A catapult launch device and catapult takeoff method for unmanned aerial vehicles

Abstract

This invention relates to a UAV catapult launch device and catapult takeoff method, solving the technical problem of complex structures in some existing catapult devices. It includes a base; a catapult arm, one end of which is hinged to the base and the other end has a bracket for supporting the UAV, the initial position of the catapult arm being horizontal; an elastic energy storage element connected between the base and the catapult arm, used to store elastic potential energy when the catapult arm rotates backward; a release mechanism disposed between the base and the catapult arm, used to lock the catapult arm in the backward-rotating energy storage position or to unlock it; and a locking device disposed on the bracket, used to releasably fix the UAV to the bracket before catapult launch and automatically unlock it during catapult launch. This invention has a simple and reliable structure, is easy to operate, and is suitable for short-distance, rapid takeoff of small UAVs.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a UAV catapult device and catapult takeoff method. Background Technology

[0002] Small unmanned aerial vehicles (UAVs) with a takeoff weight of 1-3 kg are widely used in military reconnaissance, agricultural plant protection, emergency rescue, and other fields. Among the traditional takeoff methods, runway takeoff requires a long runway and is not suitable for ship decks, mountainous areas, or confined urban spaces; hand-launch takeoff requires high physical fitness from the operator and it is difficult to ensure consistent initial velocity; vertical takeoff and landing UAVs have problems with short endurance and small payload.

[0003] Catapult launch can effectively shorten takeoff distance. Existing catapult methods include: pneumatic catapults, which require a high-pressure air source and are bulky; gunpowder catapults, which are disposable and have poor safety; and motor-driven winch catapults, which require electricity and are complex systems. These solutions either rely on external energy sources or have complex structures, making them inconvenient for rapid deployment in the field. For small drones, there is an urgent need for a catapult device that is simple in structure, manually operable, and can provide sufficient initial velocity. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a catapult device and catapult take-off method for unmanned aerial vehicles, thereby solving the technical problem of complex structure of some existing catapult devices.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows: A drone ejection device, comprising: Base; catapult arm, one end of which is hinged to the base and the other end is equipped with a bracket for carrying the drone. The initial position of the catapult arm is horizontal. An elastic energy storage element is connected between the base and the ejection arm to store elastic potential energy when the ejection arm rotates backward. A release mechanism, located between the base and the ejection arm, is used to lock the ejection arm in the rearward-rotating energy storage position or to unlock it. And a lock located on the bracket, used to releasably secure the drone to the bracket before ejection and automatically unlock it during ejection.

[0006] Furthermore, the elastic energy storage element is a tension spring, with one end fixed to the base near the bracket and the other end fixed to the middle of the ejection arm.

[0007] Furthermore, the release mechanism includes a locking pin slidably mounted on the base and a locking hole mounted on the ejector arm; when the ejector arm rotates backward to the energy storage position, the locking pin aligns with the locking hole, the locking pin is locked when inserted into the locking hole, and the locking pin is released when pulled out.

[0008] Furthermore, a pull cord is provided at the end of the locking pin.

[0009] Furthermore, the locking device includes an electromagnet fixed on the bracket and an armature mounted on the UAV landing gear.

[0010] Furthermore, it also includes a first sensor, a second sensor, and a controller mounted on the base; the first and second sensors are installed at a preset angle offset from each other along the rotation direction of the launch arm; a trigger is fixed on the launch arm; the controller is electrically connected to the electromagnet, the first sensor, and the second sensor respectively; when the launch arm rotates forward and upward, the trigger triggers the second sensor and the first sensor in sequence; the controller determines the direction of movement of the launch arm as forward based on the order in which the second sensor and the first sensor are triggered, and when the first sensor is triggered, the controller controls the electromagnet to de-energize, thereby realizing the automatic release of the UAV; when the launch arm rotates backward, the controller does not output a power-off signal.

[0011] Furthermore, both the first and second sensors are Hall sensors, and the trigger element is a permanent magnet.

