Portable protection and launch device for drones

Abstract

Launching device (10) for an aircraft (50), comprising Receiving devices (20) designed to be able to pick up and release the aircraft, a guidance device (30) designed to specify a takeoff direction (31) during takeoff of the aircraft, and an acceleration device (40) designed to accelerate at least part of the receiving means with the received aircraft during the take-off of the aircraft substantially along the guidance device.

Description

TECHNICAL AREA

[0001] The present invention relates to a launching device for aircraft, in particular for small and ultralight aircraft, drones and UAVs. The device is designed to protect the aircraft and to enable its takeoff. BACKGROUND

[0002] In many applications, it is necessary to deploy aircraft, such as drones, quickly and reliably. However, conventional launch methods are often impractical or unsuitable in obstacle-filled environments or confined spaces. Furthermore, the aircraft are exposed to environmental influences and damage during transport and storage.

[0003] Therefore, there is a need for a launching device that enables the aircraft to be launched under difficult conditions and also provides protection during transport and storage. BRIEF DESCRIPTION OF THE DRAWINGS

[0004] The subject matter of the present invention will be described in more detail below with reference to exemplary drawings. The drawings show examples of advantageous embodiments of the invention.

[0005] They show: Fig. 1 a perspective external view of the launching device according to one embodiment, Fig. 2 a semi-transparent perspective view of embodiments of the system according to the invention, comprising the launching device including receiving means and guidance device; and the aircraft, Fig. 3 an illustration of the acceleration process of the receiving means by the acceleration device essentially along the guide device according to embodiments of the invention, and Fig. 4 An illustration of the process of releasing the aircraft by the receiving means according to embodiments. DETAILED DESCRIPTION

[0006] The invention is based on the objective of providing a launching device for aircraft that enables the aircraft to be launched under difficult conditions and also provides protection during transport, storage and the launch process.

[0007] The present invention solves this problem by means of a launching device (1, 2) for an aircraft (3), comprising receiving means (2b) designed to receive and release the aircraft, a guidance device (2a) designed to specify a launch direction during the launch of the aircraft, and an acceleration device designed to accelerate at least part of the receiving means with the received aircraft substantially along the guidance device during the launch of the aircraft.

[0008] The advantageous embodiments disclosed in the dependent claims can each be implemented individually or in combination with one another and thus constitute expedient further developments of the claimed invention.

[0009] In a preferred embodiment, the receiving means comprise at least two protective means, wherein at least two protective means are movably designed to release the aircraft when required, and are designed to be adjacent to one another in order to receive the aircraft protected from external influences.

[0010] Furthermore, at least two protective devices can be arranged opposite each other in a tapered position and moved into an open position by means of a spreading movement, so that the protective devices are slowed down more by air resistance than the aircraft, and the protective devices and aircraft move away from each other. Additionally, the tapered arrangement causes liquids adhering to the protective devices, such as rain or condensation, to run off, thus increasing the aircraft's protection factor; at the same time, the tapered arrangement provides favorable aerodynamic properties, as flow separation and vortex formation are minimized, thereby reducing air resistance and improving stability during acceleration.

[0011] The receiving device can be designed to be integrated with the guidance device, whereby the connection between the receiving device and the guidance device is released during the acceleration process, so that the receiving device and the aircraft do not unintentionally detach during transport and the take-off process can still be carried out.

[0012] The acceleration device may comprise at least one of the following systems: a spring system, a pneumatic system, an electromagnetic system, and / or a pyrotechnic system. Combinations of these systems are also possible.

[0013] The launching device may also include a fastening device configured to attach the launching device to another structure (e.g., a building or a vehicle).

[0014] The launching device may also include an acceleration control device configured to initiate the acceleration of the receiving means by the acceleration device essentially along the guide device. This allows the acceleration process to be initiated even without physical contact with the launching device.

[0015] The receiving device can include a release control unit configured to receive a release signal or control pulse and, upon receipt, to move at least two protective devices to release the aircraft. The release signal can be generated automatically based on the values ​​of at least one extrinsic parameter or sent by an operator. This allows the release process to be initiated even without physical contact with the launch device.

[0016] The at least one extrinsic parameter can describe one or more of the following quantities: speed of the receiving means, acceleration of the receiving means, height of the receiving means, or time after the start of the acceleration process.

