CN215707102U - Detachable combined material unmanned aerial vehicle undercarriage - Google Patents
Detachable combined material unmanned aerial vehicle undercarriage Download PDFInfo
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- CN215707102U CN215707102U CN202121804613.2U CN202121804613U CN215707102U CN 215707102 U CN215707102 U CN 215707102U CN 202121804613 U CN202121804613 U CN 202121804613U CN 215707102 U CN215707102 U CN 215707102U
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- unmanned aerial
- aerial vehicle
- supporting rod
- support rod
- landing gear
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Abstract
The utility model discloses a detachable composite material unmanned aerial vehicle undercarriage, which belongs to the technical field of unmanned aerial vehicles and comprises: a U-shaped fixing plate and a supporting rod; the bracing piece includes: the upper skin of the supporting rod, the lower skin of the supporting rod, the ribbed plate of the supporting rod and the force-bearing carbon tube; the force bearing carbon tube is inserted and bonded on the rib plate of the support rod; the upper skin and the lower skin of the support rod are bonded on the whole body formed by the force bearing carbon tube and the rib plate of the support rod; wherein, the U-shaped fixed plate is connected at one end of the supporting rod. The whole landing gear product provided by the utility model is made of carbon fiber materials, so that the landing gear product is light in weight, high in structural strength and simple in forming process, the cost for re-processing the die is saved, and the cost for product development is reduced.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a detachable composite material unmanned aerial vehicle undercarriage.
Background
In the unmanned aerial vehicle field of making, aircraft undercarriage part needs intensity height, quality light, and the strong material of shaping designability, and carbon-fibre composite's characteristics are just in line with the performance requirement of unmanned aerial vehicle undercarriage. The resin-based composite material product is light in weight, high in strength, good in environmental adaptability and strong in product forming designability, and is widely developed and used in the field of aviation parts.
Current medium-sized unmanned aerial vehicle undercarriage is mostly metal structure, and the undercarriage quality is heavy, has increased complete machine weight. And metal undercarriage and organism junction are connected for the xenogenesis material, and junction intensity is weak, and when unmanned aerial vehicle take off and land in-process atress was uneven, especially at the test flight in-process, unstable factor makes the take off and land very unstable, and the very easy landing that begins breaks or breaks at the junction. The unmanned aerial vehicle undercarriage appearance is mostly heterotypic curved surface structure, and metal shaping curved surface technology is complicated, and the cost is higher.
Need design the unmanned aerial vehicle undercarriage of a combined material structural style to above problem.
SUMMERY OF THE UTILITY MODEL
Aiming at the problems, the utility model provides a detachable composite material unmanned aerial vehicle undercarriage.
The technical scheme adopted by the utility model is as follows: a detachable composite material unmanned aerial vehicle undercarriage, comprising: a U-shaped fixing plate and a supporting rod;
the bracing piece includes: the upper skin of the supporting rod, the lower skin of the supporting rod, the ribbed plate of the supporting rod and the force-bearing carbon tube;
the force bearing carbon tube is inserted and bonded on the rib plate of the support rod; the upper skin and the lower skin of the support rod are bonded on the whole body formed by the force bearing carbon tube and the rib plate of the support rod;
wherein, the U-shaped fixed plate is connected at one end of the supporting rod.
Furthermore, two ribbed plates of the support rod are provided, and one force bearing carbon tube is provided;
after the rib plates of the support rods are connected with the force-bearing carbon tubes, a space is reserved between the two rib plates of the support rods, and the thickness of each rib plate of the support rods is 2 mm.
Furthermore, the force bearing carbon tube is arranged at the upper part of one end of the ribbed plate of the support rod.
Furthermore, the whole body formed by the force bearing carbon tube and the rib plate of the support rod is also bonded with carbon cloth.
Further, the carbon cloth is provided with three layers.
Furthermore, the U-shaped fixing plate is connected with the supporting rod through bonding.
Furthermore, a riveting piece is arranged at the connection contact part of the U-shaped fixing plate and the supporting rod.
Furthermore, when the U-shaped fixing plate is bonded with the supporting rod, carbon cloth is used for bonding, and the number of the carbon cloth layers is three.
Furthermore, four screw holes are formed in the U-shaped fixing plate, and the screws matched with the screw holes are M6 screws.
Furthermore, one end of the supporting rod is larger than the other end of the supporting rod, and the whole supporting rod is in a water drop shape.
