Speed reduction device suitable for air-drop type unmanned aerial vehicle

Abstract

The invention relates to a speed reducer suitable for an air-drop type unmanned aerial vehicle, and belongs to the technical field of aircrafts. The parachute comprises a parachute cover (1), parachute cords (2), a wire bundling hoop (3) and a connector (4), the connector (4) comprises a connector upper shell (5), a connector base (6), an upper ball bearing (7), a lower ball bearing, an upper connecting ring (8) and a lower connecting ring (9), the speed reduction device is in a cross-shaped parachute form, the lower connecting ring is connected with the decelerated cylindrical unmanned aerial vehicle through the parachute cords, and the parachute cords are connected with the lower connecting ring through the lower connecting ring. The upper connecting ring and the lower connecting ring are both installed in the connector shell, the maximum outer diameter of the upper connecting ring and the maximum outer diameter of the lower connecting ring are both slightly smaller than the inner diameter of the connector shell, the speed reduction and rotation reduction technology of the air-drop type unmanned aerial vehicle is broken through, speed reduction and rotation reduction of the air-drop type unmanned aerial vehicle in the parachute landing process are achieved, and the scheme is simple in design, high in reliability, simple in process, low in machining cost and light in weight; the popularization value is realized.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft, and in particular relates to a deceleration device suitable for an airdrop type unmanned aerial vehicle. Background Art

[0002] In recent years, with the continuous development of anti-access / area denial capabilities in various countries around the world, the air defense combat system is gradually improving its global perception, global command and control, and global strike capabilities by building a global killing network. When a single unmanned combat platform performs low-altitude and low-speed reconnaissance or ground strike missions, it faces detection, interference and attacks from the enemy's air defense combat system. Single-machine combat is no longer safe enough. Therefore, coordinated combat between multiple aircraft will be the development trend in the future.

[0003] The core purpose of multi-machine coordinated operations is to use drones with different divisions of labor to form distributed, wide-area, and flexible combat capabilities, in order to expand the combat capabilities of main combat equipment and supplement combat resources. In multi-machine coordination, drones taking off from the ground are restricted by flight time and range, making it difficult to achieve a larger combat range; the flight speed constraint makes it difficult for them to quickly reach the combat area.

[0004] Airdrop UAVs can be quickly delivered to the battlefield, effectively shortening the firepower response time of combat equipment and greatly improving the combat effectiveness of weapons and equipment. After being dropped from the air by a vehicle, airdrop UAVs rely on a deceleration device to decelerate and stabilize their descent. The deceleration device is generally composed of a guide parachute, a main parachute, and a storage and opening mechanism. Traditional deceleration devices usually only consider the deceleration effect of the terminal section when designing, ignoring the posture requirements of the decelerated object. Therefore, the design method of traditional deceleration devices is not suitable for airdrop UAVs. The deceleration device suitable for airdrop UAVs must consider the posture requirements of the hanging UAV when designing, and minimize the rotation of the hanging UAV around the axis as much as possible, that is, to achieve deceleration on the basis of ensuring the deceleration effect, so as to avoid the failure of the UAV launch. Summary of the invention

[0005] 1. Technical issues to be resolved

[0006] The technical problem to be solved by the present invention is how to provide a deceleration device suitable for airdrop-type UAVs, so as to solve the problem that the existing deceleration device spins severely after being dropped in the air, affecting the air launch of the UAV loaded with the deceleration tube.

[0007] (II) Technical solution

[0008] In order to solve the above technical problems, the present invention proposes a deceleration device suitable for airdrop type UAV, comprising: a canopy 1, a canopy rope 2, a cable hoop 3, and a connector 4;

[0009] The umbrella surface 1 is set as a cross-shaped plane, and each corner of the umbrella surface 1 is connected to an umbrella rope 2, and the other ends of multiple umbrella ropes 2 are gathered and passed through a cable hoop 3;

[0010] The connector 4 comprises: a connector upper shell 5, a connector base 6, an upper ball bearing 7, a lower ball bearing, an upper connecting ring 8 and a lower connecting ring 9;

[0011] The connector base 6 is configured as a hollow structure with an opening at the bottom and a threaded structure on the outer wall. A lower ball bearing is provided in the connector base 6, a lower connecting ring 9 is provided above the lower ball bearing, an upper connecting ring 8 is provided above the lower connecting ring, an upper ball bearing 7 is provided above the upper connecting ring 8, and a connector upper shell 5 is provided above the upper ball bearing 7. The connector upper shell 5 is configured as a hollow structure, and the lower part of the upper shell 5 is threadedly connected to the outer wall of the connector base 6 through an internal thread;

[0012] The upper connecting ring 8 has the same structure as the lower connecting ring 9, with a circular ring at the end, a cylinder at the middle of the circular ring, and radial through holes at the ends of the two cylinders. The through holes of the upper connecting ring 8 are used to connect the umbrella surface through the umbrella rope 3, and the through holes of the lower connecting ring 9 are used to connect the decelerated tube-mounted drone through the umbrella rope 2;

[0013] The umbrella cover 3 is connected to the decelerated airdrop type UAV through the connector 4 to isolate the umbrella cover 1 from rotating.

[0014] Wherein, the material of the umbrella cover 3 is polyethylene silk;

[0015] The cross-shaped plane of the umbrella surface is provided with 8 right-angle ends in total.

[0016] Wherein, the material of the parachute rope 2 is polyethylene wire;

[0017] The number of the parachute ropes 2 placed at the top for connecting the parachute cover 3 and the upper connecting ring 8 is set to 8.

[0018] The cable tie 3 is in the shape of a hollow ring and is used to tie up the parachute ropes 2 to prevent the parachute ropes 2 from getting tangled with each other.

[0019] The material of the cable tie 3 is aluminum alloy.

[0020] The upper ball bearing 7 has the same structure as the lower ball bearing, including a bearing body and balls;

[0021] The bearing body is used to provide a fixing and moving space for the balls.

[0022] The upper ball bearing 7 and the lower ball bearing convert the original sliding friction between the upper and lower connecting rings and the connector housing 5 into rolling friction between the balls and the housing, thereby effectively reducing the friction force, allowing the upper and lower connecting rings to rotate freely without mutual interference, thereby isolating the rotation interference of the umbrella face on the decelerated airdrop type drone.

[0023] The maximum outer diameters of the upper and lower connecting rings are slightly smaller than the inner diameter of the connector housing 5 , so that the upper and lower connecting rings can rotate freely inside the connector housing 5 .

[0024] (III) Beneficial effects

[0025] The present invention proposes a deceleration device suitable for airdrop-type UAVs, which adopts a cross parachute form and can effectively reduce the rotation of the deceleration parachute itself; uses a ball bearing to effectively isolate the rotation of the parachute surface and avoid transmitting the rotational angular velocity of the parachute surface to the tube-mounted UAV; calculates the parachute surface area according to the load weight requirement, and can achieve a preset balanced falling speed at a specified altitude; and can provide a curve of the balanced falling speed changing with the altitude, which is convenient for determining the working state of the deceleration device. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0027] Figure 2 is a schematic diagram of the connector structure;

[0028] Figure 3 is a schematic diagram of a connector housing;

[0029] Figure 4 is a schematic diagram of a ball bearing;

[0030] Figure 5 This is a curve showing the relationship between the falling speed and the altitude of the example of the present invention;

[0031] Figure 6 This is a curve showing the relationship between resistance and altitude in an example of the present invention. DETAILED DESCRIPTION

[0032] In order to make the purpose, content and advantages of the present invention more clear, the specific implementation methods of the present invention are further described in detail below in conjunction with the drawings and examples.

[0033] This embodiment provides a deceleration device suitable for an airdrop type UAV, comprising: a canopy 1, a canopy rope 2, a cable tie 3, and a connector 4;

[0034] The umbrella surface 1 is set as a cross-shaped plane, and each corner of the umbrella surface 1 is connected to an umbrella rope 2, and the other ends of multiple umbrella ropes 2 are gathered and passed through a cable hoop 3;

[0035] The connector 4 comprises: a connector upper shell 5, a connector base 6, an upper ball bearing 7, a lower ball bearing, an upper connecting ring 8 and a lower connecting ring 9;

[0036] The connector base 6 is configured as a hollow structure with an opening at the bottom and a threaded structure on the outer wall. A lower ball bearing is provided in the connector base 6, a lower connecting ring 9 is provided above the lower ball bearing, an upper connecting ring 8 is provided above the lower connecting ring, an upper ball bearing 7 is provided above the upper connecting ring 8, and a connector upper shell 5 is provided above the upper ball bearing 7. The connector upper shell 5 is configured as a hollow structure, and the lower part of the upper shell 5 is threadedly connected to the outer wall of the connector base 6 through an internal thread;

[0037] The upper connecting ring 8 has the same structure as the lower connecting ring 9, with a circular ring at the end, a cylinder at the middle of the circular ring, and radial through holes at the ends of the two cylinders. The through holes of the upper connecting ring 8 are used to connect the umbrella surface through the umbrella rope 3, and the through holes of the lower connecting ring 9 are used to connect the decelerated tube-mounted drone through the umbrella rope 2;

[0038] The umbrella cover 3 is connected to the decelerated airdrop type UAV through the connector 4 to isolate the umbrella cover 1 from rotating.

[0039] Wherein, the material of the umbrella cover 3 is polyethylene silk;

[0040] The cross-shaped plane of the umbrella surface is provided with 8 right-angle ends in total.

[0041] Wherein, the material of the parachute rope 2 is polyethylene wire;

[0042] The number of the parachute ropes 2 placed at the top for connecting the parachute cover 3 and the upper connecting ring 8 is set to 8.

[0043] The cable tie 3 is in the shape of a hollow ring and is used to tie up the parachute ropes 2 to prevent the parachute ropes 2 from getting tangled with each other.

[0044] The material of the cable tie 3 is aluminum alloy.

[0045] The upper ball bearing 7 has the same structure as the lower ball bearing, including a bearing body and balls;

[0046] The bearing body is used to provide a fixing and moving space for the balls.

[0047] The upper ball bearing 7 and the lower ball bearing convert the original sliding friction between the upper and lower connecting rings and the connector housing 5 into rolling friction between the balls and the housing, thereby effectively reducing the friction force, allowing the upper and lower connecting rings to rotate freely without mutual interference, thereby isolating the rotation interference of the umbrella face on the decelerated airdrop type drone.

[0048] The maximum outer diameters of the upper and lower connecting rings are slightly smaller than the inner diameter of the connector housing 5 , so that the upper and lower connecting rings can rotate freely inside the connector housing 5 .

[0049] The ball bearing includes a bearing body and a ball. The bearing body can provide a fixed and movable space for the ball. In the entire connector structure, two ball bearings are arranged, one is located between the connector upper shell and the upper connecting ring, and the other is located between the connector base and the lower connecting ring. These two parts are the main parts where friction is generated. The ball bearings are arranged here, which can transform the original sliding friction between the upper and lower connecting rings and the connector shell into rolling friction between the ball and the shell, thereby effectively reducing the friction, so that the upper and lower connecting rings can rotate freely without mutual interference, thereby isolating the umbrella face from the rotation interference of the suspended airdrop type drone.

[0050] Figure 5 This is the calculation curve of the equilibrium falling speed of an airdropped UAV during parachute landing as it changes with altitude. Figure 6 This is the calculation curve of the resistance changing with altitude during parachuting. The initial conditions of the example are that the total weight of the tube-loaded airdropped drone is 20kg, the drop height is 10km, and the initial speed is 0m / s. The solution method of this example is based on the six-degree-of-freedom dynamic equations, which are obtained by discretizing the motion equations using the classic fourth-order Runge-Kutta method.

[0051] Depend on Figure 6 It can be seen that the resistance of the parachute drop process begins to increase rapidly from the beginning of the release. Under the action of gravity, the falling speed first increases and then decreases. When the altitude drops to 9.6km, the resistance is balanced with gravity, and the tube-mounted drone enters a stable landing state. After that, as the altitude decreases and the air density increases, the balanced falling speed of the tube-mounted drone will decrease slightly.

[0052] This example has achieved the design requirement of a steady descent speed of 15m / s at an altitude of 2km.

[0053] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A deceleration device suitable for airdrop type UAV, characterized in that: include: Umbrella canopy (1), umbrella rope (2), cable hoop (3), connector (4); The umbrella surface (1) is arranged as a cross-shaped plane, each corner of the umbrella surface (1) is connected to an umbrella rope (2), and the other ends of a plurality of umbrella ropes (2) are gathered and passed through a cable hoop (3); The connector (4) comprises: a connector upper shell (5), a connector base (6), an upper ball bearing (7), a lower ball bearing, an upper connecting ring (8) and a lower connecting ring (9); The connector base (6) is configured as a hollow structure with a hole at the bottom and a threaded structure on the outer wall. A lower ball bearing is provided inside the connector base (6), a lower connecting ring (9) is provided above the lower ball bearing, an upper connecting ring (8) is provided above the lower connecting ring, an upper ball bearing (7) is provided above the upper connecting ring (8), and a connector upper shell (5) is provided above the upper ball bearing (7). The connector upper shell (5) is configured as a hollow structure, and the lower part of the upper shell (5) is threadedly connected to the outer wall of the connector base (6) via an internal thread. The upper connecting ring (8) and the lower connecting ring (9) have the same structure, with the ends being circular rings, a cylinder being provided in the middle of the circular rings, and radial through holes being provided at the ends of the two cylinders. The through holes of the upper connecting ring (8) are used to connect the umbrella surface via the umbrella rope (3), and the through holes of the lower connecting ring (9) are used to connect the decelerated tube-mounted drone via the umbrella rope (2); The umbrella cover (3) is connected to the decelerated airdrop-type UAV via the connector (4) to prevent the umbrella cover (1) from rotating.

2. The deceleration device for an airdrop type UAV as claimed in claim 1, characterized in that: The material of the umbrella cover (3) is polyethylene silk; The cross-shaped plane of the umbrella surface is provided with 8 right-angle ends in total.

3. The deceleration device for an airdrop type UAV as claimed in claim 1, characterized in that: The material of the parachute rope (2) is polyethylene wire; The number of umbrella ropes (2) placed on the top and used to connect the umbrella surface (3) and the upper connecting ring (8) is set to 8.

4. The deceleration device for an airdrop type UAV as claimed in claim 1, characterized in that: The cable tie (3) is in the shape of a hollow ring as a whole and is used to tie up the parachute ropes (2) to prevent the parachute ropes (2) from being entangled with each other. The material of the cable tie (3) is aluminum alloy.

5. The deceleration device for an airdrop type UAV as claimed in claim 1, characterized in that: The upper ball bearing (7) has the same structure as the lower ball bearing, and comprises a bearing body and balls; The bearing body is used to provide a fixing and moving space for the balls; The upper ball bearing (7) and the lower ball bearing convert the original sliding friction between the upper and lower connecting rings and the connector housing (5) into rolling friction between the balls and the housing, thereby effectively reducing the friction force, allowing the upper and lower connecting rings to rotate freely without mutual interference, thereby isolating the rotation interference of the umbrella surface on the decelerated airdrop type drone.

6. The deceleration device for an airdrop type UAV as claimed in claim 1, characterized in that: The maximum outer diameters of the upper and lower connecting rings are slightly smaller than the inner diameter of the connector housing (5), so that the upper and lower connecting rings can rotate freely inside the connector housing (5).

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