Undercarriage of hypersonic unmanned aerial vehicle with self-locking function

Abstract

The invention discloses an undercarriage of a hypersonic unmanned aerial vehicle with a self-locking function, and relates to the technical field of structures of undercarriages of hypersonic unmanned aerial vehicles. A wheel lowering assembly located on the right side comprises a first connecting rod hinged to the right end of a connecting rod through a first pin shaft, and a second connecting rod hinged to the right side wall of a stand column through a second pin shaft; a supporting plate is fixedly arranged at the lower end of the second connecting rod and hinged to the other end of the first connecting rod through a third pin shaft, the wheel lowering assembly located on the right side further comprises a cantilever hinged to the interior of the bin opening through a hinge base, the other end of the cantilever extends into an inner cavity of the machine body, and a wheel is rotationally installed at the extending end. The upper end part of the cantilever is hinged to the other end of the third connecting rod through a fifth pin shaft; a self-locking assembly used for locking the wheels is arranged between the top wall of the cantilever and the top wall of the bin opening. The method has the beneficial effects that the manufacturing cost of the hypersonic unmanned aerial vehicle is greatly saved, and the flight stability of the hypersonic unmanned aerial vehicle is improved.

Description

Technical Field

[0001] The invention relates to the technical field of the structure of a landing gear of a hypersonic unmanned aerial vehicle, in particular to a landing gear of a hypersonic unmanned aerial vehicle with a self-locking function. Background Art

[0002] Gaochao UAV is a wing-type UAV. Compared with spiral UAV, it has the following advantages: 1. It can be equipped with high-definition cameras and infrared sensors to quickly search and locate earthquake-stricken areas and find trapped people. 2. It can be used as a communication relay to provide temporary mobile networks for disaster areas to ensure smooth communication in the disaster areas.

[0003] The structure of a certain hypersonic drone is as follows Figure 1~Figure 2 As shown, it includes a body 3, wings 1 respectively arranged on the left and right sides of the body 3, and hatches 2 connected to the inner cavity of the body 3 are opened on the bottom surfaces of the two wings 1. Landing gears are arranged between the two wings 1 and the body 3. The landing gear located on the right side includes an electric cylinder 5 hinged on the top wall of the inner cavity of the body 3, and a cantilever 16 rotatably installed in the hatch 2 via a hinge seat 15. The other end of the cantilever 16 is rotatably installed with a wheel 17, and the wheel 17 is located at the intersection area between the inner cavity of the body 3 and the hatch 2; the piston rod of the electric cylinder 5 is rotatably installed on the cantilever 16 via a rotating shaft; the hypersonic UAV is in a flying state.

[0004] When the hypersonic UAV is about to land, the operator controls the piston rods of the electric cylinders 5 of the two landing gears to extend downward at the same time, and the piston rods drive the corresponding cantilevers 16 to rotate downward around the hinge seat 15, and the cantilever 16 drives the wheels 17 to move downward. When the wheels 17 are fully lowered, the hypersonic UAV can land on the ground through the two wheels 17.

[0005] However, although this kind of high-tech drone can be used, it still has the following technical defects: I. Both landing gears need to be equipped with an electric cylinder 5 to correspondingly complete the lowering of the wheels 17, which undoubtedly increases the manufacturing cost of the high-speed UAV.

[0006] II. When the hypersonic drone is in flight, if one of the electric cylinders 5 fails, the piston rod of the electric cylinder 5 will extend uncontrollably, causing the wheels 17 of the hypersonic drone to be exposed outside the body 3, thereby affecting the flight stability of the hypersonic drone.

[0007] Therefore, there is an urgent need for a landing gear that can greatly save the manufacturing cost of a hypersonic UAV and improve the flight stability of a hypersonic UAV. Summary of the invention

[0008] The purpose of the present invention is to overcome the shortcomings of the prior art and provide a landing gear for a hypersonic UAV with a self-locking function, which greatly saves the manufacturing cost of the hypersonic UAV and improves the flight stability of the hypersonic UAV.

