CN107600386A - The cantilever of electronic unmanned plane - Google Patents
The cantilever of electronic unmanned plane Download PDFInfo
- Publication number
- CN107600386A CN107600386A CN201710978317.6A CN201710978317A CN107600386A CN 107600386 A CN107600386 A CN 107600386A CN 201710978317 A CN201710978317 A CN 201710978317A CN 107600386 A CN107600386 A CN 107600386A
- Authority
- CN
- China
- Prior art keywords
- cantilever
- motor
- unmanned aerial
- outer diameter
- aerial vehicle
- 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.)
- Granted
Links
- 230000007246 mechanism Effects 0.000 claims description 21
- 238000013461 design Methods 0.000 abstract description 10
- 230000000694 effects Effects 0.000 abstract description 5
- 238000003780 insertion Methods 0.000 abstract 1
- 230000037431 insertion Effects 0.000 abstract 1
- 230000004580 weight loss Effects 0.000 abstract 1
- 239000013585 weight reducing agent Substances 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000005622 photoelectricity Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
This application provides a kind of cantilever of electronic unmanned plane, motor is supported for being connected on the fuselage of electronic unmanned plane, first end that the cantilever includes be connected with the fuselage, the second end for supporting the motor and the interlude between the first end and the second end；The first end is made up of the isodiametric cylinder of length direction；The second end is equally made up of the isodiametric cylinder of length direction；The interlude is taper tubular structure.The cantilever of the electronic unmanned plane of the application is generally in hollow cylindrical structure, and the weight under same strength conditions is lighter, can obtain bigger twisting property.Both ends are firmly connected for the ease of insertion tubular attachment structure, have been designed to isodiametric cylinder.Interlude is designed as taper tubular structure, can form uniform strength design, and weight loss effect is more excellent.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an electric unmanned aerial vehicle with multiple rotors, and particularly relates to a cantilever of the electric unmanned aerial vehicle.
Background
With the development of the global general aviation industry, the development of various rotor airplanes is increasing day by day, and particularly, the rotor electric unmanned aircraft is widely applied to tasks such as agricultural protection, forest fire monitoring, aerial photography, land survey, post-disaster loss assessment and the like. Electric unmanned aerial vehicle simple structure, the noise is little, has advantages such as flexible, quick, the operation requirement of reaction is low, and is very big in the occupation ratio in consumption level market. However, the power of the electric unmanned aerial vehicle is provided by the battery, the weight of the battery cannot be consumed like fuel oil, so that the effective load of the electric unmanned aerial vehicle is very limited, the cruising time is short, and the electric unmanned aerial vehicle is rarely used as a weapon striking platform.
Most of the electric unmanned aerial vehicles in the current consumer-grade market are multi-axis unmanned aerial vehicles, such as four-axis, six-axis and the like, the whole take-off weight is very small, the cruising time is very short, the strength and the weight reduction problem are not fully considered in various fuselage structural designs, the load level is low, the structural layout is unreasonable, the unmanned aerial vehicle is difficult to exert the control and safety advantages, and the development and application of the unmanned rotor wing aircraft in the military and monitoring fields are limited.
CN 206278267U discloses many rotor unmanned aerial vehicle, including the unmanned aerial vehicle body, the unmanned aerial vehicle body comprises horn, well core plate and foot support, and the horn includes arm sleeve, arm of force pole, motor cabinet, motor and paddle, and the motor is fixed on the motor cabinet, and the paddle is fixed on the motor, and the motor cabinet is fixed in arm of force pole one end, and the arm of force pole other end sets up the arm sleeve of force to be connected with well core plate through the arm of force cover. This unmanned aerial vehicle of prior art's motor setting is installed on the arm of force pole of rod-like structure, and the arm of force pole adopts the solid pole of uniform diameter, and intensity distribution is unreasonable, and structure weight is big, has run up partial load weight on foot, is unfavorable for the improvement of duration.
