Vertical aircraft takeoff and landing stabilization devices, systems, and methods

Abstract

The present disclosure relates to vertical aircraft takeoff and landing stabilization devices, systems, and methods. With aspects of the present invention, a vertical takeoff and landing vehicle (VTOL) of the type used for point-to-point delivery and transport of payloads (e.g., packages, devices, etc.) and personnel is significantly stabilized, at least during takeoff and landing, thereby significantly improving or significantly eliminating the effects of instability (including ground effect) during VTOL takeoff and / or landing.

Description

Technical Field

[0001] This disclosure generally relates to the field of vertical takeoff and vertical descent aircraft. More specifically, this disclosure relates to improvements in the use of vertical takeoff and vertical descent vehicles near inhabited locations. Background Technology

[0002] The demand for point-to-point delivery of packages, payloads, and personnel has increased the potential need for aircraft used for such delivery and personnel transport. Rotor-driven aircraft (e.g., rotorcraft), including small, unmanned rotorcraft collectively referred to as “unmanned aerial vehicles” (UAVs), are typically vertical takeoff and vertical landing vehicles that generate the lift required for flight by engaging one or more powerful rotors. Such “vertical aircraft” generate significant air turbulence, noise, and safety issues during takeoff and landing, and can otherwise adversely affect structures and personnel located at the ground level, for example, during takeoff and landing. Furthermore, the vehicle itself may be damaged during takeoff and landing due to instability caused by ground-effect turbulence. These and other issues have become obstacles to the large-scale adoption of aircraft for service and personnel transport in residential areas. Unless explicitly stated otherwise, no statement herein is to be acknowledged as prior art simply because it is included in the Technical Field and / or Background Art sections. Summary of the Invention

[0003] Point-to-point transport and delivery of goods and people can be facilitated by using aircraft that do not require large takeoff and landing spaces. Therefore, vertical takeoff and landing vehicles (referred to herein as "vertical takeoff and landing vehicles" (VTOLs)) include rotorcraft that do not require runways or similar structures to achieve the lift needed for takeoff and offer numerous advantages. However, the disadvantages of increasing the adoption of VTOLs (including their commercial use) include increased local noise, rotor ground effect, safety concerns, and the possibility of damage to the VTOL or land-based structures during takeoff and landing. Furthermore, various factors (including gusts) can affect the stability, flight, and performance of VTOLs during takeoff and landing. This method, system, and apparatus address, significantly improve, and / or eliminate the disadvantages of widespread (e.g., commercial) adoption of VTOLs and further promote the increased use of VTOLs, including their widespread adoption in residential areas (including densely populated residential areas).

[0004] According to this aspect, a method for launching and landing a vertical takeoff and landing (VTOL) vehicle is disclosed. The method includes providing a vertical orientation support element having a first end and a second end, the first end being close to a base, extending from the first end to the second end, the second end being located at a selected distance away from the first end, and the vertical orientation support element including a first cooperative stabilizing element positioned close to or integral with the second end. The method further includes: providing a VTOL vehicle including at least one second cooperative stabilizing element sized to engage with a first cooperative stabilizing element; and engaging the first cooperative stabilizing element of the vertical orientation support element with the second cooperative stabilizing element of the VTOL vehicle.

[0005] On the other hand, one approach also includes stabilizing the vertical takeoff and landing vehicle during at least one of takeoff and landing.

[0006] According to another aspect, stabilizing a vertical takeoff and landing vehicle during at least one of takeoff and landing may include horizontal stabilization, angular stabilization, and combinations thereof, which may further include stabilization of air conditions, including, for example, at least one of pitch, yaw, roll, and combinations thereof.

[0007] On the other hand, the method also includes limiting the angular movement of the vertical takeoff and landing vehicle toward and away from the vertical orientation support element during takeoff and landing. The limitation of angular movement can be a horizontal limitation or an angular limitation other than a plane (defined as 0° or 180°).

[0008] On the other hand, the method includes using multiple vertically oriented support elements.

[0009] On the other hand, the base is close to the ground level.

[0010] On the other hand, the first end of the vertically oriented support element is attached to the base.

[0011] On the other hand, the first end of the vertically oriented support element is integrated with the base.

[0012] On the other hand, the method includes using a frame comprising at least one vertically oriented support element.

[0013] On the other hand, the second end of the vertical orientation support element is located at a distance from the first end of the vertical orientation support element, the distance ranging from about 4 feet to about 100 feet.

[0014] On the other hand, the first cooperative stabilizing element includes at least one of the following: a convex attachment portion and a concave attachment portion.

[0015] On the other hand, the second cooperative stabilizing element includes at least one of the following: a convex attachment portion and a concave attachment portion.

[0016] On the other hand, the first cooperative stabilizing element includes a support element configured to extend outward from the vertically oriented support element and configured to engage the second cooperative stabilizing element.

[0017] On the other hand, the second cooperative stabilizing element includes a support element configured to engage the first cooperative stabilizing element.

[0018] On the other hand, the second cooperative stabilizing element is configured to extend outward from the vertical takeoff and landing vehicle structure.

[0019] In addition, the support elements are configured to extend outward from the rotor protection device of the vertical take-off and landing vehicle.

[0020] On the other hand, the support components are integrated with the vertical take-off and landing vehicle.

