CN106741852A - Tailplane and shipping unmanned plane with trim elevator high - Google Patents
Tailplane and shipping unmanned plane with trim elevator high Download PDFInfo
- Publication number
- CN106741852A CN106741852A CN201611125022.6A CN201611125022A CN106741852A CN 106741852 A CN106741852 A CN 106741852A CN 201611125022 A CN201611125022 A CN 201611125022A CN 106741852 A CN106741852 A CN 106741852A
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- tailplane
- elevator
- trim
- unmanned plane
- wing
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 6
- 238000013461 design Methods 0.000 abstract description 6
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
This application discloses a kind of tailplane and shipping unmanned plane with trim elevator high, belong to aircraft field, tailplane only one of which control rudder face, specially：The tailplane includes wing plate, and wing plate rear side is provided with the breach for installing elevator, and being rotatably connected in breach has elevator, and the elevator is upper surface radian and lower surface radian identical integral structure.Traditional elevator of left and right two is combined into an elevator by such design, only leaves a control rudder face, simplifies flight control system, and compared with the tailplane of prior art, trim ability is stronger.
Description
Technical field
The present invention relates to a kind of aircraft, more particularly to a kind of tailplane and shipping with trim elevator high nobody
Machine.
Background technology
Be mainly used in taking photo by plane in civil area unmanned plane at present, agricultural, plant protection, auto heterodyne, shipping, disaster relief, sight
Examine wild animal, monitoring infectious disease, mapping, news report, electric inspection process, the disaster relief, movies-making, manufacture romance etc. field.
With flourishing for Express Logistics industry, unmanned air vehicle technique is more and more applied to Express Logistics row, but
The tailplane and its elevator of shipping unmanned plane of the prior art are all traditional designs, are respectively had at tailplane trailing edge or so
One lifting rudder face, the design of traditional lifting rudder face handling good, the big advantage of aircraft turn angle that has aircraft is applicable
In most of field, but for shipping field, because the weight and flying speed of its aircraft change greatly, the rudder face control to unmanned plane
System requires that simple and stability is high, and requires relatively low for the handling of aircraft, and the elevator of conventional design cannot meet newly
The need for type shipping unmanned plane.
The content of the invention
In view of drawbacks described above of the prior art or deficiency, a kind of with trim elevator high present invention aim at providing
Tailplane and the unmanned plane equipped with tailplane.
Concrete technical scheme includes：A kind of tailplane with trim elevator high, the tailplane only one of which control
Rudder face processed, specially：The tailplane includes wing plate, and wing plate rear side is provided with breach for installing elevator, breach with can
The mode of rotation is provided with elevator, and the elevator is upper surface radian and lower surface radian identical integral structure, this
Traditional elevator of left and right two is combined into an elevator by the design of sample, only leaves a control rudder face, simplifies flight control
System processed, compared with the tailplane of prior art, trim ability is stronger.
A kind of preferred scheme：The tailplane is swept-back wing, and swept-back wing reduces relative air speed to a certain extent, is dropped
Low shock wave, makes wave resistance diminish, and is primarily adapted for use in flying speed than shipping unmanned plane faster.The aerofoil profile of the tailplane is
NACA0015, and be symmetrical airfoil structure, the horizontal specific parameter of tail is：Root chord length is L, and length is 4L, after 1/4 string of a musical instrument
The angle of sweep angle is 16 °, wherein, 1/4 string of a musical instrument is 0.25L, the length of described elevator is 3.2L, width be 0.23L~
0.24L.The gross area of the tailplane is 2.9L2, wherein, described elevator account for the tailplane gross area 24.3%~
24.8%.Above-mentioned wing dimension and the gold size that elevator size is the tailplane, according to hydrodynamics numerical computations,
Under this dimensions, the trim performance of tailplane reaches most preferably.The leading edge shape of the wingtip of the tailplane is shaped form,
By checking, this wingtip leading edge shape can weaken the influence of wingtip vortex, influence smaller to elevator pneumatic efficiency.And class
The elliptic systems tailplane wing is loaded with beneficial to Structural Strength Design.The scope of the elevator angle degree is -20 °~20 °, its
In, partially for just under elevator, it is upper be partially it is negative, it is such to can be designed so that tailplane on the premise of trim high is met, and also
With enough steering forces, make its scope of application wider.
