Locking structure for thrust covering cap of unmanned aerial vehicle

Abstract

The invention discloses an unmanned aerial vehicle thrust opening cover locking structure which comprises a vehicle body, a thrust opening cover locking mechanism and a locking mechanism, and the vehicle body is provided with an opening which is provided with a front end and a rear end; the first end of the cover plate is rotationally installed at the front end of the opening, the cover plate can seal the opening or turn over downwards to open the opening, a reset torsional spring is arranged at the rotational connection position of the cover plate and the machine body, and the reset torsional spring is used for enabling the cover plate to have the rotating tendency of rotating towards the side close to the opening; the locking seat is arranged in the machine body and located at the rear end of the opening, and a locking hole is formed in the locking seat; the locking assembly is installed on the inner side wall of the cover plate, and the locking assembly is used for being matched with the locking hole of the locking seat; and the winding assembly is arranged in the machine body and located on one side of the front end of the opening, the winding assembly is provided with a winding rope, and the winding rope is connected with the second end of the cover plate. The cover plate can be further ensured to be closed in place through the winding rope of the winding assembly until the locking assembly is matched with the locking hole of the locking seat, and the cover plate is locked.

Description

Technical Field

[0001] The invention relates to the field of unmanned aerial vehicles, and in particular to a thrust port cover locking structure of an unmanned aerial vehicle. Background Art

[0002] Some drones, such as target drones, are often launched with rocket boosters. To ensure the aerodynamic shape, the force transmission point between the rocket and the fuselage is arranged inside the fuselage, so a reversible cover needs to be arranged near the thrust point. Before launch, the cover is opened to connect the rocket and the thrust point. After the launch is completed, the rocket falls off and the cover automatically resets and closes under the action of a torsion spring (such as a spring hinge).

[0003] For small and low-speed UAVs, the aerodynamic force on the cover is small and can be locked by a torsion spring. However, for medium and large high-speed UAVs, the cover area increases and the aerodynamic force increases at the same time. Considering the space limitations of the cabin, the specifications of the torsion spring cannot be increased indefinitely. At this time, the cover will flip over under the action of external aerodynamic force, destroying the aerodynamic shape of the UAV and affecting the flight state of the UAV. Summary of the invention

[0004] In view of the above problems, the present invention proposes a thrust port cover locking structure for a UAV.

[0005] The technical solution adopted by the present invention is as follows:

[0006] A thrust cover locking structure for an unmanned aerial vehicle, comprising:

[0007] A fuselage, wherein the lower part of the fuselage has an opening, wherein the opening has a front end and a rear end, wherein the front end of the opening is close to the head of the fuselage, and the rear end of the opening is far from the head of the fuselage;

[0008] A cover plate, wherein a first end of the cover plate is rotatably mounted on the front end of the opening, the cover plate can close the opening or flip downward to open the opening, and a return torsion spring is provided at the rotation connection between the cover plate and the body, and the return torsion spring is used to make the cover plate have a rotation tendency to rotate toward a side close to the opening;

[0009] A locking seat, arranged in the body and located at the rear end of the opening, and having a locking hole;

[0010] A locking assembly, mounted on the inner side wall of the cover plate, the locking assembly being used to cooperate with the locking hole of the locking seat;

[0011] The winding assembly is arranged in the machine body and is located at the front end side of the opening. The winding assembly has a winding rope, and the winding rope is connected to the second end of the cover plate.

[0012] During launch, the second end of the cover flips downward and opens. After launch, the rocket separates from the drone. Because the first end of the cover is rotatably mounted on the fuselage, it can be rotated upward to close the opening under the action of the return torsion spring and air pressure, and the winding rope of the winding assembly can further ensure that the cover is closed in place until the locking assembly cooperates with the locking hole of the locking seat to lock the cover.

[0013] In one embodiment of the present invention, the locking assembly includes:

[0014] A locking shell is fixed on the cover plate, and a mounting hole is provided on a side of the locking shell facing the locking seat;

[0015] A locking pin is slidably mounted on the mounting hole, and the locking pin is used to cooperate with the locking hole. When the locking pin is inserted into the locking hole, the cover plate is locked;

[0016] The first spring is arranged in the mounting hole and is used to make the locking pin have a movement tendency to move outward.

[0017] In one embodiment of the present invention, an upper portion of the end of the locking pin has an inclined guide surface.

[0018] In actual use, the cover can be flipped upward under the action of the return torsion spring and the air stand. At this time, the inclined guide surface will contact the fuselage. After the inclined guide surface is subjected to force, the locking pin can automatically retract into the locking shell, so that the cover is completely closed. After it is completely closed, the locking pin is no longer resisted, and it pops out under the action of the first spring and extends into the locking hole to achieve locking.

