CN204279928U - Multi-axis aircraft automatic deploying and retracting alighting gear - Google Patents
Multi-axis aircraft automatic deploying and retracting alighting gear Download PDFInfo
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- CN204279928U CN204279928U CN201420591156.7U CN201420591156U CN204279928U CN 204279928 U CN204279928 U CN 204279928U CN 201420591156 U CN201420591156 U CN 201420591156U CN 204279928 U CN204279928 U CN 204279928U
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Abstract
The utility model discloses a kind of Multi-axis aircraft automatic deploying and retracting alighting gear, comprise left shell and the right shell body of left and right fastening, the side of left shell and right shell body all has pilot hole and fixed orifice, a driving head is provided with between left shell and right shell body, driving head side is in " 7 " font, driving head front end has pin-and-hole, connecting pin is provided with in pin-and-hole, driving head bottom has locating notch, the axis of guide is provided with in locating notch, the left end of the axis of guide, right-hand member are arranged in the pilot hole of left shell, right shell body respectively, and driving head front end is connected with connection tube head by connecting pin.The utility model effectively promotes in unmanned vehicle descent by simple machine structure safety of landing, facilitate the operation of load bearing equipment, good damping effect, is applicable to multiple environment with a varied topography, ensures that unmanned vehicle safety and steady lands, and the obstacle of large volume can be evaded, integral structure takes up room little, and overall volume is little, and quality is light, sensitivity and reliability high, applied range.
Description
Technical field
The utility model relates to a kind of compact conformation, portable and smart, controls simple, the Multi-axis aircraft automatic deploying and retracting alighting gear of applied range.
Background technology
Chinese Patent Application No.: 201420016221.3, disclose a kind of operation of landing gear, comprise stand frame and supporting leg, supporting leg is rotationally connected with the first end of stand frame, between stand frame and supporting leg, interlock has U-shaped connecting rod and drive link, stand frame is fixed with driving steering wheel, steering wheel is driven to be connected to drive link and to drive drive link to swing, drive link swings and drives U-shaped connecting rod to carry out dipping and heaving, the lifting of U-shaped connecting rod realizes carrying out push-and-pull to supporting leg, steering wheel is driven to be installed on stand frame by steering wheel mount pad, start space is formed between steering wheel mount pad and stand frame, rudder angle assembly is provided with in start space, rudder angle assembly has an anchor shaft, anchor shaft is connected to drive link, the power of steering wheel is driven to drive to drive link by rudder angle assembly, rotate to drive drive link.
Chinese Patent Application No.: 201410033875.1, discloses a kind of alighting gear of aircraft, and this alighting gear comprises: mounting base, the first foot rest, the second foot rest and transmission device.First foot rest and the second foot rest are oppositely arranged, and are rotationally connected with mounting base respectively.Transmission device is connected with the second foot rest with the first foot rest respectively, with by transmission device transferring power and then drive the first foot rest and the second foot rest to rotate around mounting base.
Chinese Patent Application No.: 201410012085.5, disclose a kind of operation of landing gear, comprise stand frame and supporting leg, described supporting leg is rotationally connected with the first end of described stand frame, between described stand frame and supporting leg, also interlock has U-shaped connecting rod and drive link, described stand frame is fixed with driving steering wheel, this driving steering wheel is connected to described drive link and drives described drive link to swing, drive link swings and drives described U-shaped connecting rod to carry out dipping and heaving, and the lifting of described U-shaped connecting rod realizes carrying out push-and-pull to supporting leg further.
Foregoing invention creates unreasonable structure, later maintenance is complicated, from great, stability and safety poor performance, be different from the operation of landing gear that tradition adopts steering wheel transmission on the market, its moment and stability and safety performance are much higher than steering wheel transmission, drive rudder angle and the rudder angle groove of steering wheel assembly, be the product that market can directly obtain, without creative; The alighting gear of servo driving in actual applications, if control bad to unmanned vehicle, easily damages inner gear parts, and moment and stability and safety poor.
Utility model content
The purpose of this utility model is, overcomes the above-mentioned defect of prior art, provides a kind of compact conformation, easy accessibility, portable and smart, the Multi-axis aircraft automatic deploying and retracting alighting gear of safety and stability.
For achieving the above object, the technical scheme that the utility model provides is as follows: a kind of Multi-axis aircraft automatic deploying and retracting alighting gear, comprise left shell and the right shell body of left and right fastening, the side of left shell and right shell body all has pilot hole and fixed orifice, a driving head is provided with between left shell and right shell body, driving head side is in " 7 " font, driving head front end has pin-and-hole, connecting pin is provided with in pin-and-hole, driving head bottom has locating notch, the axis of guide is provided with in locating notch, the left end of the axis of guide, right-hand member is arranged at left shell respectively, in the pilot hole of right shell body, driving head front end is connected with connection tube head by connecting pin.
