Device for launching an aerodynamically controlled aircraft

Abstract

Mobile device (100) for launching an aerodynamically controllable aircraft (101) which can be detachably coupled to the mobile device (100) by means of a coupling mechanism (104), wherein the coupling mechanism (104) is designed and configured such that - in the coupled state of aircraft (101) and mobile device (100) a rotational movement of the aircraft (101) relative to the mobile device (100) about a rotational axis (105) oriented parallel to a transverse axis (106) of the aircraft (101) is possible, and - the coupling between the mobile device (100) and the aircraft (101) is automatically released when a rotation angle α about the axis of rotation (105) referenced to a reference rotation angle α0 := 0° exceeds a predetermined maximum rotation angle α maxreached or exceeds, wherein the mobile device (100) comprises a frame structure (102), a receiving unit (103) for receiving the aircraft (101), and the coupling mechanism (104) for releasably coupling the aircraft (101) received in the receiving unit (103) to the mobile device (100), wherein the receiving unit (103) is rotatably connected to the frame structure (102) of the mobile device (100) about the axis of rotation (105).

Description

[0001] The invention relates to a device for launching an aerodynamically controllable aircraft.

[0002] Aerodynamically controlled aircraft typically have fixed or retractable landing gear, which allows the aircraft to roll along a runway during takeoff and landing. However, there are also aerodynamically controlled aircraft (e.g., aerodynamically controlled drones, etc.) that, for various reasons, do not have landing gear, meaning that at least the takeoff process must be implemented differently. Catapults are a well-known method for accelerating such landing gear-less aircraft to a sufficient speed.

[0003] A device for launching an aerodynamically controllable aircraft is known in the prior art from patent application US 2022 / 0340298 A1.

[0004] The object of the invention is to provide a device for launching an aerodynamically controllable aircraft that is easy to implement and reliable in operation.

[0005] The invention is defined by the features of the independent claim. Advantageous further developments and embodiments are the subject of the dependent claims. Further features, applications, and advantages of the invention will become apparent from the following description and the explanation of exemplary embodiments of the invention illustrated in the figures.

[0006] The problem is solved by a mobile device for launching an aerodynamically controllable aircraft, which can be detachably coupled to the mobile device by means of a coupling mechanism, as described below. The aerodynamically controllable aircraft advantageously has one or more wings and advantageously one or more aerodynamically effective control surfaces for steering the aircraft, such as a rudder, an elevator, and / or an aileron.

[0007] The coupling mechanism is designed and configured according to the invention such that, in the coupled state of the aircraft and the mobile device, a rotational movement of the aircraft relative to the mobile device about an axis of rotation oriented parallel to a transverse axis of the aircraft is possible, and the coupling between the mobile device and the aircraft is automatically released when a rotation angle α about the axis of rotation, referenced to a reference rotation angle α0 := 0°, exceeds a predetermined maximum rotation angle α max reached or exceeded. In this context, the term "parallel" is understood to mean essentially "parallel." This includes deviations of up to + / -10°.

[0008] Advantageous is the reference rotation angle α0, the rotation angle of the aircraft around the axis of rotation, which the aircraft exhibits in the rest state of the mobile device and in the coupled state of the aircraft and mobile device.

[0009] The aircraft's transverse axis and rotational axis can be identical.

[0010] Furthermore according to the invention, the mobile device has a preferably rigid frame structure, a receiving unit for mechanically receiving the aircraft, and the coupling mechanism for releasably coupling the aircraft received in the receiving unit with the mobile device, wherein the receiving unit is rotatably connected to the frame structure of the mobile device about the axis of rotation.

[0011] Advantageously, the mobile device is designed and configured such that, when the aircraft and mobile device are coupled, the aircraft's center of gravity is located in a longitudinal axis (in the direction of travel) of the mobile device forward of the axis of rotation. Advantageously, without airflow or with only minimal airflow over the aircraft's wings and aerodynamically active control surfaces, the aircraft's position relative to the mobile device does not change; in particular, advantageously, no rotation of the aircraft about the axis of rotation occurs in these cases. Furthermore, this also advantageously prevents the aircraft from rotating about the axis of rotation during accelerations of the mobile devices during normal operation.

[0012] It is advantageous if both the transverse axis of the aircraft and the axis of rotation are oriented orthogonally to a longitudinal axis of the mobile device (longitudinal axis of the mobile device).

[0013] Particularly preferably, the movement about the axis of rotation, relative to the reference rotation angle α0 := 0°, includes a rotation angle range of 45°, 40°, 35°, 30°, 25°, 20°, 15°, 10°, or 5°, i.e., that a rotational movement about the axis of rotation is possible, for example, in the case of a rotation angle range of 15° from α = 0° to α = 15°, wherein the coupling between the aircraft and the mobile device is automatically released when the maximum rotation angle α max where the respective rotation angle range reaches or exceeds 15°.

