CN220924547U - Quick detach formula unmanned aerial vehicle undercarriage and unmanned aerial vehicle - Google Patents
Quick detach formula unmanned aerial vehicle undercarriage and unmanned aerial vehicle Download PDFInfo
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- CN220924547U CN220924547U CN202322385636.XU CN202322385636U CN220924547U CN 220924547 U CN220924547 U CN 220924547U CN 202322385636 U CN202322385636 U CN 202322385636U CN 220924547 U CN220924547 U CN 220924547U
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- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims abstract description 12
- 239000000741 silica gel Substances 0.000 claims abstract description 12
- 229910002027 silica gel Inorganic materials 0.000 claims abstract description 12
- 239000003365 glass fiber Substances 0.000 claims abstract description 7
- 238000003780 insertion Methods 0.000 claims description 11
- 230000037431 insertion Effects 0.000 claims description 11
- 239000002131 composite material Substances 0.000 claims description 9
- 239000000853 adhesive Substances 0.000 claims description 8
- 230000001070 adhesive effect Effects 0.000 claims description 8
- 239000004952 Polyamide Substances 0.000 claims description 6
- 229920002647 polyamide Polymers 0.000 claims description 6
- 238000006073 displacement reaction Methods 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 229920000049 Carbon (fiber) Polymers 0.000 abstract description 5
- 239000004917 carbon fiber Substances 0.000 abstract description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 abstract description 5
- 230000003139 buffering effect Effects 0.000 abstract description 2
- 238000013016 damping Methods 0.000 abstract description 2
- 229920001296 polysiloxane Polymers 0.000 description 4
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229920002379 silicone rubber Polymers 0.000 description 1
- 239000004945 silicone rubber Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000012876 topography Methods 0.000 description 1
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Abstract
The utility model discloses a quick-dismantling type unmanned aerial vehicle landing gear and an unmanned aerial vehicle, and relates to the technical field, and the following scheme is provided at present: the landing gear comprises a main landing gear, landing gear and wheel system connecting structures fixed at the two end heads of the main landing gear, and wheel systems connected at the two ends of the main landing gear through the landing gear and wheel system connecting structures; the hollow glass fiber plate spring landing gear is integrally formed, so that the cost and the weight can be effectively reduced, the product performance is improved, the same-ratio carbon fiber plate spring landing gear is adopted, the impact energy of an unmanned aerial vehicle during landing can be effectively absorbed, the cost is low, and the weight is light. The utility model adopts the quick-dismantling type mounting structure, the disassembly and the assembly are simpler, the disassembly and the assembly time are shorter, and compared with the prior art, the utility model has the advantages that the silica gel layer is adhered between the mounting structure and the landing gear frame body, and the functions of buffering, damping and reducing stress concentration are realized.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a quick-dismantling type unmanned aerial vehicle landing gear.
Background
Unmanned aerial vehicles, namely unmanned aerial vehicles, are widely applied to the fields of aerial photography, geographical topography mapping, disaster relief, power inspection, communication relay, target positioning and the like at present; in the current society, the market has been occupied by virtue of a series of advantages of low cost, strong environmental adaptability, high operation efficiency and the like.
In recent years, low cost and light weight of unmanned aerial vehicles have become a focus of attention. However, most existing unmanned aerial vehicle landing gears in the market still adopt oil-gas buffer landing gears or carbon fiber composite plate spring landing gears; the traditional oil-gas buffer landing gear has high reliability, but has larger weight, higher product cost and maintenance cost, and is suitable for a large unmanned aerial vehicle; the carbon fiber composite plate spring landing gear has the advantage of light weight, and is suitable for small-sized, medium-sized and large-sized unmanned aerial vehicles; although the weight of the landing gear is reduced by the carbon fiber composite plate spring for the medium-sized and large-sized unmanned aerial vehicle, the cost is still high, and the impact energy absorption efficiency in the aircraft landing process is low.
The existing plate spring landing gear is often fastened by screws, so that the surface of the composite material is easily scratched, local stress concentration is caused, the difficulty of disassembly and assembly is increased, and the time of disassembly and assembly is greatly increased; or the existing plate spring landing gear adopts a metal piece to directly extrude and clamp the outer surface structure of the composite material, so that the surface fiber layer is easily damaged, and the product is damaged.