Similarly, CN 204587305U discloses an eight rotor electric unmanned aerial vehicle of multi-functional folded cascade, mainly solves the problem that current rotor electric unmanned aerial vehicle usage is single, the structure is complicated, complete machine transportation difficulty. The device comprises a machine body, a flight control mechanism, a power mechanism, a foldable cantilever mechanism, a spraying mechanism and a lithium battery pack. The power mechanism comprises a motor and a propeller; the foldable cantilever mechanism comprises a cantilever and a foldable pipe clamp, wherein the cantilever is arranged on the foldable pipe clamp, one end of the foldable pipe clamp is arranged between the lower side bearing platform and the upper side bearing platform, and the other end of the foldable pipe clamp fixes the cantilever. This prior art's unmanned aerial vehicle's cantilever adopts the solid pole of isodiametric equally, and intensity distribution is unreasonable, and structure weight is also big.
Disclosure of Invention
The technical problem to be solved by the present invention is to provide a suspension arm of an electric unmanned aerial vehicle to reduce or avoid the aforementioned problems.
In order to solve the technical problem, the invention provides a cantilever of an electric unmanned aerial vehicle, which is used for being connected to a body of the electric unmanned aerial vehicle to support a motor, wherein the electric unmanned aerial vehicle comprises a plurality of cantilevers, each cantilever supports one motor, and each motor is provided with a propeller, wherein: the cantilever comprises a first end part connected with the body, a second end part supporting the motor and a middle section positioned between the first end part and the second end part; the first end portion is formed by a cylinder with equal diameter in the length direction and has a first outer diameter R1; the second end portion is also formed by a cylinder with equal diameter in the length direction and has a second outer diameter R2; the second outer diameter R2 is less than the first outer diameter R1; the middle section is a conical cylindrical structure, the outer diameter of the middle section is equal to the first outer diameter R1 when the middle section is connected with the first end part, and the outer diameter of the middle section is equal to the second outer diameter R2 when the middle section is connected with the second end part.
Preferably, the first end portion, the second end portion and the middle section have a first centerline, a second centerline and a third centerline, respectively; when the cantilever is installed on the machine body, the second center line is in a horizontal state.
Preferably, the first centerline and the third centerline are located on the same line.
Preferably, a break α is provided between the second centerline and the third centerline, and the break α is between 170 and 178 degrees.
Preferably, a foldable mechanism is arranged at the joint of the cantilever and the machine body, and the cantilever can be folded downwards through the foldable mechanism.
Preferably, the foldable mechanism comprises a fixed part connected with the body and a folding part which can rotate around a rotating shaft of the fixed part, the folding part is a cylindrical structure with an inner diameter larger than the first outer diameter R1, and the first end part is inserted into the folding part and fixedly connected with the folding part through a screw.
Preferably, the motor is mounted at the second end through a motor mount; the motor base comprises a cylindrical connecting part with the inner diameter larger than the second outer diameter R2 and a sheet-shaped connecting part horizontally extending outwards from the cylindrical connecting part; the cylindrical connecting part is inserted into the outer side of the second end part and fixedly connected through a bolt; the motor is fixedly connected to the upper surface of the sheet-shaped connecting part through a screw.
Preferably, the cylindrical connecting portion includes a semi-cylindrical upper cover and a semi-cylindrical lower cover integrally connected to the sheet-like connecting portion, and the upper cover and the lower cover are fixedly connected to the outer side of the second end portion by bolts.
