CN208165273U - A kind of tail sitting posture unmanned vertical flight - Google Patents
A kind of tail sitting posture unmanned vertical flight Download PDFInfo
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- CN208165273U CN208165273U CN201820143027.XU CN201820143027U CN208165273U CN 208165273 U CN208165273 U CN 208165273U CN 201820143027 U CN201820143027 U CN 201820143027U CN 208165273 U CN208165273 U CN 208165273U
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Abstract
The utility model 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, is equipped with freight house in the fuselage, the wing is equipped with aileron, the utility model propulsive efficiency with higher, it is small in size, it is readily disassembled maintenance, operational stability is good, and wind resistance is good.
Description
Technical field
The utility model relates to air vehicle technique fields, and in particular to a kind of tail sitting posture unmanned vertical flight.
Background technique
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 when hovering only leans on propellerslip rudder 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.
Utility model content
The purpose of the utility model is to overcome the deficiencies in existing product, provide a kind of unmanned VTOL flight of tail sitting posture
Device.
In order to achieve the above object, the utility model is achieved through 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 device, described
First power device includes propeller A, the first brshless DC motor, first motor governor, the first nothing of the propeller A connection
Brushless motor, first brshless DC motor connect first motor governor, and it is dynamic that four empennages are both provided with second
Power device, second power device include propeller B, the second brshless DC motor, the second machine governor, the propeller
B the second brshless DC motor 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,
Second brshless DC motor connects propeller B, and four empennage arrangements are in X-shaped, is designed on the end of four empennages
Elastic support is designed with control surface on four empennages.
The center line that aileron described in the utility model extends length direction is parallel with the shaft of propeller A, the aileron edge
The distance between the center line in length direction and the shaft of propeller A are less than 1/10th of the diameter length of propeller A.
The control surface of the utility model is located at the rear of four empennages.
Angle between adjacent two empennage of the utility model is 90 °.
The wing of the utility model is the wing of falling sea-gull.
The utility model power device includes brshless DC motor, machine governor, and brshless DC motor connects motor tune
Fast device.
The utility model further includes spring, guide rod, and the tail portion of fuselage is equipped with slot and through-hole, and spring pocket is in guide rod
On, one end of guide rod is fixedly connected with telescopic tail bone, and one end of guide rod is matched with slot, telescopic tail bone with
Through-hole interference fit.
The utility model aileron is located at the rear of wing.
Power device arrangement in the power device being arranged on wing of the utility model and four empennages is in M shape.
First power device, the arrangement of the second power device are in M shape.
The beneficial effects of the utility model are as follows：Power device in power device on wing and four empennages is set
Arrangement is in M shape, and propeller provides power by power device, so that aircraft has lower paddle disk in VTOL and carries
Lotus, while in the cruising flight of wing carrying, propulsive efficiency with higher, flying speed substantially increases；After fuselage
Portion is set there are four empennage, and it is in X-shaped that four empennages, which arrange, and the angle between two adjacent empennages is 90 °, reduces the ruler of aircraft
Very little, so that structure is more compact, number of components is few, small in size, is readily disassembled maintenance, and in VTOL stage, four tails
Wing arrangement is in X-shaped, and wind resistance is good, good in the flat operational stability flown when cruising；The tail portion of fuselage is equipped with telescopic tail bone,
It is pressed into inside endpiece when VTOL or ground are parked, damper leg can be also taken on when landing and is used；It stretches out, guarantees when flat winged
Fuselage endpiece smoothness transition, to reduce the pressure drag of fuselage, operational stability is good.Wing is the wing of falling sea-gull, so that realizing
The plane that the symmetry axis of propeller and the axis of shaft are constituted at left and right sides of wing by the mass center of aircraft so that hang and
It is easier when VTOL so that the propeller B load on wing on propeller A and empennage tends to be equal, the end of four empennages
It is designed with elastic support on end, so that slowing down when the contact ground of aircraft plays buffer function, substantially increases safety；Four
It is designed with control surface on a empennage, so that more stable when taking off, assisted diversion, so that turning to more stable；It puts down and flies when cruise
When, it is carried and is flown using wing, lift resistance ratio is big, and can reach quick cruise, small power consumption with lower power consumption.