[0019] Because the flying direction of the drone will change, the reset torsion spring and air force alone cannot ensure that the cover can be completely closed. By setting up a winding component, further pulling force can be provided to ensure that the cover can be completely closed.

[0020] Compared with the design of turning the cover to open inside the fuselage, the design of the cover opening outwards can reduce the occupation of the internal space of the fuselage and improve the utilization rate of the internal space of the fuselage.

[0021] In one embodiment of the present invention, the mounting hole includes a large diameter portion and a small diameter portion, the small diameter portion is closer to the locking seat, the locking pin has an anti-slip portion located inside the large diameter portion, the outer diameter of the anti-slip portion is larger than the inner diameter of the small diameter portion; the first spring is arranged inside the large diameter portion.

[0022] In one embodiment of the present invention, it further includes:

[0023] A mounting groove is provided through the cover plate, the mounting groove has a large diameter area and a small diameter area, a limiting step is provided between the large diameter area and the small diameter area, and the small diameter area is closer to the outer side wall of the cover plate;

[0024] An unlocking rod is slidably mounted on the mounting groove, the unlocking rod has a positioning portion located in the large diameter area, the outer diameter of the positioning portion is larger than the inner diameter of the small diameter area, and in an initial state, the first end of the unlocking rod is located in the small diameter area, and the second end of the unlocking rod is located on a side of the locking shell facing away from the locking seat;

[0025] An unlocking rope, one end of which is connected to the end of the locking pin away from the locking seat, and the other end of which passes through the locking shell and is connected to the second end of the unlocking rod;

[0026] The second spring is installed in the installation groove and is used to push the unlocking rod to move downward so that the positioning part abuts against the limiting step.

[0027] In the initial state, the cover is locked and cannot be flipped outward. Before launch, a pointed tool (such as a thimble with a handle) is inserted into the small-diameter area to drive the unlocking rod to move inward from the fuselage. At this time, the second end of the unlocking rod will drive the unlocking rope to move, thereby retracting the locking pin and disengaging from the locking hole. The pointed tool then drives the cover to flip downward. After the cover is opened, the operator can hold the second end of the cover with his hand, and then pass the rocket's push rod through the opening to counteract the thrust point inside the fuselage.

[0028] In actual use, preferably, in the initial state (the positioning portion abuts against the limiting step), the lower end of the unlocking rod is flush with and matched with the outer side wall of the cover plate, and does not protrude from the outer side wall of the cover plate.

[0029] In actual use, the installation groove also has a hollow locking nut on one side of the inner wall of the cover plate, one end of the second spring abuts against the locking nut, and the other end abuts against the positioning portion of the unlocking rod.

[0030] In one embodiment of the present invention, the axis of the unlocking rod forms an acute angle with the axis of the locking pin.

[0031] In actual use, the acute angle range is 30° to 60°. Compared with the 90° setting, this setting can ensure that the pointed tool can drive the unlocking rope to move a greater distance after being pushed in, so as to facilitate unlocking the locking pin.

[0032] In one embodiment of the present invention, the winding assembly includes a winding wheel, a winding rope and a winding motor.

[0033] In one embodiment of the present invention, a portion of the inner wall of the cover plate close to the second end of the cover plate has a connecting portion, and the reeling rope is connected to the connecting portion.

[0034] In one embodiment of the present invention, the locking assembly and the connecting portion are respectively disposed on the left and right sides of the cover plate.

[0035] This arrangement allows the cover to be stressed on both sides, ensuring a relatively uniform stress structure. In addition, after the left and right settings, there are no parts in the middle area, making it easier for the rocket's push rod to better coordinate with the thrust points inside the fuselage.

[0036] In one embodiment of the present invention, a sensing switch is disposed on the bottom wall of the locking hole, and the sensing switch is used to sense whether the locking pin is inserted into the locking hole.

[0037] In actual use, the induction switch can be a mechanical switch or an infrared sensor or other components.

[0038] The beneficial effects of the present invention are as follows: during launch, the second end of the cover is flipped downward to open, and after launch, the rocket is separated from the UAV. Because the first end of the cover is rotatably mounted on the fuselage, it can be rotated upward to close the opening under the action of the return torsion spring and air pressure, and the winding rope of the winding assembly can further ensure that the cover is closed in place until the locking assembly cooperates with the locking hole of the locking seat to lock the cover. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 is a schematic diagram of a UAV having a UAV thrust port cover locking structure;

[0040] Figure 2 It is a schematic diagram when the cover plate closes the opening;

[0041] Figure 3 This is a schematic diagram after the cover is opened;

[0042] Figure 4 This is a schematic diagram of another angle after the cover is opened;

[0043] Figure 5 This is a partial schematic diagram of the locking structure of the thrust cover of the UAV;

[0044] Figure 6 It is a partial cross-sectional view of the UAV thrust cover locking structure.

[0045] The reference numerals in the figures are:

[0046] 1. Body; 11. Opening; 111. Front end; 112. Rear end; 2. Cover plate; 21. First end of cover plate; 22. Second end of cover plate; 23. Mounting groove; 231. Large diameter area; 232. Small diameter area; 233. Limiting step; 24. Connecting part; 3. Locking seat; 31. Locking hole; 32. Induction switch; 4. Locking assembly; 41. Locking shell; 411. Mounting hole; 4111. Large diameter part; 4112. Small diameter part; 42. Locking pin; 421. Inclined guide surface; 422. Anti-slip part; 43. First spring; 5. Winding assembly; 51. Winding wheel; 52. Winding rope; 61. Unlocking rod; 611. Positioning part; 612. First end of unlocking rod; 613. Second end of unlocking rod; 62. Unlocking rope; 63. Second spring; 64. Locking nut. DETAILED DESCRIPTION

[0047] In order to make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations.

[0048] In the description of this application, it should be noted that the terms "inside", "outside", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the application is usually placed when in use, which is only for the convenience of describing this application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0049] In the description of this application, it should also be noted that, unless otherwise clearly specified and limited, the terms "disposed" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0050] The present invention is described in detail below in conjunction with the accompanying drawings.

[0051] like Figure 1 to Figure 6 As shown, a thrust port cover locking structure of a UAV includes:

[0052] A fuselage 1, wherein the lower portion of the fuselage 1 has an opening 11, and the opening 11 has a front end 111 and a rear end 112, wherein the front end 111 of the opening 11 is close to the head of the fuselage 1, and the rear end 112 of the opening 11 is far from the head of the fuselage 1;

[0053] The cover plate 2, the first end 21 of the cover plate is rotatably mounted on the front end 111 of the opening 11, the cover plate 2 can close the opening 11 or flip downward to open the opening 11, and a return torsion spring (omitted and not shown in the figure) is provided at the rotation connection between the cover plate 2 and the body 1, and the return torsion spring is used to make the cover plate 2 have a rotation tendency to rotate toward the side close to the opening 11;

[0054] A locking seat 3 is disposed in the body 1 and located at the rear end 112 of the opening 11, and has a locking hole 31;

[0055] A locking assembly 4 is mounted on the inner wall of the cover plate 2, and the locking assembly 4 is used to cooperate with the locking hole 31 of the locking seat 3;

[0056] The reeling assembly 5 is disposed in the body 1 and is located at a side of the front end 111 of the opening 11 . The reeling assembly 5 comprises a reeling rope 52 , and the reeling rope 52 is connected to the second end 22 of the cover plate.

[0057] During launch, the second end 22 of the cover is flipped downward and opened. After launch, the rocket is separated from the UAV. Because the first end 21 of the cover is rotatably mounted on the fuselage 1, it can be rotated upward to close the opening 11 under the action of the return torsion spring and air pressure, and the winding rope 52 of the winding assembly 5 can further ensure that the cover 2 is closed in place until the locking assembly 4 cooperates with the locking hole 31 of the locking seat 3 to lock the cover 2.

[0058] like Figure 6 As shown, in this embodiment, the locking assembly 4 includes:

[0059] The locking shell 41 is fixed on the cover plate 2, and a mounting hole 411 is formed on a side of the locking shell 41 facing the locking seat 3;

[0060] The locking pin 42 is slidably mounted on the mounting hole 411. The locking pin 42 is used to cooperate with the locking hole 31. When the locking pin 42 is inserted into the locking hole 31, the cover plate 2 is locked;

[0061] The first spring 43 is disposed in the mounting hole 411 and is used to make the locking pin 42 have a movement tendency to move outward.

[0062] like Figure 3 and Figure 6 As shown, in this embodiment, an inclined guide surface 421 is provided above the end of the locking pin 42 .

[0063] In actual use, the cover 2 can be flipped upward under the action of the return torsion spring and the air stand. At this time, the inclined guide surface 421 will contact the fuselage 1. After the inclined guide surface 421 is subjected to force, the locking pin 42 can automatically retract into the locking shell 41, so that the cover 2 is completely closed. After it is completely closed, the locking pin 42 is no longer resisted, and it pops out under the action of the first spring 43 and extends into the locking hole 31 to achieve locking.

[0064] Because the flying direction of the drone may change, the cover 2 cannot be completely closed only by the reset torsion spring and the air force. By setting the winding assembly 5, further pulling force can be provided to ensure that the cover 2 can be completely closed.

[0065] Compared with the design of rotating the cover 2 to open inside the fuselage 1 , the design of the cover 2 opening outwards can reduce the occupation of the internal space of the fuselage 1 and improve the utilization rate of the space inside the fuselage 1 .

[0066] like Figure 6 As shown, in this embodiment, the mounting hole 411 includes a large diameter portion 4111 and a small diameter portion 4112, the small diameter portion 4112 is closer to the locking seat 3, the locking pin 42 has an anti-slip portion 422 located in the large diameter portion 4111, and the outer diameter of the anti-slip portion 422 is larger than the inner diameter of the small diameter portion 4112; the first spring 43 is arranged in the large diameter portion 4111.

[0067] like Figure 2 , 4 , 5 and 6, in this embodiment, the UAV thrust cover locking structure also includes:

[0068] The mounting groove 23 is provided through the cover plate 2. The mounting groove 23 has a large diameter area 231 and a small diameter area 232. A limiting step 233 is provided between the large diameter area 231 and the small diameter area 232. The small diameter area 232 is closer to the outer wall of the cover plate 2.

[0069] The unlocking lever 61 is slidably mounted on the mounting groove 23. The unlocking lever 61 has a positioning portion 611 located in the large diameter region 231. The outer diameter of the positioning portion 611 is greater than the inner diameter of the small diameter region 232. In the initial state, the first end 612 of the unlocking lever is located in the small diameter region 232, and the second end 613 of the unlocking lever is located on the side of the locking shell 41 facing away from the locking seat 3.

[0070] An unlocking rope 62, one end of which is connected to the end of the locking pin 42 away from the locking seat 3, and the other end of which passes through the locking shell 41 and is connected to the second end 613 of the unlocking rod;

[0071] The second spring 63 is installed in the installation slot 23 and is used to push the unlocking rod 61 downward so that the positioning portion 611 abuts against the limiting step 233 .

[0072] In the initial state, the cover 2 is locked and cannot be flipped outward. Before launching, a pointed tool (such as a thimble with a handle) is inserted into the small-diameter area 232 to drive the unlocking rod 61 to move toward the inside of the fuselage 1. At this time, the second end 613 of the unlocking rod will drive the unlocking rope 62 to move, thereby retracting the locking pin 42 and disengaging from the locking hole 31. Then the pointed tool drives the cover 2 to flip downward. After the cover 2 is opened, the operator can hold the second end 22 of the cover by hand, and then push the push rod of the rocket through the opening 11 to resist the thrust point inside the fuselage 1.

[0073] In actual use, preferably, in the initial state (the positioning portion 611 abuts against the limiting step 233 ), the lower end of the unlocking rod 61 is flush with and matched with the outer side wall of the cover plate 2 , and does not protrude from the outer side wall of the cover plate 2 .

[0074] In actual use, the installation groove 23 also has a hollow locking nut 64 on one side of the inner wall of the cover plate 2 , and one end of the second spring 63 abuts against the locking nut 64 , and the other end abuts against the positioning portion 611 of the unlocking rod 61 .

[0075] like Figure 6 As shown, in this embodiment, the axis of the unlocking rod 61 forms an acute angle with the axis of the locking pin 42. In actual use, the acute angle ranges from 30° to 60°. Compared with the 90° setting, this setting can ensure that the pointed tool can drive the unlocking rope 62 to move a greater distance after being pushed in, so as to facilitate unlocking the locking pin 42.

[0076] like Figure 5 As shown, in this embodiment, the winding assembly 5 includes a winding wheel 51, a winding rope 52 and a winding motor (omitted and not shown in the figure).

[0077] like Figure 5 and 6 As shown, in this embodiment, the inner side wall of the cover plate 2 near the second end 22 of the cover plate has a connecting portion 24, and the winding rope 52 is connected to the connecting portion 24. The locking assembly 4 and the connecting portion 24 are respectively arranged on the left and right sides of the cover plate 2. In this way, the cover plate 2 can be stressed on both the left and right sides, ensuring that the stress structure is relatively uniform. In addition, after the left and right settings, there are no parts in the middle area, which facilitates the rocket's push rod to better cooperate with the thrust point inside the fuselage 1.