The utility model provides an electric unmanned aerial vehicle's cantilever is hollow cylinder structure on the whole, and weight under the same intensity condition is lighter, can obtain bigger torsional properties. The two ends are designed into cylinders with equal diameters for the convenience of inserting the cylindrical connecting structure for firm connection. The middle section is designed to be a conical cylindrical structure, so that an equal-strength design can be formed, and the weight reduction effect is better.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein,
fig. 1 is a schematic perspective view of an electric drone according to an embodiment of the present invention;
fig. 2 shows a schematic view of a folding structure of the electric drone shown in fig. 1;
fig. 3 shows a schematic folded state of the boom of the electric drone according to an embodiment of the present application;
fig. 4 shows an exploded view of a boom of an electric drone according to another particular embodiment of the present application;
fig. 5 is an exploded view of a motor mount coupled to the boom of the electric drone of fig. 4;
fig. 6 shows a side view of a boom of an electric drone according to a particular embodiment of the present application.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
The current multiaxis unmanned aerial vehicle that the background art part mentioned all adopts the holohedral layout, leads to the focus position to concentrate on a bit, and the load overall arrangement receives very big restriction, and because the rotor of holohedral layout has all blocked unmanned aerial vehicle's all directions, leads to the load that carries on can't be to oblique top transmission weapon or observe, has restricted current unmanned aerial vehicle's range of application. Based on this, the present application provides an electric unmanned aerial vehicle, as shown in fig. 1 and 2, wherein fig. 1 shows a schematic perspective view of an electric unmanned aerial vehicle according to an embodiment of the present invention; fig. 2 shows a schematic view of a folding structure of the electric unmanned aerial vehicle shown in fig. 1.
Referring to fig. 1-2, the electric unmanned aerial vehicle of the present application includes fuselage 1 and a plurality of cantilevers 3 connected on fuselage 1, and each cantilever 3 has all supported one motor 4, and each motor 4 all has screw 5. Different with current multiaxis unmanned aerial vehicle is, the electronic unmanned aerial vehicle's of this application fuselage 1 is rectangular shape on the whole, along rectangular shape fuselage 1's length direction, can carry structures such as photoelectricity nacelle and weapon launching tube in the below of fuselage 1. That is, the basic idea of this application is that the unblock rectangular shape passageway that is favorable to setting up load such as photoelectricity nacelle and weapon launching tube has been formed in the below of electric unmanned aerial vehicle's rectangular shape fuselage 1, and interference takes place with cantilever 3 and screw 5 etc. when avoiding observation and weapon launch, influences use and combat efficiency, has improved unmanned aerial vehicle's range of application. In addition, the strip-shaped machine body 1 facilitates the symmetrical distribution of the structures such as the cantilever 3 and the motor 4 on the cantilever on the two sides of the machine body 1, so that a larger-range load mounting point can be obtained in the longitudinal direction of the machine body, and the load layout is easy to expand. In addition, the loads such as weapon launching tubes need to provide an oblique upward elevation angle, if obstacles such as a rotor wing exist in the front of the weapon launching tubes, missiles or rocket projectiles are difficult to launch (the unmanned aerial vehicle crashes under the interference condition), and the rear of the weapon launching tubes also needs to prevent the tail flame of the rocket engine from firing the rotor wing, so that the load gravity center balance of the unmanned aerial vehicle can be realized by the arrangement mode of the strip-shaped fuselage 1, the unmanned aerial vehicle is convenient to control, the design difficulty of flight control software is simplified, and the weapon launching tubes are particularly suitable for being used as a.
In the folding structure of the electric unmanned aerial vehicle shown in fig. 2, in order to facilitate folding of the unmanned aerial vehicle, the structure of the propeller 5 and the weapon launching tube and the like of the unmanned aerial vehicle are removed, so as to avoid interference with the undercarriage after folding, and a smaller folding volume can be obtained, so as to facilitate boxing transportation. Specifically, a foldable mechanism 11 is provided at a connection point of the cantilever 3 and the body 1, and the cantilever 3 can be folded downward by the foldable mechanism 11.
The related connection structure of the cantilever of the electric unmanned aerial vehicle of the present application is further specifically described with reference to fig. 3 to 5, wherein fig. 3 is a schematic diagram showing a folded state of the cantilever of the electric unmanned aerial vehicle according to an embodiment of the present application, and fig. 4 is a schematic diagram showing an exploded view of the cantilever of the electric unmanned aerial vehicle according to another embodiment of the present application; fig. 5 is an exploded view of the motor base connected to the boom of the electric drone shown in fig. 4. As shown in fig. 3-5, the cantilever 3 of the electric unmanned aerial vehicle of the present application is generally a hollow cylindrical structure, which may be made of light metal alloy, or may be made of high-strength carbon fiber composite material.