[0012] A method for launching an unmanned aerial vehicle (UAV) using a catapult launcher includes the following steps: Step 1: Place the drone on the bracket, energize the electromagnet to attract the armature, and lock the drone in place. Step 2: Manually pull the free end of the catapult arm backward to rotate the catapult arm around the hinge point to the energy storage position. The elastic energy storage element is stretched to store potential energy and locked by the release mechanism. Step 3: Start the drone's power system to bring the propellers or rotors to the predetermined speed; Step 4: Operate the release mechanism to unlock; Step 5: The elastic energy storage element releases the stored elastic potential energy, driving the catapult arm to rotate forward rapidly; Step 6: During the forward rotation of the launch arm, the trigger sequentially triggers the second and first sensors. The controller determines that the movement is forward based on the triggering sequence. When the launch arm rises forward to the preset angle and the first sensor is triggered, the controller controls the electromagnet to de-energize, the drone automatically unlocks, and obtains an initial upward velocity to fly off the bracket.

[0013] Compared with the prior art, the present invention has the following beneficial effects: This invention uses a tension spring as an elastic energy storage element. The operator can manually pull the catapult arm backward to complete the energy storage. It does not rely on a gas source, gunpowder or external power. The structure is simple and suitable for rapid deployment in the field.

[0014] The present invention allows for manual insertion of the locking pin into the locking hole when the ejector arm rotates to its position. The tail of the locking pin is equipped with a pull rope, which can be pulled to unlock the device. The operation is simple and reliable.

[0015] This invention uses an electromagnet to attract and lock an armature to a drone when energized. The controller automatically cuts off the power and releases the drone when it detects that the launch arm has reached a preset angle, without the need for manual intervention, and the release timing is precise.

[0016] This invention starts the UAV's power system before launching, and the propeller has reached the predetermined speed when the UAV leaves the launcher. It has its own thrust while obtaining the initial launch velocity, and the takeoff is stable. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the ejection device of the present invention when it is locked.

[0018] Figure 2 This is a schematic diagram of the initial state of the catapult device of the present invention.

[0019] Figure 3 This is a block diagram of the electrical equipment connection of the present invention.

[0020] The names corresponding to the reference numerals in the attached figures are as follows: 1-Base, 2-Ejection arm, 3-Bracket, 4-Tension spring, 5-Locking pin, 6-Locking hole, 7-Electromagnet, 8-Armature, 9-First sensor, 10-Second sensor, 11-Controller, 12-Trigger, 13-Pull rope. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are merely some embodiments of this invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0022] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0023] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; of course, they can also refer to a mechanical connection or an electrical connection; furthermore, they can refer to a direct connection, an indirect connection through an intermediate medium, or a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0024] like Figures 1-3 As shown, the present invention provides a drone catapult device, comprising: Base 1; catapult arm 2, one end of which is hinged to base 1, and the other end is provided with a bracket 3 for carrying the drone. The initial position of the catapult arm is horizontal. An elastic energy storage element is connected between the base 1 and the ejection arm 2, and is used to store elastic potential energy when the ejection arm 2 rotates backward. A release mechanism is provided between the base 1 and the ejection arm 2, used to lock the ejection arm 2 in the rearward rotating energy storage position or to unlock it. And a lock located on bracket 3, used to releasably secure the drone to the bracket before ejection and automatically unlock it during ejection.

[0025] Working principle: In the initial state, the catapult arm 2 is in a horizontal position, the drone is placed on the bracket 3, and the locker locks the drone; the operator manually pulls the free end of the catapult arm backward to the energy storage position, the elastic energy storage element stores elastic potential energy, and the release mechanism locks the catapult arm in the energy storage position; during takeoff, the operator releases the lock on the catapult arm through the release mechanism, the elastic energy storage element releases potential energy to drive the catapult arm to rotate forward quickly, when the catapult arm rises forward to the preset angle, the locker automatically unlocks, and the drone flies out.

[0026] In some embodiments, the elastic energy storage element is a tension spring 4, one end of which is fixed to the base 1 near the bracket 3, and the other end is fixed to the middle of the catapult arm 2. Compared with pneumatic catapults (requiring a high-pressure air source), gunpowder catapults (disposable and dangerous), or motor winches (requiring a power source), tension springs have a simple structure, low cost, are reusable, do not require external energy, and by reasonably selecting the spring stiffness (e.g., 3~8N / mm), the maximum tension can be controlled within a range that is within human reach (200~300N), making them suitable for manual rapid energy storage of small drones.