[0017] Furthermore, the receiving equipment and / or the guidance system may include a vibration damping mechanism to protect the aircraft during transport.

[0018] The present invention further comprises a system comprising a launching device and an aircraft designed to be picked up by the receiving means of the launching device and to be released again by the receiving means of the launching device.

[0019] In this system, the aircraft can be picked up by the receiving devices in a folded state and is designed to transition to an unfolded state after being released from the receiving devices.

[0020] Preferred embodiments of the invention are described below with reference to the Fig. 1 to 4 explained. Fig. Figure 1 shows a perspective external view of the launching device (10). The receiving means (20) are visible at the upper end of the launching device (10). In this preferred embodiment, the receiving means (20) are tapered. It can be seen that the receiving means (20) in this embodiment comprise at least two protective means (21, 22). The protective means (21, 22) are adjacent to each other in the closed state and form a tight seal to prevent the ingress of any media (water, dust, dirt).

[0021] Fig. Figure 2 shows a semi-transparent perspective view of the system (100) according to the invention. The system (100) comprises the launching device (10) and the aircraft (50). The launching device (10) comprises receiving means (20) configured to receive and release the aircraft (50), a guidance device (30) designed to specify a launch direction (31) during the launch of the aircraft (50), and an acceleration device (40) designed to accelerate at least a portion of the receiving means (20) with the received aircraft (50) substantially along the guidance device (30) during the launch of the aircraft (50). The acceleration device (40) can be arranged in the launching device (10) below the receiving means (20). This arrangement is supported by most implementations of the acceleration device (40) and results in a purely axial force transmission during the launch process.In another embodiment, the acceleration device (40) can be arranged above the receiving means (20). This creates a tensile load that minimizes the risk of buckling. In yet another embodiment, the acceleration device (40) can be arranged laterally to the receiving means (20). This allows the height of the launching device to be reduced.

[0022] The receiving means (20) can be received by the guide device (30) and can be formed as a single unit, the connection being designed such that the receiving means (20) detach from the guide device (30) during the acceleration process. In a preferred embodiment, the connection between the receiving means (20) and the guide device (30) can be formed by shear pins, a ball detent, or a magnetic connection. In this embodiment, the kinetic energy generated by the acceleration device (40) during the acceleration process is sufficient to release the connection. In a further embodiment, the control pulse can be sent by the acceleration control device and trigger an active separation process between the receiving means (20) and the guide device (30).In this embodiment, the connection can be formed by a locking bolt and the active disconnection process can be formed by an electrical, electromagnetic or pneumatic system which unlocks the locking bolt before or during the acceleration process.

[0023] The receiving means (20) and / or the guiding device (30) may include a vibration damping mechanism to protect the aircraft (50) during transport. The vibration damping may be implemented by rubber dampers, oil or air dampers, friction surfaces, built-in counterweights, active systems with sensors and motors, or similar systems.

[0024] Fig. Figure 3 shows the acceleration process of the receiving means (20) by the acceleration device (40) essentially along the guidance device (30). The guidance device (30) defines a guidance direction (31) by its structure. The acceleration device (40) accelerates the receiving means (20) by means of an acceleration system. The acceleration system can comprise a spring system, a pneumatic system, an electromagnetic system, a pyrotechnic system, or a combination of these systems. Through the acceleration or a separate control impulse, the receiving means (20) are released from the guidance device (30) if both were connected or adjacent, and are accelerated essentially along the guidance device (30). As a result, the receiving means (20) leave the guidance device (30) with the aircraft (50) along the guidance direction (31).

[0025] The starting device (10) can further comprise an acceleration control unit configured to trigger the acceleration of the receiving means (20) by the acceleration device (40) essentially along the guide device (30). The acceleration control unit can receive a start command and initiate the acceleration process by means of a start signal. The start command can be received via a communication interface. The start signal can be released after a preset delay time.