Wherein, L represents length ratio, L2Relative expression area, due to the size of different size of aircraft tailplane
Difference, but under the model of identical tailplane, the ratio between each dimensional parameters of tailplane is identical, according to different aircrafts
Size L can take different numerical value, in this application, refer in particular to L=276mm.
Another preferred scheme：The tailplane is the straight wing, it is adaptable to the slower shipping unmanned plane of flying speed, is put down
The characteristics of straight wing is big wing area, makes aircraft airborne period long, straight for the slower shipping unmanned plane of flying speed
The wing more facilitates acquisition aerodynamic force.
Technical scheme also includes：A kind of unmanned plane equipped with tailplane, including fuselage, also including above-mentioned water
The horizontal tail wing, described tailplane is arranged on the afterbody of fuselage.If it is larger that shipping unmanned plane is responsible for shipping mass volume specially
During goods, when not high to aircraft flight rate request, the main wing and tailplane of the fuselage use the straight wing；If shipping nobody
Machine be responsible for specially shipping mass it is relatively light and higher to aircraft flight rate request when, the main wing and tailplane of the fuselage are equal
Using swept-back wing.
The established angle of described tailplane is 2 ° 30 '~3 ° 30 ', and shipping unmanned plane falls within transporter, so using T
The empennage layout of type, will tailplane be arranged on the top of vertical tail, and established angle refers to the edge phase of tailplane
For the angle that horizontal plane raises up, drawn by experiment repeatedly, under most of air speed, when the established angle of tailplane is for about
When 3 °, the influence of fuselage itself angle of attack and fuselage flow field to tailplane is counteracted.
The beneficial effects of the invention are as follows：
1. the elevator of tailplane of the present invention is integral type structure, considerably increases the trim ability of aircraft, is more fitted
For shipping unmanned plane.
2. the scope of elevator angle degree is -20 °~20 ° so that tailplane is gone back on the premise of trim high is met
With enough steering forces, make its scope of application wider.
3. the rational dimensions of tailplane, makes its trim performance splendid while taking into account good handling, more in fact
With.
Brief description of the drawings
By the detailed description made to non-limiting example made with reference to the following drawings of reading, the application other
Feature, objects and advantages will become more apparent upon：
Fig. 1 is the 3 dimensional drawing of the unmanned plane tailplane with elevator of example of the present invention.；
Fig. 2 is the top view of the unmanned plane tailplane with elevator of example of the present invention；
Fig. 3 is the longitudinal section of the tailplane of example of the present invention；
Fig. 4 is the elevator inflection point schematic diagram of example of the present invention；
Fig. 5 is that tailplane is produced in the different angles of attack and deflection angle in the case where setting angle is 3 ° of air speed 20m/s
Lift schematic diagram.
In figure：1. wing plate, 2. elevator, 3. width, 4. trailing edge, the 5. length of tailplane, the 6. length of elevator, 7.
Wingtip, 8. angle of sweep, 9. leading edge.
Specific embodiment
The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining related invention, rather than the restriction to the invention.It also should be noted that, in order to
It is easy to description, the part related to invention is illustrate only in accompanying drawing.
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the application can phase
Mutually combination.Describe the application in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Embodiment 1
As shown in Fig. 1 to Fig. 4, for the shipping unmanned plane of high-performance cruise, its Dead Weight Cargo quality is relatively light, so should
The main wing and tailplane of shipping unmanned plane use swept-back wing, wherein, tailplane is arranged on the top of afterbody vertical tail
Portion, established angle is 3 °, tailplane only one of which control rudder face, including wing plate 1, and the rear side of wing plate 1 is provided with for installing lifting
The breach of rudder, being rotatably connected in breach has elevator 2, and the elevator 2 is upper surface radian and lower surface radian identical
Integral structure, described elevator 2 is the integral structure for being shaped as rectangle.The root chord length of the tailplane is L, level
The length 5 of empennage is 4L, and tailplane is 16 degree from root to angle of sweep at the 0.8L along length 8.The exhibition of described elevator
Long 6 is 3.2L, width 3 is 0.225L.The gross area of the tailplane is 2.9L2, wherein, described elevator 2 accounts for level
The 24.6% of the empennage gross area.The leading edge 9 of the wingtip 7 of the tailplane is shaped as parabola shaped.The deflection angle of the elevator 2
Scope be -20 °~20 °, wherein, partially for just under elevator, upper is partially negative.