One end of the cantilever 3 is connected with the machine body 1, and the other end is used for supporting the motor 4. As described above, the foldable mechanism 11 is provided at the connection between the cantilever 3 and the main body 1, the foldable mechanism 11 includes the fixed portion 111 connected to the main body 1 and the folding portion 113 rotatable about the rotation shaft 112 of the fixed portion 111, the folding portion 113 has a cylindrical structure, and the corresponding end of the cantilever 3 is inserted into the folding portion 113 and fixedly connected by a screw. Cantilever 3 of this application is pegged graft through tubular structure with folding portion 113 of folding mechanism 11, can obtain bigger area of contact and obtain bigger frictional force, and firm in connection just easily passes through bolted connection and dismouting, and the reliability is high, the dismouting of being convenient for operation such as maintenance.
A motor base 41 for supporting the motor 4 is arranged at the end of the cantilever 3 opposite to the foldable mechanism 11, wherein the motor base 41 comprises a cylindrical connecting part 401 and a sheet-shaped connecting part 402 horizontally extending outwards from the cylindrical connecting part 401; the cylindrical connecting portion 401 is inserted outside the cantilever 3 and fixedly connected by a bolt; the motor 4 may be fixedly attached to the upper surface of the sheet-like connection portion 402 by a screw.
Further, the cylindrical connecting portion 401 includes a semi-cylindrical upper cover 403 and a semi-cylindrical lower cover 404 integrally connected to the sheet-like connecting portion 402, and the upper cover 403 and the lower cover 404 are fixedly attached to the outer side of the distal end of the cantilever 3 by bolts. The utility model provides an electric unmanned aerial vehicle's motor 4 cup joints in the terminal outside of cantilever 3 through the cylindric connecting portion 401 of motor cabinet 41, for prior art bind the operation such as the dismouting maintenance of being more convenient for of the connected mode, and owing to bind the setting and slide around the cantilever easily, motor location difficulty, the stability of controlling is influenced, need frequently adjust motor position, and structural reliability is very poor. The sleeve connection mode is large in contact area, larger friction force can be provided through tightening the bolt, connection is reliable, operation is convenient, and the sleeve connection mode is particularly suitable for high-reliability connection of military striking platforms.
The structure of the cantilever of the present application is specifically described below with reference to fig. 6, where fig. 6 shows a side view of the cantilever of the electric drone according to one specific embodiment of the present application. As shown, the boom 3 of the present application includes a first end portion 301 connected to the body 1, a second end portion 302 supporting the motor 4, and an intermediate section 303 located between the first end portion 301 and the second end portion 302; the first end 301 is formed of a cylinder of equal diameter in the longitudinal direction and has a first outer diameter R1; the second end 302 is also formed of a cylinder of equal diameter in the length direction and having a second outer diameter R2; the second outer diameter R2 is less than the first outer diameter R1; the middle section 303 is a tapered cylindrical structure having an outer diameter equal to the first outer diameter R1 where it meets the first end 301 and equal to the second outer diameter R2 where it meets the second end 302.
The utility model provides an electric unmanned aerial vehicle's cantilever 3 is hollow cylinder structure on the whole, and weight under the same intensity condition is lighter, can obtain bigger torsional properties. The two ends are designed to be equal-diameter cylinders for the convenience of inserting and firmly connecting the cylindrical connecting structures (the folding part 113 of the foldable mechanism 11 and the cylindrical connecting part 401 of the motor base 41). The middle section 303 is designed to be a conical cylindrical structure, so that an equal-strength design can be formed, and the weight reduction effect is better.
Further, the first end portion 301, the second end portion 302, and the middle segment 303 have a first centerline 311, a second centerline 312, and a third centerline 313, respectively; the second centerline 312 is horizontal when the boom 3 is mounted on the body 1. That is, the end (the second end 302) of the cantilever 3 of the present application is used for supporting the motor 4, and the center line thereof is designed to be horizontal, so as to facilitate the installation and debugging of the motor 4, and the deflection attack angle and the like of the motor 4 can be easily simulated and calculated, so that the calculation intensity in the design and optimization stage can be greatly reduced, the labor cost can be reduced, and the error is not easy to occur.
