CN210338274U - Single undercarriage and large-scale VTOL fixed wing unmanned aerial vehicle undercarriage - Google Patents
Single undercarriage and large-scale VTOL fixed wing unmanned aerial vehicle undercarriage Download PDFInfo
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- CN210338274U CN210338274U CN201921121095.7U CN201921121095U CN210338274U CN 210338274 U CN210338274 U CN 210338274U CN 201921121095 U CN201921121095 U CN 201921121095U CN 210338274 U CN210338274 U CN 210338274U
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Abstract
The utility model discloses a single undercarriage and large-scale vertical take-off and landing fixed wing unmanned aerial vehicle undercarriage, which comprises an arched bracket with a downward concave surface, wherein the two ends of the bracket are fixed with bracket protecting pieces, and the top of the bracket is fixed with two upper connecting pieces which are used for connecting with the belly; the bottom of the support protection piece is provided with a plurality of sawtooth-shaped grooves. The fixed wing unmanned aerial vehicle undercarriage comprises two single undercarriages which are longitudinally distributed on the surface of the belly along the fuselage. An object of the utility model is to provide a single undercarriage and large-scale VTOL fixed wing unmanned aerial vehicle undercarriage to when solving the weight of taking off among the prior art and reaching 100 kilograms levels, current undercarriage atress very easily produces the problem of great deformation, and the security and the purpose of stability when realizing guaranteeing 100 kilograms of large-scale VTOL unmanned aerial vehicle of level take off and land.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field, concretely relates to single undercarriage and large-scale VTOL fixed wing unmanned aerial vehicle undercarriage.
Background
The vertical take-off and landing fixed wing unmanned aerial vehicle has large take-off weight and has higher requirements on the performances of bearing the undercarriage and keeping the stability of the aircraft during landing. Particularly, when the takeoff weight reaches 100 kilograms, the existing landing gear is easy to deform greatly under stress. Therefore, the landing gear of the unmanned aerial vehicle with a simple structure is urgently needed to ensure the taking-off and landing stability and safety of the unmanned aerial vehicle.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a single undercarriage and large-scale VTOL fixed wing unmanned aerial vehicle undercarriage to when solving the weight of taking off among the prior art and reaching 100 kilograms levels, current undercarriage atress very easily produces the problem of great deformation, and the security and the purpose of stability when realizing guaranteeing 100 kilograms of large-scale VTOL unmanned aerial vehicle of level take off and land.
The utility model discloses a following technical scheme realizes:
a single undercarriage comprises an arched bracket with a downward concave surface, wherein two ends of the bracket are fixed with bracket protecting pieces, and two upper connecting pieces are fixed at the top of the bracket and are used for being connected with an abdomen; the bottom of the support protection piece is provided with a plurality of sawtooth-shaped grooves.
When weight to take off among the prior art reaches 100 kilograms, the problem of great deformation is very easily produced to current undercarriage atress, the utility model discloses at first provide a single undercarriage, this single undercarriage is one in the unmanned aerial vehicle undercarriage, including bow-shaped support, the support concave surface is convenient for down cushion the unmanned aerial vehicle organism when falling to the ground. Two upper connecting pieces are fixed on the top of the bracket and are used for being connected with the belly, so that the bracket is connected with the belly. The bottom of support protection piece sets up the recess of a plurality of cockscomb structures, can increase the frictional force with ground, stability when increasing unmanned aerial vehicle take off and land.
And each upper connecting piece is provided with a through hole penetrating through the upper connecting piece and the corresponding support. The via hole is used to connect the bracket to the belly.
The support protection piece comprises a base plate and two side plates which are integrally formed, wherein the two side plates are positioned above the base plate and are parallel to each other; the end part of the bracket is inserted between the two side plates, and the bracket is connected with the two side plates through bolts. Even every support protection piece all includes a bottom plate and two blocks of curb plates, and the bottom plate is integrated into one piece with two blocks of curb plates, is used for inserting the tip of support between two blocks of curb plates, provides horizontal spacing for the support bottom through two blocks of curb plates, realizes fastening connection through the bolt simultaneously.
The part of the support, which is in contact with the belly, is a rectangular section, and the rest part of the support is an airfoil section. The part of the support contacting with the belly is a rectangular section, so that the support is better matched with the plane of the belly, and the rest part is a wing section, so that good pneumatic performance is ensured.
The thickness of the cross section of the support is 4-6 mm.
And two reinforcing ribs are fixed on the surface of the support. Further improving the strength.
