CN209757501U - Rhombus wing mounting structure and aircraft with same - Google Patents
Rhombus wing mounting structure and aircraft with same Download PDFInfo
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- CN209757501U CN209757501U CN201920575390.3U CN201920575390U CN209757501U CN 209757501 U CN209757501 U CN 209757501U CN 201920575390 U CN201920575390 U CN 201920575390U CN 209757501 U CN209757501 U CN 209757501U
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Abstract
The utility model discloses a rhombus wing mounting structure and have aircraft of this mounting structure relates to unmanned vehicles technical field, mounting structure mainly includes the mounting structure of front wing and fuselage, link together through the reinforcement between front wing and the fuselage, fuselage or vertical fin and back between the wing and all connect through the mode of plug between rear wing and the front wing, quick convenient dismantlement and equipment not only can be realized to this kind of mounting structure, the aircraft that uses this mounting structure still has the structural strength who satisfies the flight requirement moreover, can guarantee normal flight and use.
Description
Technical Field
The utility model relates to an unmanned vehicles technical field, in particular to rhombus wing mounting structure and have this mounting structure's aircraft.
background
The rhombus wing aircraft has unique layout of front and back connection of wings and empennage, and the overall design can conveniently arrange various sensors to meet the requirements of various tasks. In addition, the diamond-shaped wing has great lift-drag ratio due to the excellent aerodynamic characteristics, and has important significance for improving the flight time and enlarging the mission radius.
The aircraft which is quickly disassembled and assembled has the advantages of convenient carrying and use, and has very practical and important significance for quick maneuvering, field operation and the like. The wings of the rhombic wing aircraft also enhance the structural strength, and provide a foundation for quick disassembly and assembly.
At present, the mounting structure of the wings of the unmanned aerial vehicle mostly adopts a screw or a magnetic suction mode, for example, the Chinese patent invention CN101970292B adopts a magnetic suction mode to connect the body and the wings. However, the screw connection method is inconvenient to disassemble and assemble, and the magnetic connection method has a low connection strength.
SUMMERY OF THE UTILITY MODEL
The embodiment of the utility model provides a rhombus wing mounting structure and have this mounting structure's aircraft, all adopt the form of pegging graft to connect between fuselage and back wing and the front wing, adopt special design's reinforcement to connect between fuselage and the front wing, not only can satisfy the intensity requirement of equipment, it is all very convenient to dismantle moreover and assemble.
The embodiment of the utility model provides a rhombus wing mounting structure, including the mounting structure of front wing and fuselage, link together through the reinforcement between the anterior segment of front wing and fuselage, the fuselage bottom has seted up the spread groove, be fixed with a plurality of bottom cardboards on the bottom surface of spread groove, the both sides edge of each bottom cardboard has all seted up the draw-in groove, the draw-in groove size of one side on all the bottom cardboards is equivalent and the position is the same; the end face of the tail end of the front wing is provided with a fixture block and a clamping part, the position of the fixture block corresponds to the position of a clamping groove in the bottom clamping plate, and the width of the clamping part is half of the width of the bottom clamping plate; the reinforcing piece is of a U-shaped structure, the width of the reinforcing piece is equal to the sum of the widths of the clamping parts on the two front wings, when the two front wings are clamped on the two sides of the bottom clamping plate, the clamping blocks on the front wings are clamped in the clamping grooves of the bottom clamping plate, and the reinforcing piece clamps the clamping parts of the two front wings together, so that the front wings are stably installed on the machine body.
the embodiment of the utility model provides a rhombus wing mounting structure and have this mounting structure's aircraft, mounting structure mainly includes the mounting structure of front wing and fuselage, link together through the reinforcement between front wing and the fuselage, fuselage or between vertical fin and the back wing and all connect through the mode of plug between back wing and the front wing, quick convenient dismantlement and equipment not only can be realized to this kind of mounting structure, the aircraft that uses this mounting structure still has the structural strength who satisfies the flight requirement moreover, can guarantee normal flight and use.
