CN206954491U - A kind of unmanned plane and its fixed-wing - Google Patents
A kind of unmanned plane and its fixed-wing Download PDFInfo
- Publication number
- CN206954491U CN206954491U CN201720769852.6U CN201720769852U CN206954491U CN 206954491 U CN206954491 U CN 206954491U CN 201720769852 U CN201720769852 U CN 201720769852U CN 206954491 U CN206954491 U CN 206954491U
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- China
- Prior art keywords
- reinforcer
- fixed
- stretching
- wing
- rudder face
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- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/20—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by multiple flaps
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model provides a kind of unmanned plane and its fixed-wing, and the fixed-wing includes body, rudder face, stretching reinforcer and shearing reinforcer；Rudder face is arranged side by side in the trailing edge of the body；Stretching reinforcer is connected across between body and rudder face, and is bonded fixation with body and rudder face respectively, to improve side by side tensile strength direction on of the fixed-wing in body and rudder face；Shearing reinforcer fitting is fixed on stretching reinforcer and is not stretched on the body and/or rudder face of reinforcer covering, to improve shear strength of the fixed-wing in the vertical direction in direction side by side.Pass through above-mentioned fixed-wing, its anti-shear ability can be improved while fixed-wing tensile resistance is improved, reduce fixed-wing and be stretched power and shearing force and impaired risk, improve the reliability and service life of fixed-wing, and then improve flight reliability and the flight life-span of unmanned plane.
Description
Technical field
Unmanned air vehicle technique field is the utility model is related to, more particularly to a kind of unmanned plane and its fixed-wing.
Background technology
UAV abbreviation " unmanned plane ", the thrust advanced by the power set generation of unmanned plane or pulling force, and by
The fixed-wing of unmanned plane produces lift and causes unmanned plane during flying, in flight course, if necessary to change direction, then needs solid
The rudder face for determining the wing is rotated relative to the body of fixed-wing, and in rotary course, caused pulling force can cause in a rotational direction
Fixed-wing is damaged.
In the prior art, typically by setting the reinforcer of fitting body and rudder face on the body and rudder face of fixed-wing,
Such as High-strength adhesive tape, to rotate during by above-mentioned pulling force relative to body in rudder face, improve the stretch-proof of fixed-wing
Intensity, but this method, when in rotary course by the shearing force vertical with direction of rotation, it can not but improve anti-shearing energy
Power, and then cause fixed-wing still to have impaired risk.
Utility model content
The utility model is mainly to provide a kind of unmanned plane and its fixed-wing, it is intended to which the fixed-wing for solving unmanned plane is cut
Shear force and easily be damaged the problem of.
In order to solve the above technical problems, the technical scheme that the utility model uses is：A kind of consolidating for unmanned plane is provided
Determine the wing, the fixed-wing includes：Body；Rudder face, the rudder face are arranged side by side in the trailing edge of the body；Stretch reinforcer, institute
State stretching reinforcer to be connected across between the body and the rudder face, and be bonded fixation with the body and the rudder face respectively,
To improve side by side tensile strength direction on of the fixed-wing in the body and the rudder face；Reinforcer is sheared, it is described
Shearing reinforcer fitting is fixed on the stretching reinforcer and not by the body and/or described of the stretching reinforcer covering
On rudder face, to improve shear strength of the fixed-wing in the vertical direction in the direction side by side.
Wherein, the quantity of the stretching reinforcer is at least two, at least two stretching reinforcer and the body
It is intervally installed with the fitting fixed area of at least one of the rudder face, it is solid that the shearing reinforcer is connected across the fitting
Determine between area.
Wherein, at least two stretchings reinforcer is each other side by side or arranged in a crossed manner.
Wherein, the reinforcer of shearing includes the first shearing reinforcer and the second shearing reinforcer, and first shearing adds
Strong part is arranged on the body, and is bonded and is fixed on the stretching reinforcer and not described in the stretching reinforcer covering
On body, the second shearing reinforcer is arranged on the rudder face, and is bonded and is fixed on the stretching reinforcer and not by institute
On the rudder face for stating stretching reinforcer covering.
Wherein, the stretching reinforcer and the shearing reinforcer are set in strip respectively, the length of the stretching reinforcer
Degree direction is set along the direction side by side or the direction setting side by side described in of its part component, the length of the shearing reinforcer
Direction is set along the vertical direction or its part component is set along the vertical direction.