In one embodiment, it is preferred that the first centerline 311 and the third centerline 313 are located on the same line. That is, in this embodiment, the first center line 311 and the third center line 313 are located on the same straight line, which means that the first end portion 301 and the middle portion 303 can be coaxially stretched or cured during manufacturing, which is beneficial for demolding and can reduce manufacturing cost.
Further, it is preferable that the second centerline 312 and the third centerline 313 have a break angle α therebetween, and it is preferable that the break angle α is between 170 and 178 degrees, that is, in the present embodiment, since the root diameter R1 of the cantilever 3 connected to the main body 1 is larger and the diameter R2 of the tip is relatively smaller, the tip of the propeller 5 connected to the motor 4 may interfere with the cantilever 3, and in order to avoid the interference problem, the cantilever 3 of the present embodiment provides a dihedral angle, and the portion of the cantilever 3 connected to the main body 1 is slightly lower than the tip of the cantilever 3 to offset the interference problem caused by the thicker root of the cantilever 3. more preferably, the magnitude of the break angle α can be obtained by approximation calculation according to the following formula:
tan (180- α) ═ R1-R2/L, where L is the length of the second centerline 312 of the intermediate segment 303, and the break angle α units are degrees.
That is, to different cantilever designs, the electric unmanned aerial vehicle of whatever size all can adopt the above-mentioned formula that this application provided to directly obtain the approximate size of available dog-ear α, has reduced the numerical range of design and experiment, can reduce design cost, has improved efficiency.
More specifically, the foldable mechanism 11 connected to the body 1 is connected to the first end portion 301 of the arm 3, the folded portion 113 of the foldable mechanism 11 is a cylindrical structure having an inner diameter larger than the first outer diameter R1, and the first end portion 301 is inserted into the folded portion 113. The motor 4 is arranged at the second end 302 of the cantilever 3 through the motor base 41; the inner diameter of cylindrical connecting portion 401 of motor mount 41 is larger than second outer diameter R2 so that cylindrical connecting portion 401 can be inserted outside second end 302. More specifically, an upper cover 403 and a lower cover 404 constituting the cylindrical connecting portion 401 are fixedly attached to the outside of the second end portion 302 by bolts.
To sum up, electric unmanned aerial vehicle's of this application cantilever is hollow cylinder structure on the whole, and weight under the same intensity condition is lighter, can obtain bigger torsional properties. The two ends are designed into cylinders with equal diameters for the convenience of inserting the cylindrical connecting structure for firm connection. The middle section is designed to be a conical cylindrical structure, so that an equal-strength design can be formed, and the weight reduction effect is better.
It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (8)
1. The utility model provides an electric unmanned aerial vehicle's cantilever for connect support motor (4) on electric unmanned aerial vehicle's fuselage (1), electric unmanned aerial vehicle includes a plurality of cantilever (3), every cantilever (3) support one motor (4), every motor (4) all have screw (5), its characterized in that: the cantilever (3) comprises a first end part (301) connected with the body (1), a second end part (302) supporting the motor (4) and a middle section (303) positioned between the first end part (301) and the second end part (302); the first end (301) is formed by a cylinder with equal diameter in the length direction and has a first outer diameter R1; the second end (302) is likewise formed by a cylinder of equal diameter in the longitudinal direction, having a second outer diameter R2; the second outer diameter R2 is less than the first outer diameter R1; the middle section (303) is a tapered cylindrical structure having an outer diameter equal to the first outer diameter R1 where it meets the first end (301) and an outer diameter equal to the second outer diameter R2 where it meets the second end (302).
2. The boom of an electric drone of claim 1, wherein the first end (301), the second end (302), and the middle section (303) have a first centerline (311), a second centerline (312), and a third centerline (313), respectively; when the cantilever (3) is installed on the machine body (1), the second central line (312) is in a horizontal state.
3. The boom of an electric drone of claim 2, wherein the first centerline (311) and the third centerline (313) are located on the same line.
