CN112429192A - Carbon fiber unmanned aerial vehicle frame - Google Patents
Carbon fiber unmanned aerial vehicle frame Download PDFInfo
- Publication number
- CN112429192A CN112429192A CN202011522411.9A CN202011522411A CN112429192A CN 112429192 A CN112429192 A CN 112429192A CN 202011522411 A CN202011522411 A CN 202011522411A CN 112429192 A CN112429192 A CN 112429192A
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- China
- Prior art keywords
- fuselage
- bolts
- wall
- fixedly connected
- wing
- 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.)
- Pending
Links
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 19
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 19
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 19
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 13
- 239000010959 steel Substances 0.000 claims abstract description 13
- 239000003292 glue Substances 0.000 claims description 11
- 239000000463 material Substances 0.000 claims description 3
- 238000013016 damping Methods 0.000 description 6
- 230000035939 shock Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 4
- 230000001681 protective effect Effects 0.000 description 4
- 238000004026 adhesive bonding Methods 0.000 description 3
- 239000006096 absorbing agent Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000005489 elastic deformation Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
- B64C25/64—Spring shock-absorbers; Springs using rubber or like elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Vibration Dampers (AREA)
Abstract
本发明公开了一种碳纤维无人机机架，包括机身，所述机身的一侧外壁上通过螺栓固定连接有机翼杆，所述机翼杆上远离机身的一端通过螺栓固定连接有机翼连接座，所述机身的一侧外壁上靠近机翼杆的一侧位置处通过螺栓固定连接有支撑座，所述机身相邻于支撑座的一侧外壁上通过螺栓固定连接有第一导流座，所述支撑座上远离机身的一侧外壁上通过螺栓固定连接有第二导流座。该碳纤维无人机机架，通过钢索的拉拽，进一步的保证四个机翼杆支撑的稳定，围绕在机身外侧的钢索也可以为机身提供保护，避免碰撞时外部物体直接与机身硬力碰撞而造成内部电控元件损坏的问题，提高无人机的防护能力和使用寿命。
The invention discloses a carbon fiber unmanned aerial vehicle frame. A wing connecting seat, a support seat is fixedly connected by bolts on one side of the outer wall of the fuselage near the wing rod, and a first outer wall of the fuselage adjacent to the support seat is connected by bolts. A guide seat, a second guide seat is fixedly connected to the outer wall of the side away from the fuselage by bolts on the support seat. The carbon fiber UAV frame can further ensure the stability of the support of the four wing rods through the pulling of the steel cable. The steel cable surrounding the outer side of the fuselage can also provide protection for the fuselage, so as to prevent external objects from directly contacting the fuselage during collision. The problem of damage to the internal electronic control components caused by the hard collision of the fuselage improves the protection ability and service life of the drone.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a carbon fiber unmanned aerial vehicle frame.
Background
The unmanned plane is an unmanned plane operated by radio remote control equipment and a self-contained program control device, and is provided with an automatic pilot, a program control device and other equipment.
However, the most structural strength of current unmanned aerial vehicle frame is relatively poor, the inside electric control element's of unmanned aerial vehicle frame damage appears easily when receiving the hard force collision, current unmanned aerial vehicle frame protective capacities and crashworthiness are all relatively poor, current unmanned aerial vehicle frame receives the impact on the different positions easily when descending, and buffer capacity is limited, and the shock attenuation effect is poor, is difficult to guarantee the steady that unmanned aerial vehicle descends.
Disclosure of Invention
The invention aims to provide a carbon fiber unmanned aerial vehicle frame, and aims to solve the problems that most existing unmanned aerial vehicle frames are poor in structural strength, protective capacity and anti-collision capacity, limited in buffering capacity and poor in damping effect.