As shown in figure 5, along abscissa direction, representing the angle of attack of tailplane, along ordinate direction, tailplane is represented
Lift；In the case where the deflection angle of elevator is constant, the angle of attack more lift is bigger；In the case where the angle of attack is constant, lifting
Rudder kick angle is in the range of -20 °~20 °, and deflection angle more lift is bigger.
Embodiment 2
As shown in Fig. 1 to Fig. 4, for the shipping unmanned plane of high-performance cruise, its Dead Weight Cargo quality is relatively light, so should
The main wing and tailplane of shipping unmanned plane use swept-back wing, wherein, tailplane is arranged on the top of afterbody vertical tail
Portion, established angle is 2 ° 30 ', tailplane only one of which control rudder face, including wing plate 1, and the rear side of wing plate 1 is provided with for installing liter
The breach of rudder drops, being rotatably connected in breach has elevator 2, the elevator 2 is that upper surface radian is identical with lower surface radian
Integral structure, described elevator 2 is the integral structure for being shaped as rectangle.The root chord length of the tailplane is L, water
The length 5 of the horizontal tail wing is 4L, and tailplane is 16 degree from root to angle of sweep at the 0.8L along length 8.Described elevator
Length 6 is 3.2L, width 3 is 0.221L.The gross area of the tailplane is 2.9L2, wherein, described elevator 2 accounts for water
The 24.3% of the horizontal tail wing gross area.The leading edge 9 of the wingtip 7 of the tailplane is shaped as parabola shaped.The deflection angle of the elevator 2
The scope of degree is -20 °~20 °, wherein, partially for just, upper is partially negative under elevator.
Embodiment 3
As shown in Fig. 1 to Fig. 4, for the shipping unmanned plane of high-performance cruise, its Dead Weight Cargo quality is relatively light, so should
The main wing and tailplane of shipping unmanned plane use swept-back wing, wherein, tailplane is arranged on the top of afterbody vertical tail
Portion, established angle is 3 ° 30 ', tailplane only one of which control rudder face, including wing plate 1, and the rear side of wing plate 1 is provided with for installing liter
The breach of rudder drops, being rotatably connected in breach has elevator 2, the elevator 2 is that upper surface radian is identical with lower surface radian
Integral structure, described elevator 2 is the integral structure for being shaped as rectangle.The root chord length of the tailplane is L, water
The length 5 of the horizontal tail wing is 4L, and tailplane is 16 degree from root to angle of sweep at the 0.8L along length 8.Described elevator
Length 6 is 3.2L, width 3 is 0.229L.The gross area of the tailplane is 2.9L2, wherein, described elevator 2 accounts for water
The 24.8% of the horizontal tail wing gross area.The leading edge 9 of the wingtip 7 of the tailplane is shaped as parabola shaped.The deflection angle of the elevator 2
The scope of degree is -20 °~20 °, wherein, partially for just, upper is partially negative under elevator.
Embodiment 4
The shipping unmanned plane relatively low for flying speed, its loading capacity is larger, thus it is higher to aerodynamic force requirement, so should
The main wing and tailplane of shipping unmanned plane use the straight wing, wherein, the straight wing is arranged on the top of afterbody vertical tail,
And setting angle is 3 °.
It is worth noting that, the shipping unmanned plane scope of application described in embodiment 1~3 is wider, especially embodiment
1, and the shipping unmanned plane in embodiment 2 is applied to the very heavy article of shipping mass, it is actually used smaller.
Above description is only the preferred embodiment and the explanation to institute's application technology principle of the application.People in the art
Member is it should be appreciated that involved invention scope in the application, however it is not limited to the technology of the particular combination of above-mentioned technical characteristic
Scheme, while should also cover in the case where the inventive concept is not departed from, is carried out by above-mentioned technical characteristic or its equivalent feature
Other technical schemes for being combined and being formed.Such as features described above has similar work(with (but not limited to) disclosed herein
The technical scheme that the technical characteristic of energy is replaced mutually and formed.
Claims (10)
1. a kind of tailplane with trim elevator high, it is characterized in that, the tailplane includes wing plate, and wing plate rear side is provided with
Elevator is pivotally installed, elevator is rectangle and lacks with described in the breach for installing elevator, breach
The shape of mouth is adapted, and the elevator is upper surface radian and lower surface radian identical integral structure.
2. a kind of tailplane with trim elevator high according to claim 1, it is characterized in that, the tailplane is
Swept-back wing.