Driving head left surface, right flank are respectively to being convexly equipped with left fix shaft, right fix shaft outward, left fix shaft, right fix shaft are arranged in the fixed orifice of left shell, right shell body respectively, difference sheathed left copper sheathing, right copper sheathing between the fixed orifice of left fix shaft, right fix shaft and left shell, right shell body.
Screw is had in the middle part of the axis of guide, transmission shaft is bolted with in screw, transmission shaft is made up of bolt, the front end of transmission shaft is screw rod, rear end is nut, transmission shaft rear end laterally offers screens notch, transmission shaft rear end is connected with drop-gear box, and the screens notch that the output shaft of drop-gear box is inserted into transmission shaft is attached thereto, and drop-gear box input end is provided with motor.
Transmission shaft front end sleeve is provided with clutch shaft bearing, rear end is arranged with the second bearing.
Structural principle: this alighting gear is installed on the bottom of unmanned vehicle, connection tube head connects inverse-T-shaped gear support bar, connects tube head can customize different length diameter according to practical application, facilitates the gear support bar of different size to connect; Motor driving drop-gear box is controlled by remote controller, drop-gear box drives in transmission shaft by output shaft, the crank-rocker structure formed by transmission shaft and the axis of guide makes the axis of guide on transmission shaft from front to back or displacement back to front, make the axis of guide in pilot hole from from left to right or from right toward moving left, positioning shaft sleeve due to driving head is located in fixed orifice, thus driving head is rotated up or down centered by fix shaft, realize with this object controlling alighting gear automatic deploying and retracting; Put down the gear support pole pair unmanned vehicle being connected to connection tube head during landing to support, to take photo by plane or in other actual job process, gear support bar can be controlled pack up, the gear support bar packed up no longer hinders taking lens, ensure 360 degree of photographic goods comprehensive smoothness shootings, or be convenient to the work operations of load bearing equipment bottom unmanned vehicle; This alighting gear coordinates control circuit to have " locked " function, ensures unmanned vehicle whole machine of energy safety supports in descent, protection load bearing equipment.
Usefulness of the present utility model is: effectively promote in unmanned vehicle descent by compact physical construction safety of landing, facilitate the operation of load bearing equipment, good damping effect, is applicable to multiple environment with a varied topography, ensures that unmanned vehicle safety and steady lands, and the obstacle of large volume can be evaded, integral structure takes up room little, and overall volume is little, and quality is light, sensitivity and reliability high, applied range.
Accompanying drawing explanation
Fig. 1 is the utility model Multi-axis aircraft automatic deploying and retracting alighting gear exploded view;
Fig. 2 is the utility model Multi-axis aircraft automatic deploying and retracting alighting gear block diagram;
Fig. 3 is the utility model Multi-axis aircraft automatic deploying and retracting alighting gear operating diagram.
Detailed description of the invention
Be further described with regard to the technical solution of the utility model below in conjunction with accompanying drawing and preferred embodiment.
As shown in Figure 1-Figure 3, a kind of Multi-axis aircraft automatic deploying and retracting alighting gear described in the utility model, comprise left shell 1 and the right shell body 2 of left and right fastening, realize being fastened and connected by some shell joint pins 9 between left shell 1 and right shell body 2, the side of left shell 1 has left pilot hole 11 and left fixed orifice 12, the side of right shell body 2 has right pilot hole 21 and right fixed orifice 22, a driving head 3 is provided with between left shell 1 and right shell body 2, driving head 3 side is in " 7 " font, driving head 3 front end has pin-and-hole 30, connecting pin 31 is provided with in pin-and-hole 30, driving head 3 bottom has locating notch 32, laterally the axis of guide 4 is provided with in locating notch 32, the left end of the axis of guide 4, right-hand member is arranged at left pilot hole 11 respectively, in right pilot hole 21, driving head 3 front end is connected with by connecting pin 31 and connects tube head 10.
Driving head 3 left surface, right flank are respectively to being convexly equipped with left fix shaft 33, right fix shaft 34 outward, left fix shaft 33, right fix shaft 34 are arranged in left fixed orifice 12, right fixed orifice 22 respectively, difference sheathed left copper sheathing 331, right copper sheathing 341 between left fix shaft 33, right fix shaft 34 and left fixed orifice 12, right fixed orifice 22.
Screw is had in the middle part of the axis of guide 4, transmission shaft 5 is bolted with in screw, transmission shaft 5 is made up of bolt, the front end of transmission shaft 5 is screw rod, rear end is nut, transmission shaft 5 rear end laterally offers screens notch 50, transmission shaft 5 rear end is connected with drop-gear box 6, and the screens notch 50 that the output shaft 61 of drop-gear box 6 is inserted into transmission shaft 5 is attached thereto, and drop-gear box 6 input end is provided with motor 7.
Transmission shaft 5 front end sleeve is provided with clutch shaft bearing 81, rear end is arranged with the second bearing 82.