In order to achieve the purpose, the invention provides the following technical scheme: a carbon fiber unmanned aerial vehicle frame comprises a body, wherein a wing rod is fixedly connected to the outer wall of one side of the body through a bolt, a wing connecting seat is fixedly connected to one end, far away from the body, of the wing rod through a bolt, a supporting seat is fixedly connected to the position, close to the wing rod, of one side of the outer wall of one side of the body through a bolt, a first flow guide seat is fixedly connected to the outer wall of one side, adjacent to the supporting seat, of the body through a bolt, a second flow guide seat is fixedly connected to the outer wall, far away from the body, of one side of the supporting seat through a bolt, a flow guide hole is formed in the outer wall of one side of the wing rod, a steel cable penetrates through the first flow guide seat, the second flow guide seat and the flow guide hole, a cover is fixedly connected to the central position of the top of the body through a bolt, the bottom of the supporting seat is fixedly, the utility model discloses a damping column, including horizontal pole, bolt fixedly connected with connecting plate, ring, inner chamber, spring, damping column, the one end of horizontal pole is passed through the bolt fixedly connected with connecting plate, the ring is risen and fallen through bolt fixedly connected with annular to the bottom of connecting plate, the inner chamber has been seted up to the bottom of ring that rises and falls, glue is glued through gluing at the inside top of inner chamber and is glutinous being connected with the spring, glue is glued through gluing in the bottom of spring and is connected with the damping column, glue is glued through gluing in the bottom.
Preferably, the number of the wing rods is four, and the four wing rods are symmetrically arranged on the outer wall of the fuselage.
Preferably, the outer walls of one sides of the first flow guide seat and the second flow guide seat are provided with through holes with diameters larger than that of the steel cable.
Preferably, the inner cavity is connected with the sliding block in a sliding mode.
Preferably, the supporting seats are arranged in two numbers, and the two supporting seats are symmetrically arranged on the outer wall of the machine body.
Preferably, the fuselage, the wing rods and the foot rods are all made of carbon fiber materials.
Compared with the prior art, the invention has the beneficial effects that: this carbon fiber unmanned aerial vehicle frame, draw through dragging of cable wire, the stability that four wing pole supports of further assurance, can also provide the protection for the fuselage around the cable wire in the fuselage outside, external object is direct when avoiding colliding collides with the fuselage hard power and causes the problem that inside electrical control element damaged, unmanned aerial vehicle's protective capacities and life are improved, a plurality of shock attenuation posts through annular ring bottom of rising and falling, the impact on the equidirectional not when can descending unmanned aerial vehicle cushions, the elastic deformation of spring cushions the impact force, the stable level when guaranteeing unmanned aerial vehicle frame take off and land.
Drawings
FIG. 1 is a top view of the present invention;
FIG. 2 is a front view of the present invention;
FIG. 3 is a bottom view of the annular landing gear of the present invention;
FIG. 4 is a schematic view of the internal structure of the annular landing gear of the present invention;
FIG. 5 is a front view of a wing spar of the present invention.
In the figure: 1. a body; 2. a wing rod; 3. a wing connection seat; 4. a supporting seat; 5. a first flow guide seat; 6. a second flow guide seat; 7. a flow guide hole; 8. a steel cord; 9. a machine cover; 10. a foot bar; 11. a cross bar; 12. a connecting plate; 13. an annular landing ring; 14. an inner cavity; 15. a spring; 16. a shock-absorbing post; 17. a rubber pad; 18. a slide block.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-5, the present invention provides a technical solution: a carbon fiber unmanned aerial vehicle frame comprises a body 1, a wing rod 2 is fixedly connected on the outer wall of one side of the body 1 through a bolt, a wing connecting seat 3 is fixedly connected on one end of the wing rod 2 far away from the body 1 through a bolt, a supporting seat 4 is fixedly connected on the outer wall of one side of the body 1 close to the wing rod 2 through a bolt, a first guide seat 5 is fixedly connected on the outer wall of one side of the body 1 adjacent to the supporting seat 4 through a bolt, a second guide seat 6 is fixedly connected on the outer wall of one side of the supporting seat 4 far away from the body 1 through a bolt, a guide hole 7 is formed on the outer wall of one side of the wing rod 2, a steel cable 8 penetrates through the inner parts of the first guide seat 5, the second guide seat 6 and the guide hole 7, a cover 9 is fixedly connected on the central position of the top of the body 1 through a bolt, and a foot rod 10, bolt fixedly connected with horizontal pole 11 is passed through to the bottom of foot pole 10, bolt fixedly connected with connecting plate 12 is passed through to the one end of horizontal pole 11, bolt fixedly connected with annular ring 13 that rises and falls is passed through to the bottom of connecting plate 12, inner chamber 14 has been seted up to the bottom of annular ring 13 that rises and falls, the inside top of inner chamber 14 is glued through glue and is glutinous and be connected with spring 15, glue is glued through glue in the bottom of spring 15 and is glutinous and be connected with shock absorber column 16, glue is glued through glue in the bottom of shock absorber column 16 and is connected with rubber pad 17, and the embedding has slider 18 on.
