CN106005378A - Undercarriage for shipborne unmanned aerial vehicle - Google Patents
Undercarriage for shipborne unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106005378A CN106005378A CN201610501902.2A CN201610501902A CN106005378A CN 106005378 A CN106005378 A CN 106005378A CN 201610501902 A CN201610501902 A CN 201610501902A CN 106005378 A CN106005378 A CN 106005378A
- Authority
- CN
- China
- Prior art keywords
- buffer unit
- undercarriage
- gimbal lever
- stay tube
- joint
- 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
Classifications
-
- 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
-
- 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
-
- 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
- B64C2025/325—Alighting gear characterised by elements which contact the ground or similar surface specially adapted for helicopters
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
The invention discloses an undercarriage for a shipborne unmanned aerial vehicle. The undercarriage comprises one first joint, two second joints, two supporting devices and one balancing device, wherein the two ends of the lower part of the first joint are respectively connected with the two supporting devices; the two second joints are respectively arranged at one ends of the two supporting devices away from the first joint; the balancing device is connected with the two second joints; the two ends of the balancing device respectively penetrate through the two second joints; each of the supporting devices comprises a first supporting pipe and a second supporting pipe; the second supporting pipe is sleeved in the first supporting pipe; a first buffering device is arranged in the first supporting pipe; the first buffering device is in contact with the second supporting pipe. The buffering device is used for supplying a counter acting force when the unmanned aerial vehicle lands, so that the stability of the unmanned aerial vehicle while landing is greatly increased.
Description
Technical field
The present invention relates to boat-carrying unmanned air vehicle technique field, particularly relate to the undercarriage of a kind of boat-carrying unmanned plane.
Background technology
At present, domestic rotor craft undercarriage uses the pattern of a monolateral bar mostly, i.e. aircraft both sides are respectively arranged with the support of T character form structure, the undercarriage of this structure of tradition, structure is single and support strength is poor, and when landing, stability is inadequate, has rollover probability, commonly used integrated manufacture in manufacture process simultaneously, hence in so that manufacturing cost is the highest.
Summary of the invention
The invention aims to solve shortcoming present in prior art, and the undercarriage of a kind of boat-carrying unmanned plane proposed.
To achieve these goals, present invention employs following technical scheme:
A kind of undercarriage of boat-carrying unmanned plane, including first joint, two the second joints, two support meanss and a bascule, first two ends, joint bottom is connected with two support meanss respectively, two the second joints are separately positioned on two support meanss one end away from the first joint, bascule connects two the second joints, and the two ends of bascule extend through two the second joints；Support means includes first stay tube and second stay tube, and second supports pipe box is located in first stay tube, is provided with the first buffer unit, and the first buffer unit and second stay tube contact in first stay tube；Bascule includes that first gimbal lever and second gimbal lever, first gimbal lever and second gimbal lever are connected by connecting rod, is equipped with the second buffer unit offseted with connecting rod in first gimbal lever and second gimbal lever.
Preferably, the first buffer unit, the second buffer unit all use pneumatic buffer device, and pneumatic buffer device is connected by guide rail and first stay tube, and the end at guide rail is provided with baffle plate.
Preferably, the first buffer unit, the second buffer unit all use spring, are equipped with, in first stay tube, first gimbal lever and second gimbal lever, the ring baffle offseted with spring.
Preferably, support means two ends are connected by the first locking device and the first joint, and bascule is connected by the second locking device and the second joint, and the first locking device and the second locking device all use fastened by screw mode.
After the present invention uses above-mentioned structure, traditional monolateral supporting construction is changed into bilateral support structure, buffer unit is set in support means, on bascule simultaneously, greatly adds support strength, it is ensured that will not turn on one's side during unmanned plane landing.The present invention uses and arranges buffer unit in first stay tube, first gimbal lever, second gimbal lever, one counteracting force when buffer unit provides land when unmanned plane lands, and greatly adds the unmanned plane stability when landing.In the present invention, buffering uses pneumatic buffer device, and pneumatic buffer device is connected with tube wall by guide rail, it is ensured that the stationarity that unmanned plane lands, it is to avoid unmanned plane is turned on one's side.
Accompanying drawing explanation
Fig. 1 is the structural representation of the undercarriage of a kind of boat-carrying unmanned plane that the present invention proposes.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is only a part of embodiment of the present invention rather than whole embodiments.
With reference to Fig. 1, a kind of undercarriage of boat-carrying unmanned plane, including first joint 2, two support meanss 3 of 1, two the second joints and a bascule 4, first two ends, joint 1 bottom is connected with two support meanss 3 respectively, two the second joints 2 are separately positioned on two support meanss 3 one end away from the first joint 1, bascule 4 connects two the second joints 2, and the two ends of bascule 4 extend through two the second joints 2；Support means 3 includes that first stay tube 31 and second stay tube 32, second stay tube 32 are set in first stay tube 31, is provided with the first buffer unit 6, and the first buffer unit 6 contacts with second stay tube 32 in first stay tube 31；Bascule 4 includes first gimbal lever 41 and second gimbal lever 42, and first gimbal lever 41 and second gimbal lever 42 are connected by connecting rod 5, are equipped with, in first gimbal lever 41 and second gimbal lever 42, the second buffer unit 7 offseted with connecting rod 5.