Principle of work: by left shell, the contiguous block 9 that right shell body bottom is arranged is connected with aircraft, at the connection tube head of this alighting gear, gear support bar is set, connect tube head and driving head when the down state of gear support bar and left shell, right shell body is parallel, when gear support bar needs to pack up, control motor by remote controller to rotate forward, drive drop-gear box, drop-gear box drives to the transmission shaft be arranged on the locating notch of driving head bottom by output shaft, because the screw-rod structure on transmission shaft is threaded with the screw of the axis of guide, cause axis of guide displacement from front to back on transmission shaft, and make the axis of guide in pilot hole by moving from left to right, further, positioning shaft sleeve due to driving head is located in fixed orifice, thus the crank-rocker structure making driving head be formed by transmission shaft and the axis of guide is rotated up centered by fix shaft, pack up being arranged at the gear support bar connecting tube head, when gear support bar needs to put down, control motor by remote controller to reverse.
Above-described is only principle of the present utility model and preferred embodiment.It should be pointed out that to those skilled in the art, under the prerequisite not departing from the utility model principle, some modification and improvement can also be made, also should be considered as belonging to protection domain of the present utility model.
Claims (4)
1. a Multi-axis aircraft automatic deploying and retracting alighting gear, comprise left shell and the right shell body of left and right fastening, it is characterized in that: the side of left shell and right shell body all has pilot hole and fixed orifice, a driving head is provided with between left shell and right shell body, driving head side is in " 7 " font, driving head front end has pin-and-hole, connecting pin is provided with in pin-and-hole, driving head bottom has locating notch, the axis of guide is provided with in locating notch, the left end of the axis of guide, right-hand member are arranged in the pilot hole of left shell, right shell body respectively, and driving head front end is connected with connection tube head by connecting pin.
2. Multi-axis aircraft automatic deploying and retracting alighting gear according to claim 1, it is characterized in that: described driving head left surface, right flank are respectively to being convexly equipped with left fix shaft, right fix shaft outward, left fix shaft, right fix shaft are arranged in the fixed orifice of left shell, right shell body respectively, difference sheathed left copper sheathing, right copper sheathing between the fixed orifice of left fix shaft, right fix shaft and left shell, right shell body.
3. Multi-axis aircraft automatic deploying and retracting alighting gear according to claim 1, it is characterized in that: in the middle part of the described axis of guide, have screw, transmission shaft is bolted with in screw, transmission shaft is made up of bolt, the front end of transmission shaft is screw rod, rear end is nut, and transmission shaft rear end laterally offers screens notch, and transmission shaft rear end is connected with drop-gear box, the screens notch that the output shaft of drop-gear box is inserted into transmission shaft is attached thereto, and drop-gear box input end is provided with motor.
4. Multi-axis aircraft automatic deploying and retracting alighting gear according to claim 3, is characterized in that: described transmission shaft front end sleeve is provided with clutch shaft bearing, rear end is arranged with the second bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420591156.7U CN204279928U (en) | 2014-10-13 | 2014-10-13 | Multi-axis aircraft automatic deploying and retracting alighting gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420591156.7U CN204279928U (en) | 2014-10-13 | 2014-10-13 | Multi-axis aircraft automatic deploying and retracting alighting gear |
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| Publication Number | Publication Date |
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| CN204279928U true CN204279928U (en) | 2015-04-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420591156.7U Active CN204279928U (en) | 2014-10-13 | 2014-10-13 | Multi-axis aircraft automatic deploying and retracting alighting gear |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107521673A (en) * | 2016-06-22 | 2017-12-29 | 北京臻迪机器人有限公司 | Connect the holder device of foot stool and fuselage |
| CN108177762A (en) * | 2017-12-22 | 2018-06-19 | 航天神舟飞行器有限公司 | A kind of Quick folding mechanism of multi-rotor unmanned aerial vehicle undercarriage |
| CN109895999A (en) * | 2019-03-21 | 2019-06-18 | 北京航空航天大学 | A kind of undercarriage control device for lightweight aircraft |
-
2014
- 2014-10-13 CN CN201420591156.7U patent/CN204279928U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107521673A (en) * | 2016-06-22 | 2017-12-29 | 北京臻迪机器人有限公司 | Connect the holder device of foot stool and fuselage |
| CN107521673B (en) * | 2016-06-22 | 2022-03-25 | 北京臻迪机器人有限公司 | Support device for connecting foot rest and machine body |
| CN108177762A (en) * | 2017-12-22 | 2018-06-19 | 航天神舟飞行器有限公司 | A kind of Quick folding mechanism of multi-rotor unmanned aerial vehicle undercarriage |
| CN108177762B (en) * | 2017-12-22 | 2021-06-04 | 航天神舟飞行器有限公司 | Quick folding mechanism of many rotor unmanned aerial vehicle undercarriage |
| CN109895999A (en) * | 2019-03-21 | 2019-06-18 | 北京航空航天大学 | A kind of undercarriage control device for lightweight aircraft |
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