Portable unmanned aerial vehicle mounting structure

Abstract

The utility model discloses a portable unmanned aerial vehicle mounting structure which comprises a machine head body and a machine body, the machine head body is detachably connected with the machine body, a bullet head cavity is formed in the machine head body, a bullet body cavity is formed in the machine body, and a bullet head is arranged in the bullet body cavity. The bullet head cavity and the bullet body cavity are communicated to form a cavity used for containing a guided missile. The device has the effect of reducing wind resistance.

Description

Technical Field

[0001] The present application relates to the field of drones, and in particular to a portable drone mounting structure. Background Art

[0002] At present, in modern military operations, rapid and accurate strikes are the key to victory. Currently, most bomb-carrying drones have bombs hanging under the fuselage. In addition, the fuselage is equipped with multiple propellers with vertically set rotating shafts. The propellers are rotated by the fuselage's own motor to provide power for transporting ammunition.

[0003] Because the ammunition is placed under the fuselage, the overall windward area of ​​the aircraft is large, and the force-bearing area is also large, making it difficult to increase the flight speed and meet the modern combat requirements of rapid strikes. Therefore, there is still room for improvement. Summary of the invention

[0004] In order to reduce wind resistance, the present application provides a portable drone installation structure.

[0005] The portable drone installation structure provided in this application adopts the following technical solution:

[0006] A portable unmanned aerial vehicle installation structure comprises a nose body and a fuselage body, wherein the nose body is detachably connected to the fuselage body, a warhead chamber is arranged inside the nose body, a body chamber is arranged inside the fuselage body, and the warhead chamber is connected with the body chamber to form a cavity for accommodating a missile.

[0007] By adopting the above technical solution, the UAV is divided into two parts, namely, a nose body and a fuselage body, and a chamber for accommodating a warhead is provided inside the nose body, and a body chamber for accommodating a body is provided inside the fuselage body. When the nose body and the fuselage body are assembled into a UAV, the missile is completely accommodated in the cavity formed by the warhead chamber and the body chamber, thereby completely hiding the missile inside the UAV, thereby replacing the traditional external missile loading method, which is beneficial to reducing wind resistance and facilitating improving the flight speed and flight stability of the UAV.

[0008] Preferably, the splicing surface of the head body is provided with an annular protrusion, the outer peripheral surface of the annular protrusion is provided with an external thread, the splicing surface of the body body is provided with a groove, the inner peripheral wall of the groove is provided with an internal thread, and the head body and the body body are connected by the annular protrusion and the groove thread.

[0009] By adopting the above technical solution, the annular protrusion plays a connecting role so that it can be threadedly connected to the fuselage body of the drone, thereby achieving the purpose of detaching the nose body and the fuselage of the drone, which is beneficial to improving the connection stability between the fuselage body and the nose body of the drone.

[0010] Preferably, an anti-loosening washer is provided on the outside of the annular protrusion, and the anti-loosening washer is clamped between the head body and the fuselage.

[0011] The adoption of the above technical solution is helpful to reduce the looseness of the UAV during flight and improve the flight stability of the UAV.

[0012] Preferably, the exterior of the nose body is in a bullet shape, the exterior of the fuselage body is in a cylindrical shape, and the outer wall of the nose body and the outer wall of the fuselage body are smoothly transitioned.

[0013] By adopting the above technical solution, the cylindrical fuselage is combined with the bullet-shaped nose, which improves the wind-breaking ability of the nose and helps reduce wind resistance.

[0014] Preferably, a tail propeller is provided at one end of the fuselage body away from the nose body.

[0015] By adopting the above technical solution, a tail propeller is installed at the end of the fuselage body, and the propeller has a boosting effect on the flight of the UAV, which is beneficial to increasing the flight speed of the UAV.

[0016] Preferably, a plurality of side wings are arranged on the outer peripheral surface of the fuselage body, the side wings are inclined toward the tail end of the fuselage body, and the plurality of side wings are distributed around the circumference.

[0017] By adopting the above technical solution, the circularly distributed side wings play a role in heading balance and stability during the flight of the UAV, which is beneficial to improving the stability of the UAV flight.

[0018] Preferably, the outer peripheral wall of the fuselage body is provided with a plurality of connecting parts, the plurality of connecting parts correspond to a plurality of side wings one by one, the connecting parts are staggeredly connected with the side wings, and a front propeller is provided at one end of the connecting part away from the fuselage body.

[0019] By adopting the above technical solution, the connecting part is connected with the side wing, and a front propeller is installed at the end of the connecting part away from the fuselage body. The front propeller improves the wind-breaking ability of the UAV and is beneficial to increasing the flight speed of the UAV.

[0020] Preferably, a fixing rod is provided between the connecting portion and the corresponding side wing, and the length direction of the fixing rod is parallel to the length direction of the fuselage body.

[0021] By adopting the above technical solution, the fixed rod plays a role in reinforcing the connecting part and the side wing, thereby improving the stability of the connection between the two and further improving the flight stability of the UAV. At the same time, the fixed rod is parallel to the fuselage body, which is beneficial to reducing the area of ​​the windward surface of the fixed rod and reducing wind resistance.

[0022] In summary, the present application includes at least one of the following beneficial technical effects:

[0023] By splitting the UAV into a nose body and a fuselage body, and providing a chamber for accommodating a warhead inside the nose body, and providing a body chamber for accommodating a body of the warhead inside the body, when the nose body and the body body are assembled into a UAV, the missile is completely accommodated in the cavity formed by the warhead chamber and the body chamber, so that the missile is completely hidden inside the UAV, thereby replacing the traditional missile external loading method, which is beneficial to reducing wind resistance and facilitating improving the flight speed and flight stability of the UAV;

[0024] By connecting the connecting part with the side wing and installing a front propeller at the end of the connecting part away from the fuselage body, the front propeller improves the wind-breaking ability of the UAV, which is conducive to increasing the flight speed of the UAV;

[0025] By setting the fixing rod, the connection stability between the connecting part and the side wing is improved, and the flight stability of the UAV is further improved. At the same time, the fixing rod is parallel to the fuselage body, which is beneficial to reducing the area of ​​the windward surface of the fixing rod and reducing wind resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of the overall structure of a portable UAV installation structure according to an embodiment of the present application.

[0027] Figure 2 It is a schematic diagram of the internal structure of a portable UAV installation structure according to an embodiment of the present application.

[0028] Explanation of the reference numerals: 1. nose body; 11. warhead chamber; 12. annular protrusion; 2. fuselage body; 21. warhead chamber; 22. groove; 3. side wing; 4. connecting part; 5. fixing rod; 6. front propeller; 7. anti-loosening washer; 8. tail propeller. DETAILED DESCRIPTION

[0029] The following is combined with Figure 1-2 This application is described in further detail.

[0030] The present application embodiment discloses a portable drone installation structure. Figure 1 and Figure 2 , including a nose body 1 and a body body 2, the nose body 1 and the body body 2 are detachably connected, in this embodiment, the sides of the nose body 1 and the body body 2 facing each other are their respective joint surfaces. A warhead chamber 11 is arranged inside the nose body 1, the opening position of the warhead chamber 11 is arranged at the joint surface of the nose body 1, and the shape of the warhead chamber 11 is adapted to the shape of the warhead of the missile, and is used to accommodate the warhead of the missile.

[0031] A body chamber 21 is provided inside the fuselage body 2, and the opening position of the body chamber 21 is provided at the joint surface of the fuselage body 2, and the shape of the body chamber 21 is adapted to the shape of the missile body, and is used to accommodate the warhead of the missile. The warhead chamber 11 is connected with the body chamber 21 to form a cavity for accommodating the missile. By completely hiding the missile inside the drone, instead of the traditional missile external loading method, it is beneficial to reduce the wind resistance of the drone during flight, and it is convenient to improve the flight speed and flight stability of the drone.

[0032] In this embodiment, the nose body 1 is in a bullet shape, the body body 2 is in a cylindrical shape, and the outer wall of the nose body 1 and the outer wall of the body body 2 are smoothly transitioned. The cylindrical body and the nose in the shape of a bullet improve the wind-breaking ability of the nose and help reduce wind resistance.

[0033] In order to improve the connection stability between the nose body 1 and the fuselage body 2, an annular protrusion 12 is provided on the joint surface of the nose body 1, and an external thread is provided on the outer peripheral surface of the annular protrusion 12. A groove 22 is provided on the joint surface of the fuselage body 2, and an internal thread is provided on the inner peripheral wall of the groove 22. The nose body 1 and the fuselage body 2 are threadedly connected through the annular protrusion 12 and the groove 22. And the outer sleeve of the annular protrusion 12 is provided with an anti-loosening washer 7. When the nose body 1 and the fuselage body 2 are assembled, the anti-loosening washer 7 is sandwiched between the nose body 1 and the fuselage. Reduce the looseness of the drone during flight, thereby improving the flight stability of the drone.

[0034] In this embodiment, a tail propeller is installed at one end of the fuselage body 2 away from the nose body 1, and a tail motor for driving the tail propeller to rotate is embedded in the tail of the fuselage body 2. The tail propeller boosts the flight of the drone and helps to increase the flight speed of the drone.

[0035] In addition, in order to improve the flight stability of the UAV, a plurality of side wings 3 are installed on the outer peripheral surface of the fuselage body 2. The side wings 3 are inclined toward the tail end of the fuselage body 2. The plurality of side wings 3 are distributed circumferentially. In the present embodiment, there are a total of four side wings 3. The four side wings 3 work together to balance the heading and stabilize the UAV during flight.

[0036] The outer peripheral wall of the fuselage body 2 is provided with a plurality of connecting parts 4, and the plurality of connecting parts 4 correspond to the plurality of side wings 3 one by one, and the connecting parts 4 are staggered and fixedly connected with the side wings 3. In addition, a front propeller 6 is provided at one end of the connecting part 4 away from the fuselage body 2, and a front motor for driving the front propeller 6 to rotate is installed at the end of the connecting part 4. The front propeller 6 improves the wind-breaking ability of the UAV, which is beneficial to improving the flight speed of the UAV.

[0037] In this embodiment, in order to improve the flight stability of the UAV, a fixing rod 5 is provided between the connecting portion 4 and the corresponding side wing 3. The fixing rod 5 serves to reinforce the connecting portion 4 and the side wing 3. In addition, the length direction of the fixing rod 5 is parallel to the length direction of the fuselage body 2, which is beneficial to reducing the area of ​​the windward surface of the fixing rod 5, thereby reducing wind resistance.

[0038] The implementation principle of a portable drone installation structure in the embodiment of the present application is:

[0039] When installing the bomb, the nose body 1 is removed from the UAV fuselage body 2, and then the bomb is loaded into the bomb body chamber 21 of the fuselage body 2, and then the anti-loosening washer 7 is mounted on the outer periphery of the annular protrusion 12, and then the nose body 1 and the fuselage body 2 are threadedly connected to complete the assembly of the bomb-carrying UAV.

[0040] When the UAV is flying, the circularly distributed side wings 3 play a role in heading balance and stability during the flight of the UAV, which is beneficial to improving the stability of the UAV's flight. In addition, the tail motor drives the tail propeller to rotate, and the front motor drives the front propeller 6 to rotate. The tail propeller boosts the flight of the UAV, and the front propeller 6 improves the UAV's wind-breaking ability, which is beneficial to increasing the UAV's flight speed.

[0041] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. A portable drone installation structure, characterized in that: The invention comprises a nose body (1) and a fuselage body (2), wherein the nose body (1) is detachably connected to the fuselage body (2), a warhead chamber (11) is arranged inside the nose body (1), a body chamber (21) is arranged inside the body body (2), and the warhead chamber (11) is connected to the body chamber (21) to form a cavity for accommodating a missile.

2. A portable drone installation structure according to claim 1, characterized in that: The joint surface of the head body (1) is provided with an annular protrusion (12), the outer peripheral surface of the annular protrusion (12) is provided with an external thread, the joint surface of the body body (2) is provided with a groove (22), the inner peripheral wall of the groove (22) is provided with an internal thread, and the head body (1) and the body body (2) are threadedly connected via the annular protrusion (12) and the groove (22).

3. A portable drone installation structure according to claim 2, characterized in that: The annular protrusion (12) is sleeved with an anti-loosening washer (7) on the outside, and the anti-loosening washer (7) is clamped between the head body (1) and the fuselage.

4. A portable drone installation structure according to claim 1, characterized in that: The exterior of the head body (1) is in the shape of a bullet, the exterior of the body body (2) is in the shape of a cylinder, and the outer wall of the head body (1) and the outer wall of the body body (2) are in smooth transition.

5. The portable drone installation structure according to claim 1, characterized in that: A tail propeller is arranged at one end of the fuselage body (2) away from the nose body (1).

6. A portable drone installation structure according to claim 1, characterized in that: The outer peripheral surface of the fuselage body (2) is provided with a plurality of side wings (3), the side wings (3) are inclined toward the tail end direction of the fuselage body (2), and the plurality of side wings (3) are distributed around the circumference.

7. A portable UAV installation structure according to claim 6, characterized in that: The outer peripheral wall of the fuselage body (2) is provided with a plurality of connecting parts (4), the plurality of connecting parts (4) correspond to the plurality of side wings (3) one by one, the connecting parts (4) are staggeredly connected to the side wings (3), and a front propeller (6) is provided at one end of the connecting part (4) away from the fuselage body (2).

8. A portable drone installation structure according to claim 7, characterized in that: A fixing rod (5) is provided between the connecting portion (4) and the corresponding side wing (3), and the length direction of the fixing rod (5) is parallel to the length direction of the fuselage body (2).

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