[0014] Advantageously, the receiving unit is designed in the form of a rocker, whereby the rocker is rotatably connected to the frame structure around the axis of rotation.

[0015] Particularly preferably, the coupling mechanism comprises a first deflection pulley arranged on the rocker, a second deflection pulley arranged on the frame structure, a mechanically actuated coupling unit arranged on the rocker, and a cable pulley, wherein the cable pulley is connected to the frame structure at its first end and is connected to the coupling unit via the first deflection pulley and the second deflection pulley for actuation of the coupling unit depending on a rotational movement of the rocker about the axis of rotation.

[0016] The mobile device is advantageously designed and set up in such a way that the cable pull is under mechanical pretension, e.g. by means of a mechanical spring.

[0017] The advantage is that the cable pull is detachably and firmly connected to the frame structure.

[0018] The adjustable length of the cable is advantageous.

[0019] The coupling unit is advantageously designed in the style of a mechanically operated glider tow coupling.

[0020] Advantageously, the mobile device is designed and configured in such a way that, in the coupled state, the aircraft is fundamentally connected to the mobile device in such a way that the reference rotation angle α0 := 0° is present, wherein the reference rotation angle α0 := 0° is chosen such that, in the case of a planned longitudinal movement of the mobile device with a corresponding flow over the main lift surfaces (wings) of the aircraft, essentially no aerodynamic lift is generated on the main lift surfaces of the aircraft.

[0021] Advantageously, the mobile device is designed and configured in such a way that, in the event of a planned longitudinal movement of the mobile device with a corresponding flow over the main lift surfaces of the aircraft, a change in the angle of rotation α about the axis of rotation can be generated / initiated by changing the position of an elevator of the aircraft and the aerodynamic moments thereby generated on the aircraft.

[0022] Advantageously, the mobile device is designed and configured in such a way that it can be coupled to a drive unit, e.g., a motor vehicle, to generate the intended longitudinal movement. Advantageously, the mobile device is designed as a trailer for a motor vehicle. Alternatively or additionally, the mobile device is equipped with its own drive unit (a motor including controls, etc.) to generate its intended longitudinal movement.

[0023] The aircraft is advantageously mounted in a coupled state within the mobile device in such a way that even when the mobile device moves at a speed that reaches or exceeds the aircraft's takeoff speed, no significant lift is generated at the main lifting surfaces. The aircraft is advantageously mounted on a rocker that can rotate about its axis of rotation. The pivot point of the axis of rotation is preferably located slightly behind the aircraft's center of gravity, so that horizontal accelerations of the mobile device do not cause it to rotate about its axis. The mobile device is advantageously designed as a trailer that can be towed by a towing vehicle.

[0024] For the takeoff of the aircraft initially coupled to the mobile device, the mobile device is advantageously accelerated to a speed that corresponds at least to the minimum takeoff speed of the aircraft. This speed is advantageously held constant for a certain period. If, at this speed, an aerodynamic control surface of the aircraft that influences the angle of attack, e.g., the elevator of the coupled aircraft, is deflected upwards, a rotational movement of the aircraft about the axis of rotation is initiated, so that a larger angle of attack relative to the oncoming air is established on the main lifting surface(s). This rotational movement causes, provided the angle of rotation about the axis of rotation does not exceed the specified maximum angle of rotation α, maxThis triggers or exceeds the coupling mechanism, thus releasing the aircraft. The specified maximum rotation angle α max is advantageously specified in such a way that it provides an angle of attack of the main lifting surface(s) which, at a given speed of the mobile device, is certainly sufficient for the aircraft to lift off independently from the mobile device.

[0025] Depending on the aircraft, speeds of the mobile device in the range of 5 to 30 m / s are typically sufficient.

[0026] The aircraft can be operated manned or unmanned (UAV).

[0027] The pilot alone (in the aircraft cockpit or at its remote control) decides whether to lift off from the moving mobile device and the liftoff point by deflecting the elevator. This eliminates the need for coordination of the takeoff process, minimizing risks. The release itself is advantageously passive and automated. The coupling mechanism contains no active components or electronic controllers that could cause damage in the event of failure or other malfunction. The takeoff process can therefore be aborted by braking the movement of the mobile device without triggering the coupling mechanism. The release of the coupling mechanism (i.e., the transition from the coupled to the uncoupled state) can be calibrated so that the forces acting on the coupling mechanism are small compared to the flight and control forces, thus barely affecting takeoff and flight characteristics.

[0028] Further advantages, features, and details will become apparent from the following description, in which – possibly with reference to the drawing – at least one embodiment is described in detail. Identical, similar, and / or functionally equivalent parts are marked with the same reference numerals.

[0029] They show: Fig. 1. An embodiment of the mobile device in its entirety Fig. 2 the embodiment of Fig. 1 in a first magnification, Fig. 3 the embodiment of Fig. 1 in a second magnification.

[0030] Fig. Figure 1 shows an embodiment of the mobile device 100 in its entirety, together with an aerodynamically controllable aircraft 101 coupled to it. The aircraft 101 is an ultralight, remotely controlled solar-powered aircraft that can take off and fly at an approach speed of approximately 10 m / s. Due to mass limitations, this solar-powered aircraft has no landing gear, but only landing skids. However, these skids are so small that the propellers of the aircraft 101 can no longer rotate freely when the skids make contact with the ground. The proposed mobile device 100 is easy and reliable to use for such aircraft.

[0031] The mobile device 100 is designed in this case as a vehicle trailer, which can be towed by a car, for example.

[0032] The aircraft 101 has a longitudinal axis 121 and a transverse axis 106. The mobile device 100 has a longitudinal axis 120. The axis of rotation 105 of the coupling mechanism 104 is arranged parallel to the transverse axis 106. Both the axis of rotation 105 and the transverse axis 106 are arranged perpendicular to the longitudinal axis 120 of the mobile device 100. The longitudinal axis 121 of the aircraft 101 and the longitudinal axis 120 of the mobile device 101 are parallel to each other.

[0033] The coupling mechanism 104 is designed and configured in such a way that, in the coupled state of aircraft 101 and mobile device 100, a rotational movement of the aircraft 101 relative to the mobile device 100 about a rotational axis 105 oriented parallel to a transverse axis 106 of the aircraft 101 is possible, and the coupling between the mobile device 100 and the aircraft 101 is automatically released when a rotational angle α about the rotational axis 105, referenced to a reference rotational angle α0 := 0°, exceeds a predetermined maximum rotational angle α max reached or exceeded.

[0034] In this embodiment, lateral outriggers 140 are rigidly arranged on the frame structure 102 to support the wings of the aircraft 101, and the wings rest on these outriggers.

[0035] Fig. 2 shows the embodiment of Fig. Figure 1 shows a first magnification. The mobile device 100 has a frame structure 102 and a receiving unit 103 for the mechanical receiving of the aircraft 101. The receiving unit 103 is designed in the form of a rocker 107, wherein the rocker 107 is rotatably connected to the frame structure 102 about the axis of rotation 105, so that a rotational movement of the aircraft 101 mounted in the receiving unit about the axis of rotation 105 is possible.

[0036] When aircraft 101 and mobile device 100 are coupled, the center of gravity of aircraft 101 is located in a longitudinal axis of the mobile device 100 in front of the axis of rotation 105. This is intended to ensure that, when the mobile unit accelerates, the aircraft does not rotate about the axis of rotation 105.

[0037] Fig. Figure 3 shows the embodiment of Fig. 1 and Fig.2 in a second magnification. It can be clearly seen that the receiving unit 103 is designed in the form of a rocker 107, wherein the rocker 107 is rotatably connected to the frame structure 102 about the axis of rotation 105.

[0038] The coupling mechanism 104 comprises a first deflection pulley 108 arranged on the rocker 107, a second deflection pulley 109 arranged on the frame structure 102, a mechanically actuated coupling unit 110 arranged on the rocker 107 and has a cable pull 111, wherein the cable pull 111 is connected at its first end to the frame structure 102 and is connected via the first deflection pulley 108 and the second deflection pulley 109 to the coupling unit 110 for the actuation of which depending on a rotational movement of the rocker 107 about the axis of rotation 105.

[0039] The coupling mechanism 104 comprises a coupling unit 110, which is designed as a release coupling, i.e., a so-called "nose coupling" from glider construction. The coupling is released by pulling a release lever on the coupling. The release lever is internally spring-loaded and connected to the second end of the cable 111. The nose coupling only releases after the release lever has been pulled, for example, approximately 3 cm.

[0040] The length of the cable pull 111 is advantageously adjustable. This allows the maximum rotation angle α to be adjusted. max A threshold is specified, upon reaching or exceeding which the clutch is triggered.

