CN204279927U - There is with elastic ball the rotor craft alighting gear of rotor protected effect - Google Patents
There is with elastic ball the rotor craft alighting gear of rotor protected effect Download PDFInfo
- Publication number
- CN204279927U CN204279927U CN201420612782.XU CN201420612782U CN204279927U CN 204279927 U CN204279927 U CN 204279927U CN 201420612782 U CN201420612782 U CN 201420612782U CN 204279927 U CN204279927 U CN 204279927U
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- China
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- rotor
- aircraft
- lifting lever
- articulated
- elastic ball
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Abstract
The utility model relates to the rotor craft alighting gear with elastic ball with rotor protected effect, comprise several articulated brackets be fixedly connected with aircraft body, the electric linear motor of identical number and lifting lever, with the controller of aircraft of central processor unit, the number of described articulated bracket is identical with the number of the rotor bar of rotor set on aircraft, and described each articulated bracket includes articulated bracket articulated section and tractive unit from inside to outside successively, the inner and the aircraft body of each lifting lever are hinged in perpendicular, and each lifting lever is protruding and axis and corresponding rotor rod axis horizontal plane angle are not more than 15 ° from aircraft body central bottom, the articulated bracket articulated section of articulated bracket and the body of aircraft are hinged, the extreme length at edge when the extreme length of lifting lever end is greater than rotor wing rotation described lifting lever is retracted into level attitude during along articulated section, the length of outer most edge when length due to lifting lever is greater than the blade rotary of rotor, therefore the damage of blade can be avoided, elastic ball also can play the protective effect of elastic buffer simultaneously.
Description
Technical field
The utility model relates to a kind of aircraft devices, particularly relate to a kind of for aircraft with elastic ball with protect aircraft rotor and landing damping aircraft landing gear.
Background technology
Many rotor unmanned aircrafts have rotor number to be more than or equal to 4 and are symmetrically distributed in body surrounding, a kind of aircraft that rotating configures in pairs, due to it, to have structure simple, flight stability, be easy to manipulation, noise is low, pollution-free, easy to carry, the features such as safety hazard is little, therefore play a role in many fields, also there are some potential defects in current quadrotor self, because the load of these unmanned vehicles and power are all less, cause the wind loading rating of aircraft poor, easily cause aircraft get out of hand or control error too close to other neighbouring objects, cause the blade of rotation and other close article to collide to damage, particularly in the process of flight, if blade is damaged can cause aircraft get out of hand, not only cause the failure of task, and to make from falling from high altitude and also can make into the equipment of taking photo by plane of unmanned plane and lift-launch or the damage of other expensive equipments, cause larger material damage, therefore in unmanned vehicle flight course, the blade of unmanned plane is effectively protected, unanimously exploring the problem solved without aircraft production firm.In order to carry out actv. protection to aircraft blade, current people adopt the method increasing guardrail around unmanned vehicle blade, and this method has certain effect, but shortcoming is the increase in the weight and volume of aircraft.
Utility model content
The utility model is to solve above-mentioned technical matters, provides a kind of setting on board the aircraft level can establish the alighting gear packed up and fix the rotor craft alighting gear with protected effect of elastic ball in lower end.
The utility model adopts following technical scheme: the rotor craft alighting gear should with rotor protected effect, comprise the retractable landing gear device be fixedly connected with aircraft body bottom portion, described retractable landing gear device comprises several articulated brackets be fixedly connected with aircraft body, the electric linear motor of identical number and lifting lever, with the controller of aircraft of central processor unit, the number of described articulated bracket is identical with the number of the rotor bar of rotor set on aircraft, and described each articulated bracket includes articulated bracket articulated section and tractive unit from inside to outside successively, the inner and the aircraft body of each lifting lever are hinged in perpendicular, and each lifting lever is protruding and axis and corresponding rotor rod axis horizontal plane angle are not more than 15 ° from aircraft body central bottom, the articulated bracket articulated section of articulated bracket and the body of aircraft are hinged, and this articulated bracket hinge point is in the top of the articulated position of corresponding lifting lever and aircraft, each one end of electric linear motor is fixedly connected with the tractive unit of articulated bracket, the other end of electric linear motor and lifting lever are hinged near one end of aircraft body, described electric linear motor is connected with controller of aircraft, the extreme length of blade outer rim when the extreme length of lifting lever end is greater than rotor wing rotation described lifting lever is retracted into level attitude during along articulated section.
Have with elastic ball in the rotor craft alighting gear of rotor protected effect of the present utility model, also include the elastic ball that several diameters are identical with weight, described each elastic ball is fixedly connected on corresponding lifting lever end.
Useful effect: owing to adopting above-mentioned technical scheme; the lifting lever with elastic ball with the rotor craft alighting gear of rotor protected effect of the present utility model; under the effect of electric linear motor, upwards level attitude can be raised to after unmanned vehicle takes off; because linear telescopic motor adopts turbine and worm transmission to be thus fixed on horizontal position; the length of outer most edge when length due to lifting lever is greater than the blade rotary of rotor; therefore can avoid the damage of blade, elastic ball also can play the protective effect of elastic buffer simultaneously.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the utility model is described in further detail.
Fig. 1, block diagram for aircraft of the present utility model;
Fig. 2, the structural representation be connected with aircraft body for lifting lever of the present utility model, articulated bracket;
Fig. 3, be schematic block circuit diagram of the present utility model.