Disclosure of Invention
In view of the above drawbacks, the present invention aims to provide:
Quick detach formula unmanned aerial vehicle undercarriage and unmanned aerial vehicle include:
The landing gear comprises a main landing gear which is in a letter 'C' shape and is placed in an inverted mode, a landing gear and machine wheel system connecting structure which is fixed at the two end heads of the main landing gear, and a machine wheel system which is connected at the two ends of the main landing gear through the landing gear and machine wheel system connecting structure; the surface of the middle section of the main landing gear is provided with two groups of landing gear and machine body connecting structures for connecting the unmanned aerial vehicle;
the wheel system comprises a wheel hub and tires which are fastened on two ends of the main landing gear through bolts;
The landing gear and machine train connecting structure comprises an embedded block clamped in the inner cavities of the ports at the two ends of the main landing gear, and a backboard which penetrates through the embedded block and the main landing gear through bolts and is connected to the side wall of the main landing gear and used for reducing local stress concentration;
The landing gear and the machine body connecting structure comprises two groups of upper hoops and lower hoops which are tightly held up and down on the surface of the middle section of the main landing gear through screws, quick-release bolts are arranged in the inner part of the upper hoops in a penetrating manner, and jacks for the quick-release bolts to be inserted are formed in the inner part of the upper hoops.
In the above technical scheme of the quick-release unmanned aerial vehicle landing gear, preferably, the front and rear surfaces of the upper clamp are provided with jacks into which the quick-release bolts are inserted, and the quick-release bolts are in a tight combination state with the jacks.
In the above technical scheme of the quick-dismantling unmanned aerial vehicle landing gear, preferably, rectangular clamping grooves are formed in the front surface and the rear surface of the top of the upper clamp, and the rectangular clamping grooves are mutually communicated with jacks in the upper clamp.
In the above technical scheme of the quick-release unmanned aerial vehicle landing gear, preferably, the surface of the shaft pin of the quick-release bolt is fixedly attached to the polyamide elastic pad through an adhesive, and the polyamide elastic pad is also fixedly attached to the jack of the upper clamp through the adhesive, so as to increase the firmness of the quick-release bolt after insertion.
In the above-mentioned technical scheme of quick detach formula unmanned aerial vehicle undercarriage, preferably, have the silica gel layer through the adhesive on the middle section surface of main undercarriage, and the silica gel layer is located the clamp and holds between the gap that the clamp was held tightly down, and the silica gel layer thickness slightly is greater than the gap for with main undercarriage card between last clamp and lower clamp, the displacement and the rotation of restriction main undercarriage degree of freedom.
In the above technical solution of a quick-dismantling type unmanned aerial vehicle landing gear, preferably, the embedded block is embedded inside a port of the main landing gear for preventing local crushing; and the main landing gear is tightly held and connected with the back plate through the outer hoop.
In the above technical scheme of the quick-dismantling type unmanned aerial vehicle landing gear, preferably, the transverse section of the main landing gear is a long-waist-shaped hollow section, the size of the main landing gear is determined according to the whole layout of the aircraft and the landing gear load, the main landing gear is inflated by the air bag to carry out internal pressurization, and the main landing gear made of glass fiber composite materials is integrally formed.
A quick disconnect unmanned aerial vehicle, comprising:
The machine body comprises a machine body structure, and four machine body fixing lugs fixed on the front and rear surfaces of the bottom of the machine body structure.
In the above-mentioned technical scheme of quick detach formula unmanned aerial vehicle, preferably, the bottom of the fixed tab of fuselage is all vertically inserted in the rectangle draw-in groove at last clamp top, and is fixed with the jack that supplies quick detach bolt horizontal male in the inside of the fixed tab of fuselage.
In the above-mentioned technical scheme of quick detach formula unmanned aerial vehicle, preferably, undercarriage and fuselage connection structure that fuselage structure bottom is connected uses the main undercarriage to form the pin joint as the base point, and the main undercarriage can rotate for the pin joint, compares the mode that links firmly through bolt and fuselage, and is less to connection structure intensity and rigidity requirement to lighten connection structure's weight.