The reinforcing ribs are fixed on the inner surface of the support. Avoiding the interference to the abdomen.
The support protection piece and the upper connecting piece are both made of aluminum alloy materials.
The bracket is made of all-carbon fiber composite material.
Large-scale VTOL fixed wing unmanned aerial vehicle undercarriage includes two single undercarriages, and two single undercarriages distribute in the ventral surface around along the fuselage is vertical.
Compared with the prior art, the utility model, following advantage and beneficial effect have:
the utility model relates to a single undercarriage and large-scale VTOL fixed wing unmanned aerial vehicle undercarriage, simple structure makes things convenient for the dismouting, security and stability when can guaranteeing 100 kilograms of level large-scale VTOL unmanned family's take off and land. And meanwhile, the wing section is adopted, so that good pneumatic performance is ensured.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
fig. 1 is a front view of embodiment 1 of the present invention;
fig. 2 is an isometric view of a bracket protector according to embodiment 1 of the present invention;
fig. 3 is an isometric view of an upper connector in accordance with an embodiment of the present invention 1;
fig. 4 is a schematic structural diagram of embodiment 2 of the present invention.
Reference numbers and corresponding part names in the drawings:
1-bracket, 2-bracket protection piece, 201-bottom plate, 202-side plate, 203-groove, 3-upper connecting piece, 4-via hole and 5-reinforcing rib.
Detailed Description
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 following examples and drawings, and the exemplary embodiments and descriptions thereof of the present invention are only used for explaining the present invention, and are not intended as limitations of the present invention.
Example 1:
a single undercarriage as shown in fig. 1 to 3 comprises an arched bracket 1 with a downward concave surface, wherein two ends of the bracket 1 are fixed with bracket protecting pieces 2, the top of the bracket 1 is fixed with two upper connecting pieces 3, and the upper connecting pieces 3 are used for connecting with the belly; the bottom of the bracket protector 2 is provided with a plurality of serrated grooves 203. Every goes up and all sets up the via hole 4 that runs through last connecting piece 3, the support 1 that corresponds on the connecting piece 3. The bracket protection piece 2 comprises a bottom plate 201 and two side plates 202 which are integrally formed, wherein the two side plates 202 are positioned above the bottom plate 201, and the two side plates 202 are parallel to each other; the end of the bracket 1 is inserted between the two side plates 202, and the bracket 1 is connected with the two side plates 202 by bolts. The part of the bracket 1 contacting with the belly is a rectangular section, and the rest part is an airfoil section. The thickness of the cross section of the support 1 is 4-6 mm. Two reinforcing ribs 5 are fixed on the surface of the support 1.
Preferably, in this embodiment, a through hole is formed at a position 10mm above the end of the bracket 1, and the through hole is connected with the side plates 202 at two sides through a penetrating bolt, wherein a movable gap of about 1mm is left between any one side plate 202 and the side surface of the end of the bracket embedded between the two side plates.
Preferably, in this embodiment, the through hole 4 is a through hole at the head of a rivet nut, and in this embodiment, the bracket 1 is connected to the belly through the rivet nut.
Example 2:
the landing gear of the large vertical take-off and landing fixed wing unmanned aerial vehicle shown in fig. 4 comprises a front single landing gear and a rear single landing gear which are longitudinally distributed in the front and the rear of a fuselage. Fixed wing unmanned aerial vehicle takes off and land perpendicularly at the in-process of taking off and land, the undercarriage structure constitutes four point support and is used for bearing impact force and moment when the aircraft lands, passes through the toppling moment that the screw passed on the support frame through last connecting piece dispersion fuselage, prevents to turn on one's side.
In this embodiment, the stent is an arch stent, and the front and rear stents form a double arch.
In this embodiment, the bracket is fixed on the plane of the belly by screws through the upper connecting piece, so that the disassembly and assembly are convenient. The upper connecting piece is made of aluminum alloy material, has a certain width and a certain length, and can disperse impact force and moment transmitted to the support from the machine body through screws, so that the stability and the safety of the support frame are ensured.
In the embodiment, the bracket is subjected to strict finite element analysis, the thickness of the section is determined to be 5mm +/-1 mm, and the two reinforcing ribs are arranged on the inner surface of the bracket, so that the safety margin of 3 times of the strength and the rigidity of the bracket is ensured when the bracket bears 100 kg.