In the invention: the number of the wing rods 2 is four, and the four wing rods 2 are symmetrically arranged on the outer wall of the fuselage 1; four wings are convenient to install, so that the flying stability of the unmanned aerial vehicle is ensured.
In the invention: through holes with the diameter larger than that of the steel cable 8 are formed in the outer walls of one sides of the first guide seat 5 and the second guide seat 6; the steel cable 8 can conveniently pass through the first guide seat 5 and the second guide seat 6 to fix the wing rod 2.
In the invention: the inner cavity 14 is connected with the sliding block 18 in a sliding way; the stability of the shock absorption column 16 in lifting in the inner cavity 14 is ensured.
In the invention: the number of the supporting seats 4 is two, and the two supporting seats 4 are symmetrically arranged on the outer wall of the machine body 1; the stability of the support of the machine foot rod 10 is ensured.
In the invention: the fuselage 1, the wing rods 2 and the foot rods 10 are all made of carbon fiber materials; improve the structural strength of unmanned aerial vehicle frame.
The working principle is as follows: when the unmanned aerial vehicle is used, the body 1, the wing rods 2, the wing connecting seats 3, the foot rods 10, the cross rods 11 and the annular lifting ring 13 are assembled together to complete the assembly of the frame of the unmanned aerial vehicle, the cover 9 is opened, the electric control element of the unmanned aerial vehicle is installed in the body 1, the steel cable 8 passes through the first guide seat 5, the second guide seat 6 and the guide holes 7 on the wing rods 2, the stability of the support of the four wing rods 2 is further ensured by pulling the steel cable 8, the steel cable 8 surrounding the outer side of the body 1 can also provide protection for the body 1, the problem that the internal electric control element is damaged due to the fact that an external object directly collides with the body 1 with hard force during collision is solved, the protection capability and the service life of the unmanned aerial vehicle are improved, when the unmanned aerial vehicle is lifted and descended, the damping columns 16 on the annular lifting ring 13 are extruded, the damping columns 16 extrude the springs 15, impact force during lifting and descending are, also guarantee the stable level when unmanned aerial vehicle frame takes off and land.
In summary, the following steps: this carbon fiber unmanned aerial vehicle frame, draw through dragging of cable wire 8, the stability of four wing pole 2 supports of further assurance, it also can provide the protection for fuselage 1 around cable wire 8 in the fuselage 1 outside, external object is direct and the problem that causes the damage of inside automatically controlled component with the 1 hard collision of fuselage when avoiding colliding, improve unmanned aerial vehicle's protective capacities and life, a plurality of shock attenuation posts 16 through annular ring 13 bottoms, can cushion the impact of unmanned aerial vehicle on the not equidirectional when descending, the elastic deformation of spring 15 cushions the impact force, the stable level when guaranteeing unmanned aerial vehicle frame to take off and land.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The electrical components presented in the document are all electrically connected with an external master controller and 220V mains, and the master controller can be a conventional known device controlled by a computer or the like.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011522411.9A CN112429192A (en) | 2020-12-22 | 2020-12-22 | Carbon fiber unmanned aerial vehicle frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011522411.9A CN112429192A (en) | 2020-12-22 | 2020-12-22 | Carbon fiber unmanned aerial vehicle frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112429192A true CN112429192A (en) | 2021-03-02 |
Family
ID=74696836
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011522411.9A Pending CN112429192A (en) | 2020-12-22 | 2020-12-22 | Carbon fiber unmanned aerial vehicle frame |
Country Status (1)
| Country | Link |
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| CN (1) | CN112429192A (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3856236A (en) * | 1973-05-07 | 1974-12-24 | All American Ind | Composite aircraft |
| CN108190010A (en) * | 2018-01-15 | 2018-06-22 | 天津聚飞创新科技有限公司 | Logistics unmanned plane and intelligent logistics system |
| US20180312257A1 (en) * | 2017-04-27 | 2018-11-01 | Cyborg, Inc. | Multirotor vehicle |
| US20180319476A1 (en) * | 2015-11-05 | 2018-11-08 | Elio Tecnologia, Servicos E Participacoes Ltda. | Unmanned ellipsoid multi-rotor airship and respective method of construction |
| CN109050900A (en) * | 2018-09-21 | 2018-12-21 | 南通志乐新材料有限公司 | A kind of wear-resisting express delivery unmanned plane |
| JP2019026244A (en) * | 2017-07-26 | 2019-02-21 | 株式会社ジェック | Ceiling traveling unmanned aerial vehicle |
| CN208699044U (en) * | 2018-08-24 | 2019-04-05 | 安徽中天保安服务集团有限公司 | A kind of crash protection on fire-fighting unmanned plane |
| CN209192214U (en) * | 2018-12-12 | 2019-08-02 | 志阳(天津)航空科技有限公司 | A kind of unmanned plane falling protecting device |
| CN209617510U (en) * | 2019-03-20 | 2019-11-12 | 中国农业科学院棉花研究所 | Experimental plot cell spray stalk unmanned plane |
| CN110758728A (en) * | 2019-11-04 | 2020-02-07 | 西安交通大学 | A force feedback multi-rotor unmanned aerial vehicle |
| CN211996156U (en) * | 2019-12-31 | 2020-11-24 | 潍坊翱蓝农业科技服务有限公司 | Agricultural unmanned aerial vehicle convenient to adjust and spray angle |
| CN112046757A (en) * | 2020-08-31 | 2020-12-08 | 黎云 | Unmanned aerial vehicle for flood site relief |
-
2020
- 2020-12-22 CN CN202011522411.9A patent/CN112429192A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3856236A (en) * | 1973-05-07 | 1974-12-24 | All American Ind | Composite aircraft |
| US20180319476A1 (en) * | 2015-11-05 | 2018-11-08 | Elio Tecnologia, Servicos E Participacoes Ltda. | Unmanned ellipsoid multi-rotor airship and respective method of construction |
| US20180312257A1 (en) * | 2017-04-27 | 2018-11-01 | Cyborg, Inc. | Multirotor vehicle |
| JP2019026244A (en) * | 2017-07-26 | 2019-02-21 | 株式会社ジェック | Ceiling traveling unmanned aerial vehicle |
| CN108190010A (en) * | 2018-01-15 | 2018-06-22 | 天津聚飞创新科技有限公司 | Logistics unmanned plane and intelligent logistics system |
| CN208699044U (en) * | 2018-08-24 | 2019-04-05 | 安徽中天保安服务集团有限公司 | A kind of crash protection on fire-fighting unmanned plane |
| CN109050900A (en) * | 2018-09-21 | 2018-12-21 | 南通志乐新材料有限公司 | A kind of wear-resisting express delivery unmanned plane |
| CN209192214U (en) * | 2018-12-12 | 2019-08-02 | 志阳(天津)航空科技有限公司 | A kind of unmanned plane falling protecting device |
| CN209617510U (en) * | 2019-03-20 | 2019-11-12 | 中国农业科学院棉花研究所 | Experimental plot cell spray stalk unmanned plane |
| CN110758728A (en) * | 2019-11-04 | 2020-02-07 | 西安交通大学 | A force feedback multi-rotor unmanned aerial vehicle |
| CN211996156U (en) * | 2019-12-31 | 2020-11-24 | 潍坊翱蓝农业科技服务有限公司 | Agricultural unmanned aerial vehicle convenient to adjust and spray angle |
| CN112046757A (en) * | 2020-08-31 | 2020-12-08 | 黎云 | Unmanned aerial vehicle for flood site relief |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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Application publication date: 20210302 |