According to the technical scheme, the quick-dismantling type unmanned aerial vehicle landing gear and the unmanned aerial vehicle have the following beneficial effects compared with the prior art:
The hollow glass fiber plate spring landing gear is integrally formed, so that the cost and the weight can be effectively reduced, the product performance is improved, the same-ratio carbon fiber plate spring landing gear is adopted, the impact energy of an unmanned aerial vehicle during landing can be effectively absorbed, the cost is low, and the weight is light. The invention adopts the quick-dismantling type mounting structure, the disassembly and the assembly are simpler, the disassembly and the assembly time are shorter, and compared with the prior art, the invention has the advantages that the silica gel layer is adhered between the mounting structure and the landing gear frame body, and the functions of buffering, damping and reducing stress concentration are realized.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will make brief description and illustrations of the drawings used in the description of the embodiments of the present invention or the prior art. It is obvious that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 is a schematic structural view of an unmanned aerial vehicle landing gear;
FIG. 2 is a schematic view of a main landing gear system with a fuselage quick disconnect;
FIG. 3 is an exploded view of the landing gear and fuselage connection.
In fig. 1 to 3, the corresponding relationship of the parts is as follows:
100. A body; 110. a fuselage structure; 120. a body-securing tab; 200. landing gear and fuselage connection structure; 210. a quick release bolt; 220. a clamping hoop is arranged; 230. a silica gel layer; 240. a lower clamp; 300. a main landing gear; 400. a wheel system; 500. landing gear and machine train connection structure.
Detailed Description
The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is apparent that the embodiments described below are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention. In order to make the explanation and the description of the technical solution and the implementation of the present invention clearer, several preferred embodiments for implementing the technical solution of the present invention are described below.
Specific example 1.
Referring to fig. 1 to 3;
the embodiment comprises the following steps:
The landing gear system comprises a main landing gear 300 which is arranged in a C-shaped inverted buckle, a landing gear and gear train connecting structure 500 which is fixed at the two end heads of the main landing gear 300, and a gear train system 400 which is connected at the two ends of the main landing gear 300 through the landing gear and gear train connecting structure 500; and two sets of landing gear and fuselage connection structures 200 are provided on the mid-section surface of the main landing gear 300 for connection to the unmanned aerial vehicle.
Wheel system 400 includes a hub and tires secured to the ends of main landing gear 300 by a bolt lock; the landing gear and machine train connection structure 500 comprises an embedded block clamped in the inner cavities of the ports at the two ends of the main landing gear 300, and a back plate which penetrates through the embedded block, the main landing gear 300 and the machine train connection structure 400 through bolts and is connected to the side wall of the main landing gear 300; the landing gear and body connecting structure 200 comprises two groups of upper clamp 220 and lower clamp 240 which are tightly held up and down on the middle section surface of the main landing gear 300 through screws, and a quick release plug 210 is arranged in the upper clamp 220 through an inserting hole.
The front and rear surfaces of the upper clip 220 are provided with insertion holes into which the quick release pins 210 are inserted, and the quick release pins 210 are tightly combined with the insertion holes; rectangular clamping grooves are formed in the front surface and the rear surface of the top of the upper clamp 220, and the rectangular clamping grooves are communicated with jacks in the upper clamp 220; the surface of the shaft pin of the quick release latch 210 is fixedly attached with a polyamide elastic pad by an adhesive, and the jack of the upper clamp 220 is fixedly attached with a polyamide elastic pad by the adhesive, so as to increase the firmness of the quick release latch 210 after being inserted.
The middle section surface of the main landing gear 300 is attached with a silica gel layer 230 through an adhesive, the silica gel layer 230 is positioned between the gaps tightly held by the upper clamp 220 and the lower clamp 240, and the thickness of the silica gel layer 230 is slightly larger than the gaps and is used for clamping the main landing gear 300 between the upper clamp 220 and the lower clamp 240 so as to limit the displacement and rotation of the degree of freedom of the main landing gear 300.
The embedded blocks are embedded inside the ports of the main landing gear 300 for preventing local crushing; the back plate is used for reducing local stress concentration, and the main landing gear 300 is tightly held and connected with the outer hoop through the back plate; the transverse section of the main landing gear 300 is a long-waist hollow section, the size of the main landing gear 300 is determined according to the overall layout of the aircraft and the landing gear load, and the main landing gear 300 is inflated by an air bag to carry out internal pressurization, so that the main landing gear 300 made of the glass fiber composite material is integrally formed.