The utility model has the advantages that:
1. covering appearance is the special-shaped curved surface about the bracing piece, and the shaping uses current unmanned aerial vehicle airfoil mould, and U type fixed plate uses unmanned aerial vehicle's rotor pole to form for the mould shaping, and the floor adopts 2mm thick carbon fiber board machinery cutting to form, has saved the expense of mould processing.
2. The whole product is made of carbon fiber materials, so that the weight is light, the structural strength is high, the forming process is simple, the cost for re-processing the die is saved, and the cost for product development is reduced.
3. The undercarriage that the shaping was assembled passes through U type fixed plate, and the dress card is fixed firmly with the undercarriage at the corresponding position of horn, uses four M6's screw, can loosen the screw when needing to dismantle and dismantle the change, has improved unmanned aerial vehicle's packaging efficiency.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the utility model and, together with the description, serve to explain the utility model and not to limit the utility model.
FIG. 1 is a schematic top view of an embodiment of the present invention;
FIG. 2 is a front cut-away schematic view of an embodiment of the present invention;
fig. 3 is a schematic perspective view of an embodiment of the present invention.
Reference numerals:
the support rod comprises a support rod upper skin 1, a support rod lower skin 2, a support rod rib plate 3, a force bearing carbon tube 4 and a U-shaped fixing plate 5.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further 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 utility model and are not intended to limit the utility model.
Referring to fig. 1 to 3, as shown in fig. 1 to 3, a detachable composite material unmanned aerial vehicle landing gear comprises: a U-shaped fixing plate and a supporting rod;
the bracing piece includes: the upper skin of the supporting rod, the lower skin of the supporting rod, the ribbed plate of the supporting rod and the force-bearing carbon tube;
the force bearing carbon tube is inserted and bonded on the rib plate of the support rod; the upper skin and the lower skin of the support rod are bonded on the whole body formed by the force bearing carbon tube and the rib plate of the support rod;
wherein, the U-shaped fixed plate is connected at one end of the supporting rod.
The product consists of an upper supporting rod skin, a lower supporting rod skin, a supporting rod rib plate, a force bearing carbon tube and a U-shaped fixing plate, and the whole parts are all molded by adopting a carbon fiber composite material.
The appearance of the upper skin and the lower skin of the supporting rod are special-shaped curved surfaces, the existing unmanned aerial vehicle airfoil surface mold is used for forming, the mold processing cost is saved, prepreg is laid according to a laying method of technological requirements, and the prepreg is placed into an oven and subjected to vacuum bag press forming after the prepreg is laid. The U-shaped fixing plate is formed by using a rotor wing rod of an unmanned aerial vehicle as a mould, demolding cloth is pasted on the rotor wing rod, carbon cloth is paved on the demolding cloth according to a paving method of technological requirements, then glue is brushed, after the carbon cloth is paved to a specified number of layers, a thermal shrinkage belt is wound on the outer side, and after a hot air gun is heated, the carbon cloth is cured and formed at normal temperature. The ribbed plate is formed by mechanically cutting a 2mm thick carbon fiber plate, and the force-bearing carbon tube is a carbon fiber tube with standard specification
In an embodiment of the present invention, two rib plates of the support rod are provided, and one force-bearing carbon tube is provided;
after the rib plates of the support rods are connected with the force-bearing carbon tubes, a space is reserved between the two rib plates of the support rods, and the thickness of each rib plate of the support rods is 2 mm.
In an embodiment of the present invention, the force-bearing carbon tube is disposed on an upper portion of one end of a rib plate of the support rod.
Wherein, the ribbed plate is formed by mechanically cutting a carbon fiber plate with the thickness of 2mm, and the force-bearing carbon tube is a carbon fiber tube with standard specification.
In an embodiment of the utility model, the whole body formed by the force bearing carbon tube and the rib plate of the support rod is also bonded with carbon cloth.
Wherein, in order to strengthen the strength of the whole body formed by the force-bearing carbon tube and the rib plate of the support rod, the upper and lower skin-jointed surfaces are sewed by 3 layers of carbon cloth for strengthening.
In an embodiment of the present invention, the carbon cloth is provided with three layers.
In an embodiment of the utility model, the U-shaped fixing plate is connected with the supporting rod by adhesion.
In an embodiment of the utility model, the connecting contact between the U-shaped fixing plate and the supporting rod is further provided with a riveting member.
Wherein, in order to firmly be connected U type fixed plate and bracing piece firmly, wrap up the bonding with three-layer carbon cloth earlier, then use the rivet to fix.