[0027] In some embodiments, the release mechanism includes a locking pin 5 slidably mounted on the base 1 and a locking hole 6 on the ejector arm 2. When the ejector arm 2 rotates backward to the energy storage position, the locking pin aligns with the locking hole. Inserting the locking pin into the locking hole locks the ejector arm, and pulling out the locking pin releases it. This achieves mechanical locking of the ejector arm in the energy storage position, preventing accidental rebound during energy storage. Pulling out the locking pin instantly releases the lock and triggers ejection.

[0028] In some embodiments, the locking pin 5 is equipped with a pull rope 13 at its tail. This allows the operator to pull the locking pin from a distance by pulling the rope, achieving remote unlocking. Compared to solutions that require directly inserting or removing the locking pin by hand or using a wrench, the pull rope allows the operator to maintain a safe distance, especially after the UAV's power is started, avoiding accidental injury from the ejection arm or propeller, thus improving operational safety. Furthermore, the pull rope can be flexibly arranged to adapt to the layout of different launch platforms.

[0029] In some embodiments, the locking device includes an electromagnet 7 fixed on the bracket 3 and an armature 8 mounted on the UAV landing gear.

[0030] It also includes a first sensor 9 and a second sensor 10 mounted on the base 1, and a controller 11; the first sensor 9 and the second sensor 10 are installed at a preset angle offset from the rotation direction of the ejection arm 2; a trigger 12 is fixed on the ejection arm 2; the controller 11 is electrically connected to the electromagnet 7, the first sensor 9, and the second sensor 10 respectively; when the ejection arm rotates forward and upward, the trigger 12 triggers the second sensor 10 and the first sensor 9 in sequence; the controller 11 determines the movement direction of the ejection arm 2 as forward based on the triggering order of the second sensor 10 and the first sensor 9, and when the first sensor 9 is triggered, the controller 11 controls the electromagnet 7 to de-energize, realizing the automatic release of the drone; when the ejection arm 2 rotates backward, the controller 11 does not output a power-off signal. By using dual sensors and the triggering order to determine whether the movement direction of the ejection arm is forward or backward, the power is de-energized and the drone is released only when it rotates forward and upward to the preset angle, avoiding accidental release during the backward energy storage process.

[0031] In some embodiments, both the first sensor 9 and the second sensor 10 are Hall effect sensors, and the trigger 12 is a permanent magnet. Non-contact position detection is achieved using the Hall effect; the permanent magnet moves with the launch arm, triggering the Hall effect sensor to output a switching signal. Compared to mechanical contact microswitches, Hall effect sensors have no physical contact, no wear, fast response, and long lifespan, and the permanent magnet does not require power, making them suitable for detecting high-speed launch arms. Compared to photoelectric sensors, Hall effect sensors are less sensitive to dust and oil, making them more suitable for drone launch operations in outdoor or harsh environments.

[0032] A method for launching an unmanned aerial vehicle (UAV) using a catapult launcher includes the following steps: Step 1: Place the drone on the bracket, energize the electromagnet to attract the armature, and lock the drone in place. Step 2: Manually pull the free end of the catapult arm backward to rotate the catapult arm around the hinge point to the energy storage position. The elastic energy storage element is stretched to store potential energy and locked by the release mechanism. Step 3: Start the drone's power system to bring the propellers or rotors to the predetermined speed; Step 4: Operate the release mechanism to unlock; Step 5: The elastic energy storage element releases the stored elastic potential energy, driving the catapult arm to rotate forward rapidly; Step 6: During the forward rotation of the launch arm, the trigger sequentially triggers the second and first sensors. The controller determines that the movement is forward based on the triggering sequence. When the launch arm rises forward to the preset angle and the first sensor is triggered, the controller controls the electromagnet to de-energize, the drone automatically unlocks, and obtains an initial upward velocity to fly off the bracket.

[0033] In this invention, the preferred controller model is STM32F103C8T6.

[0034] In this invention, the ejection arm 2 is an aluminum alloy hollow tube with a length of 0.8~1.0m.

[0035] The electromagnet, first sensor, second sensor, and controller used in this invention are all existing known electrical devices, and all can be purchased and used directly on the market. Their structure, circuit, and control principle are all existing known technologies. Therefore, the structure, circuit, and control principle of the electromagnet, first sensor, second sensor, and controller will not be described in detail here.