Specific example 2.
Reference is made to figures 1, 2 and 3;
the embodiment comprises the following steps:
The body 100, the body 100 includes a body structure 110, and four body fixing lugs 120 fixed on the front and rear surfaces of the body bottom of the body structure 110; the bottom ends of the body fixing lugs 120 are vertically inserted into rectangular clamping grooves at the top of the upper clamp 220, and insertion holes for transversely inserting the quick release bolts 210 are fixed in the body fixing lugs 120; the landing gear and the fuselage connection structure 200 that fuselage structure 110 bottom is connected take main landing gear 300 as the base point to form the pin joint, and main landing gear 300 can rotate for the pin joint, compares the mode that links firmly with the fuselage through the bolt, and is less to connection structure intensity and rigidity requirement to alleviate connection structure's weight.
The technical scheme of the invention is described in detail as follows:
The main landing gear 300 is made of hollow glass fiber materials, and a plate spring landing gear is used as a design blueprint; the section is a long waist-shaped hollow section, and the size of the section can be determined according to the overall layout of the aircraft and the load of the landing gear; the invention can realize the integral molding of the hollow section plate spring landing gear made of the glass fiber composite material by internally pressurizing the product after the air bag is inflated, and compared with a solid plate spring landing gear, the invention reduces the weight, improves the product performance and reduces the product cost.
The main landing gear system is connected with the body fixing lug 120 through a quick release bolt 210; when the unmanned aerial vehicle is removed, the quick-release bolt 210 is pulled out, so that the main landing gear 300 is separated from the main body, the quick release is realized, the operation is simple, the dismounting time is greatly shortened, and the unmanned aerial vehicle is convenient to transport and maintain; the stress mode of the main landing gear can be seen as that the left and right main landing gears are respectively connected with the machine body through two hinge points, the main landing gear can rotate relative to the hinge points, and compared with the mode of fixedly connecting the main landing gear with the machine body through bolts, the stress mode of the main landing gear has lower requirements on the strength and rigidity of the connecting structure, and the weight of the connecting structure is effectively reduced;
the wheel system 400 is bolted to the main landing gear 300, wherein the main landing gear inserts are protected from partial crushing; the installation backplate can reduce local stress concentration to the main landing gear is held tightly through backplate and outside staple bolt and is connected, and the bolt all needs to beat pretightning moment, and landing gear landing load is overcome by the frictional force of this department, and backplate can increase area of contact, increases this department frictional force.
The silicone layer 230 (preferably a silicone pad, with a thickness slightly greater than the structural gap) is attached to the upper and lower clips 220, 240 by an adhesive (preferably silicone rubber), the lower clip 240 with the silicone layer 230 is connected to the upper clip 220 with the silicone layer 230 by a screw, and the main landing gear 300 is clamped between the upper and lower clips 220, 240, so as to limit the displacement and rotation of the respective degrees of freedom.
Finally, it should be further noted that the structures, proportions, sizes, etc. shown in the drawings are merely for the purpose of understanding and reading the disclosure, and are not intended to limit the applicable scope of the present application, so that any structural modifications, proportional changes, or adjustments of sizes may not be technically significant, and all fall within the scope of the disclosure without affecting the efficacy and achievement of the present application. The present application is not limited to the above-mentioned preferred embodiments, and any person who can learn the structural changes made under the teaching of the present application can fall within the scope of the present application if the present application has the same or similar technical solutions.