In the present invention, first buffer unit the 6, second buffer unit 7 all uses pneumatic buffer device, pneumatic buffer device 61 to be connected with first stay tube 31 by guide rail 62, and the end at guide rail 62 is provided with baffle plate；Pneumatic buffer device 71 is connected with connecting rod 5 two ends by guide rail 72, and the end at guide rail 62 is provided with baffle plate；One counteracting force when buffer unit provides land when unmanned plane lands, greatly adds the unmanned plane stability when landing, it is ensured that the stationarity that unmanned plane lands, it is to avoid unmanned plane is turned on one's side.
After the present invention uses above-mentioned structure, traditional monolateral supporting construction is changed into bilateral support structure, buffer unit is set in support means, on bascule simultaneously, greatly adds support strength, it is ensured that will not turn on one's side during unmanned plane landing.
In the present invention, support means 3 two ends are connected by the first locking device and the first joint 1, bascule 4 is connected by the second locking device and the second joint 2, first locking device and the second locking device all use fastened by screw mode, connected mode is simple and reliable, convenience easy to manufacture, greatly reduces manufacturing cost.
The above; it is only the present invention preferably detailed description of the invention; but protection scope of the present invention is not limited thereto; any those familiar with the art is in the technical scope that the invention discloses; according to technical scheme and inventive concept equivalent or change in addition thereof, all should contain within protection scope of the present invention.
Claims (4)
1. the undercarriage of a boat-carrying unmanned plane, it is characterized in that, including first joint, two the second joints, two support meanss and a bascule, first two ends, joint bottom is connected with two support meanss respectively, two the second joints are separately positioned on two support meanss one end away from the first joint, bascule connects two the second joints, and the two ends of bascule extend through two the second joints；Support means includes first stay tube and second stay tube, and second supports pipe box is located in first stay tube, is provided with the first buffer unit, and the first buffer unit and second stay tube contact in first stay tube；Bascule includes that first gimbal lever and second gimbal lever, first gimbal lever and second gimbal lever are connected by connecting rod, is equipped with the second buffer unit offseted with connecting rod in first gimbal lever and second gimbal lever.
The undercarriage of a kind of boat-carrying unmanned plane the most according to claim 1, it is characterised in that the first buffer unit, the second buffer unit all use pneumatic buffer device, pneumatic buffer device is connected by guide rail and first stay tube, and the end at guide rail is provided with baffle plate.
The undercarriage of a kind of boat-carrying unmanned plane the most according to claim 1, it is characterised in that the first buffer unit, the second buffer unit all use spring, is equipped with, in first stay tube, first gimbal lever and second gimbal lever, the ring baffle offseted with spring.
The undercarriage of a kind of boat-carrying unmanned plane the most according to claim 1, it is characterized in that, support means two ends are connected by the first locking device and the first joint, bascule is connected by the second locking device and the second joint, and the first locking device and the second locking device all use fastened by screw mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610501902.2A CN106005378A (en) | 2016-06-30 | 2016-06-30 | Undercarriage for shipborne unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610501902.2A CN106005378A (en) | 2016-06-30 | 2016-06-30 | Undercarriage for shipborne unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106005378A true CN106005378A (en) | 2016-10-12 |
Family
ID=57104511
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610501902.2A Pending CN106005378A (en) | 2016-06-30 | 2016-06-30 | Undercarriage for shipborne unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106005378A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108773477A (en) * | 2018-03-12 | 2018-11-09 | 芜湖翼讯飞行智能装备有限公司 | A kind of unmanned plane landing safety protection bracket |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4976967B2 (en) * | 2007-09-18 | 2012-07-18 | トヨタ自動車株式会社 | Mobile landing gear |
| CN204822063U (en) * | 2015-06-30 | 2015-12-02 | 江苏首控制造技术有限公司 | Unmanned aerial vehicle undercarriage |
| CN204916167U (en) * | 2015-07-21 | 2015-12-30 | 天津晓奇科技发展有限公司 | Many rotor unmanned aerial vehicle carbon pipe damping shock attenuation undercarriage |
| CN205150225U (en) * | 2015-11-21 | 2016-04-13 | 长沙学院 | Six rotor crafts of area buffering foot rest |
-
2016
- 2016-06-30 CN CN201610501902.2A patent/CN106005378A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4976967B2 (en) * | 2007-09-18 | 2012-07-18 | トヨタ自動車株式会社 | Mobile landing gear |
| CN204822063U (en) * | 2015-06-30 | 2015-12-02 | 江苏首控制造技术有限公司 | Unmanned aerial vehicle undercarriage |
| CN204916167U (en) * | 2015-07-21 | 2015-12-30 | 天津晓奇科技发展有限公司 | Many rotor unmanned aerial vehicle carbon pipe damping shock attenuation undercarriage |
| CN205150225U (en) * | 2015-11-21 | 2016-04-13 | 长沙学院 | Six rotor crafts of area buffering foot rest |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108773477A (en) * | 2018-03-12 | 2018-11-09 | 芜湖翼讯飞行智能装备有限公司 | A kind of unmanned plane landing safety protection bracket |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20161012 |