CN114013633B - Unmanned aerial vehicle with descending buffer structure - Google Patents
Unmanned aerial vehicle with descending buffer structure Download PDFInfo
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- CN114013633B CN114013633B CN202111294645.7A CN202111294645A CN114013633B CN 114013633 B CN114013633 B CN 114013633B CN 202111294645 A CN202111294645 A CN 202111294645A CN 114013633 B CN114013633 B CN 114013633B
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- aerial vehicle
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
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- 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
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- 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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention is suitable for the technical field of unmanned aerial vehicles, and provides an unmanned aerial vehicle with a landing buffer structure, which comprises an unmanned aerial vehicle main body and further comprises: descending buffer gear, descending buffer gear respectively installs a set ofly in both sides around the bottom of unmanned aerial vehicle main part, descending buffer gear is including the installation pole, cooperation slip is rotated and is installed two sliding sleeves on the installation pole, still installs the elastic component that is used for carrying out elastic support to the sliding sleeve on the installation pole, the upside of sliding sleeve is connected with the unmanned aerial vehicle main part through swing back and forth buffering subassembly, and vertical buffering subassembly, two are installed to the downside of sliding sleeve still connect through elastic expansion piece between the vertical buffering subassembly of sliding sleeve side-mounting. The invention has better combined landing buffering effect and is convenient for protecting the unmanned aerial vehicle to the maximum extent.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle with a landing buffer structure.
Background
An unmanned aircraft, referred to as "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer.
Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + the industry application is really just needed by the unmanned aerial vehicle; the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand the industrial application and develop the unmanned aerial vehicle technology.
Present unmanned aerial vehicle does not have excellent descending buffer structure, and when unmanned aerial vehicle was forced to descend, its inside part of fragile influences life. Therefore, aiming at the above current situation, there is an urgent need to develop an unmanned aerial vehicle with a landing buffer structure to overcome the shortcomings in the current practical application.
Disclosure of Invention
The embodiment of the invention aims to provide an unmanned aerial vehicle with a landing buffer structure, and aims to solve the problems that the existing unmanned aerial vehicle does not have an excellent landing buffer structure, and when the unmanned aerial vehicle is forced to land, internal parts of the unmanned aerial vehicle are easily damaged, and the service life of the unmanned aerial vehicle is influenced.
The embodiment of the invention is realized in such a way that the unmanned aerial vehicle with the landing buffer structure comprises an unmanned aerial vehicle main body and further comprises: descending buffer gear, descending buffer gear respectively installs a set ofly in both sides around the bottom of unmanned aerial vehicle main part, descending buffer gear is including the installation pole, cooperation slip is rotated and is installed two sliding sleeves on the installation pole, still installs the elastic component that is used for carrying out elastic support to the sliding sleeve on the installation pole, the upside of sliding sleeve is connected with the unmanned aerial vehicle main part through swing back and forth buffering subassembly, and vertical buffering subassembly, two are installed to the downside of sliding sleeve still connect through elastic expansion piece between the vertical buffering subassembly of sliding sleeve side-mounting.
Further technical scheme, the installation pole is "U" shape structure, the both ends of installation pole all with the bottom fixed connection of unmanned aerial vehicle main part, two slip bushes are left-right symmetry setting on the installation pole.
Further technical scheme, the elastic component is including solid fixed ring and first spring, the both sides of sliding sleeve all are equipped with a first spring on the installation pole, and two inboard first spring tip of sliding sleeve still installs on the installation pole and are fixed with solid fixed ring, just gu fixed ring is used for spacing first spring, first spring is used for supporting sliding sleeve elastic.
Further technical scheme, the back and forth swing buffering subassembly is including swing board, the two-way elastic telescopic link of arc, first ball and second ball, the bottom of unmanned aerial vehicle main part corresponds the installation pole and has seted up a lower shed swing chamber, the side-mounting of sliding sleeve is fixed with a swing board, and the swing board stretches into the swing intracavity, and the top in swing chamber is convex structure, and the one end that the sliding sleeve was kept away from to the swing board is installed first ball, and first ball supports and leans on the top in swing chamber, one side that the sliding sleeve was kept away from to the swing board still the installation is fixed with the two-way elastic telescopic link of arc, and a second ball is all installed at the both ends of the two-way elastic telescopic link of arc, and the second ball supports and leans on the side chamber wall in swing chamber.