[0026] Fig.Figure 4 shows the release process of the aircraft (50) by the receiving means (20). After the receiving means (20) and the aircraft (50) have left the guidance device (30) along the guidance direction (31), the receiving means (20) can release the aircraft (50). At least two guards (21, 22) of the receiving means (20) are movable to release the aircraft (50). At least two guards (21, 22) can be arranged opposite each other and moved into an open position by means of a spreading movement. As a result, the guards (21, 22) have a larger cross-sectional area in the direction of flight than the aircraft (50). Consequently, they experience greater air resistance and are decelerated more quickly than the aircraft (50) itself. As a result, the guards (21, 22) and the aircraft (50) move away from each other.The aircraft (50) can then initiate its own flight mechanism and the launch procedure is complete.

[0027] The aircraft (50) can be picked up by the receiving means (20) in a folded state and, after partial or complete release from the receiving means (20), transition to an unfolded state, or may already have already transitioned to this state. This enables the aircraft (50) to be picked up compactly by the receiving means (20). This simplifies transport and improves the aerodynamic properties of the receiving means (20) during the launch process.

[0028] Furthermore, the receiving means (20) can include a release control device configured to receive a release signal or control pulse and, upon receipt, to move the at least two guards (21, 22) to release the aircraft (50). The release signal can be generated automatically based on the values ​​of at least one extrinsic parameter or sent by an operator. The at least one extrinsic parameter can be related to or calculated based on one or more of the following quantities: velocity of the receiving means (20), acceleration of the receiving means (20), the takeoff altitude reached by the receiving means (20), or a time after the start of the acceleration process. If the release signal is generated automatically, the operator only needs to initiate the acceleration process to execute the takeoff procedure.The ability to send the release signal manually allows for early or delayed release of the aircraft and, with regard to delayed release, provides a failsafe in case the automated release fails.

Claims

[1] Launching device (10) for an aircraft (50), comprising Receiving devices (20) designed to be able to pick up and release the aircraft, a guidance device (30) designed to specify a takeoff direction (31) during takeoff of the aircraft, and an acceleration device (40) designed to accelerate at least part of the receiving means with the received aircraft during the take-off of the aircraft substantially along the guidance device. [2] Starting device (10) according to claim 1, wherein the receiving means (20) comprise at least two protective means (21, 22), wherein at least two protective means are trained to be mobile in order to release the aircraft (50) when necessary, and are designed to be adjacent to one another in order to protect the aircraft from external influences. [3] Starting device (10) according to one of claims 1-2, wherein the receiving means (20) comprise at least two protective means (21, 22), wherein at least two protective means are arranged opposite each other, preferably tapering to a point, and can be moved into an open position by means of a spreading movement. [4] Starting device (10) according to one of claims 1-3, wherein: the receiving means (20) are designed to be connected to the control device (30), and the connection between the receiving device and the guiding device breaks during the acceleration process. [5] Starting device (10) according to one of claims 1-4, wherein the acceleration device (40) comprises at least one of the following systems: a spring system a pneumatic system, an electromagnetic system and / or a pyrotechnic system. [6] Launching device (10) according to any one of claims 1-5, further comprising a fastening device configured to attach the launching device to another structure. [7] Starting device (10) according to one of claims 1-6, further comprising an acceleration control device configured to trigger the acceleration of the receiving means (20) by the acceleration device (40) substantially along the guide device (30). [8] Starting device (10) according to one of claims 2-3, wherein the receiving means (20) comprise a release control device configured to to receive a release signal or a control pulse, and After receiving, move the at least two protective devices (21, 22) to release the aircraft (50). [9] Starting device (10) according to claim 8, wherein the release signal either automatically based on the values ​​of at least one extrinsic parameter, or is sent by an operator. [10] Starting device (10) according to claim 9, wherein the at least one extrinsic parameter describes one or more of the following quantities: Speed ​​of the recording devices (20), Acceleration of the absorption process, Level of the absorption facilities, or Time after the acceleration process has started. [11] Launching device (10) according to one of claims 1-10, wherein the receiving means (20) and / or the guiding device (30) comprise a vibration damping mechanism to protect the aircraft (50) during transport. [12] System (100), comprising: a starting device (10) according to any one of claims 1 to 11; and an aircraft (50) designed to be picked up by the receiving means (20) of the launching device and to be released again by the receiving means of the launching device. [13] The system according to claim 12, wherein the aircraft (50) is received by the receiving means (20) in a folded state and is configured to transition to an unfolded state after release from the receiving means.

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