[0041] Although the invention has been further illustrated and explained in detail by means of preferred embodiments, the invention is not limited by the disclosed examples, and other variations can be derived from them by a person skilled in the art without departing from the scope of protection of the invention. It is therefore clear that a multitude of possible variations exist. It is also clear that the embodiments mentioned as examples are truly only examples and are not to be understood in any way as limiting, for example, the scope of protection, the possible applications, or the configuration of the invention.Rather, the preceding description and the description of the figures enable the person skilled in the art to implement the exemplary embodiments in concrete terms, whereby the person skilled in the art, with knowledge of the disclosed inventive concept, can make various changes, for example with regard to the function or the arrangement of individual elements mentioned in an exemplary embodiment, without leaving the scope of protection defined by the claims and their legal equivalents, such as a further explanation in the description. Reference symbol list 100 mobile devices 101 aerodynamically controllable aircraft 102 Framework structure 103 Recording unit 104 Coupling mechanism 105 axis of rotation 106 Transverse axis of the aircraft 101 107 Seesaw 108 first pulley 109 second pulley 110 coupling unit 111 Pulley 120 Longitudinal axis of the aircraft 101 121 Longitudinal axis of the mobile device 140 lateral outriggers

Claims

[1] Mobile device (100) for launching an aerodynamically controllable aircraft (101) which can be detachably coupled to the mobile device (100) by means of a coupling mechanism (104), wherein the coupling mechanism (104) is designed and configured such that - in the coupled state of aircraft (101) and mobile device (100) a rotational movement of the aircraft (101) relative to the mobile device (100) about a rotational axis (105) oriented parallel to a transverse axis (106) of the aircraft (101) is possible, and - the coupling between the mobile device (100) and the aircraft (101) is automatically released when a rotation angle α about the axis of rotation (105) referenced to a reference rotation angle α0 := 0° exceeds a predetermined maximum rotation angle α maxreached or exceeds, wherein the mobile device (100) comprises a frame structure (102), a receiving unit (103) for receiving the aircraft (101), and the coupling mechanism (104) for releasably coupling the aircraft (101) received in the receiving unit (103) to the mobile device (100), wherein the receiving unit (103) is rotatably connected to the frame structure (102) of the mobile device (100) about the axis of rotation (105). [2] Mobile device (100) according to claim 1, wherein in the coupled state of aircraft (101) and mobile device (100) the center of gravity of the aircraft (101) is arranged in a longitudinal axis of the mobile device (100) in front of the axis of rotation (105). [3] Mobile device (100) according to one of claims 1 or 2, wherein the transverse axis (106) of the aircraft and the axis of rotation (105) are oriented orthogonally to a longitudinal axis (120) of the mobile device (100). [4] Mobile device (100) according to any one of claims 1 to 3, wherein the movement about the axis of rotation (105) with respect to the reference rotation angle α0 := 0° includes a rotation angle range of 45° or 40° or 35° or 30° or 25° or 20° or 15° or 10° or 5°, wherein the coupling between aircraft (101) and mobile device (100) is automatically released when the maximum rotation angle α max the respective rotation angle range is reached or exceeded. [5] Mobile device (100) according to one of claims 1 to 4, wherein the receiving unit (103) is designed in the form of a rocker (107), wherein the rocker (107) is rotatably connected to the frame structure (102) about the axis of rotation (105). [6] Mobile device (100) according to claim 5, wherein the coupling mechanism (104) comprises a first deflection pulley (108) arranged on the rocker (107), a second deflection pulley (109) arranged on the frame structure (102), a mechanically actuated coupling unit (110) arranged on the rocker (107) and a cable pull (111), wherein the cable pull (111) is connected at its first end to the frame structure (102) and is connected via the first deflection pulley (108) and the second deflection pulley (109) to the coupling unit (110) for actuating it depending on a rotational movement of the rocker (107) about the axis of rotation (105). [7] Mobile device (100) according to any one of claims 1 to 6, wherein in the coupled state the aircraft (101) is basically connected to the mobile device (100) such that the reference rotation angle α0 := 0° is present, wherein the reference rotation angle α0 := 0° is selected such that, in the case of a planned longitudinal movement of the mobile device (100) with a corresponding flow onto the main lift surfaces of the aircraft (101), essentially no aerodynamic lift is generated on the main lift surfaces of the aircraft. [8] Mobile device (100) according to one of claims 1 to 7, wherein the mobile device (100) is designed and configured such that, in the case of a planned longitudinal movement of the mobile device (100) with a corresponding flow of air to the main lift surfaces of the aircraft (101), a change in the angle of rotation α about the axis of rotation (105) can be generated by changing the position of an elevator of the aircraft (101) and the aerodynamic moments thereby generated on the aircraft (100). [9] Mobile device (100) according to any one of claims 1 to 8, wherein the mobile device (100) can be coupled to a drive unit, e.g. a motor vehicle, for generating a planned longitudinal movement or is equipped with its own drive unit.

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