In an embodiment of the utility model, the U-shaped fixing plate and the support rod are bonded by using carbon cloth, and the number of carbon cloth layers is three.
In an embodiment of the present invention, four screw holes are disposed on the U-shaped fixing plate, and the screws used in cooperation with the screw holes are M6 screws.
Wherein, the undercarriage that the shaping was assembled passes through U type fixed plate, and the dress card is in the corresponding position of horn, uses 4M 6's screw to fix the undercarriage firmly. When needing to be disassembled, the screws can be loosened to be disassembled and replaced, so that the assembly efficiency of the unmanned aerial vehicle is improved
In an embodiment of the utility model, one end of the supporting rod is larger, and the other end of the supporting rod is smaller, so that the whole supporting rod is in a water drop shape.
When the detachable composite material unmanned aerial vehicle landing gear is assembled, firstly, upper and lower skins of a supporting rod, a rib plate and a carbon tube are cemented and assembled strictly according to the assembly size shown in the drawing, the rib plate is completely bonded with the upper and lower skins, the carbon tube is completely bonded with the rib plate, after the upper and lower skins are completely cured, the upper and lower skin composite surfaces are sewn and reinforced by three layers of carbon cloth, and the surface is polished after the upper and lower skins are completely cured;
then, the assembled support rod and the U-shaped fixing plate are bonded and then riveted according to the positions shown in the drawing, the root part of the two parts is manually pasted with three layers of carbon cloth for reinforcement, the two parts are placed into an oven for complete curing, and the surface is polished and finished.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the utility model, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. A detachable combined material unmanned aerial vehicle undercarriage, its characterized in that includes: a U-shaped fixing plate and a supporting rod;
the bracing piece includes: the upper skin of the supporting rod, the lower skin of the supporting rod, the ribbed plate of the supporting rod and the force-bearing carbon tube;
the force bearing carbon tube is inserted and bonded on the rib plate of the support rod; the upper skin and the lower skin of the support rod are bonded on the whole body formed by the force bearing carbon tube and the rib plate of the support rod;
wherein, the U-shaped fixed plate is connected at one end of the supporting rod.
2. The detachable composite material unmanned aerial vehicle landing gear of claim 1, wherein the number of the support rod rib plates is two, and the number of the force bearing carbon tubes is one;
after the rib plates of the support rods are connected with the force-bearing carbon tubes, a space is reserved between the two rib plates of the support rods, and the thickness of each rib plate of the support rods is 2 mm.
3. The detachable composite material unmanned aerial vehicle landing gear of claim 2, wherein the carbon bearing tubes are arranged at the upper part of one end of a rib plate of the support rod.
4. The detachable composite material unmanned aerial vehicle landing gear of claim 1, wherein the force-bearing carbon tubes and the support bar rib plates are integrally bonded with carbon cloth.
5. The detachable composite unmanned aerial vehicle landing gear of claim 4, wherein the carbon cloth is provided with three layers.
6. The detachable composite material unmanned aerial vehicle landing gear of claim 1, wherein the U-shaped fixing plate is connected with the support rod through bonding.
7. The detachable composite material unmanned aerial vehicle landing gear of claim 6, wherein a riveting piece is further arranged at the connection contact of the U-shaped fixing plate and the supporting rod.
8. The detachable composite material unmanned aerial vehicle landing gear of claim 6, wherein the U-shaped fixing plate is bonded to the support rod by carbon cloth, and the number of carbon cloth layers is three.
9. The detachable composite material unmanned aerial vehicle landing gear of claim 1, wherein the U-shaped fixing plate is provided with four screw holes, and the screws matched with the screw holes are M6 screws.
10. The detachable composite material unmanned aerial vehicle landing gear of claim 1, wherein the support rod is large at one end and small at the other end, and is drop-shaped as a whole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121804613.2U CN215707102U (en) | 2021-08-04 | 2021-08-04 | Detachable combined material unmanned aerial vehicle undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121804613.2U CN215707102U (en) | 2021-08-04 | 2021-08-04 | Detachable combined material unmanned aerial vehicle undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215707102U true CN215707102U (en) | 2022-02-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121804613.2U Active CN215707102U (en) | 2021-08-04 | 2021-08-04 | Detachable combined material unmanned aerial vehicle undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215707102U (en) |
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2021
- 2021-08-04 CN CN202121804613.2U patent/CN215707102U/en active Active
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