[0078] like Figure 6 As shown, in this embodiment, the bottom wall of the locking hole 31 is provided with a sensor switch 32, and the sensor switch 32 is used to sense whether the locking pin 42 is inserted into the locking hole 31. In actual use, the sensor switch 32 can be a mechanical switch or an infrared sensor or other components. The sensor switch 32 can be linked with the winding component 5, and when the sensor switch 32 detects that the locking pin 42 is inserted into the locking hole 31, the operation stops.

[0079] The above description is only a preferred embodiment of the present invention, and does not limit the patent protection scope of the present invention. Any equivalent structural transformation made by using the contents of the present invention and the drawings, directly or indirectly used in other related technical fields, is also included in the protection scope of the present invention.

Claims

1. A UAV thrust port cover locking structure, characterized in that: include: A fuselage, wherein the lower part of the fuselage has an opening, wherein the opening has a front end and a rear end, wherein the front end of the opening is close to the head of the fuselage, and the rear end of the opening is far from the head of the fuselage; A cover plate, wherein a first end of the cover plate is rotatably mounted on the front end of the opening, the cover plate can close the opening or flip downward to open the opening, and a return torsion spring is provided at the rotation connection between the cover plate and the body, and the return torsion spring is used to make the cover plate have a rotation tendency to rotate toward a side close to the opening; A locking seat, arranged in the body and located at the rear end of the opening, and having a locking hole; A locking assembly, mounted on the inner side wall of the cover plate, the locking assembly being used to cooperate with the locking hole of the locking seat; The winding assembly is arranged in the machine body and is located at the front end side of the opening. The winding assembly has a winding rope, and the winding rope is connected to the second end of the cover plate.

2. The UAV thrust port cover locking structure according to claim 1, characterized in that: The locking assembly comprises: A locking shell is fixed on the cover plate, and a mounting hole is provided on a side of the locking shell facing the locking seat; A locking pin is slidably mounted on the mounting hole, and the locking pin is used to cooperate with the locking hole. When the locking pin is inserted into the locking hole, the cover plate is locked; The first spring is arranged in the mounting hole and is used to make the locking pin have a movement tendency to move outward.

3. The UAV thrust port cover locking structure according to claim 2, characterized in that: An inclined guide surface is provided above the end of the locking pin.

4. The UAV thrust port cover locking structure as claimed in claim 3, characterized in that: The mounting hole includes a large diameter portion and a small diameter portion, the small diameter portion is closer to the locking seat, the locking pin has an anti-slip portion located in the large diameter portion, the outer diameter of the anti-slip portion is larger than the inner diameter of the small diameter portion; the first spring is arranged in the large diameter portion.

5. The UAV thrust port cover locking structure as claimed in claim 4, characterized in that: Also includes: A mounting groove is provided through the cover plate, the mounting groove has a large diameter area and a small diameter area, a limiting step is provided between the large diameter area and the small diameter area, and the small diameter area is closer to the outer side wall of the cover plate; An unlocking rod is slidably mounted on the mounting groove, the unlocking rod has a positioning portion located in the large diameter area, the outer diameter of the positioning portion is larger than the inner diameter of the small diameter area, and in an initial state, the first end of the unlocking rod is located in the small diameter area, and the second end of the unlocking rod is located on a side of the locking shell facing away from the locking seat; An unlocking rope, one end of which is connected to the end of the locking pin away from the locking seat, and the other end of which passes through the locking shell and is connected to the second end of the unlocking rod; The second spring is installed in the installation groove and is used to push the unlocking rod to move downward so that the positioning part abuts against the limiting step.

6. The UAV thrust port cover locking structure according to claim 5, characterized in that: The axis of the unlocking lever forms an acute angle with the axis of the locking pin.

7. The UAV thrust port cover locking structure according to claim 1, characterized in that: The winding assembly comprises a winding wheel, a winding rope and a winding motor.

8. The UAV thrust port cover locking structure according to claim 7, characterized in that: A portion of the inner side wall of the cover plate close to the second end of the cover plate has a connecting portion, and the winding rope is connected to the connecting portion.

9. The UAV thrust port cover locking structure according to claim 8, characterized in that: The locking assembly and the connecting portion are respectively arranged on the left and right sides of the cover plate.

10. The UAV thrust port cover locking structure according to claim 1, characterized in that: The bottom wall of the locking hole is provided with an induction switch, and the induction switch is used to sense whether the locking pin is inserted into the locking hole.

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