Further technical scheme, vertical buffering subassembly is including first branch, damping ring, second branch, grab ground claw and second spring, the downside of sliding sleeve is articulated to be equipped with two bilateral symmetry's first branch, and the sliding sleeve below is equipped with grabs the ground claw, and the upside of grabbing the ground claw is articulated to be equipped with two bilateral symmetry's second branch, and the upper end correspondence of two second branches is connected with the lower extreme of two first branches is articulated, still install a damping ring between first branch and the second branch, second branch still is connected through second spring and grab the ground claw.
According to the further technical scheme, the first supporting rod and the second supporting rod are identical in length.
Further technical scheme, the damping ring is "C" shape structure, and the opening of two damping rings of same sliding sleeve below keeps away from the setting mutually, the both ends of damping ring respectively with first branch and second branch fixed connection.
According to a further technical scheme, the ground grabbing claw is of an 1/2 elliptical ring structure with a lower opening, the left side and the right side of the upper portion of the ground grabbing claw are respectively provided with a second spring, and the other ends of the two second springs are correspondingly connected and fixed with the two second supporting rods.
According to the technical scheme, the elastic telescopic piece comprises a linear bidirectional elastic telescopic rod and hinged supports, the hinged supports are mounted on hinged shafts between a first supporting rod and a second supporting rod, the left side and the right side of the hinged supports are close to each other, and the linear bidirectional elastic telescopic rod is fixedly mounted between the two hinged supports.
According to the technical scheme, the linear bidirectional elastic telescopic rod comprises inner rods, an outer barrel and a third spring, wherein the two sides of the outer barrel are respectively matched with the inner rods in a sliding mode, the third spring is arranged between the two inner rods and on the inner side of the outer barrel, the two ends of the third spring are respectively and correspondingly fixedly connected with the two inner rods, and one end, far away from the two inner rods, of the third spring is correspondingly and fixedly connected with the hinged support.
According to the unmanned aerial vehicle with the landing buffer structure, the installation rod is arranged, and the sliding sleeve is connected with the installation rod in a sliding and rotating mode, so that when the unmanned aerial vehicle lands, if the unmanned aerial vehicle falls on uneven ground, the landing buffer structure can swing adaptively, and the unmanned aerial vehicle has a good swing buffer effect through the front and rear swing buffer assemblies; simultaneously, through elastic component to sliding sleeve elastic support, also have certain buffering effect about to the setting of vertical buffering subassembly of cooperation, holistic vertical buffering shock attenuation effect preferred. In addition, through installing the elastic expansion piece between two vertical buffering subassemblies, can make the part of installation produce certain relevance on two sliding sleeves of same group's descending buffer gear, promote the descending buffering effect of combination, be convenient for carry out furthest's protection to unmanned aerial vehicle to increase of service life.
Drawings
Fig. 1 is a schematic front view of an unmanned aerial vehicle with a landing buffer structure according to an embodiment of the present invention;
fig. 2 is a schematic perspective view of a U-shaped mounting rod portion of an unmanned aerial vehicle with a landing cushioning structure according to an embodiment of the present invention;
fig. 3 is a schematic side cross-sectional structural view of a mounting portion of a main body of a drone and a swing plate with a landing buffer structure according to an embodiment of the present invention;
FIG. 4 is a schematic perspective view of the swing plate and related components of FIG. 3;
fig. 5 is a schematic cross-sectional structural view of a linear bidirectional elastic telescopic rod part in the unmanned aerial vehicle with a landing buffer structure provided by the embodiment of the invention;
fig. 6 is a schematic perspective view of a ground-grasping claw portion of the unmanned aerial vehicle with a landing buffering structure according to the embodiment of the present invention.
In the figure: 1-unmanned aerial vehicle main body, 2-installation rod, 3-fixed ring, 4-first spring, 5-swinging plate, 6-sliding sleeve, 7-first supporting rod, 8-damping ring, 9-second supporting rod, 10-ground claw, 11-second spring, 12-linear bidirectional elastic telescopic rod, 13-hinged support, 14-swinging cavity, 15-arc bidirectional elastic telescopic rod, 16-first ball, 17-second ball, 18-inner rod, 19-outer cylinder and 20-third spring.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Specific implementations of the present invention are described in detail below with reference to specific embodiments.
As shown in fig. 1 to 3, an unmanned aerial vehicle with a landing buffer structure provided for an embodiment of the present invention includes an unmanned aerial vehicle main body 1, and further includes:
descending buffer gear, descending buffer gear respectively installs a set ofly in the bottom front and back both sides of unmanned aerial vehicle main part 1, descending buffer gear is including installation pole 2, installation pole 2 is gone up the cooperation slip and is rotated and install two sliding sleeves 6, still installs the elastic component that is used for carrying out elastic support to sliding sleeve 6 on the installation pole 2, sliding sleeve 6's upside is connected with unmanned aerial vehicle main part 1 through swing back and forth buffering subassembly, and vertical buffering subassembly, two are installed to sliding sleeve 6's downside still connect through elastic expansion piece between the vertical buffering subassembly of the side-mounting of sliding sleeve 6.
In the embodiment of the invention, the installation of the installation rod 2 is adopted, and the sliding sleeve 6 is connected with the installation rod 2 in a sliding and rotating manner, so that when the unmanned aerial vehicle lands, if the unmanned aerial vehicle falls on uneven ground, the landing buffer mechanism can swing adaptively, and the front and rear swing buffer assemblies have a better swing buffer effect; simultaneously, through the elastic component to 6 elastic support of sliding sleeve, also have certain buffering effect about to the setting of vertical buffering subassembly of cooperation, holistic vertical buffering shock attenuation effect preferred. In addition, through installing the elastic expansion piece between two vertical buffering subassemblies, can make the part of installation produce certain relevance on two sliding sleeves 6 of same group's descending buffer gear, promote the descending buffering effect of combination, be convenient for carry out furthest's protection to unmanned aerial vehicle to increase of service life.
As shown in fig. 1-2, as a preferred embodiment of the present invention, the installation rod 2 is a U-shaped structure, two ends of the installation rod 2 are both fixedly connected to the bottom of the main body 1 of the unmanned aerial vehicle, two sliding sleeves 6 are symmetrically arranged on the installation rod 2, the elastic member includes a fixing ring 3 and a first spring 4, two sides of the sliding sleeves 6 are both sleeved with the first spring 4 on the installation rod 2, the end portions of the first springs 4 inside the two sliding sleeves 6 are also fixedly installed on the installation rod 2, the fixing ring 3 is used for limiting the first spring 4, and the first spring 4 is used for elastically supporting the sliding sleeves 6. Through the setting of first spring 4, can make sliding sleeve 6 have certain buffering effect about.
As shown in fig. 1 to 4, as a preferred embodiment of the present invention, the fore-and-aft swinging buffer assembly comprises a swinging plate 5, an arc-shaped bidirectional elastic telescopic rod 15, a first ball 16 and a second ball 17, the bottom of the unmanned aerial vehicle main body 1 is provided with a swing cavity 14 with a lower opening corresponding to the mounting rod 2, a swing plate 5 is fixedly arranged on the upper side of the sliding sleeve 6, the swing plate 5 extends into the swing cavity 14, the top of the swing cavity 14 is of an arc structure and can adapt to the swing of the swing plate 5, a first ball 16 is arranged at one end of the swing plate 5 far away from the sliding sleeve 6, and first ball 16 supports and leans on the top of swing chamber 14, swing plate 5 is kept away from one side of sliding sleeve 6 and is still installed and be fixed with two-way elastic telescopic rod 15 of arc, and a second ball 17 is all installed at the both ends of two-way elastic telescopic rod 15 of arc, and second ball 17 supports and leans on the side chamber wall of swing chamber 14. When sliding sleeve 6 rotates, swing board 5 swings in swing chamber 14, and first ball 16 supports with swing chamber 14 top all the time and leans on, promotes wobbling stability, and when swing board 5 swung, has better buffering effect through two-way elastic telescopic rod 15 of arc. In addition, through the arrangement of the first ball 16 and the second ball 17, the swing plate 5 can also be adapted to move along the mounting rod 2 along with the sliding sleeve 6, namely, the swing and the movement of the sliding sleeve 6 are not influenced, and the application reliability and effect are improved.
As shown in fig. 1, 5 and 6, as a preferred embodiment of the present invention, the longitudinal buffer assembly includes a first support rod 7, a shock absorbing ring 8, a second support rod 9, a ground grabbing claw 10 and a second spring 11, the lower side of the sliding sleeve 6 is hinged with two first support rods 7 which are bilaterally symmetrical, the lower side of the sliding sleeve 6 is provided with the ground grabbing claw 10, the upper side of the ground grabbing claw 10 is hinged with two second support rods 9 which are bilaterally symmetrical, the upper ends of the two second support rods 9 are correspondingly hinged with the lower ends of the two first support rods 7, the shock absorbing ring 8 is further installed between the first support rods 7 and the second support rods 9, and the second support rods 9 are further connected with the ground grabbing claw 10 through the second spring 11.
Further, the first strut 7 and the second strut 9 have the same length; the damping rings 8 are of C-shaped structures, openings of the two damping rings 8 below the same sliding sleeve 6 are far away from each other, and two ends of each damping ring 8 are fixedly connected with the first supporting rod 7 and the second supporting rod 9 respectively; the ground grabbing claw 10 is of an 1/2 elliptical ring structure with a lower opening, the left side and the right side of the upper portion of the ground grabbing claw 10 are respectively provided with a second spring 11, and the other ends of the two second springs 11 are correspondingly connected and fixed with the two second support rods 9.
In the embodiment of the invention, the two damping rings 8 have a longitudinal elastic supporting effect, and can keep the structure of the first supporting rod 7 and the second supporting rod 9 stable; the ground gripping claw 10 can be elastically supported by the second spring 11, and the ground gripping claw 10 can be kept stable; when unmanned aerial vehicle descends, grab ground claw 10 at first contact ground, second spring 11 is to grabbing 10 elastic support of ground claw, make and grab ground claw 10 and have certain swing buffering effect, first branch 7 and second branch 9 are compressed immediately, damping ring 8 can provide vertical buffering effect, through sliding sleeve 6 again, elastic component and swing back and forth buffering subassembly provide the elastic buffering effect that corresponds, the buffering effect after the combination is better, be convenient for carry out maximum protection to unmanned aerial vehicle, with increase of service life.
As shown in fig. 1, 4 and 5, as a preferred embodiment of the present invention, the elastic expansion member includes a linear bidirectional elastic expansion link 12 and a hinged support 13, a hinged support 13 is mounted on a hinged shaft between a first support 7 and a second support 9 which are close to each other on the left and right sides, a linear bidirectional elastic expansion link 12 is mounted and fixed between the two hinged supports 13, the linear bidirectional elastic expansion link 12 and an arc bidirectional elastic expansion link 15 have similar structures, which is now described by taking the linear bidirectional elastic expansion link 12 as an example, as shown in fig. 5, the linear bidirectional elastic expansion link 12 includes an inner rod 18, an outer cylinder 19 and a third spring 20, an inner rod 18 is slidably disposed on each side of the outer cylinder 19, a third spring 20 is disposed between the two inner rods 18 and inside the outer cylinder 19, and both ends of the third spring 20 are respectively and fixedly connected to the two inner rods 18, the ends of the two inner rods 18 far away from each other are correspondingly connected and fixed with the hinged support 13.
In the embodiment of the invention, the linear bidirectional elastic telescopic rod 12 and the hinged support 13 are arranged, so that the longitudinal buffer assembly can be limited to a certain extent, the stability of the longitudinal buffer assembly is ensured, and after the first supporting rod 7 and the second supporting rod 9 of one longitudinal buffer assembly are extruded, the linear bidirectional elastic telescopic rod 12 can generate linkage influence on the longitudinal buffer assembly on the other side, so that the overall buffer effect is improved; simultaneously, when a sliding sleeve 6 on the installation pole 2 removed, also can be through the linkage effect of the two-way elasticity telescopic link 12 of straight line for another sliding sleeve 6 produces the linkage influence, promotes holistic descending buffering effect through this kind of structural grouping promptly, is convenient for carry out furthest's protection to unmanned aerial vehicle, with increase of service life, is worth promoting. In addition, the specific types of the components are not particularly limited, and the components can be flexibly arranged in practical application.
The above description is intended to be illustrative of the preferred embodiment of the present invention and should not be taken as limiting the invention, but rather, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the invention.
Claims (8)
1. The utility model provides an unmanned aerial vehicle with descending buffer structure, includes the unmanned aerial vehicle main part, its characterized in that still includes:
the landing buffer mechanisms are respectively arranged on the front side and the rear side of the bottom of the unmanned aerial vehicle main body in a group;
the landing buffer mechanism comprises an installation rod, two sliding sleeves are arranged on the installation rod in a sliding and rotating mode in a matching mode, and an elastic piece used for elastically supporting the sliding sleeves is further arranged on the installation rod;
the upper side of the sliding sleeve is connected with the unmanned aerial vehicle main body through a front-back swing buffer assembly, the lower side of the sliding sleeve is provided with a longitudinal buffer assembly, and the longitudinal buffer assemblies arranged on the lower sides of the two sliding sleeves are connected through an elastic telescopic piece;
the front-back swinging buffer component comprises a swinging plate, an arc-shaped bidirectional elastic telescopic rod, a first ball and a second ball;
the bottom of the unmanned aerial vehicle main body is provided with a swing cavity with a lower opening corresponding to the mounting rod;
a swing plate is fixedly arranged on the upper side of the sliding sleeve and extends into the swing cavity, the top of the swing cavity is of an arc-shaped structure, and a first ball is arranged at one end of the swing plate, which is far away from the sliding sleeve, and abuts against the top of the swing cavity;
an arc-shaped bidirectional elastic telescopic rod is further fixedly arranged on one side, away from the sliding sleeve, of the swinging plate, two ends of the arc-shaped bidirectional elastic telescopic rod are respectively provided with a second ball, and the second balls abut against the side cavity wall of the swinging cavity;
the longitudinal buffer assembly comprises a first support rod, a shock absorption ring, a second support rod, a ground grabbing claw and a second spring;
the lower side of the sliding sleeve is hinged with two first support rods which are bilaterally symmetrical, a ground grabbing claw is arranged below the sliding sleeve, two second support rods which are bilaterally symmetrical are hinged with the upper side of the ground grabbing claw, and the upper ends of the two second support rods are correspondingly hinged with the lower ends of the two first support rods;
a damping ring is further arranged between the first supporting rod and the second supporting rod;
the second supporting rod is also connected with the ground grabbing claw through a second spring.
2. An unmanned aerial vehicle with a landing buffering structure according to claim 1, wherein the mounting rod is of a U-shaped structure, two ends of the mounting rod are fixedly connected with the bottom of the unmanned aerial vehicle body, and the two sliding sleeves are symmetrically arranged on the mounting rod.
3. A landing buffer configuration for a drone as claimed in claim 2, wherein the resilient member includes a fixed ring and a first spring;
the two sides of the sliding sleeve are respectively provided with a first spring in a sleeved mode on the installation rod, the end portions of the first springs on the inner sides of the two sliding sleeves are fixedly provided with a fixing ring on the installation rod, the fixing rings are used for limiting the first springs, and the first springs are used for elastically supporting the sliding sleeves.
4. A drone with a landing buffer structure according to any of claims 1 to 3, wherein the first and second struts are of the same length.
5. An unmanned aerial vehicle with a landing buffering structure according to claim 4, wherein the damping ring is of a C-shaped structure, openings of two damping rings below the same sliding sleeve are far away from each other, and two ends of the damping ring are fixedly connected with the first supporting rod and the second supporting rod respectively.
6. The unmanned aerial vehicle with the landing buffering structure of claim 4, wherein the ground grabbing claw is an 1/2 oval ring structure with a lower opening, the left side and the right side of the upper portion of the ground grabbing claw are respectively provided with a second spring, and the other ends of the two second springs are correspondingly connected and fixed with the two second supporting rods.
7. The unmanned aerial vehicle with the landing buffering structure of claim 1, wherein the elastic expansion part comprises a linear bidirectional elastic expansion rod and a hinged support, a hinged support is mounted on a hinged shaft between a first supporting rod and a second supporting rod which are close to each other at the left and right sides, and a linear bidirectional elastic expansion rod is fixedly mounted between the two hinged supports.
8. The unmanned aerial vehicle with the landing buffering structure of claim 7, wherein the linear bidirectional elastic telescopic rod comprises an inner rod, an outer cylinder and a third spring;
the two sides of the outer barrel are respectively provided with an inner rod in a matched sliding mode, a third spring is arranged between the two inner rods and on the inner side of the outer barrel, the two ends of the third spring are respectively and correspondingly fixedly connected with the two inner rods, and one end, far away from the two inner rods, of the third spring is correspondingly and fixedly connected with the hinged support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202111294645.7A CN114013633B (en) | 2021-11-03 | 2021-11-03 | Unmanned aerial vehicle with descending buffer structure |
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| CN202111294645.7A CN114013633B (en) | 2021-11-03 | 2021-11-03 | Unmanned aerial vehicle with descending buffer structure |
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| CN114013633A CN114013633A (en) | 2022-02-08 |
| CN114013633B true CN114013633B (en) | 2022-08-12 |
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| CN113371181A (en) * | 2021-07-27 | 2021-09-10 | 宁波阿瑞斯自动化技术有限公司 | Unmanned aerial vehicle balancing unit |
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| US9896222B2 (en) * | 2014-11-20 | 2018-02-20 | Insitu, Inc. | Capture devices for unmanned aerial vehicles, including track-borne capture lines, and associated systems and methods |
| CN208731211U (en) * | 2018-08-10 | 2019-04-12 | 平湖市佳诚房地产测绘有限公司 | A kind of mapping unmanned plane for highlands |
| CN109809018B (en) * | 2019-02-21 | 2020-04-28 | 浙江工商大学 | Shoulder carrying transportation back frame |
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| GB878385A (en) * | 1958-09-03 | 1961-09-27 | Rech Etudes Prod | Multi purpose aircraft landing gear with wheels in tandem |
| WO2005014390A2 (en) * | 2003-01-17 | 2005-02-17 | The Insitu Group | Methods and apparatuses for storing, launching, and capturing unmanned aircraft |
| JP2018024431A (en) * | 2017-10-24 | 2018-02-15 | エスゼット ディージェイアイ テクノロジー カンパニー リミテッドＳｚ Ｄｊｉ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．，Ｌｔｄ | Unmanned aerial vehicle, control system and method therefor, and landing control method for unmanned aerial vehicle |
| CN211844889U (en) * | 2020-02-23 | 2020-11-03 | 刘成锐 | Stable surveying and mapping unmanned aerial vehicle rises and falls |
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| CN113371181A (en) * | 2021-07-27 | 2021-09-10 | 宁波阿瑞斯自动化技术有限公司 | Unmanned aerial vehicle balancing unit |
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| CN114013633A (en) | 2022-02-08 |
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