3. a kind of tailplane equipped with elevator according to claim 2, it is characterized in that, the aerofoil profile of the tailplane is
NACA0015, and be symmetrical airfoil structure.
4. a kind of tailplane with trim elevator high according to claim 3, it is characterized in that, the tailplane
Root chord length is L, and the length of described elevator is 3.2L, and the width of elevator is 0.22L~0.23L.
5. a kind of tailplane with trim elevator high according to claim 4, it is characterized in that, the tailplane
The gross area is 2.9L2, wherein, described elevator accounts for the 24.3%~24.8% of the tailplane gross area.
6. a kind of tailplane with trim elevator high according to claim 5, it is characterized in that, the tailplane
The leading edge shape of wingtip is shaped form.
7. a kind of tailplane with trim elevator high according to claim 6, it is characterized in that, the elevator is inclined
The scope of gyration is -20 °~20 °, wherein, partially for just, upper is partially negative under elevator.
8. a kind of tailplane equipped with elevator according to claim 1, it is characterized in that, the tailplane is straight
The wing.
9. a kind of shipping unmanned plane, including fuselage, it is characterized in that, also including the water described in any one in claim 1~8
The horizontal tail wing, described tailplane is arranged on the afterbody of fuselage.
10. a kind of shipping unmanned plane according to claim 9, it is characterized in that, the established angle of described tailplane is 2 °
30 '~3 ° 30 '.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611125022.6A CN106741852A (en) | 2016-12-08 | 2016-12-08 | Tailplane and shipping unmanned plane with trim elevator high |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611125022.6A CN106741852A (en) | 2016-12-08 | 2016-12-08 | Tailplane and shipping unmanned plane with trim elevator high |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106741852A true CN106741852A (en) | 2017-05-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611125022.6A Pending CN106741852A (en) | 2016-12-08 | 2016-12-08 | Tailplane and shipping unmanned plane with trim elevator high |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB524865A (en) * | 1939-01-27 | 1940-08-16 | Hendrik Martinus Arends | Improvements in the control surfaces of aircraft |
| CN1400141A (en) * | 2001-07-30 | 2003-03-05 | 罗专予 | Balancing steering dual-purpose holizontal rear fin |
| CN200985092Y (en) * | 2006-12-22 | 2007-12-05 | 中国科技开发院 | Pneumatic arrangement for ground effect aircraft |
| CN203638087U (en) * | 2013-12-13 | 2014-06-11 | 珲春国遥博诚科技有限公司 | Unmanned mapping machine and tail wing for same |
| CN104097474A (en) * | 2013-04-03 | 2014-10-15 | 上海同捷科技股份有限公司 | Rear parallel wings for amphicar |
| CN206537489U (en) * | 2016-12-08 | 2017-10-03 | 顺丰科技有限公司 | Tailplane and shipping unmanned plane with high trim elevator |
-
2016
- 2016-12-08 CN CN201611125022.6A patent/CN106741852A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB524865A (en) * | 1939-01-27 | 1940-08-16 | Hendrik Martinus Arends | Improvements in the control surfaces of aircraft |
| CN1400141A (en) * | 2001-07-30 | 2003-03-05 | 罗专予 | Balancing steering dual-purpose holizontal rear fin |
| CN200985092Y (en) * | 2006-12-22 | 2007-12-05 | 中国科技开发院 | Pneumatic arrangement for ground effect aircraft |
| CN104097474A (en) * | 2013-04-03 | 2014-10-15 | 上海同捷科技股份有限公司 | Rear parallel wings for amphicar |
| CN203638087U (en) * | 2013-12-13 | 2014-06-11 | 珲春国遥博诚科技有限公司 | Unmanned mapping machine and tail wing for same |
| CN206537489U (en) * | 2016-12-08 | 2017-10-03 | 顺丰科技有限公司 | Tailplane and shipping unmanned plane with high trim elevator |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20210723 Address after: 518063 5th floor, block B, building 1, software industry base, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Applicant after: Fengyi Technology (Shenzhen) Co.,Ltd. Address before: 518061 Intersection of Xuefu Road (south) and Baishi Road (east) in Nanshan District, Shenzhen City, Guangdong Province, 6-13 floors, Block B, Shenzhen Software Industry Base Applicant before: SF TECHNOLOGY Co.,Ltd. |
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| TA01 | Transfer of patent application right | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170531 |
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| RJ01 | Rejection of invention patent application after publication |