Drawings
Fig. 1 is a schematic overall structural diagram of an aircraft provided in an embodiment of the present invention;
FIG. 2 is a schematic view of the connection of the rear wing and the vertical tail of the aircraft of FIG. 1;
FIG. 3 is a schematic view of the front wing and rear wing connection of the aircraft of FIG. 1;
FIG. 4 is a schematic structural view of the stiffener for connecting the front wing and the fuselage of FIG. 1;
FIG. 5 is a schematic illustration of the installation location of the attachment member of FIG. 4 on an aircraft;
fig. 6 is a schematic structural view of a junction between the fuselage and the front wing in fig. 5.
The reference numbers illustrate:
100-fuselage, 110-connecting slot, 120-bottom clip, 130-separating clip, 140-connecting rod, 200-front wing, 210-clip, 300-rear wing, 310-connecting part, 400-vertical tail, 500-stiffener.
Detailed Description
In the following, an embodiment of the present invention will be described in detail with reference to the drawings, but it should be understood that the scope of the present invention is not limited by the embodiment.
Referring to fig. 1, the present invention provides an aircraft with rhombic wings, which comprises a fuselage 100, a front wing 200, a rear wing 300 and a vertical fin 400, wherein one end of the front wing 200 is installed at the front section of the fuselage 100, the other end is installed at one end of the rear wing 300, the other end of the rear wing 300 is installed at the rear section of the fuselage 100 or on the vertical fin 400, and the vertical fin 400 is installed at the rear section of the fuselage 100. In the present invention, the rear wing 300 is mounted on the vertical fin 400 as an example, and those skilled in the art can use the connection structure between the two to connect the rear wing 300 and the rear section of the fuselage 100.
It should be understood that the fuselage 100 has a power plant mounted thereon for providing power for the flight of the aircraft, which power plant may be electrically driven.
All adopt purpose-made mounting structure to carry out demountable installation between fuselage 100 and the front wing 200, between front wing 200 and the back wing 300 and between back wing 300 and the vertical fin 400, concrete mounting structure refers to fig. 2-6, adopts the utility model discloses a mounting structure not only can make the equipment between each part of aircraft and dismantle more swiftly simply, structural strength when can guaranteeing the aircraft flight moreover.
The rear wing 300 and the vertical fin 400 are detachably connected in an inserting manner, as shown in fig. 2, specifically, a clamping groove for inserting the tail end of the rear wing 300 is formed in the vertical fin 400, the rear wings 300 at two sides are respectively inserted into the clamping grooves in the vertical fin 400 from two sides, and the rear wing 300 and the vertical fin 400 can form self-locking after the rear wing 300 generates an overhead wing load in the flying process of the aircraft. In order to further improve the connection strength, after the rear wing 300 is inserted into the slot of the vertical fin 400, a screw may be used to connect the rear wing 300 and the vertical fin 400, or the rear wings 300 on both sides may be connected.
The front wing 200 and the rear wing 300 are also detachably connected in an inserting manner, as shown in fig. 3, specifically, the tail end of the rear wing 300 is provided with a connecting portion 310 perpendicular to the top surface thereof, a slot for inserting the front wing 200 is formed in a position on the side surface of the connecting portion 310 close to the top end, and after the tail end of the front wing 200 is inserted into the slot, the front wing 200 and the rear wing 300 can form self-locking after the front wing 200 generates a natural wing load in the flying process of the aircraft. In order to further improve the connection strength, after the front wing 200 is inserted into the slot of the connection part 310, the front wing 200 and the connection part 310 may be connected by using a screw.
During flight of the aircraft, most of the loading of the wing-in-the-sky and the aircraft's own weight act on the front wing 200, so the strength requirement at the junction of the front wing 200 and the fuselage 100 is relatively high. The utility model discloses in adopt front wing 200 to peg graft on fuselage 100 to the mode that uses reinforcement 500 further reinforcement to make front wing 200 and fuselage 100's connection satisfy the intensity requirement of aircraft.
As shown in fig. 4, 5 and 6, a section of connecting groove 110 is formed at the bottom of the body 100, the length of the connecting groove 110 is equal to the width of the end of the front wing 200, a plurality of bottom clamping plates 120 are fixed on the bottom surface of the connecting groove 110, the bottom clamping plates 120 are sequentially arranged from one end of the bottom surface of the connecting groove 110 close to one side surface to one end of the bottom surface close to the other side surface, clamping grooves are formed in both side edges of each bottom clamping plate 120, and the clamping grooves on one side of all the bottom clamping plates 120 are equal in size and same in position. In order to strengthen the strength of the connecting groove 110 of the fuselage 100, the embodiment of the present invention is further characterized in that a connecting rod 140 is connected between two side surfaces of the connecting groove 110, the number of the connecting rods 140 is at least one, one end of the connecting rod 140 is connected to one side surface of the connecting groove 110, and the other end of the connecting rod 140 is connected to the other side surface of the connecting groove 110 after passing through all the bottom clamping plates 120 in sequence.