4. The boom of claim 3, wherein a break α is provided between the second centerline (312) and the third centerline (313), and the break α is between 170 and 178 degrees.
5. The cantilever of the electric unmanned aerial vehicle as claimed in claim 1, wherein a foldable mechanism (11) is disposed at the joint of the cantilever (3) and the fuselage (1), and the cantilever (3) can be folded downwards by the foldable mechanism (11).
6. The cantilever of the electric unmanned aerial vehicle of claim 5, wherein the foldable mechanism (11) comprises a fixed part (111) connected with the body (1) and a folding part (113) rotatable around a rotating shaft (112) of the fixed part (111), the folding part (113) is a cylindrical structure with an inner diameter larger than the first outer diameter R1, and the first end part (301) is inserted into the folding part (113) and fixedly connected with the same through a screw.
7. The boom of an electric drone according to claim 1, characterized in that the motor (4) is mounted at the second end (302) by means of a motor mount (41); the motor base (41) comprises a cylindrical connecting part (401) with the inner diameter larger than the second outer diameter R2 and a sheet-shaped connecting part (402) horizontally extending outwards from the cylindrical connecting part (401); the cylindrical connecting part (401) is inserted outside the second end part (302) and fixedly connected by a bolt; the motor (4) is fixedly connected to the upper surface of the sheet-shaped connecting part (402) through a screw.
8. The boom of an electric unmanned aerial vehicle according to claim 7, wherein the cylindrical connecting part (401) comprises a semi-cylindrical upper cover (403) and a semi-cylindrical lower cover (404) connected with the sheet-shaped connecting part (402) into a whole, and the upper cover (403) and the lower cover (404) are fixedly connected to the outer side of the second end part (302) through bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710978317.6A CN107600386B (en) | 2017-10-18 | 2017-10-18 | Cantilever of electric unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710978317.6A CN107600386B (en) | 2017-10-18 | 2017-10-18 | Cantilever of electric unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107600386A true CN107600386A (en) | 2018-01-19 |
| CN107600386B CN107600386B (en) | 2023-11-07 |
Family
ID=61077638
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710978317.6A Active CN107600386B (en) | 2017-10-18 | 2017-10-18 | Cantilever of electric unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107600386B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910012A (en) * | 2018-07-26 | 2018-11-30 | 瀚伦贝尔通用航空器有限公司 | A kind of big boom device of folding aircraft |
| CN108942871A (en) * | 2018-09-10 | 2018-12-07 | 安徽灵翔智能机器人技术有限公司 | A kind of plant protection cruise monitoring robot based on unmanned plane |
| CN109484612A (en) * | 2018-12-24 | 2019-03-19 | 沈阳旋飞航空技术有限公司 | A kind of pole bracket for the dynamic unmanned plane of oil |
| CN111717367A (en) * | 2020-06-04 | 2020-09-29 | 天津爱思达航天科技有限公司 | A horn structure for VTOL aircraft |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB120450A (en) * | 1917-11-15 | 1918-11-14 | Blackburn Aeroplane & Motor Co | Improvements in the Construction of Fuselages, Boats or Floats particularly applicable to Flying Machines. |
| US4245801A (en) * | 1979-02-15 | 1981-01-20 | United Technologies Corporation | Tail rotor control cable-pylon fold accommodation |
| CN2315021Y (en) * | 1997-11-04 | 1999-04-21 | 梁创成 | Motorcycle seat cushion sun protection device |
| US6416280B1 (en) * | 2000-11-27 | 2002-07-09 | General Electric Company | One piece spinner |
| CN201498669U (en) * | 2009-09-09 | 2010-06-02 | 富士康(昆山)电脑接插件有限公司 | electrical connector |
| CN202065633U (en) * | 2011-06-03 | 2011-12-07 | 朱灿 | Folding laptop computer support |