[0009] The purpose of the present invention is achieved through the following technical solutions: a landing gear of a superb UAV with a self-locking function, which includes hatches opened on the bottom surfaces of two wings of the UAV, the two hatches are both connected to the inner cavity of the UAV body, and the columns are fixedly arranged on the bottom wall of the inner cavity of the body, the top of the column is fixedly arranged with an electric cylinder, the top of the piston rod of the electric cylinder is fixedly arranged with a connecting rod, and the left and right sides of the electric cylinder are both provided with wheel lowering components; The wheel lowering assembly located on the right side includes a first connecting rod hinged to the right end of the connecting rod via a first pin shaft, a second connecting rod hinged to the right side wall of the column via a second pin shaft, a support plate is fixedly arranged on the lower end of the second connecting rod, the support plate is hinged to the other end of the first connecting rod via a third pin shaft, and the other end of the second connecting rod is hinged to the third connecting rod via a fourth pin shaft; the wheel lowering assembly located on the right side also includes a cantilever hinged to the hatch through a hinge seat, the other end of the cantilever extends into the inner cavity of the machine body, and a wheel is rotatably mounted on the extended end, the wheel is located in the intersection area between the inner cavity of the machine body and the hatch, and the upper end of the cantilever is hinged to the other end of the third connecting rod via a fifth pin shaft; A self-locking component for locking the wheels is arranged between the top wall of the cantilever and the top wall of the bay opening. The self-locking component includes a sleeve welded to the top wall of the cantilever and located outside the fifth pin shaft, and a screw nut pair arranged on the top wall of the bay opening. A movable block is fixed on the bottom surface of the nut of the screw nut pair, and an insert rod is welded to the left end face of the movable block. The insert rod is embedded in the sleeve from right to left to self-lock the cantilever, and then self-lock the wheels on the cantilever.

[0010] The column and the electric cylinder are on the same vertical line, and the bottom of the column is welded to the bottom wall of the inner cavity of the machine body.

[0011] The two wheel lowering assemblies are arranged symmetrically about the column.

[0012] The length of the first connecting rod is greater than that of the second connecting rod, and the length of the second connecting rod is greater than that of the third connecting rod.

[0013] A bracket is welded on the column surface of the column, and the second connecting rod is hinged to the bracket via a second pin shaft.

[0014] The screw-nut pair includes a guide rail fixed on the top surface of the bayonet and two mounting seats, the two mounting seats are respectively located on the left and right sides of the guide rail, a screw is rotatably mounted between the two mounting seats, a self-locking motor is fixed on the right end surface of the mounting seat located on the right, and the output shaft of the self-locking motor is connected to the screw; the nut is threadedly connected to the screw, a slider is welded on the top wall of the nut, and the slider is slidably mounted on the guide rail.

[0015] The self-locking motor and the electric cylinder are both remotely controlled by the controller of the hypersonic UAV.

[0016] The present invention has the following advantages: greatly saving the manufacturing cost of the hypersonic UAV and improving the flight stability of the hypersonic UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the structure of a certain hypersonic drone; Figure 2 for Figure 1 AA cross-section diagram; Figure 3 It is a structural schematic diagram of the present invention; Figure 4 for Figure 3 BB cross-section diagram; Figure 5 is a structural schematic diagram of the first connecting rod; Figure 6 is a schematic structural diagram of the second connecting rod; Figure 7 It is a schematic diagram of the connection between the cantilever, sleeve and wheel; Figure 8 It is a connection diagram of the electric cylinder, column and connecting rod; Fig. 9 for Figure 4 A partial enlarged view of the C part; Fig.10 It is a connection diagram of the plug rod, the movable block and the nut; Fig.11 A schematic diagram showing the insertion rod being completely removed from the sleeve; Fig.12 A schematic diagram showing the wheels of two wheel lowering assemblies being lowered; In the figure: 1-wing, 2-port, 3-body, 4-column, 5-electric cylinder, 6-connecting rod; 7-first pin, 8-first connecting rod, 9-second pin, 10-second connecting rod, 11-support plate, 12-third pin, 13-fourth pin, 14-third connecting rod, 15-hinge seat, 16-cantilever, 17-wheel, 18-fifth pin; 19- sleeve, 20- nut, 21- movable block, 22- plug rod, 23- guide rail, 24- mounting seat, 25- lead screw, 26- self-locking motor. DETAILED DESCRIPTION