Detailed description of the invention
Please refer to Fig. 1, shown in Fig. 2 and Fig. 3, for the structural representation with elastic ball with a kind of embodiment of the rotor craft alighting gear of rotor protected effect of the present utility model, the rotor craft alighting gear of rotor protected effect should be had with elastic ball, comprise the retractable landing gear device be fixedly connected with aircraft body bottom portion, described retractable landing gear device comprises several articulated brackets 5 be fixedly connected with aircraft body 1, the electric linear motor 9 of identical number and lifting lever 8, with the controller of aircraft of central processor unit, the number of described articulated bracket is identical with the number of the rotor bar 2 of rotor set on aircraft, and described each articulated bracket includes articulated bracket articulated section and tractive unit from inside to outside successively, the inner and the aircraft body of each lifting lever are hinged in perpendicular, and each lifting lever is protruding and axis and corresponding rotor rod axis horizontal plane angle are not more than 15 ° from aircraft body central bottom, the articulated bracket articulated section of articulated bracket and the body of aircraft are hinged, and this articulated bracket hinge point is in the top of the articulated position of corresponding lifting lever and aircraft, each one end of electric linear motor is fixedly connected with the tractive unit of articulated bracket, the other end of electric linear motor and lifting lever are hinged near one end of aircraft body, described electric linear motor is connected with controller of aircraft, the extreme length at edge when the extreme length of lifting lever end is greater than rotor wing rotation described lifting lever is retracted into level attitude during along articulated section.
Further, have with elastic ball in the rotor craft alighting gear of rotor protected effect of the present utility model, also include several diameters elastic ball identical with weight 7, described each elastic ball is fixedly connected on corresponding lifting lever end.Owing to adopting above-mentioned technical scheme; the lifting lever with elastic ball with the rotor craft alighting gear of rotor protected effect of the present utility model; under the effect of electric linear motor, upwards level attitude can be raised to after unmanned vehicle takes off; and then be fixed on horizontal position; the length of outer most edge when length due to lifting lever is greater than the blade rotary of rotor; therefore can avoid the damage of blade, elastic ball also can play the protective effect of elastic buffer simultaneously.
Claims (2)
1. there is with elastic ball the rotor craft alighting gear of rotor protected effect, it is characterized in that: comprise the retractable landing gear device be fixedly connected with aircraft body bottom portion, described retractable landing gear device comprises several articulated brackets be fixedly connected with aircraft body, the electric linear motor of identical number and lifting lever, with the controller of aircraft of central processor unit, the number of described articulated bracket is identical with the number of the rotor bar of rotor set on aircraft, and described each articulated bracket includes articulated bracket articulated section and tractive unit from inside to outside successively, the inner and the aircraft body of each lifting lever are hinged in perpendicular, and each lifting lever is protruding and axis and corresponding rotor rod axis horizontal plane angle are not more than 15 ° from aircraft body central bottom, the articulated bracket articulated section of articulated bracket and the body of aircraft are hinged, and this articulated bracket hinge point is in the top of the articulated position of corresponding lifting lever and aircraft, each one end of electric linear motor is fixedly connected with the tractive unit of articulated bracket, the other end of electric linear motor and lifting lever are hinged near one end of aircraft body, described electric linear motor is connected with controller of aircraft, the extreme length of blade outer rim when the extreme length of lifting lever end is greater than rotor wing rotation described lifting lever is retracted into level attitude during along articulated section.
2. the rotor craft alighting gear with elastic ball with rotor protected effect as claimed in claim 1, it is characterized in that: also include the elastic ball that several diameters are identical with weight, described each elastic ball is fixedly connected on corresponding lifting lever end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420612782.XU CN204279927U (en) | 2014-10-23 | 2014-10-23 | There is with elastic ball the rotor craft alighting gear of rotor protected effect |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420612782.XU CN204279927U (en) | 2014-10-23 | 2014-10-23 | There is with elastic ball the rotor craft alighting gear of rotor protected effect |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204279927U true CN204279927U (en) | 2015-04-22 |
Family
ID=52863114
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420612782.XU Expired - Fee Related CN204279927U (en) | 2014-10-23 | 2014-10-23 | There is with elastic ball the rotor craft alighting gear of rotor protected effect |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204279927U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131848A (en) * | 2018-08-30 | 2019-01-04 | 芜湖翼讯飞行智能装备有限公司 | A kind of safe forced landing system and its auxiliary device for unmanned plane |
| CN112793766A (en) * | 2021-02-04 | 2021-05-14 | 郑州航空工业管理学院 | Unmanned aerial vehicle is patrolled and examined to undercarriage folded cascade |
-
2014
- 2014-10-23 CN CN201420612782.XU patent/CN204279927U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131848A (en) * | 2018-08-30 | 2019-01-04 | 芜湖翼讯飞行智能装备有限公司 | A kind of safe forced landing system and its auxiliary device for unmanned plane |
| CN109131848B (en) * | 2018-08-30 | 2022-05-17 | 四川九强通信科技有限公司 | Safe forced landing system for unmanned aerial vehicle and auxiliary device thereof |
| CN112793766A (en) * | 2021-02-04 | 2021-05-14 | 郑州航空工业管理学院 | Unmanned aerial vehicle is patrolled and examined to undercarriage folded cascade |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150422 Termination date: 20171023 |