Claims (10)
1. A quick detach formula unmanned aerial vehicle undercarriage, its characterized in that:
Comprises a main landing gear (300), a landing gear and wheel system connecting structure (500) fixed at the two ends of the main landing gear (300), and a wheel system (400) connected at the two ends of the main landing gear (300) through the landing gear and wheel system connecting structure (500); two sets of landing gear and body connecting structures (200) are arranged on the surface of the middle section of the main landing gear (300) and are used for connecting the unmanned aerial vehicle;
The wheel system (400) comprises a wheel hub and a tire which are fastened on two ends of the main landing gear (300) through a bolt lock;
The landing gear and machine train connecting structure (500) comprises an embedded block clamped in the inner cavities of the ports at the two ends of the main landing gear (300), and a backboard which penetrates through the embedded block and the main landing gear (300) through bolts and is connected to the side wall of the main landing gear (300) and used for reducing local stress concentration;
the landing gear and machine body connecting structure (200) comprises two groups of upper clamping bands (220) and lower clamping bands (240) which are tightly held on the middle section surface of the main landing gear (300) up and down through screws, a quick-release bolt (210) is arranged in the upper clamping band (220) in a penetrating mode, and insertion holes for the quick-release bolt (210) are formed in the upper clamping band (220).
2. The landing gear of a quick-release unmanned aerial vehicle according to claim 1, wherein the front and rear surfaces of the upper clip (220) are provided with insertion holes into which the quick-release bolts (210) are inserted, and the quick-release bolts (210) are tightly combined with the insertion holes.
3. The landing gear of a quick-release unmanned aerial vehicle according to claim 1, wherein rectangular clamping grooves are formed in the front and rear surfaces of the top of the upper clamp (220), and the rectangular clamping grooves are mutually communicated with insertion holes in the upper clamp (220).
4. The landing gear of claim 1, wherein a polyamide elastic pad is fixed on the surface of the shaft pin of the quick release bolt (210) through adhesion, and the polyamide elastic pad is fixed in the insertion hole of the upper clamp (220) through adhesion, so as to increase the firmness of the quick release bolt (210) after insertion.
5. The quick release unmanned aerial vehicle landing gear according to claim 1, wherein a silica gel layer (230) is attached to the surface of the middle section of the main landing gear (300) through an adhesive, and the silica gel layer (230) is located between the slit where the upper clamp (220) and the lower clamp (240) are tightly held, and the thickness of the silica gel layer (230) is greater than the slit, so that the main landing gear (300) is clamped between the upper clamp (220) and the lower clamp (240), and the displacement and rotation of the degree of freedom of the main landing gear (300) are limited.
6. The quick release unmanned aerial vehicle landing gear of claim 1, wherein the insert is embedded inside a port of the main landing gear (300) for preventing local crushing; and the main landing gear (300) is tightly connected with the back plate through an outer hoop.
7. The quick-release unmanned aerial vehicle landing gear according to claim 1, wherein the transverse section of the main landing gear (300) is a long-waist-shaped hollow section, and the main landing gear (300) is internally pressurized by inflating the main landing gear (300) through an airbag, so that the main landing gear (300) made of the glass fiber composite material is integrally formed.
8. A quick disconnect unmanned aerial vehicle, characterized in that it is adapted for use in a quick disconnect unmanned aerial vehicle landing gear according to any one of claims 1 to 6; the novel portable electric power machine also comprises a machine body (100), wherein the machine body (100) comprises a machine body structure (110) and four machine body fixing lugs (120) fixed on the front surface and the rear surface of the bottom of the machine body structure (110).
9. The quick release unmanned aerial vehicle of claim 8, wherein the bottom ends of the body fixing lugs (120) are vertically inserted into rectangular clamping grooves at the top of the upper clamp (220), and insertion holes for transversely inserting the quick release bolts (210) are fixed in the body fixing lugs (120).
10. The quick release unmanned aerial vehicle of claim 8, wherein the landing gear and the fuselage connection structure (200) connected to the bottom of the fuselage structure (110) form a hinge point with the main landing gear (300) as a base point, and the main landing gear (300) is rotatable relative to the hinge point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322385636.XU CN220924547U (en) | 2023-09-04 | 2023-09-04 | Quick detach formula unmanned aerial vehicle undercarriage and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322385636.XU CN220924547U (en) | 2023-09-04 | 2023-09-04 | Quick detach formula unmanned aerial vehicle undercarriage and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220924547U true CN220924547U (en) | 2024-05-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322385636.XU Active CN220924547U (en) | 2023-09-04 | 2023-09-04 | Quick detach formula unmanned aerial vehicle undercarriage and unmanned aerial vehicle |
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| Country | Link |
|---|---|
| CN (1) | CN220924547U (en) |
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2023
- 2023-09-04 CN CN202322385636.XU patent/CN220924547U/en active Active
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