Wherein, the stretching reinforcer is flexible belt, and is fixed on the body and the rudder face with bonding method fitting
On.
Wherein, the shearing reinforcer be rigid plate, and is fixed on bonding method fitting and described stretches reinforcer and not
By on the body of the stretching reinforcer covering and/or the rudder face.
Wherein, the shearing reinforcer is comprised at least along described with the fixed area that is bonded of the body and/or the rudder face
The region that vertical direction is disposed adjacent with the stretching reinforcer.
Wherein, the fixed-wing further comprises the connecting material layer for connecting the body and the rudder face, described
Stretching reinforcer and the shearing reinforcer are arranged on the connecting material layer.
In order to solve the above technical problems, another technical scheme that the utility model uses is：A kind of unmanned plane, institute are provided
Stating unmanned plane includes above-mentioned fixed-wing.
The beneficial effects of the utility model are：The situation of prior art is different from, the utility model passes through in fixed-wing
Fixed stretching reinforcer is bonded on body and rudder face to improve the tensile strength of fixed-wing, stretch reinforcer and be not stretched
Fixed shear reinforcer is bonded on the body and/or rudder face of reinforcer covering to improve the anti-shear ability of fixed-wing, is being improved
Its anti-shear ability is improved while fixed-wing tensile resistance, fixed-wing is reduced and is stretched power and shearing force and is damaged
Risk, improve the reliability and service life of fixed-wing, and then improve flight reliability and the flight life-span of unmanned plane.
Brief description of the drawings
Fig. 1 is the decomposition texture schematic diagram of the fixed-wing embodiment of unmanned plane provided by the utility model；
Fig. 2 is the fitting schematic diagram that reinforcer is stretched in Fig. 1；
Fig. 3 is to shear reinforcer in Fig. 1 to be bonded schematic diagram with stretching the first of reinforcer；
Fig. 4 is to shear reinforcer in Fig. 1 to be bonded schematic diagram with stretching the second of reinforcer；
Fig. 5 is to shear reinforcer in Fig. 1 to be bonded schematic diagram with stretching the 3rd of reinforcer the；
Fig. 6 is to shear reinforcer in Fig. 1 to be bonded schematic diagram with stretching the 4th of reinforcer the.
Fig. 7 is the schematic diagram of unmanned aerial vehicle example provided by the utility model.
Embodiment
To make those skilled in the art more fully understand the technical solution of the utility model, below in conjunction with the accompanying drawings and specifically
Embodiment is described in further detail to unmanned plane provided by the utility model and its fixed-wing.
Refering to Fig. 1, the embodiment of fixed-wing 10 of unmanned plane provided by the utility model includes body 11, rudder face 12, stretching
Reinforcer 13 and shearing reinforcer 14.
Wherein, rudder face 12 is arranged side by side in the trailing edge of body 11, and optionally, rudder face 12 can be with as shown by the arrows in Figure 1
Body 11 and rudder face 12 direction side by side for radial rotary direction and rotated relative to body 11.
Common refer to Fig. 1 and Fig. 2, the stretching fitting of reinforcer 13 is connected across between body 11 and rudder face 12, and respectively with
Body 11 and the fitting of rudder face 12 are fixed, to improve the fixed-wing 10 in the present embodiment in body 11 and rudder face 12 side by side on direction
Tensile strength.
Specifically, stretching reinforcer 13 includes two parts, and a portion is positioned at stretching reinforcer 13 and body 11
Fitting fixed area 111 and be bonded fixations with body 11, another part be located at stretch reinforcer 13 and rudder face 12 be bonded fixed area
121 and fixation is bonded with rudder face 12, with the above-mentioned tensile strength for improving fixed-wing 10 on direction side by side.
Optionally, tensile strength part 13 is flexible belt, and is bonded with bonding method on fixed and body 11 and rudder face 12, than
If tensile strength part 13 is High-strength adhesive tape, with rudder face 12 carry out it is above-mentioned rotated relative to body 11 when, High-strength adhesive tape
Generation elastic stretching, and then in the tensile strength for radially improving fixed-wing 10 of rotation.
Optionally, tensile strength part 13 is set in strip, and the length direction of the tensile strength part 13 set in strip is along upper
Along this, direction is set the setting of direction side by side stated or part thereof component side by side, i.e., direction is parallel side by side with this.
