) * | 2017-09-03 | 2017-12-29 | 佛山市龙远科技有限公司 | A kind of rotatable more amphibious unmanned planes of power VTOL of wing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103144769B (en) | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct | |
| CN105059542B (en) | A kind of fixation chord endurance aircraft of VTOL | |
| CN107176286A (en) | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems | |
| CN106882371A (en) | A kind of hybrid tilting rotor wing unmanned aerial vehicle | |
| CN103963959B (en) | Based on Moving technology can floating type folded wing lifting body aircraft | |
| CN205440869U (en) | Fixed chord flight time aircraft of canard configuration of VTOL | |
| CN108001679A (en) | Three shrouded propeller power modes can VTOL fixed-wing unmanned vehicle | |
| CN106005395B (en) | The inclining rotary mechanism of wing can be hidden in | |
| CN106143895B (en) | Thrust type tilt rotor aircraft | |
| CN207208447U (en) | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems | |
| CN106218887A (en) | A kind of vertically taking off and landing flyer of distributed-power device layout | |
| CN103158856B (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| CN104058093A (en) | Novel tiltable rotor wing vertical take-off and landing plane | |
| CN106043696A (en) | Flying system for unmanned aerial vehicle | |
| CN105480416A (en) | Unmanned aerial vehicle with tilted rotors | |
| CN106240814A (en) | A kind of power-controlled tail sitting posture mixed layout vertically taking off and landing flyer | |
| CN106628162A (en) | Composite unmanned aerial vehicle | |
| CN204197290U (en) | A kind of novel tiltrotor aircraft | |
| CN109533319A (en) | A kind of tilting rotor unmanned vehicle structural system with the overlap joint wing | |
| CN206327567U (en) | A kind of compound unmanned vehicle | |
| CN208165273U (en) | A kind of tail sitting posture unmanned vertical flight | |
| CN107021208A (en) | The tail sitting posture VUAV and control method of a kind of utilization duct | |
| CN106628115A (en) | Four-duct flying-wing type unmanned aerial vehicle | |
| CN211281472U (en) | Duct tail sitting posture VTOL unmanned aerial vehicle | |
| CN108791873A (en) | A kind of file vector DCB Specimen electric vertical landing unmanned plane and its control method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20180928 |