| CN103387045A (en) * | 2012-05-07 | 2013-11-13 | 波音公司 | Method and system for use in assembling fuselage |
-
2017
- 2017-10-18 CN CN201710978317.6A patent/CN107600386B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB120450A (en) * | 1917-11-15 | 1918-11-14 | Blackburn Aeroplane & Motor Co | Improvements in the Construction of Fuselages, Boats or Floats particularly applicable to Flying Machines. |
| US4245801A (en) * | 1979-02-15 | 1981-01-20 | United Technologies Corporation | Tail rotor control cable-pylon fold accommodation |
| CN2315021Y (en) * | 1997-11-04 | 1999-04-21 | 梁创成 | Motorcycle seat cushion sun protection device |
| US6416280B1 (en) * | 2000-11-27 | 2002-07-09 | General Electric Company | One piece spinner |
| CN201498669U (en) * | 2009-09-09 | 2010-06-02 | 富士康(昆山)电脑接插件有限公司 | electrical connector |
| CN202065633U (en) * | 2011-06-03 | 2011-12-07 | 朱灿 | Folding laptop computer support |
| CN103387045A (en) * | 2012-05-07 | 2013-11-13 | 波音公司 | Method and system for use in assembling fuselage |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910012A (en) * | 2018-07-26 | 2018-11-30 | 瀚伦贝尔通用航空器有限公司 | A kind of big boom device of folding aircraft |
| CN108942871A (en) * | 2018-09-10 | 2018-12-07 | 安徽灵翔智能机器人技术有限公司 | A kind of plant protection cruise monitoring robot based on unmanned plane |
| CN108942871B (en) * | 2018-09-10 | 2022-02-11 | 安徽灵翔智能机器人技术有限公司 | Plant protection monitoring robot that cruises |
| CN109484612A (en) * | 2018-12-24 | 2019-03-19 | 沈阳旋飞航空技术有限公司 | A kind of pole bracket for the dynamic unmanned plane of oil |
| CN111717367A (en) * | 2020-06-04 | 2020-09-29 | 天津爱思达航天科技有限公司 | A horn structure for VTOL aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107600386B (en) | 2023-11-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107600386A (en) | The cantilever of electronic unmanned plane | |
| US5746391A (en) | Mounting for coupling a turbofan gas turbine engine to an aircraft structure | |
| CN102616379A (en) | Fastener device, associated aircraft, and associated method | |
| CN101450715A (en) | Suspension of a turbojet to an aircraft | |
| CN107697280B (en) | A load-carrying structure for electric unmanned aerial vehicle | |
| WO2020019629A1 (en) | Truss-type unmanned aerial vehicle frame and unmanned aerial vehicle | |
| CN207550494U (en) | A kind of electronic unmanned plane undercarriage | |
| CN106892083B (en) | Bionic rack of crossed double-rotor helicopter | |
| CN212458140U (en) | Cylinder subsonic small missile | |
| CN207292370U (en) | The cantilever of electronic unmanned plane | |
| US8308105B2 (en) | Aircraft engine pylon attachment | |
| CN107672784A (en) | The support bar quick-disassembly structure of the dynamic unmanned plane of oil | |
| CN107672799A (en) | A kind of electronic unmanned plane | |
| CN114212238A (en) | High-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings | |
| CN210235329U (en) | Novel examine and beat integrative unmanned helicopter organism weapon and hang roof beam | |
| US11988153B2 (en) | Assembly for an aircraft gas turbine engine comprising an accessory gearbox | |
| CN109484611B (en) | Fuselage bearing structure of oil-driven unmanned aerial vehicle | |
| US2565733A (en) | Aircraft engine mount | |
| CN207450220U (en) | The supporting rod quick-disassembly structure of the dynamic unmanned plane of oil | |
| CN107757883A (en) | A kind of dynamic unmanned plane undercarriage of oil | |
| CN107600385B (en) | Cantilever folding mechanism of electric unmanned aerial vehicle | |
| CN207450227U (en) | A kind of dynamic unmanned plane undercarriage of oil | |
| CN101654151B (en) | Supporting mechanism applied unmanned aerial vehicle launching system | |
| CN213455167U (en) | Carrier rocket | |
| CN109484617A (en) | A kind of oblique pull cable wire and assembly and disassembly methods for the dynamic unmanned plane of oil |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |