A solar-powered UAV rapid release mechanism and release method

Abstract

The present invention proposes a solar drone rapid release mechanism and release method, including a hanger, a support plate, a support column, a suspension rope, a traction rope, a blocking column, a rear wall, etc., which is suitable for the takeoff of an extremely low wing-loaded solar drone. The present invention adopts the principle of swinging, and the solar drone is installed on the support plate through the support column. The support plate is suspended on the hanger, and the support plate is pulled to a certain height by a traction rope and then released. When the support plate reaches the lowest point, the support column is released, and the solar drone obtains sufficient initial velocity to separate from the support plate to achieve takeoff. The solar drone takeoff mechanism and method of the present invention are simple and effective, easy to use, and can be adaptively adjusted according to the weight and size of the drone.

Description

Technical Field

[0001] The invention relates to a solar-powered unmanned aerial vehicle (UAV) rapid flight release mechanism and a flight release method, which are used for the take-off of a low-wing-loaded solar-powered unmanned aerial vehicle (UAV), and belong to the technical field of UAV take-off and landing. Background Art

[0002] High-altitude long-flight solar drones are electric unmanned aerial vehicles that use solar energy as their only energy source and have theoretically unlimited flight time. Limited by the current level of energy technology, high-altitude long-flight solar drones often have very low wing loads, usually around 10kg / m 2 As a result, the equivalent takeoff speed is also very low, usually below 15m / s.

[0003] Most of the existing solar drones at home and abroad adopt autonomous taxiing, vehicle-mounted or hand-throwing takeoff methods. Autonomous taxiing takeoff method needs to rely on runways and landing gear. The landing gear is waste weight and drag most of the time during long-distance flights, affecting the flight performance of the drone. The vehicle-mounted takeoff method has a complex system and requires high control of the vehicle and drone. The hand-throwing takeoff method is only suitable for small solar drones and has a limited scope of application. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and provide a solar-powered UAV rapid launch mechanism and launch method, which can achieve rapid take-off of the solar-powered UAV without relying on a runway, landing gear and launch vehicle.

[0005] The technical solution of the present invention is:

[0006] A solar-powered UAV rapid-flying mechanism comprises: a hanger, a supporting plate, a supporting column, a blocking column, a hanging rope, a traction rope and a rear wall;

[0007] Hanger: It consists of two columns and a beam, installed on the ground;

[0008] Pallet: flat plate structure;

[0009] Support column: installed on the support plate, used to lift and release the drone;

[0010] Stop column: After the pallet reaches the lowest point, it stops the pallet from moving forward. The stop column is installed on the ground.

[0011] Lifting rope: hang the pallet on the hanger;

[0012] Traction rope: traction pallet reaches a certain height;

[0013] Rear wall: Supported by traction ropes for lifting, the rear wall is installed on the ground.

[0014] Furthermore, a support column is installed under the wings and tail of the UAV, a hanging point is set on the UAV, a rope is set on the support column, and the hanging point on the UAV is connected by the rope to fix the UAV. When releasing, the rope is cut and the column is knocked down.

[0015] Furthermore, the support plate is provided with openings to reduce resistance during the descent process; and the stop column is provided with a buffer pad to prevent the support plate from being damaged due to excessive impact when it collides with the stop column.

[0016] Furthermore, the traction rope is pulled by manpower or a vehicle; a groove is provided at a corresponding position on the rear wall through which the traction rope passes, so as to prevent the traction rope from moving left and right; and a scale line showing the height is marked on the rear wall, so as to accurately determine the lifting height.

[0017] Furthermore, a pulley is installed at the groove, and the traction rope is pulled through the pulley.

[0018] Furthermore, the solar drone is installed on the pallet through a support column, the pallet is suspended on the hanger through a suspension rope, and the pallet is pulled up to a certain height using a traction rope and then released. When the pallet reaches the lowest point, the support column is released, and the stop column is used to prevent the pallet from moving forward further. The solar drone obtains sufficient initial velocity to separate from the pallet and take off.

[0019] Furthermore, the present invention also proposes a method for quickly launching a solar-powered UAV, comprising:

[0020] The solar drone is installed on the support plate through the support column, and the support plate is hung on the hanger through the suspension rope;

[0021] The pallet is pulled to a certain height by a pulling device;

[0022] Start the solar drone motor and propellers;

[0023] Disconnect the traction of the traction device and release the pallet;

[0024] The pallet converts gravitational potential energy into kinetic energy to gain forward speed;

[0025] When the pallet reaches the lowest point, the solar drone is released;

[0026] The solar drone detaches from the pallet, and the motor and propeller drive the drone to continue flying forward, completing the take-off process.

[0027] Furthermore, the solar-powered UAV is a low-wing-loading solar-powered UAV.

[0028] Furthermore, the solar-powered UAV is mounted on the support plate at a positive mounting angle, so that the solar-powered UAV flies out at a positive angle of attack when released.

[0029] Furthermore, the pulling of the pallet to a certain height is specifically calculated by the following formula:

[0030] h=Km / (ρSC L )

[0031] Where h is the height difference between the highest and lowest points of the pallet, K is the coefficient correction considering the aerodynamic resistance of the pallet and the solar drone, m is the total takeoff weight of the drone, ρ is the atmospheric density, S is the reference area of ​​the drone, and C L is the design lift coefficient of the UAV in its current posture.

[0032] The beneficial effects of the present invention compared with the prior art are:

[0033] (1) The solar-powered UAV rapid launch mechanism and method proposed in the present invention can realize the rapid take-off of the solar-powered UAV without relying on a runway and landing gear, requires less space, and is more flexible to use.

[0034] (2) The solar-powered UAV rapid launch mechanism proposed in the present invention has a simple structure and is easy and quick to deploy. It can take off in a few seconds and has a higher take-off efficiency without the need for a complex take-off mechanism or system.

[0035] (3) The solar-powered UAV rapid launch mechanism and method proposed in the present invention can be adaptively adjusted according to the weight and size of the UAV.

[0036] (4) The solar-powered UAV rapid launch mechanism and method proposed in the present invention can also be used for the takeoff of other low-speed aircraft.

[0037] (5) The present invention proposes a solar-powered UAV rapid take-off structure and method, which does not require a landing gear on the aircraft, thereby eliminating the adverse effects of the waste weight and waste resistance generated by the landing gear on the long-flight performance of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 This is a schematic diagram of the mechanism for quickly launching a solar-powered UAV;

[0039] Figure 2 This is a schematic diagram of release. DETAILED DESCRIPTION

[0040] The specific embodiments of the present invention are further described in detail below with reference to the accompanying drawings.

[0041] Embodiment 1:

[0042] like Figure 1 As shown, a solar-powered UAV rapid launch mechanism provided by the present invention is suitable for low-speed aircraft with a low take-off speed, and is particularly suitable for solar-powered UAVs with low wing loading.

[0043] It includes a hanger, a supporting plate 3, a supporting column 4, a blocking column 5, a hanging rope 6, a traction rope 7 and a rear wall 8.

[0044] The hanger is composed of two columns 1 and a beam 2, and is installed on the ground;

[0045] The support plate 3 is a flat plate structure;

[0046] Support column 4 supports and releases the drone;

[0047] The stopper 5 stops the support plate 3 from moving forward after the support plate 3 reaches the lowest point and is installed on the ground;

[0048] The lifting rope 6 suspends the support plate 3 on the hanger 2;

[0049] The traction rope 7 pulls the support plate 3 to a certain height;

[0050] The rear wall 8 supports the traction rope 7 for pulling up and is installed on the ground.

[0051] The support column 4 is installed under the wings and tail of the UAV, a hanging point is set on the aircraft, and a rope is set on the support column. The hanging point is connected by the rope to fix the UAV, and the rope is cut off and the column is laid down when released.

[0052] Openings 9 are arranged on the support plate 3 to reduce the resistance during the descent process.

[0053] A buffer pad 10 is mounted on the stop column 5 to prevent the support plate 3 from being damaged due to excessive impact when it hits the stop column 5 .

[0054] The traction rope 7 is pulled by manpower or a vehicle.

[0055] A groove 11 is provided on the rear wall 8 where the traction rope 7 passes, so as to prevent the traction rope 7 from moving left and right.

[0056] The rear wall 8 is marked with scale lines 12 showing the height, so as to accurately determine the pulling height.

[0057] The sizes of the hangers 1 and 2, the support plate 3, the support column 4, the stop column 5, the suspension rope 6, the traction rope 7, the rear wall 8, etc. can be adjusted according to the weight and size of the drone.

[0058] like Figure 2 As shown, the working process of the launching mechanism of the present invention is as follows: the solar-powered UAV is installed on the support plate 3 through the support column 4 by adopting the principle of swinging, the support plate 3 is suspended on the hanger 2 by the suspension rope 6, and the support plate 3 is pulled up to a certain height by the traction rope 7 and then released. When the support plate 3 reaches the lowest point, the support column is released, and the blocking column 5 is used to prevent the support plate 3 from moving forward further, so that the solar-powered UAV obtains a sufficient initial velocity to separate from the support plate 3 and realize take-off.

[0059] Embodiment 2:

[0060] This embodiment also provides a method for quickly launching a solar-powered drone, including:

[0061] The solar drone is installed on the support plate through the support column, and the support plate is hung on the hanger through the suspension rope;

[0062] The pallet is pulled to a certain height by a pulling device;

[0063] Start the solar drone motor and propeller; stabilize the rotation speed to be enough to maintain the drone's take-off, generate forward pulling force for the drone, and make the drone easily detach from the pallet when releasing the drone.

[0064] Disconnect the traction of the traction device and release the pallet;

[0065] The pallet converts gravitational potential energy into kinetic energy to gain forward speed;

[0066] The solar drone is released when the pallet reaches the lowest point; when the pallet reaches the lowest point, the speed is the highest and in the horizontal direction, and the effect of releasing the drone is best at this time.

[0067] The solar drone detaches from the pallet, and the motor and propeller drive the drone to continue flying forward, completing the take-off process.

[0068] Preferably, the solar-powered UAV described in this embodiment is a low-wing-loading solar-powered UAV.

[0069] Preferably, the solar-powered UAV of this embodiment is installed on the support plate at a positive installation angle, so that the solar-powered UAV flies out at a positive angle of attack when released, which can reduce the take-off speed.

[0070] Preferably, in this embodiment, the pallet is pulled to a certain height, which is specifically calculated by the following formula:

[0071] h=Km / (ρSC L )

[0072] Where h is the height difference between the highest and lowest points of the pallet, K is the coefficient correction considering the aerodynamic resistance of the pallet and the solar drone, m is the total takeoff weight of the drone, ρ is the atmospheric density, S is the reference area of ​​the drone, and C L is the design lift coefficient of the UAV in its current posture.

[0073] Embodiment 3:

[0074] The working process of the present invention is further described below with a specific example:

[0075] The wingspan of a solar-powered UAV is 20m, the wing loading is 5kg / m2, the design lift coefficient is 1.0, and the take-off speed at sea level is 8.9m / s. Taking into account the coefficient correction value of the aerodynamic drag of the "swing board" and the solar-powered UAV is 2, and the calculated towing height is 8.2m.

[0076] (1) Install the solar drone on a "swing board" device with a width of about 22m, and the height of the "swing board" above the ground is more than 1m;

[0077] (2) Pull the "swing board" to a height of 8.2m using the traction device;

[0078] (3) Start the solar drone motor and propeller and stabilize the speed to a level sufficient to maintain the drone’s takeoff speed;

[0079] (4) Disconnect the traction device and release the "swing board";

[0080] (5) The "swing board" floats down from a high place, converting gravitational potential energy into kinetic energy to gain forward speed;

[0081] (6) When the "swing board" reaches the lowest point, the solar drone is released, and the speed of the drone is about 8.9 m / s;

[0082] (7) The solar-powered drone detaches from the "swing board", and the motor and propeller drive the drone to continue flying forward, completing takeoff.

[0083] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A solar-powered UAV rapid flight mechanism, characterized in that include: A hanger, a support plate (3), a support column (4), a stop column (5), a lifting rope (6), a traction rope (7) and a rear wall (8); Hanger: It consists of two uprights (1) and a crossbeam (2), and is installed on the ground; Support plate (3): a flat plate structure; Support column (4): installed on the support plate (3), used for supporting and releasing the UAV; A stopper (5) is used to stop the support plate (3) from moving forward after the support plate (3) reaches the lowest point. The stopper (5) is installed on the ground. Suspension rope (6): suspends the support plate (3) on the hanger; Traction rope (7): pulling the support plate (3) to a certain height; Rear wall (8): supports the traction rope (7) for pulling up, and the rear wall (8) is installed on the ground; The support plate (3) is provided with openings to reduce resistance during the descent process; the stop column (5) is provided with a buffer pad to prevent the support plate (3) from being damaged due to excessive impact when it hits the stop column; The traction rope (7) is pulled by manpower or a vehicle; a groove is provided at a corresponding position on the rear wall (8) through which the traction rope (7) passes, so as to prevent the traction rope from moving left and right; a scale line (12) showing the height is marked on the rear wall (8), so as to facilitate accurate determination of the lifting height; The solar drone is installed on the pallet through the support column, and the pallet is suspended on the hanger through the suspension rope. The pallet is pulled up to a certain height by the traction rope and then released. When the pallet reaches the lowest point, the support column is released, and the stop column is used to prevent the pallet from moving forward. The solar drone obtains enough initial velocity to separate from the pallet and take off. The solar-powered UAV is a low-wing-loading solar-powered UAV.

2. The solar-powered UAV rapid flight mechanism according to claim 1 is characterized by: The supporting column (4) is installed under the wings and tail of the UAV, a hanging point is set on the UAV, a rope is set on the supporting column (4), and the hanging point on the UAV is connected by the rope to fix the UAV. When releasing, the rope is cut and the column (1) is laid down.

3. The solar-powered UAV rapid flight mechanism according to claim 1 is characterized by: A pulley is installed at the groove, and the traction rope (7) is pulled through the pulley.

4. A solar-powered UAV rapid flight method implemented by the solar-powered UAV rapid flight mechanism according to any one of claims 1 to 3, characterized in that include: The solar drone is installed on the support plate through the support column, and the support plate is hung on the hanger through the suspension rope; The pallet is pulled to a certain height by a pulling device; Start the solar drone motor and propellers; Disconnect the traction of the traction device and release the pallet; The pallet converts gravitational potential energy into kinetic energy to gain forward speed; When the pallet reaches the lowest point, the solar drone is released; The solar drone detaches from the pallet, and the motor and propeller drive the drone to continue flying forward, completing the take-off process.

5. The solar-powered UAV rapid flight method according to claim 4 is characterized in that: The solar-powered UAV is a low-wing-loading solar-powered UAV.

6. The solar-powered UAV rapid flight method according to claim 5, characterized in that: The solar-powered UAV is mounted on the pallet at a positive mounting angle, so that the solar-powered UAV flies out at a positive angle of attack when released.

7. The solar-powered UAV rapid flight method according to claim 5, characterized in that: The pallet is pulled to a certain height, which is specifically calculated by the following formula: h=Km / (ρSC L ) Where h is the height difference between the highest and lowest points of the pallet, K is the coefficient correction considering the aerodynamic resistance of the pallet and the solar drone, m is the total takeoff weight of the drone, ρ is the atmospheric density, S is the reference area of ​​the drone, and C L is the design lift coefficient of the UAV in its current posture.

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