Detailed description of the invention
Fig. 1 is a kind of schematic perspective view of state of the utility model；
Fig. 2 is the partial enlarged view at I position of Fig. 1；
Fig. 3 is the schematic perspective view of another state of the utility model；
Fig. 4 is the schematic cross-sectional view of the fuselage of the utility model；
Fig. 5 is the partial enlarged view at II position of Fig. 4.
Specific embodiment
The technical solution of the utility model 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 be equipped with the first power device, first power device include propeller A5, the first brshless DC motor 6,
First motor governor 16, the first brshless DC motor of the propeller A5 connection 6, first brshless DC motor 6 connect
First motor governor 16, four empennages 3 are both provided with the second power device, and second power device includes propeller
B15, the second brshless DC motor 26, the second machine governor 36, the second brshless DC motor of the propeller B15 connection 26,
Second brshless DC motor 26 connects the second machine governor 36, and propeller A5 is spacing paddle or variable-pitch propeller, spiral
Paddle B15 is spacing paddle or folds paddle, and second brshless DC motor connects the second machine governor, second brushless direct-current
Motor connects propeller B15, and four arrangements of empennage 3 are in X-shaped, is designed with elastic support 32 on the end of four empennages 3,
Control surface 31 is designed on four empennages 3.The aileron 21 extends the center line of length direction and the shaft phase of propeller A5
In parallel, the aileron 21 extends the diameter that the distance between the center line of length direction and the shaft of propeller A5 are less than propeller A5
/ 10th of length.Two blades on the propeller A5 that the diameter of propeller A5 refers to rotate the diameter of a circle to be formed.It is described
Control surface 31 is located at the rear of four empennages 3.Corner dimension between two adjacent empennages 3 is 90 °.The wing 2
For the wing of falling sea-gull.The utility model further includes spring 7, guide rod 8, and the tail portion of the fuselage 1 is equipped with slot 12 and through-hole 13,
On guide rod 8, one end of the guide rod 8 is fixedly connected 7 sets of the spring with telescopic tail bone 4, the guide rod 8
One end is matched with slot 12, and the telescopic tail bone 4 is interference fitted with through-hole 13.Aileron 21 is located at the rear of wing 2.The
One power device, the second power device see arrangement in M shape from front to back.
Power device arrangement in power device on wing and four empennages is set in M shape, propeller passes through dynamic
Power device provides power, so that aircraft has lower disk loading in VTOL, while flying in the cruise of wing carrying
In row, is carried and flown using empennage, lift resistance ratio is big, and propulsive efficiency with higher, flying speed substantially increases, can be with lower
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 more compact, number of components is few, small in size, easily
It is wider in the flat control and stability flown when cruising and the center of gravity scope of application in demolition and maintenance；And in VTOL stage, four tails
Wing arrangement is in X-shaped, and wind resistance is good, good in the flat operational stability flown when cruising；The tail portion of fuselage is equipped with telescopic tail bone, bullet
7 sets of spring on guide rod 8, 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, take on damper leg use, when putting down winged, by bullet
Spring force acts on so that tail bone 4 is protruding, and guarantee fuselage endpiece smoothness transition, to reduce the pressure drag of fuselage, operation is steady
It is qualitative good.Wing is the wing of falling sea-gull, so that realizing what the symmetry axis of wing left and right sides propeller and the axis of shaft were constituted
Plane is by the mass center of aircraft, so that being easier when hang and VTOL so that on wing on propeller A and empennage
Propeller 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
Contact ground when slow down play buffer function, substantially increase safety；It is designed with control surface on four empennages, so that rising
It is more stable when winged, assisted diversion, so that turning to more stable；When putting down winged when cruise, is carried and flown using wing, lift resistance ratio
Greatly, and quick cruise, small power consumption can be reached with lower power consumption.Aileron 21 extends the center line of length direction and turning for propeller A5
/ 10th of diameter length of the distance between the axis less than propeller A5, aileron can be immersed in propellerslip, so that
Aileron more effectively controls airflow direction and speed.Power device also serves as lift engine and propelling motor, and wing also serves as liter
Power face, control surface, engine cantilever, empennage also serve as stabilization, control surface, engine cantilever and undercarriage, realize zero substantially
Deadweight.