Further, the quantity of tensile strength part 13 is at least two, and at least two tensile strength parts 13 are set side by side each other
Put, in the present embodiment diagram, exemplified by three, three tensile strength parts 13 are arranged side by side quantity each other.
Optionally, at least two tensile strength parts 13 and at least one of body 11 and rudder face 12 be bonded fixed area that
This is arranged at intervals.In the present embodiment diagram, three tensile strength parts 13 are bonded fixed area 111 and and rudder face with body 11
12 fitting fixed area 121 is intervally installed, and further, three stretching reinforcers 13 are also intervally installed.
Common to refer to Fig. 1 to Fig. 3, the shearing fitting of reinforcer 14 is fixed on stretching reinforcer 13 and is not stretched reinforcer 13
It is anti-shearing strong in the vertical direction in above-mentioned direction side by side to improve fixed-wing 10 on the body 11 and/or rudder face 12 of covering
Degree.
Specifically, shearing reinforcer 14 includes two parts, and a portion, which is fixed, to be fitted on stretching reinforcer 13, another
Part is bonded on fixed area 112 and/or sheared being bonded for reinforcer 14 and rudder face 12 positioned at shearing reinforcer 14 and body 11
Fixation is bonded with body 11 and/rudder face 12 on fixed area 122, to shear reinforcer 14 on body 11 and/or rudder face 12
Gland is in stretching reinforcer 13.
Optionally, it is anti-shearing strong in the vertical direction in above-mentioned direction side by side in order to greatly improve fixed-wing 10
Degree, shearing reinforcer 14 and body 11 be bonded fixed area 112 and/or shearing reinforcer 14 and rudder face 12 be bonded fixed area
122 comprise at least as shown in Figure 1 along the vertical direction region adjacent with stretching reinforcer 13, with by shearing force
When, the lifting surface area in the vertical direction is added, reduces shear strength, and then improve shear strength；Further, should
Adjacent region quantity is two, respectively positioned at the relative both sides of stretching reinforcer 13.
In other embodiments, the adjacent region quantity can also be one, and shearing reinforcer 14 is only strengthened in stretching
The side of part 13 is bonded fixation with body 11 and/or rudder face 12, in this case, when the quantity of stretching reinforcer 13 is at least
At two, shearing reinforcer 14 can be connected across at least two stretching reinforcers 13 and body 11 be bonded between fixed area 111 and/
Or two stretchings reinforcers 13 and rudder faces 12 be bonded fixed area 121 between, as shown in figure 4, being with two stretching reinforcers 13
, the two end portions for shearing reinforcer 14 are bonded fixation with two stretching reinforcers 13 respectively, and center section adds with two stretchings
The adjacent side region fitting of strong part 13 is fixed.
Optionally, shear tension part 14 is set in strip, and the length direction of the shear tension part 14 set in strip is along upper
The vertical direction stated is set or its part component is arranged in vertical, and shear tension part 14 as shown in Figure 3 adds with stretching
Strong part 13 is mutually perpendicular to.
Optionally, shear tension part 14 is rigid plate, and is fixed on stretching reinforcer 13 with bonding method and is not stretched
On the body 11 and/or rudder face 12 that reinforcer 13 covers, such as, shear tension part 14 is the plate body of carbon fibre composite,
During fitting, high intensity can be smeared stretching reinforcer 13 and being not stretched on the body 11 and/or rudder face 12 of the covering of reinforcer 13
Glue, the plate body of carbon fibre composite is then pasted onto stretching reinforcer 13 by the High-strength glue again and is not stretched
On the body 11 and/or rudder face 12 that reinforcer 13 covers.
Fig. 1 and Fig. 3 is further regarded to, shearing reinforcer 14 includes the first shearing reinforcer 141 and second and shears reinforcer
142。
Wherein, the first shearing reinforcer 141 is arranged on body 11, and is bonded and is fixed on stretching reinforcer 13 and is not drawn
The body 11 of the covering of reinforcer 13 is stretched, i.e., the first shearing reinforcer 141 is fixed positioned at shearing reinforcer 14 with being bonded for body 11
With the fixed stretching reinforcer 13 of fitting and body 11 in area 112 and stretching reinforcer 13；Second shearing reinforcer 142 is arranged at rudder
On face 12, and the rudder face 12 for being fixed on stretching reinforcer 13 and being not stretched the covering of reinforcer 13 is bonded, i.e., the second shearing is strengthened
Part 142 is strengthened positioned at shearing reinforcer 14 with the fixed stretching of fitting on fixed area 122 and stretching reinforcer 13 that is bonded of rudder face 12
Part 13 and rudder face 12.