[0036] Finally, it should be noted that the above embodiments are merely preferred embodiments of the present invention used to illustrate the technical solutions of the present invention, and are not intended to limit the invention, nor are they intended to limit the patent scope of the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention. That is to say, any changes or refinements made to the main design concept and spirit of the present invention that are not of substantial significance, but whose technical problems are still consistent with the present invention, should be included within the protection scope of the present invention. In addition, the direct or indirect application of the technical solutions of the present invention to other related technical fields are similarly included within the patent protection scope of the present invention.

Claims

1. A catapult launcher for unmanned aerial vehicles (UAVs), characterized in that, include: Base (1); catapult arm (2), one end of which is hinged to the base (1), and the other end is provided with a bracket (3) for carrying the drone. The initial position of the catapult arm is horizontal. An elastic energy storage element is connected between the base (1) and the ejection arm (2) to store elastic potential energy when the ejection arm (2) rotates backward. Release mechanism, located between base (1) and ejection arm (2), is used to lock ejection arm (2) in the rearward rotating energy storage position or to unlock it; And a lock located on the bracket (3) for releasably securing the drone to the bracket before ejection and automatically unlocking it during ejection.

2. The UAV catapult device according to claim 1, characterized in that, The elastic energy storage element is a tension spring (4), one end of which is fixed on the base (1) near the bracket (3), and the other end is fixed in the middle of the ejection arm (2).

3. The UAV catapult device according to claim 1, characterized in that, The release mechanism includes a locking pin (5) slidably mounted on the base (1) and a locking hole (6) mounted on the ejector arm (2); when the ejector arm (2) rotates backward to the energy storage position, the locking pin and the locking hole are aligned, the locking pin is inserted into the locking hole to lock, and the locking pin is pulled out to release.

4. The UAV catapult device according to claim 1, characterized in that, The locking pin (5) has a pull rope (13) at the end.

5. The UAV catapult device according to claim 1, characterized in that, The locking device includes an electromagnet (7) fixed on the bracket (3) and an armature (8) on the UAV landing gear.

6. The UAV catapult device according to claim 5, characterized in that, It also includes a first sensor (9) and a second sensor (10) set on the base (1), and a controller (11); the first sensor (9) and the second sensor (10) are installed at a preset angle offset from the rotation direction of the catapult arm (2); a trigger (12) is fixed on the catapult arm (2); the controller (11) is electrically connected to the electromagnet (7), the first sensor (9) and the second sensor (10) respectively; when the catapult arm rotates forward and upward, the trigger (12) triggers the second sensor (10) and the first sensor (9) in sequence; the controller (11) determines the movement direction of the catapult arm (2) as forward according to the order in which the second sensor (10) and the first sensor (9) are triggered, and when the first sensor (9) is triggered, the controller (11) controls the electromagnet (7) to be de-energized, so as to realize the automatic release of the UAV; when the catapult arm (2) rotates backward, the controller (11) does not output a power-off signal.

7. The UAV catapult device according to claim 6, characterized in that, Both the first sensor (9) and the second sensor (10) are Hall sensors, and the trigger (12) is a permanent magnet.

8. A catapult launch method for an unmanned aerial vehicle (UAV) according to any one of claims 1-7, characterized in that, Includes the following steps: Step 1: Place the drone on the bracket, energize the electromagnet to attract the armature, and lock the drone in place. Step 2: Manually pull the free end of the catapult arm backward to rotate the catapult arm around the hinge point to the energy storage position. The elastic energy storage element is stretched to store potential energy and locked by the release mechanism. Step 3: Start the drone's power system to bring the propellers or rotors to the predetermined speed; Step 4: Operate the release mechanism to unlock; Step 5: The elastic energy storage element releases the stored elastic potential energy, driving the catapult arm to rotate forward rapidly; Step 6: During the forward rotation of the launch arm, the trigger sequentially triggers the second and first sensors. The controller determines that the movement is forward based on the triggering sequence. When the launch arm rises forward to the preset angle and the first sensor is triggered, the controller controls the electromagnet to de-energize, the drone automatically unlocks, and obtains an initial upward velocity to fly off the bracket.

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