In this embodiment, support protection piece is installed to the support bottom, support protection piece is aluminum alloy material, and the bottom is fluted, can increase the frictional force with ground, stability when increasing unmanned aerial vehicle take off and land.
In the present embodiment, the scaffold is of an all-carbon fiber composite structure.
The beneficial effect who adopts above scheme is: the landing gear is supported by four points, the supporting strength is high, the stability is good, the bottom of the landing gear is provided with the support protection piece, the groove in the bottom of the support protection piece further increases the friction force between the landing gear and the ground, the impact force on the landing gear when an airplane lands can be better borne, meanwhile, the upper connecting piece with certain width and length disperses the force and the moment transmitted from the airplane body to the landing gear, and the safety and the stability of the landing gear are guaranteed. This undercarriage simple structure, easy dismounting, the quality is little, and it is little to satisfy unmanned aerial vehicle undercarriage weight, and intensity is high, and the requirement that the stationarity is good has ensured large-scale unmanned aerial vehicle's safety.
The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above description is only the embodiments of the present invention, and is not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. A single undercarriage comprises an arched bracket (1) with a downward concave surface, and is characterized in that a bracket protection piece (2) is fixed at two ends of the bracket (1), two upper connecting pieces (3) are fixed at the top of the bracket (1), and the upper connecting pieces (3) are used for being connected with an abdomen; the bottom of the support protection piece (2) is provided with a plurality of sawtooth-shaped grooves (203).
2. Single undercarriage according to claim 1 wherein each upper link (3) is provided with a through hole (4) passing through the upper link (3) and the corresponding bracket (1).
3. The single undercarriage according to claim 1 wherein the support protection (2) comprises a base plate (201), two side plates (202) integrally formed, the two side plates (202) being located above the base plate (201) and the two side plates (202) being parallel to each other; the end part of the bracket (1) is inserted between the two side plates (202), and the bracket (1) is connected with the two side plates (202) through bolts.
4. A single undercarriage according to claim 1 wherein the portion of the leg (1) in contact with the belly is of rectangular cross-section and the remainder is of aerofoil cross-section.
5. Single undercarriage according to claim 4 wherein the cross-sectional thickness of the carrier (1) is 4-6 mm.
6. A single undercarriage according to claim 1 wherein two reinforcing ribs (5) are fixed to the surface of the carrier (1).
7. A single undercarriage according to claim 6 wherein the reinforcing ribs (5) are fixed to the inner surface of the carrier (1).
8. Single undercarriage according to claim 1 wherein the bracket protector (2) and the upper attachment (3) are made of aluminium alloy material.
9. Single undercarriage according to claim 1 wherein the carrier (1) is made of an all carbon fibre composite material.
10. A landing gear for a large VTOL fixed wing drone, comprising two single landing gears according to any one of claims 1 to 9, longitudinally distributed along the fuselage in tandem on the ventral surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921121095.7U CN210338274U (en) | 2019-07-17 | 2019-07-17 | Single undercarriage and large-scale VTOL fixed wing unmanned aerial vehicle undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921121095.7U CN210338274U (en) | 2019-07-17 | 2019-07-17 | Single undercarriage and large-scale VTOL fixed wing unmanned aerial vehicle undercarriage |
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| Publication Number | Publication Date |
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| CN210338274U true CN210338274U (en) | 2020-04-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921121095.7U Active CN210338274U (en) | 2019-07-17 | 2019-07-17 | Single undercarriage and large-scale VTOL fixed wing unmanned aerial vehicle undercarriage |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111645853A (en) * | 2020-06-08 | 2020-09-11 | 中航飞机起落架有限责任公司 | Aircraft undercarriage |
| CN114013634A (en) * | 2021-11-19 | 2022-02-08 | 浙江省涡轮机械与推进系统研究院 | Mounting structure of fixed wing aircraft landing gear and fixed wing aircraft |
-
2019
- 2019-07-17 CN CN201921121095.7U patent/CN210338274U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111645853A (en) * | 2020-06-08 | 2020-09-11 | 中航飞机起落架有限责任公司 | Aircraft undercarriage |
| CN114013634A (en) * | 2021-11-19 | 2022-02-08 | 浙江省涡轮机械与推进系统研究院 | Mounting structure of fixed wing aircraft landing gear and fixed wing aircraft |
| CN114013634B (en) * | 2021-11-19 | 2023-07-04 | 浙江省涡轮机械与推进系统研究院 | Mounting structure of fixed wing aircraft landing gear and fixed wing aircraft |
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