Further, in other embodiments, fixed-wing 10 also includes being used for the connection material for connecting body 11 and rudder face 12
Bed of material (not shown), stretching reinforcer 13 and shearing reinforcer 14 in above-mentioned in a manner of be arranged at the connecting material layer
On, with improve the connecting material layer above-mentioned tensile strength on direction side by side and this side by side in the vertical direction in direction
Shear strength.
Optionally, the connecting material layer is foamed material layer, is added by the stretching reinforcer 13 in the present embodiment and shearing
Strong part 14 be arranged on the foamed material layer with improve the connecting material layer in above-mentioned tensile strength on direction side by side and
This is side by side after the shear strength in the vertical direction in direction, by increasing capacitance it is possible to increase rudder face 12 should caused by being rotated relative to body 11
The bending number of foamed material layer, and then improve the reliability and service life of fixed-wing 10.
Fig. 5 and Fig. 6 is referred to jointly, in other embodiments, at least two stretching reinforcers 13 can be set with intersected with each other
Put, the overlapping intersection including but not limited to as shown in Figure 5 arranged in a crossed manner or intersection in the longitudinal direction as shown in Figure 6.
Wherein, at least two stretching reinforcers 13 overlap each other it is arranged in a crossed manner include but is not limited to two-by-two it is overlapping intersect, its
In one with other it is multiple it is overlapping intersect or it is multiple it is overlapped intersect, exemplified by intersecting two-by-two in Fig. 5, the drawing that intersects two-by-two
Stretch reinforcer 13 bridge and be bonded it is fixed with body 11 and rudder face 12, the shearing fitting of reinforcer 14 be fixed on stretching reinforcer 13 and
It is not stretched on the body 11 and/or rudder face 12 of the covering of reinforcer 13, for example the first shearing reinforcer 141 is located on body 11 and pasted
Close fixed body 11 and multiple stretching reinforcers 13, the second shearing reinforcer 142 be located at fitting on rudder face 12 fix rudder face 12 and
Multiple stretching reinforcers 13；At least two stretching reinforcers 13 as shown in Figure 6 in the longitudinal direction arranged in a crossed manner, shearing plus
Strong part 14 can be bonded fixation in an identical manner, will not be repeated here.
Refering to Fig. 7, the utility model, which additionally provides unmanned aerial vehicle example, includes the fixed-wing 10 in above-described embodiment, with logical
The fixed-wing 10 for crossing above-described embodiment improves the flight reliability and service life of unmanned plane.
The situation of prior art is different from, the utility model on the body and rudder face of fixed-wing by being bonded fixed stretching
Reinforcer with improve the tensile strength of fixed-wing, stretching reinforcer and be not stretched reinforcer covering body and/or rudder
Fixed shear reinforcer is bonded on face to improve the anti-shear ability of fixed-wing, is carried while fixed-wing tensile resistance is improved
Its high anti-shear ability, reduce fixed-wing and be stretched power and shearing force and impaired risk, improve the reliable of fixed-wing
Property and service life, and then improve unmanned plane flight reliability and the flight life-span.
Embodiment of the present utility model is the foregoing is only, not thereby limits the scope of the claims of the present utility model, it is every
The equivalent structure or equivalent flow conversion made using the utility model specification and accompanying drawing content, or be directly or indirectly used in
Other related technical areas, similarly it is included in scope of patent protection of the present utility model.
Claims (10)
1. a kind of fixed-wing of unmanned plane, it is characterised in that the fixed-wing includes：
Body；
Rudder face, the rudder face are arranged side by side in the trailing edge of the body；
Stretch reinforcer, it is described stretching reinforcer be connected across between the body and the rudder face, and respectively with the body and
The rudder face fitting is fixed, strong in the stretch-proof side by side on direction of the body and the rudder face to improve the fixed-wing
Degree；
Reinforcer is sheared, the shearing reinforcer fitting is fixed on the stretching reinforcer and not by the stretching reinforcer covering
The body and/or the rudder face on, it is anti-shearing in the vertical direction in the direction side by side to improve the fixed-wing
Intensity.