[0018] The present invention is further described below in conjunction with the accompanying drawings, and the protection scope of the present invention is not limited to the following: like Figure 3~Figure 10As shown, a landing gear of a high-speed UAV with a self-locking function includes a hatch 2 opened on the bottom surface of two wings 1 of the UAV, the two hatches 2 are both connected to the inner cavity of the body 3 of the UAV, and a column 4 is fixedly arranged on the bottom wall of the inner cavity of the body 3, an electric cylinder 5 is fixedly arranged on the top of the column 4, a connecting rod 6 is fixedly arranged on the top of the piston rod of the electric cylinder 5, and wheel lowering assemblies are arranged on the left and right sides of the electric cylinder 5, and the two wheel lowering assemblies are symmetrically arranged about the column 4; the column 4 and the electric cylinder 5 are on the same vertical line, and the bottom of the column 4 is welded to the bottom wall of the inner cavity of the body 3.

[0019] The wheel lowering assembly located on the right side includes a first connecting rod 8 hinged to the right end of the connecting rod 6 via a first pin shaft 7, a second connecting rod 10 hinged to the right side wall of the column 4 via a second pin shaft 9, a support plate 11 is fixedly provided on the lower end of the second connecting rod 10, the support plate 11 is hinged to the other end of the first connecting rod 8 via a third pin shaft 12, and the other end of the second connecting rod 10 is hinged to the third connecting rod 14 via a fourth pin shaft 13; the wheel lowering assembly located on the right side also includes a cantilever 16 hinged to the hatch 2 via a hinge seat 15, the other end of the cantilever 16 extends into the inner cavity of the machine body 3, and a wheel 17 is rotatably mounted on the extended end, the wheel 17 is located at the intersection of the inner cavity of the machine body 3 and the hatch 2, and the upper end of the cantilever 16 is hinged to the other end of the third connecting rod 14 via a fifth pin shaft 18; A self-locking component for locking the wheel 17 is arranged between the top wall of the cantilever 16 and the top wall of the bay opening 2. The self-locking component includes a sleeve 19 welded to the top wall of the cantilever 16 and located on the outside of the fifth pin shaft 18, and a screw nut pair arranged on the top wall of the bay opening 2. A movable block 21 is fixed on the bottom surface of the nut 20 of the screw nut pair, and an insert rod 22 is welded to the left end face of the movable block 21. The insert rod 22 is embedded in the sleeve 19 from right to left to self-lock the cantilever 16, and then self-lock the wheel 17 on the cantilever 16.

[0020] The screw-nut pair includes a guide rail 23 fixed on the top surface of the warehouse opening 2 and two mounting seats 24, the two mounting seats 24 are respectively located on the left and right sides of the guide rail 23, a screw 25 is rotatably mounted between the two mounting seats 24, a self-locking motor 26 is fixed on the right end surface of the mounting seat 24 located on the right, and the output shaft of the self-locking motor 26 is connected to the screw 25; the nut 20 is threadedly connected to the screw 25, a slider is welded on the top wall of the nut 20, and the slider is slidably mounted on the guide rail 23.

[0021] The length of the first connecting rod 8 is greater than that of the second connecting rod 10, and the length of the second connecting rod 10 is greater than that of the third connecting rod 14. A bracket is welded on the cylindrical surface of the column 4, and the second connecting rod 10 is hinged on the bracket via a second pin 9. The self-locking motor 26 and the electric cylinder 5 are remotely controlled by the controller of the hypersonic drone. The operator can control the self-locking motor 26 to rotate forward and reverse by operating the controller, and can also control the extension or retraction of the piston rod of the electric cylinder 5, which is convenient for the operator's operation.

[0022] The steps to land the drone are as follows: S1. Control the self-locking motor 26 of the self-locking assembly to start, the self-locking motor 26 drives the screw rod 25 to rotate, the nut 20 moves outward along the screw rod 25, the nut 20 drives the movable block 21 to move outward, the movable block 21 drives the plug rod 22 to move outward, and the plug rod 22 gradually comes out of the sleeve 19; when the self-locking motor 26 works for a set time, the controller controls the self-locking motor 26 to turn off, at this time, the plug rod 22 completely comes out of the sleeve 19, such as Fig.11 As shown; S2. The operator controls the piston rod of the electric cylinder 5 to retract downward, the piston rod drives the connecting rod 6 to move downward, the connecting rod 6 drives the first connecting rod 8 to move downward, the first connecting rod 8 drives the second connecting rod 10 to rotate downward around the axis of the second pin 9, the second connecting rod 10 drives the third connecting rod 14 to move downward, the third connecting rod 14 drives the cantilever 16 to rotate downward around the hinge seat 15, the cantilever 16 drives the sleeve 19 and the wheel 17 to move downward, and the wheel 17 is gradually lowered from the warehouse opening 2; when the piston rod of the electric cylinder 5 is fully retracted, the wheels 17 of the two wheel lowering assemblies are all lowered, as shown in FIG. Fig.12 As shown, the hypersonic UAV can land on the ground via two wheels 17, thereby achieving the landing of the hypersonic UAV.

[0023] Among them, it can be seen from steps S1 to S2 that the operator only needs to control the downward retraction of the piston rod of one electric cylinder 5 to simultaneously lower the wheels 17 of the two wheel lowering assemblies of the hypersonic UAV. Therefore, compared with the above-mentioned landing gear, the present invention is more convenient. Figure 1~Figure 2 The structure of the two landing gears shown reduces the number of electric cylinders 5, thereby greatly saving the manufacturing cost of the high-speed UAV.

[0024] The steps to make the drone fly again are: S3, control the power part of the hypersonic drone to operate so that the hypersonic drone flies to a certain height; then control the piston rod of the electric cylinder 5 to extend upward, the piston rod drives the connecting rod 6 to move upward, the connecting rod 6 drives the first connecting rod 8 to move upward, the first connecting rod 8 drives the second connecting rod 10 to rotate upward around the axis of the second pin 9, the second connecting rod 10 drives the third connecting rod 14 to move upward, the third connecting rod 14 drives the cantilever 16 to rotate upward around the hinge seat 15, the cantilever 16 drives the sleeve 19 and the wheel 17 to move upward, and the wheel 17 gradually retracts into the hatch 2; when the piston rod of the electric cylinder 5 is fully extended, the wheel 17 re-enters the intersection area between the hatch 2 and the inner cavity of the body 3, and the sleeve 19 on the cantilever 16 is just opposite to the plug rod 22 of the self-locking component; S4, control the self-locking motor 26 of the self-locking assembly to reverse, the self-locking motor 26 drives the screw rod 25 to rotate in the opposite direction, the nut 20 moves inward along the screw rod 25, the nut 20 drives the movable block 21 to move inward, the movable block 21 drives the insertion rod 22 to move toward the sleeve 19, when the self-locking motor 26 works for a set time, the controller controls the self-locking motor 26 to turn off, at this time, the insertion rod 22 is just inserted into the sleeve 19, as shown in FIG. Figure 4 and Fig. 9 As shown, the cantilever 16 is self-locked, and the wheels 17 on the cantilever 16 are self-locked.

[0025] Among them, from steps S3 to S4, when the hyperdrone is in flight, and when the two wheels 17 are completely retracted to the intersection area between the hatch 2 and the inner cavity of the body 3, it is only necessary to control the self-locking motor 26 of the self-locking assembly to reverse, so that the insertion rod 22 can be inserted into the sleeve 19, thereby self-locking the cantilever 16, and then self-locking the wheels 17 on the cantilever 16. It can be seen that since the wheels 17 are self-locked, the wheels 17 will not be lowered to the outside of the body 3 due to the failure of the electric cylinder 5, and will not affect the flight of the hyperdrone, thereby greatly improving the flight stability of the hyperdrone.

[0026] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A landing gear of a high-speed UAV with a self-locking function, characterized in that: It comprises a hatch (2) formed on the bottom surface of two wings (1) of a drone, the two hatches (2) being connected to the inner cavity of a body (3) of the drone, a column (4) fixedly arranged on the bottom wall of the inner cavity of the body (3), an electric cylinder (5) fixedly arranged on the top of the column (4), a connecting rod (6) fixedly arranged on the top of the piston rod of the electric cylinder (5), and wheel lowering assemblies being arranged on the left and right sides of the electric cylinder (5); The wheel lowering assembly located on the right side comprises a first connecting rod (8) hinged to the right end of the connecting rod (6) via a first pin shaft (7), a second connecting rod (10) hinged to the right side wall of the column (4) via a second pin shaft (9), a support plate (11) fixedly provided on the lower end of the second connecting rod (10), the support plate (11) being hinged to the other end of the first connecting rod (8) via a third pin shaft (12), and the other end of the second connecting rod (10) being hinged to a support plate (11) via a fourth pin shaft (13). a third connecting rod (14); the wheel lowering assembly located on the right side further comprises a cantilever (16) hinged to the hatch (2) via a hinge seat (15); the other end of the cantilever (16) extends into the inner cavity of the machine body (3), and a wheel (17) is rotatably mounted on the extended end; the wheel (17) is located at the intersection of the inner cavity of the machine body (3) and the hatch (2); the upper end of the cantilever (16) is hinged to the other end of the third connecting rod (14) via a fifth pin shaft (18); A self-locking assembly for locking the wheel (17) is provided between the top wall of the cantilever (16) and the top wall of the bay opening (2), the self-locking assembly comprising a sleeve (19) welded to the top wall of the cantilever (16) and located outside the fifth pin shaft (18), a screw nut pair provided on the top wall of the bay opening (2), a movable block (21) fixedly provided on the bottom surface of the nut (20) of the screw nut pair, an insert rod (22) welded to the left end surface of the movable block (21), the insert rod (22) being embedded in the sleeve (19) from right to left to self-lock the cantilever (16), thereby self-locking the wheel (17) on the cantilever (16).

2. The landing gear of a high-speed UAV with a self-locking function according to claim 1, characterized in that: The column (4) and the electric cylinder (5) are located on the same vertical line, and the bottom of the column (4) is welded to the bottom wall of the inner cavity of the machine body (3).

3. The landing gear of a hypersonic UAV with a self-locking function according to claim 1, characterized in that: The two wheel lowering assemblies are arranged symmetrically about the column (4).

4. The landing gear of a hypersonic UAV with a self-locking function according to claim 1, characterized in that: The length of the first connecting rod (8) is greater than the length of the second connecting rod (10), and the length of the second connecting rod (10) is greater than the length of the third connecting rod (14).

5. The landing gear of a hypersonic UAV with a self-locking function according to claim 1, characterized in that: A bracket is welded on the column surface of the column (4), and the second connecting rod (10) is hingedly connected to the bracket via a second pin shaft (9).

6. The landing gear of a hypersonic UAV with a self-locking function according to claim 1, characterized in that: The screw-nut pair comprises a guide rail (23) fixedly arranged on the top surface of the bay opening (2) and two mounting seats (24), the two mounting seats (24) being respectively located on the left and right sides of the guide rail (23), a screw rod (25) being rotatably mounted between the two mounting seats (24), a self-locking motor (26) being fixedly arranged on the right end surface of the mounting seat (24) located on the right side, an output shaft of the self-locking motor (26) being connected to the screw rod (25); the nut (20) being threadedly connected to the screw rod (25), a slider being welded on the top wall of the nut (20), and the slider being slidably mounted on the guide rail (23).

7. The landing gear of a hypersonic UAV with a self-locking function according to claim 1, characterized in that: The self-locking motor (26) and the electric cylinder (5) are both remotely controlled by a controller of the hypersonic drone.

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