It should be noted that listed above is only a kind of specific embodiment of the utility model.Obviously, the utility model
Above embodiments are not limited to, acceptable there are many deformations.In short, those skilled in the art can disclose from the utility model
Content all deformations for directly exporting or associate, be considered as the protection scope of the utility model.
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
Have 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 equipped with telescopic tail bone
(4), the telescopic tail bone (4) is located at the rear of four empennages (3), is equipped with freight house (11) in the fuselage (1), the machine
The wing (2) is equipped with aileron (21), and the wing (2) is equipped with the first power device, and first power device 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 device, second power device include propeller B (15), the second brshless DC motor (26), the second machine governor
(36), propeller B (15) connection 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, second brshless DC motor connects propeller B (15), and four
Empennage (3) arrangement is in X-shaped, is designed with elastic support (32) on the end of four empennages (3), on four empennages (3)
It is designed 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 A (5), and the aileron (21) extends the center line and spiral of length direction
The distance between shaft of paddle A (5) is less than 1/10th of the diameter length of propeller A (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 tail sitting posture unmanned vertical flight according to claim 1, which is characterized in that further include spring (7),
The tail portion of guide rod (8), the fuselage (1) is equipped with slot (12) and through-hole (13), and the spring (7) covers on guide rod (8),
One end of the guide rod (8) is fixedly connected with telescopic tail bone (4), one end and slot (12) phase of the guide rod (8)
Cooperation, the telescopic tail bone (4) and through-hole (13) are interference fitted.
7. a kind of tail sitting posture unmanned vertical flight according to claim 1, which is characterized in that aileron (21) position
In the rear of wing (2).
8. a kind of tail sitting posture unmanned vertical flight according to claim 1, which is characterized in that the first power dress
It sets, the arrangement of the second power device is in M shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820143027.XU CN208165273U (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 |
|---|---|---|---|
| CN201820143027.XU CN208165273U (en) | 2018-01-29 | 2018-01-29 | A kind of tail sitting posture unmanned vertical flight |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208165273U true CN208165273U (en) | 2018-11-30 |
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ID=64384078
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201820143027.XU Active CN208165273U (en) | 2018-01-29 | 2018-01-29 | A kind of tail sitting posture unmanned vertical flight |
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| CN (1) | CN208165273U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109795682A (en) * | 2018-12-10 | 2019-05-24 | 清华大学 | A kind of efficient tail sitting posture VTOL Fixed Wing AirVehicle and its control method |
| CN112722264A (en) * | 2021-01-12 | 2021-04-30 | 中国人民解放军国防科技大学 | Tail sitting type vertical take-off and landing unmanned aerial vehicle |
-
2018
- 2018-01-29 CN CN201820143027.XU patent/CN208165273U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109795682A (en) * | 2018-12-10 | 2019-05-24 | 清华大学 | A kind of efficient tail sitting posture VTOL Fixed Wing AirVehicle and its control method |
| CN112722264A (en) * | 2021-01-12 | 2021-04-30 | 中国人民解放军国防科技大学 | Tail sitting type vertical take-off and landing unmanned aerial vehicle |
| CN112722264B (en) * | 2021-01-12 | 2023-02-28 | 中国人民解放军国防科技大学 | Tail sitting type vertical take-off and landing unmanned aerial vehicle |
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