CN215622655U - A dismouting is fast to be locked structure for unmanned aerial vehicle tailpiece and tail end - Google Patents
A dismouting is fast to be locked structure for unmanned aerial vehicle tailpiece and tail end Download PDFInfo
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- CN215622655U CN215622655U CN202122200472.XU CN202122200472U CN215622655U CN 215622655 U CN215622655 U CN 215622655U CN 202122200472 U CN202122200472 U CN 202122200472U CN 215622655 U CN215622655 U CN 215622655U
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Abstract
The utility model aims to solve the technical problem of providing a quick-locking structure for dismounting a tail rod and a horizontal tail of an unmanned aerial vehicle, which can realize quick installation. This quick-locking structure of dismouting includes plugboard, fixed sleeve, toper radome fairing, first mounting panel, second mounting panel, electric plug, electrical connector, the fixed spring bolt that is provided with on the second mounting panel, the position that lies in the plane cover body outside of toper radome fairing on the plugboard is provided with the jack, and whole process need not any external instrument and can accomplish fast when utilizing this quick-locking structure of dismouting to tail-stock and horizontal tail disassemble and install, can realize the connection of dock structure and electrical apparatus two parts simultaneously to safe and reliable especially in the emergent field, can realize quick installation, can not waste unnecessary time, thereby realize quick rescue's purpose. Is suitable for popularization and application in the technical field of unmanned aerial vehicles.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a quick-locking structure for dismounting a tail rod and a horizontal tail of an unmanned aerial vehicle.
Background
A drone is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device. The unmanned aerial vehicle can complete aerial photography monitoring, high-altitude reconnaissance, electric power line patrol, logistics transportation and other works in a remote control mode. The unmanned aerial vehicle is a rapid technology in recent development with the advantages of high working efficiency, low cost, high safety of the working environment of drivers and the like in the industries.
Unmanned aerial vehicle divide into many rotor unmanned aerial vehicle, fixed wing unmanned aerial vehicle and compound wing unmanned aerial vehicle, and fixed wing unmanned aerial vehicle is fit for the fast flight task of long distance, high speed more. In order to realize convenient transportation of unmanned aerial vehicles, most unmanned aerial vehicles on the market all select the detachable structure. Unmanned aerial vehicle's fin part divide into two parts of tail-bar and tail, and the tail-bar is connected fixedly through detachable construction and tail-bar and finally becomes a body structure, and detachable construction between current tail-bar and the tail-bar has all adopted bolted connection structure to with line to line connector connection electrical apparatus part. Although the structure connection structure is simple, the operation process is complex, time and labor are wasted, a matched tool is needed, particularly in the emergency field, quick installation needs to be achieved, unnecessary time is wasted in the existing installation mode, and therefore the optimal rescue time is delayed.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem of providing a quick-locking structure for dismounting a tail rod and a horizontal tail of an unmanned aerial vehicle, which can realize quick installation.
The technical scheme adopted by the utility model for solving the technical problems is as follows: the quick-locking structure for dismounting the tail rod and the horizontal tail of the unmanned aerial vehicle comprises an insertion plate, a fixing sleeve, a conical fairing, a first mounting plate and a second mounting plate, wherein the conical fairing is fixedly arranged in the middle of the front end of the horizontal tail, the plane of the conical fairing faces the tail rod, the part of a conical cover body of the conical fairing, which is connected with a skin of the horizontal tail, is in smooth transition, the first mounting plate is vertically arranged and fixedly arranged on a planar cover body of the conical fairing, the first mounting plate and the planar cover body of the conical fairing are parallel to each other, the tail end of the insertion plate sequentially penetrates through the first mounting plate and the planar cover body of the conical fairing and then extends into the skin of the horizontal tail and is fixedly connected with a wing beam of the horizontal tail, the distance between the front end of the insertion plate and the planar cover body of the conical fairing is 1/3-1/2 of the length of the insertion plate, and an electric plug is fixedly arranged on the surface of one side, which faces the tail rod, of the first mounting plate, the electric plug is positioned above the plug board, the fixing sleeve is fixed on a wing rib of the tail rod and is positioned in a skin of the tail rod, the tail end of the fixing sleeve extends to the outer surface of the wing rib of the tail rod at the joint of the tail rod and the horizontal tail, the cross section of the fixing sleeve is matched with the cross section of the plug board, an electric connector matched with the electric plug is arranged on the end surface of the tail rod facing the horizontal tail, the electric connector is fixed on the inner surface of the skin of the tail rod, a gap is formed between the lower end of the electric connector and the upper surface of the fixing sleeve, the second mounting plate is arranged on the outer surface of the wing rib of the tail rod at the joint of the tail rod and the horizontal tail, the second mounting plate is horizontally arranged, the front end of the second mounting plate is fixed on the outer surface of the wing rib of the tail rod at the joint of the tail rod and the horizontal tail, and the left and right sides of the second mounting plate are fixed on the inner surface of the skin of the tail rod, a spring bolt is fixedly arranged on the second mounting plate, an insertion hole is formed in the position, located on the outer side of the plane cover body of the conical fairing, on the insertion plate, the pin head of the spring bolt vertically faces upwards, the size of the insertion hole is matched with that of the pin head of the spring bolt, an operation hole is formed in the skin of the tail rod, and the operation hole is located right below the spring bolt; when the tail rod is connected with the front end of the horizontal tail insertion plate into a whole, the front end of the insertion plate is inserted into the fixing sleeve, the pin head of the spring pin is upwards inserted into the insertion hole, the electrical plug is inserted into the electrical connector, and the skin of the tail rod is seamlessly spliced with the plane cover body of the fairing.
Further, the cross section of the plug board is rectangular.
Further, the distance between the front end of the plugboard and the plane cover body of the conical fairing is 1/2 of the length of the plugboard.
Further, the length of the fixing sleeve is 1/2 of the length of the plugboard.
Furthermore, the plugboard, the fixing sleeve, the first mounting plate and the second mounting plate are all made of 7075 aluminum alloy.
The utility model has the beneficial effects that: this a quick-lock structure of dismouting for unmanned aerial vehicle tail-bar and flat tail when needs splice the installation to unmanned aerial vehicle's tail-bar and flat tail, only need aim at the plugboard that sets up on the flat tail and insert it, in inserting in-process with the spring bolt draw down make the plugboard can insert the fixed sleeve smoothly, after the plugboard inserts the back that targets in place, the two is connected as an organic wholely in the electrical plug also inserts electrical joint, simultaneously the covering of tail-bar and the plane cover body seamless concatenation of radome fairing are a whole, the round pin head of spring plug is located the jack directly under this moment, loosen behind the spring bolt, the plug rebound of spring bolt alright in order to insert in the jack, the plugboard just so can not remove along the fixed sleeve, so just accomplished the quick installation of tail-bar and flat tail, when disassembling, only need pull down the spring bolt hard a little, make the round pin head of spring bolt move down make the round pin head of spring bolt break away from the jack hard and pull open the tail-bar and make the bolt pull open with the flat tail hard with the flat tail The fishplate bar pulls out the change of electrical plug also can follow electrical joint from the fixed sleeve in the fishplate bar pulls out and has accomplished disassembling of tail-stock and horizontal tail, whole process need not any external instrument and can accomplish the installation of tail-stock and horizontal tail fast and disassemble, can realize the connection of dock structure and electrical apparatus two parts simultaneously, and the depth that the plugboard inserted fixed sleeve has reached more than one third of plugboard length, mounting structure is more firm, make to connect more safe and reliable, especially in the emergent field, can realize quick installation, can not waste unnecessary time, thereby realize quick rescue's purpose.
Drawings
FIG. 1 is a schematic structural view of an installed quick-lock structure for the disassembly and assembly of a tail rod and a horizontal tail of an unmanned aerial vehicle according to the present invention;
FIG. 2 is a schematic structural view of the disassembled quick lock structure for the tail rod and the horizontal tail of the unmanned aerial vehicle;
FIG. 3 is a schematic structural view of the hidden skin of the disassembled quick-lock structure for the tail rod and the horizontal tail of the unmanned aerial vehicle, according to the present invention;
FIG. 4 is a schematic structural diagram of the utility model after the skin is hidden by the horizontal tail;
FIG. 5 is a schematic structural view of the tail rod of the present invention after covering the skin;
the notation in the figure is: the air conditioner comprises a horizontal tail 1, a tail rod 2, a plug board 3, a fixing sleeve 4, a conical fairing 5, a first mounting board 6, a second mounting board 7, an electric plug 8, an electric connector 9, a spring bolt 10 and a jack 11.
Detailed Description
The technical scheme of the utility model is described in detail in the following with reference to the accompanying drawings.
As shown in fig. 1-5, the quick-locking structure for the disassembly and assembly of the tail rod and the horizontal tail of the unmanned aerial vehicle comprises an insertion plate 3, a fixing sleeve 4, a conical fairing 5, a first mounting plate 6 and a second mounting plate 7, wherein the conical fairing 5 is fixedly arranged in the middle of the front end of the horizontal tail 1, the plane of the conical fairing 5 faces the tail rod 2, the part of the conical cover body of the conical fairing 5 connected with the skin of the horizontal tail 1 is in smooth transition, the first mounting plate 6 is vertically arranged and fixedly arranged on the planar cover body of the conical fairing 5, the planar cover bodies of the first mounting plate 6 and the conical fairing 5 are parallel to each other, the tail end of the insertion plate 3 sequentially passes through the first mounting plate 6 and the planar cover body of the conical fairing 5 and then extends into the skin of the horizontal tail 1 and is fixedly connected with the wing beam of the horizontal tail 1, the distance between the front end of the insertion plate 3 and the planar cover body of the conical fairing 5 is 1/3-1/2 of the length of the insertion plate 3, the electric plug 8 is fixedly arranged on the surface of one side, facing the tail rod 2, of the first mounting plate 6, the electric plug 8 is positioned above the plug board 3, the fixing sleeve 4 is fixed on a wing rib of the tail rod 2, the fixing sleeve 4 is positioned in a covering of the tail rod 2, the tail end of the fixing sleeve 4 extends to the outer surface of the wing rib of the tail rod 2 at the joint of the tail rod 2 and the horizontal tail 1, the size of the cross section of the fixing sleeve 4 is matched with that of the plug board 3, an electric connector 9 matched with the electric plug 8 is arranged on the end surface, facing the horizontal tail 1, of the tail rod 2, the electric connector 9 is fixed on the inner surface of the covering of the tail rod 2, a gap exists between the lower end of the electric connector 9 and the upper surface of the fixing sleeve 4, the second mounting plate 7 is arranged on the outer surface of the wing rib of the tail rod 2 at the joint of the tail rod 2 and the horizontal tail 1, and the second mounting plate 7 is horizontally arranged, the front end of the second mounting plate 7 is fixed on the outer surface of a tail rod 2 wing rib at the joint of the tail rod 2 and the horizontal tail 1, the left side and the right side of the second mounting plate 7 are fixed on the inner surface of a skin of the tail rod 2, a spring bolt 10 is fixedly arranged on the second mounting plate 7, a jack 11 is arranged on the plug plate 3 and positioned outside a plane cover body of the conical fairing 5, the pin head of the spring bolt 10 faces upwards vertically, the size of the jack 11 is matched with that of the spring bolt 10, an operating hole is arranged on the skin of the tail rod 2, and the operating hole is positioned under the spring bolt 10; when the tail rod 2 is connected with the front end of the plug board 3 of the horizontal tail 1 into a whole, the front end of the plug board 3 is inserted into the fixing sleeve 4, the pin head of the spring pin 10 is upwards inserted into the jack 11, the electric plug 8 is inserted into the electric connector 9, and the skin of the tail rod 2 is seamlessly spliced with the plane cover body of the fairing. When the tail rod 2 and the horizontal tail of the unmanned aerial vehicle are required to be spliced and installed, only the plugboard 3 arranged on the horizontal tail 1 needs to be aligned with and inserted into the fixed sleeve 4, the spring bolt 10 is pulled downwards in the insertion process to enable the plugboard 3 to be smoothly inserted into the fixed sleeve 4, when the plugboard 3 is inserted in place, the electrical plug 8 is also inserted into the electrical connector 9 and connected into a whole, meanwhile, the skin of the tail rod 2 and the plane cover body of the fairing are spliced into a whole in a seamless mode, the pin head of the spring plug is positioned under the jack 11, after the spring bolt 10 is loosened, the plug of the spring bolt 10 moves upwards to be inserted into the jack 11, so that the plugboard 3 cannot move along the fixed sleeve 4, the quick installation of the tail rod 2 and the horizontal tail 1 is completed, when the tail rod 2 and the horizontal tail are disassembled, the spring bolt 10 only needs to be pulled downwards slightly, make the round pin head of spring bolt 10 remove downwards make spring bolt 10's round pin head break away from and pull open tail 2 and horizontal tail 1 hard from jack 11 and make plugboard 3 pull out from fixed sleeve 4 and electric plug 8 also can pull out the change from electric joint 9 and accomplished disassembling of tail 2 and horizontal tail 1 simultaneously, whole process need not any external instrument and can accomplish the installation and the disassembling of tail 2 and horizontal tail 1 fast, can realize the connection of dock structure and electrical apparatus two parts simultaneously, and the degree of depth that plugboard 3 inserted fixed sleeve 4 has reached more than one third of plugboard 3 length, mounting structure is more firm, make the connection safe and reliable more, especially in the emergency field, can realize quick installation, can not waste unnecessary time, thereby realize quick rescue's purpose.
In the above embodiment, in order to make the mounting structure more stable, the cross section of the plugboard 3 is rectangular. Further, the distance between the front end of the plugboard 3 and the plane cover of the conical fairing 5 is 1/2 of the length of the plugboard 3. The length of the fixing sleeve 4 is 1/2 of the length of the plugboard 3.
In addition, in order to ensure that the connecting piece has enough supporting strength, the plug board 3, the fixing sleeve 4, the first mounting board 6 and the second mounting board 7 are all made of 7075 aluminum alloy.
Claims (5)
1. A dismouting quick-lock structure for unmanned aerial vehicle tailpiece and horizontal tail, its characterized in that: the cone fairing comprises an insertion plate (3), a fixing sleeve (4), a cone fairing (5), a first mounting plate (6) and a second mounting plate (7), wherein the cone fairing (5) is fixedly arranged in the middle of the front end of a horizontal tail (1), the plane of the cone fairing (5) faces a tail rod (2), the cone cover body of the cone fairing (5) is connected with the skin of the horizontal tail (1) in a partial smooth transition mode, the first mounting plate (6) is vertically arranged and fixedly arranged on the plane cover body of the cone fairing (5), the first mounting plate (6) and the plane cover body of the cone fairing (5) are parallel to each other, the tail end of the insertion plate (3) sequentially penetrates through the first mounting plate (6) and the plane cover body of the cone fairing (5) to extend into the skin of the horizontal tail (1) and are fixedly connected with a wing beam of the horizontal tail (1), and the distance between the front end of the insertion plate (3) and the plane of the cone fairing (5) is the insertion plate (3) 1/3-1/2 of length, an electric plug (8) is fixedly arranged on the surface of one side, facing the tail rod (2), of the first mounting plate (6), the electric plug (8) is located above the insertion plate (3), the fixing sleeve (4) is fixed on a wing rib of the tail rod (2) and the fixing sleeve (4) is located in a skin of the tail rod (2), the tail end of the fixing sleeve (4) extends to the outer surface of the wing rib of the tail rod (2) at the joint of the tail rod (2) and the horizontal tail (1), the size of the cross section of the fixing sleeve (4) is matched with that of the insertion plate (3), an electric connector matched with the electric plug (8) is arranged on the end face, facing the horizontal tail (1), of the tail rod (2), the electric connector is fixed on the inner surface of the tail rod (2), a gap exists between the lower end of the electric connector and the upper surface of the fixing sleeve (4), the second mounting plate (7) is arranged on the outer surface of a wing rib of the tail rod (2) at the joint of the tail rod (2) and the horizontal tail (1), the second mounting plate (7) is horizontally arranged, the front end of the second mounting plate (7) is fixed on the outer surface of a wing rib of the tail rod (2) at the joint of the tail rod (2) and the horizontal tail (1), the left side and the right side of the second mounting plate (7) are fixed on the inner surface of the skin of the tail rod (2), a spring bolt (10) is fixedly arranged on the second mounting plate (7), a jack (11) is arranged on the plug-in plate (3) and positioned outside the plane cover body of the conical fairing (5), the pin head of the spring bolt (10) is vertically upward, the size of the jack (11) is matched with the size of the pin head of the spring bolt (10), an operating hole is formed in a skin of the tail rod (2), and the operating hole is located right below the spring bolt (10); when the tail rod (2) is connected with the front end of the plug board (3) of the horizontal tail (1) into a whole, the front end of the plug board (3) is inserted into the fixing sleeve (4), the pin head of the spring pin (10) is upwards inserted into the jack (11), the electrical plug (8) is inserted into the electrical connector, and the skin of the tail rod (2) is seamlessly spliced with the plane cover body of the fairing.
2. The quick-locking structure for the disassembly and assembly of the tail rod and the horizontal tail of the unmanned aerial vehicle according to claim 1, characterized in that: the cross section of the plugboard (3) is rectangular.
3. The quick-locking structure for the disassembly and assembly of the tail rod and the horizontal tail of the unmanned aerial vehicle according to claim 2, characterized in that: the distance between the front end of the plugboard (3) and the plane cover body of the conical fairing (5) is 1/2 of the length of the plugboard (3).
4. The quick-locking structure for the disassembly and assembly of the tail rod and the horizontal tail of the unmanned aerial vehicle as claimed in claim 3, wherein: the length of the fixing sleeve (4) is 1/2 of the length of the plugboard (3).
5. The quick-locking structure for the assembly and disassembly of the tail rod and the horizontal tail of the unmanned aerial vehicle according to claim 4, characterized in that: the plugboard (3), the fixing sleeve (4), the first mounting plate (6) and the second mounting plate (7) are all made of 7075 aluminum alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122200472.XU CN215622655U (en) | 2021-09-11 | 2021-09-11 | A dismouting is fast to be locked structure for unmanned aerial vehicle tailpiece and tail end |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122200472.XU CN215622655U (en) | 2021-09-11 | 2021-09-11 | A dismouting is fast to be locked structure for unmanned aerial vehicle tailpiece and tail end |
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| Publication Number | Publication Date |
|---|---|
| CN215622655U true CN215622655U (en) | 2022-01-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122200472.XU Active CN215622655U (en) | 2021-09-11 | 2021-09-11 | A dismouting is fast to be locked structure for unmanned aerial vehicle tailpiece and tail end |
Country Status (1)
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|---|---|
| CN (1) | CN215622655U (en) |
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2021
- 2021-09-11 CN CN202122200472.XU patent/CN215622655U/en active Active
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