2. fixed-wing according to claim 1, it is characterised in that the quantity of the stretching reinforcer is at least two, institute
The fixed area that is bonded that at least two stretching reinforcers are stated with least one of the body and the rudder face is intervally installed,
The shearing reinforcer is connected across between the fitting fixed area.
3. fixed-wing according to claim 2, it is characterised in that at least two stretchings reinforcer side by side or is handed over each other
Fork is set.
4. fixed-wing according to claim 1, it is characterised in that it is described shearing reinforcer include first shearing reinforcer and
Second shearing reinforcer, the first shearing reinforcer is arranged on the body, and is bonded and is fixed on the stretching reinforcer
And not by the body of the stretching reinforcer covering, the second shearing reinforcer is arranged on the rudder face, and is pasted
Close and be fixed on the stretching reinforcer and not by the rudder face of the stretching reinforcer covering.
5. fixed-wing according to claim 1, it is characterised in that the stretching reinforcer and the shearing reinforcer difference
Set in strip, the length direction of the stretching reinforcer along the direction side by side set or its part component edge described in side by side
Direction is set, and the length direction of the shearing reinforcer is set along the vertical direction or its part component is along the Vertical Square
To setting.
6. fixed-wing according to claim 1, it is characterised in that the stretching reinforcer is flexible belt, and with stickup side
Formula fitting is fixed on the body and the rudder face.
7. fixed-wing according to claim 1, it is characterised in that the shearing reinforcer is rigid plate, and with stickup side
Formula fitting is fixed on the stretching reinforcer and not by the body of the stretching reinforcer covering and/or the rudder face.
8. fixed-wing according to claim 1, it is characterised in that shearing reinforcer and the body and/or described
The fitting fixed area of rudder face comprises at least the region being disposed adjacent along the vertical direction with the stretching reinforcer.
9. fixed-wing according to claim 1, it is characterised in that the fixed-wing further comprises being used to connect described
The connecting material layer of body and the rudder face, the stretching reinforcer and the shearing reinforcer are arranged at the connecting material layer
On.
10. a kind of unmanned plane, it is characterised in that the unmanned plane includes the fixed-wing as described in any one of claim 1~9.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720769852.6U CN206954491U (en) | 2017-06-28 | 2017-06-28 | A kind of unmanned plane and its fixed-wing |
| CN201780069121.3A CN109963782A (en) | 2017-06-28 | 2017-07-31 | A kind of unmanned plane and its fixed-wing |
| PCT/CN2017/095210 WO2019000545A1 (en) | 2017-06-28 | 2017-07-31 | Unmanned aerial vehicle and fixed wing thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720769852.6U CN206954491U (en) | 2017-06-28 | 2017-06-28 | A kind of unmanned plane and its fixed-wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206954491U true CN206954491U (en) | 2018-02-02 |
Family
ID=61385757
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720769852.6U Expired - Fee Related CN206954491U (en) | 2017-06-28 | 2017-06-28 | A kind of unmanned plane and its fixed-wing |
| CN201780069121.3A Pending CN109963782A (en) | 2017-06-28 | 2017-07-31 | A kind of unmanned plane and its fixed-wing |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780069121.3A Pending CN109963782A (en) | 2017-06-28 | 2017-07-31 | A kind of unmanned plane and its fixed-wing |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN206954491U (en) |
| WO (1) | WO2019000545A1 (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB483018A (en) * | 1936-10-09 | 1938-04-11 | William Edward Back | Improvements in or connected with model aeroplanes |
| US5335886A (en) * | 1992-01-30 | 1994-08-09 | The United States Of America As Represented By The Seceretary Of The Navy | Lift enhancement device |
| US20030111578A1 (en) * | 2001-12-18 | 2003-06-19 | Toshio Ito | Kite and selling method of kite |
| EP3095691A1 (en) * | 2015-05-22 | 2016-11-23 | Airbus Operations, S.L. | Multi-spar torsion box structure |
-
2017
- 2017-06-28 CN CN201720769852.6U patent/CN206954491U/en not_active Expired - Fee Related
- 2017-07-31 WO PCT/CN2017/095210 patent/WO2019000545A1/en active Application Filing
- 2017-07-31 CN CN201780069121.3A patent/CN109963782A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| WO2019000545A1 (en) | 2019-01-03 |
| CN109963782A (en) | 2019-07-02 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180202 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |