CN215663972U - Novel unmanned aerial vehicle load carries device - Google Patents
Novel unmanned aerial vehicle load carries device Download PDFInfo
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- CN215663972U CN215663972U CN202122242744.2U CN202122242744U CN215663972U CN 215663972 U CN215663972 U CN 215663972U CN 202122242744 U CN202122242744 U CN 202122242744U CN 215663972 U CN215663972 U CN 215663972U
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Abstract
A novel unmanned aerial vehicle load carrying device comprises two transverse rods, two longitudinal rods, a lateral load and a lower load, wherein the two transverse rods and the two longitudinal rods are connected into a bracket structure in a shape like a Chinese character 'jing' through four cross buckles, both ends of the longitudinal rod are fixedly provided with an undercarriage connecting piece, the longitudinal rod can be fixedly arranged on the undercarriage through the undercarriage connecting piece, two ends of the transverse rod are fixedly provided with a load carrying rod which is in a Z-shaped structure, one end of the load rod is detachably embedded into the transverse rod, two lateral mounting plates are fixedly mounted between the two load rods at the two ends of the transverse rod, the lateral load is detachably and fixedly arranged on the lateral mounting plate, the lower load is detachably arranged on the two transverse rods, and the lower load is arranged between the two longitudinal rods. The utility model has simple structure and reasonable design and can adapt to the loading of loads of various specifications.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a novel unmanned aerial vehicle load mounting device.
Background
At present, along with the development of science and technology, unmanned aerial vehicles, especially unmanned helicopters, are more and more popular in the fields of logistics transportation, fire control, survey and the like. Unmanned helicopters, especially medium-sized and large-sized unmanned helicopters, are gradually drawing attention from various people due to their excellent transportation performance. With the gradual investment of social research and development, the unmanned helicopter needs to carry various task loads to execute tasks.
However, when the unmanned helicopter takes off, the requirement on the center of gravity is generally strict, and the center of gravity needs to be adjusted by using the balance weight before taking off, so that the capacity of mounting equipment of the unmanned helicopter is greatly reduced. For this reason, many unmanned helicopters adjust the center of gravity by changing the layout of their own equipment, but face diversified task load mounting requirements, which increases the design and development cost and is difficult to popularize and apply. In some unmanned helicopters, a cargo cabin or a load hanging rack is integrated with a fuselage, and cargos and loads are separated by a partition or a net, so that the weight of the unmanned helicopter is increased, and the unmanned helicopter is difficult to adapt to loading requirements of various task loads.
Through the above analysis, the problems and defects of the prior art are as follows:
(1) the unmanned helicopter has strict requirements on gravity center balancing, and the balancing weight reduces the capacity of the unmanned helicopter for mounting equipment;
(2) the task load of the unmanned helicopter has the characteristic of diversification, and the rapid replacement is difficult to realize during outfield operation;
(3) when the task load of the unmanned helicopter is changed, a very mature, reliable and efficient gravity center adjusting scheme is not available;
(4) the unmanned helicopter is integrated with a warehouse or a hanging rack, the self weight of the unmanned helicopter and the die sinking manufacturing cost are increased, and task loads of various sizes are difficult to mount.
SUMMERY OF THE UTILITY MODEL
The utility model aims to overcome the defects in the prior art, provides a novel unmanned aerial vehicle load mounting device, and solves the problems that in the prior art, a cargo cabin or a load hanger is integrated with a fuselage, the capability of unmanned helicopter mounting equipment is reduced, and the diversification of task loads is difficult to adapt.
In order to achieve the purpose, the utility model adopts the technical scheme that:
a novel unmanned aerial vehicle load carrying device comprises two transverse rods, two longitudinal rods, a lateral load and a lower load, wherein the two transverse rods and the two longitudinal rods are connected into a bracket structure in a shape like a Chinese character 'jing' through four cross buckles, both ends of the longitudinal rod are fixedly provided with an undercarriage connecting piece, the longitudinal rod can be fixedly arranged on the undercarriage through the undercarriage connecting piece, two ends of the transverse rod are fixedly provided with a load carrying rod which is in a Z-shaped structure, one end of the load rod is detachably embedded into the transverse rod, two lateral mounting plates are fixedly mounted between the two load rods at the two ends of the transverse rod, the lateral load is detachably and fixedly arranged on the lateral mounting plate, the lower load is detachably arranged on the two transverse rods, and the lower load is arranged between the two longitudinal rods.
Further, the side mounting plate pass through the connecting piece install in on the load pole, the below load passes through the connecting piece to be installed in two on the transverse bar, the connecting piece includes body and lower body, a half slot has all been seted up on last body and the lower body, the body respectively fixed mounting in down on side mounting plate and the below load, it is fixed in to go up body accessible set screw down on the body, go up the body install in when the body is gone up down, two half slots can constitute one with the circular slot of transverse bar and load pole looks adaptation.
Further, the undercarriage connecting piece includes connecting piece body and the fixed plate of "U" font, the one end of connecting piece body is fixed in on the longitudinal rod, and the semicircular mounting groove with undercarriage looks adaptation is seted up to the other end, two mounting hole have been seted up to the below of mounting groove, the open end of fixed plate also seted up two with the mounting hole that aligns, fixed plate accessible fixing bolt passes mounting hole on the fixed plate and the mounting hole on the connecting piece body are fixed in on the connecting piece body, when the fixed plate install in when the connecting piece body, the fixed plate can form an installation circular slot with undercarriage looks adaptation with the mounting groove, undercarriage connecting piece accessible the installation circular slot is fixed in on the undercarriage.
Furthermore, one end of the load carrying rod is provided with a sleeve rod, the outer diameter of the sleeve rod is smaller than the inner diameter of the transverse rod, the sleeve rod can be embedded into the transverse rod in an aligned mode, and the sleeve rod are fixed through screws.
The utility model has simple structure and reasonable design, two transverse rods and two longitudinal rods can be connected into a bracket structure in a shape like a Chinese character 'jing' through the cross buckles, and then the bracket structure is fixed on the undercarriage of the unmanned aerial vehicle through the undercarriage connecting pieces at the two ends of the longitudinal rods. Compared with an integrated load structure, the load balancing device can adjust different installation positions according to different loads so as to meet different load tasks, the two transverse rods and the two longitudinal rods are connected through the cross buckles, the sleeve rod on the load rod is fixed with the transverse rods through the screws, the adjustment is convenient and simple, the adjustment speed is high, marks can be made on the longitudinal rods and the sleeve rod according to different loads, and when the same load task is met again, the corresponding position can be found quickly, and the balancing of the gravity center is achieved.
Drawings
FIG. 1 is a schematic diagram of the apparatus of the present invention;
FIG. 2 is a schematic view of the cross fastener of the present invention;
FIG. 3 is a schematic structural view of a connector body according to the present invention;
FIG. 4 is an exploded view of the mounting structure of the load beam on the cross beam in the present invention;
FIG. 5 is a schematic view of the installation structure of the connecting member on the side mounting plate according to the present invention;
in the figure: 1. the landing gear comprises a transverse rod, 2, a longitudinal rod, 3, a side load, 4, a lower load, 5, a cross buckle, 6, a landing gear connecting piece, 61, a connecting piece body, 62, a fixing plate, 7, a load rod, 8, a side mounting plate, 9, a connecting piece, 91, an upper body, 92, a lower body, 10, a mounting groove, 11, a mounting through hole, 12, a mounting hole, 13 and a sleeve rod.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1-5, a novel unmanned aerial vehicle load carrying device comprises two transverse rods 1, two longitudinal rods 2, a lateral load 3 and a lower load 4, wherein the two transverse rods 1 and the two longitudinal rods 2 are connected into a support structure in a shape like a Chinese character jing through four cross buckles 5, two ends of each longitudinal rod 2 are fixedly provided with a landing gear connecting piece 6, the longitudinal rods 2 can be fixedly arranged on a landing gear through the landing gear connecting pieces 6, two ends of each transverse rod 1 are fixedly provided with a load rod 7, each load rod 7 is in a structure like a Chinese character "Z", one end of each load rod 7 is detachably embedded into the transverse rod 1, two lateral mounting plates 8 are fixedly arranged between the two load rods 7 at the two ends of each transverse rod 1, and the lateral load 3 is detachably and fixedly arranged on the lateral mounting plates 8, the lower load 4 is detachably arranged on the two transverse rods 1, and the lower load 4 is arranged between the two longitudinal rods 2; the lateral mounting plate 8 is mounted on the load rod 7 through a connecting piece 9, the lower load 4 is mounted on the two transverse rods 1 through a connecting piece 9, the connecting piece 9 comprises an upper body 91 and a lower body 92, the upper body 91 and the lower body 92 are both provided with a semicircular groove, the lower body 92 is fixedly mounted on the lateral mounting plate 8 and the lower load 4 respectively, the upper body 91 can be fixed on the lower body 92 through a fixing screw, and when the upper body 91 is mounted on the lower body 92, the two semicircular grooves can form a circular groove matched with the transverse rods 1 and the load rod 7; the landing gear connecting piece 6 comprises a connecting piece body 61 and a U-shaped fixing plate 62, one end of the connecting piece body 61 is fixed on the longitudinal rod 2, the other end is provided with a semicircular mounting groove 10 matched with the landing gear, two mounting through holes 11 are arranged below the mounting groove 10, two mounting holes 12 aligned with the mounting through holes 11 are also arranged at the opening end of the fixing plate 62, the fixing plate 62 can be fixed on the connector body 61 by fixing bolts passing through the mounting holes 12 on the fixing plate 62 and the mounting through holes 11 on the connector body 61, when the fixing plate 62 is mounted on the connector body 61, the fixing plate 62 and the mounting groove 10 can form a mounting circular groove matched with the landing gear, and the landing gear connector 6 can be fixed on the landing gear through the mounting circular groove; one end of the load bearing rod 7 is provided with a sleeve rod 13, the outer diameter of the sleeve rod 13 is smaller than the inner diameter of the transverse rod 1, the sleeve rod 13 can be embedded into the transverse rod 1 in an aligned mode, and the sleeve rod 13 is fixed with the sleeve rod 13 through screws.
The utility model has simple structure and reasonable design, two transverse rods 1 and two longitudinal rods 2 can be connected into a bracket structure in a shape like a Chinese character 'jing' through the cross buckles 5, and then the bracket structure is fixed on the undercarriage of the unmanned aerial vehicle through the undercarriage connecting pieces 6 at the two ends of the longitudinal rods 2, the transverse rods 1 can adjust the installation position of the cross buckles 5 on the longitudinal rods 2, thereby adjusting the gravity center of the whole flying device, and the gravity center of the whole flying device can also be adjusted by adjusting the length of the sleeve rod 13 extending into the transverse rods 1. Compared with an integrated load structure, the load balancing device can adjust different installation positions according to different loads so as to meet different load tasks, the two transverse rods 1 and the two longitudinal rods 2 are connected through the cross buckles 5, the sleeve rod 13 on the load rod 7 is fixed with the transverse rods 1 through screws, the adjustment is convenient and simple, the adjustment speed is high, marks can be made on the longitudinal rods 2 and the sleeve rod 13 according to different loads, and when the same load task is met again, the corresponding position can be found quickly, and the balancing of the gravity center is realized.
The above-described embodiments are illustrative of the present invention and not restrictive, it being understood that various changes, modifications, substitutions and alterations can be made herein without departing from the principles and spirit of the utility model, the scope of which is defined by the appended claims and their equivalents.
Claims (4)
1. A novel unmanned aerial vehicle load carrying device comprises two transverse rods (1), two longitudinal rods (2), a lateral load (3) and a lower load (4), and is characterized in that the two transverse rods (1) and the two longitudinal rods (2) are connected into a support structure in a shape like a Chinese character 'jing' through four cross buckles (5), landing gear connecting pieces (6) are fixedly mounted at the two ends of the longitudinal rods (2), the longitudinal rods (2) can be fixedly mounted on landing gears through the landing gear connecting pieces (6), a load carrying rod (7) is fixedly mounted at the two ends of each transverse rod (1), the load carrying rods (7) are in a structure like a Chinese character 'Z', one end of each load carrying rod (7) is detachably embedded into each transverse rod (1), two mounting plates (8) are fixedly mounted between the two load carrying rods (7) at the two ends of each transverse rod (1), the lateral load (3) is detachably and fixedly arranged on the lateral mounting plate (8), the lower load (4) is detachably arranged on the two transverse rods (1), and the lower load (4) is arranged between the two longitudinal rods (2).
2. The novel unmanned aerial vehicle load mounting device of claim 1, the side mounting plate (8) is mounted on the load rod (7) through a connecting piece (9), the lower load (4) is arranged on the two transverse rods (1) through connecting pieces (9), the connecting piece (9) comprises an upper body (91) and a lower body (92), the upper body (91) and the lower body (92) are both provided with a semicircular groove, the lower body (92) is respectively fixedly arranged on the side mounting plate (8) and the lower load (4), the upper body (91) can be fixed on the lower body (92) through a fixing screw, when the upper body (91) is arranged on the lower body (92), the two semicircular grooves can form a circular groove matched with the transverse rod (1) and the load rod (7).
3. The novel unmanned aerial vehicle load carrying device according to claim 1, wherein the landing gear connecting member (6) comprises a connecting member body (61) and a U-shaped fixing plate (62), one end of the connecting member body (61) is fixed on the longitudinal rod (2), the other end of the connecting member body is provided with a semicircular mounting groove (10) matched with the landing gear, two mounting through holes (11) are formed below the mounting groove (10), the open end of the fixing plate (62) is also provided with two mounting holes (12) aligned with the mounting through holes (11), the fixing plate (62) can be fixed on the connecting member body (61) by passing through the mounting holes (12) on the fixing plate (62) and the mounting through holes (11) on the connecting member body (61) through fixing bolts, when the fixing plate (62) is mounted on the connecting member body (61), the fixing plate (62) and the mounting groove (10) can form a mounting circular groove matched with the landing gear, and the landing gear connecting piece (6) can be fixed on the landing gear through the mounting circular groove.
4. The novel unmanned aerial vehicle load carrying device according to claim 1, wherein one end of the load rod (7) is provided with a sleeve rod (13), the outer diameter of the sleeve rod (13) is smaller than the inner diameter of the transverse rod (1), the sleeve rod (13) can be embedded into the transverse rod (1) in an aligned manner, and the sleeve rod (13) and the transverse rod (1) are fixed through screws.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122242744.2U CN215663972U (en) | 2021-09-16 | 2021-09-16 | Novel unmanned aerial vehicle load carries device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122242744.2U CN215663972U (en) | 2021-09-16 | 2021-09-16 | Novel unmanned aerial vehicle load carries device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215663972U true CN215663972U (en) | 2022-01-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122242744.2U Active CN215663972U (en) | 2021-09-16 | 2021-09-16 | Novel unmanned aerial vehicle load carries device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215663972U (en) |
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2021
- 2021-09-16 CN CN202122242744.2U patent/CN215663972U/en active Active
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