The end face of the tail end of the front wing 200 is provided with a fixture block and a clamping portion 210, the position of the fixture block corresponds to the position of the clamping groove in the bottom clamping plate 120, and the size of the fixture block is equivalent to that of the clamping groove, so that the fixture block can be clamped in the clamping groove of the bottom clamping plate 120. After the fixture blocks are clamped in the clamping grooves of the bottom clamping plate 120, the end faces of the ends of the front wings 200 are tightly attached to the edge of the bottom clamping plate 120, and the width of the clamping portions 210 is half of the width of the bottom clamping plate 120, so that when the two front wings 200 are respectively clamped on the bottom clamping plate 120 from two sides, the clamping portions 210 on the two front wings 200 can be abutted together.
The reinforcing member 500 has a U-shaped structure, and the width of the reinforcing member 500 is equal to the sum of the widths of the fastening portions 210 of the two front wings 200, so that when the two front wings 200 are fastened to the two sides of the bottom fastening plate 120, the fastening portions 210 of the two front wings 200 can be fastened together by using the reinforcing member 500, so that the front wings 200 can be stably mounted on the fuselage 100 and have a certain strength.
In order to reduce the weight of the reinforcing member 500, the reinforcing member 500 is composed of a plurality of U-shaped plates of the same shape, which are connected together using a rod.
In order to further improve the connection strength between the front wing 200 and the fuselage 100, in the embodiment of the present invention, two of the reinforcing members 500 are used to connect the front wing 200 to the fuselage 100, one of the two reinforcing members 500 is tightly attached to one side of the connecting slot 110, and the other reinforcing member 500 is tightly attached to the other side of the connecting slot 110.
In the embodiment of the present invention, it has a plurality of separation cardboards 130 to go back fixed mounting on the bottom surface of connecting groove 110, it is located to separate cardboard 130 the central point of connecting groove 110, the both sides of separating cardboard 130 have with the size and the same draw-in groove in position of draw-in groove on the bottom cardboard 120, so that fixture block on the front wing 200 can block wherein. The two sides of the separating clamping plate 130 are located above the clamping grooves and are also provided with separating grooves, the height of each separating groove is equal to the thickness of the clamping portion 210 on the front wing 200, the positions of the separating grooves on the separating clamping plates 130 are the same, and when the clamping portion 210 of the front wing 200 is clamped on the bottom clamping plate 120, the clamping portion 210 is also clamped in the separating grooves, so that the installation strength of the front wing 200 on the body 100 is further improved. The two reinforcing members 500 are respectively located in the space between the two sides of the separating card 130 and the two sides of the connecting slot 110.
In the flying process of the aircraft, the front wing 200 is slightly deformed under the action of the self gravity of the aircraft and the load of the skyward wing, and the slight deformation can enable the reinforcing member 500 to more firmly connect the front wing 200 and the fuselage 100 together, so that the self-locking effect is achieved.
The above disclosure is only for a few specific embodiments of the present invention, however, the present invention is not limited to the embodiments, and any changes that can be considered by those skilled in the art shall fall within the protection scope of the present invention.
Claims (9)
1. The rhombic wing mounting structure comprises a front wing and a fuselage mounting structure, and is characterized in that the front wing and the front section of the fuselage are connected together through a reinforcing member, the bottom of the fuselage is provided with a connecting groove, a plurality of bottom clamping plates are fixed on the bottom surface of the connecting groove, the edges of two sides of each bottom clamping plate are provided with clamping grooves, and the clamping grooves on one sides of all the bottom clamping plates are equal in size and same in position; the end face of the tail end of the front wing is provided with a fixture block and a clamping part, the position of the fixture block corresponds to the position of a clamping groove in the bottom clamping plate, and the width of the clamping part is half of the width of the bottom clamping plate; the reinforcing piece is of a U-shaped structure, the width of the reinforcing piece is equal to the sum of the widths of the clamping parts on the two front wings, when the two front wings are clamped on the two sides of the bottom clamping plate, the clamping blocks on the front wings are clamped in the clamping grooves of the bottom clamping plate, and the reinforcing piece clamps the clamping parts of the two front wings together, so that the front wings are stably installed on the machine body.
2. The diamond wing mounting structure of claim 1, wherein a connecting rod is connected between two side surfaces of the connecting groove, one end of the connecting rod is connected to one side surface of the connecting groove, and the other end of the connecting rod is connected to the other side surface of the connecting groove after sequentially passing through all the bottom clamping plates.
3. The diamond wing mounting structure of claim 1, wherein said stiffener is comprised of a plurality of identically shaped U-shaped plates that are joined together using rods.
4. The diamond wing mounting structure of claim 1, wherein said front wing is snap-fitted to said fuselage by two said stiffeners, one of which abuts against one side of said attachment slot and the other abuts against the other side of said attachment slot.
5. The diamond wing installation structure of claim 4, wherein a plurality of partition boards are fixedly installed on the bottom surface of the connecting groove, the partition board is located at the center of the connecting groove, the partition boards have slots with the same size and position as the slots on the bottom board on both sides, the partition boards further have partition slots on both sides, the height of the partition slots is equivalent to the thickness of the clamping portion on the front wing, the positions of the partition slots are the same, when the clamping portion of the front wing is clamped on the bottom board, the clamping portion is also clamped in the partition slots, and the two reinforcing members are respectively located in the spaces between both sides of the partition board and both sides of the connecting groove.
6. The diamond-shaped wing mounting structure according to claim 1, further comprising mounting structures of a front wing and a rear wing, and mounting structures of a rear wing and a rear section or a vertical tail of a fuselage, wherein the mounting structures of the front wing and the rear wing comprise a clamping groove formed at the tail end of the rear wing, and the tail end of the front wing is inserted into the clamping groove;
The mounting structure of the rear wing and the rear section or the vertical tail of the fuselage comprises a clamping groove formed in the rear section or the vertical tail of the fuselage, and the rear wings on two sides are respectively inserted into the clamping grooves in the rear section or the vertical tail of the fuselage from two sides.
7. The diamond-shaped wing mounting structure according to claim 6, wherein the front wing is inserted into the slot of the rear wing, and the front wing and the rear wing are connected by screws;
After the rear wing is inserted into a clamping groove of the rear section or the vertical fin of the fuselage, the rear wing is connected with the rear section or the vertical fin of the fuselage through screws, or the rear wings on two sides are connected through screws.
8. An aircraft having a diamond wing mounting structure, the aircraft comprising a fuselage and a front wing, wherein the fuselage and the front wing are connected together by a mounting structure according to any one of claims 1 to 5.
9. the aircraft having a diamond wing mounting structure according to claim 8, further comprising a rear wing and a vertical fin, wherein the rear wing and the fuselage or the vertical fin, and the front wing and the rear wing are connected together by the mounting structure according to any one of claims 6 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920575390.3U CN209757501U (en) | 2019-04-25 | 2019-04-25 | Rhombus wing mounting structure and aircraft with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920575390.3U CN209757501U (en) | 2019-04-25 | 2019-04-25 | Rhombus wing mounting structure and aircraft with same |
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| Publication Number | Publication Date |
|---|---|
| CN209757501U true CN209757501U (en) | 2019-12-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920575390.3U Expired - Fee Related CN209757501U (en) | 2019-04-25 | 2019-04-25 | Rhombus wing mounting structure and aircraft with same |
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| CN (1) | CN209757501U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927878A (en) * | 2019-04-25 | 2019-06-25 | 西安航空学院 | Diamond wing mounting structure and aircraft with the mounting structure |
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2019
- 2019-04-25 CN CN201920575390.3U patent/CN209757501U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927878A (en) * | 2019-04-25 | 2019-06-25 | 西安航空学院 | Diamond wing mounting structure and aircraft with the mounting structure |
| CN109927878B (en) * | 2019-04-25 | 2024-02-02 | 西安航空学院 | Diamond wing mounting structure and aircraft with same |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191210 Termination date: 20210425 |