[0021] On the other hand, the support components are integrated with the vertical take-off and landing rotor protection device.

[0022] On the other hand, vertical takeoff and landing vehicles are rotorcraft.

[0023] On the other hand, the frame is constructed to reside in a fixed position.

[0024] On the other hand, the frame can be moved to multiple locations.

[0025] According to another aspect, a device for stabilizing the launch and landing of a vertical takeoff and landing vehicle is disclosed. According to this aspect, the device includes a vertical orientation support element comprising a first end and a second end. The second end extends from the first end and is located at a selected distance away from the first end. The vertical orientation support element further includes at least one first cooperative stabilizing element positioned close to the second end, and wherein the at least one first cooperative stabilizing element includes at least one of the following: a convex attachment portion and a concave attachment portion.

[0026] According to another aspect of this invention, the term "vertical orientation support element" is defined as a support element comprising an angle, measured at a first end of the vertical orientation support element, relative to a plane established by a substantially horizontal base or relative to a plane established substantially perpendicular to the first end of the vertical orientation support element, and the angle ranges from about 10° to about 90°, preferably from about 30° to about 90°, and more preferably from about 70° to about 90°.

[0027] On the other hand, the second end of the vertical orientation support element is located at a distance from the first end of the vertical orientation support element, the distance ranging from about 4 feet to about 100 feet.

[0028] On the other hand, the second end of the vertical orientation support element is located at a distance from the first end of the vertical orientation support element, the distance ranging from about 1 foot to about 10 feet.

[0029] On the other hand, at least one first cooperative stabilizing element is configured to extend outward from the vertically oriented support element.

[0030] On the other hand, the first cooperative stabilizing element includes a convex attachment portion sized to accommodate a second cooperative stabilizing element, which includes a concave attachment portion.

[0031] On the other hand, the first cooperative stabilizing element includes a concave attachment portion sized to accommodate a second cooperative stabilizing element, which includes a convex attachment portion.

[0032] On the other hand, the convex attachment portion includes a groove located at the second end of the vertical orientation support element, and the groove extends longitudinally from the second end of the vertical orientation support element for a selected distance along the length of the vertical orientation support element.

[0033] On the other hand, the device also includes a guide that communicates with a second end of a vertically oriented support element, and the guide includes at least one first cooperative stabilizing element.

[0034] On the other hand, the device also includes a frame comprising a plurality of vertically oriented support elements spaced apart from each other, the frame including at least one circumferential frame support member, and the at least one circumferential frame support member being in communication with one or more of the plurality of vertically oriented support elements.

[0035] On the other hand, the frame also includes multiple connectors that communicate with one or more of a plurality of vertically oriented support elements.

[0036] On the other hand, at least one of the multiple connectors includes a horizontally oriented connector.

[0037] On the other hand, at least one frame support includes a frame-independent attachment.

[0038] On the other hand, the frame is configured to support at least one of a plurality of vertically oriented support elements.

[0039] On the other hand, the device also includes a base that is configured as a support frame.

[0040] On the other hand, the base is connected to at least one of the multiple vertically oriented support elements.

[0041] On the other hand, the device also includes a guide that is connected to the second end of a plurality of vertically oriented support elements and is also connected to at least one first cooperative stabilizing element.

[0042] On the other hand, the guide also includes an outer surface and an inner surface, the inner surface of which includes at least one directional track (also referred to herein as an inner surface channel), the dimensions of which are designed to accommodate a second cooperative stabilizing element within the inner surface channel, and the inner surface channel is in communication with a first cooperative stabilizing element.

[0043] On the other hand, the device also includes a guide that communicates with the second end of a plurality of vertically oriented support elements, and the guide also includes at least one first cooperative stabilizing element.

[0044] On the other hand, the frame includes at least one panel that communicates with a plurality of vertically oriented support elements, and wherein, for example, the at least one panel may be a door.

[0045] On the other hand, the device also includes a horizontally positioned platform in communication with a vertically oriented support element. The horizontally positioned platform includes a rigid floor comprising a mesh material with a mesh pattern selected to facilitate airflow through the rigid floor. The device also includes a drive mechanism in communication with the horizontally positioned platform for raising and lowering the platform.

[0046] On the other hand, the horizontally positioned platform is connected to at least one of a plurality of vertically oriented support elements.

[0047] In another aspect, an apparatus includes a horizontally positioned platform in communication with at least one of a plurality of vertically oriented support elements. The horizontally positioned platform includes a rigid floor comprising a mesh material, and the mesh material includes a mesh pattern selected to facilitate airflow through the rigid floor. The apparatus also includes a drive mechanism in communication with the horizontally positioned platform, and wherein the drive mechanism is configured to raise and lower the horizontally positioned platform from a first position to a second position.

[0048] On the other hand, the horizontally positioned platform is connected to multiple vertically oriented support elements.

[0049] According to another aspect, a vertical takeoff and landing (VTOL) vehicle is disclosed, comprising a VTOL body housing a motor, at least one rotor connected to the motor, the at least one rotor having a rotor length, and the VTOL vehicle further comprising a rotor guard device sized to have a rotor guard device diameter and a rotor guard device radius, the rotor guard device radius exceeding the rotor length. The VTOL vehicle also includes a support element connected to at least one of the VTOL body and the rotor guard device.

[0050] On the other hand, the vertical take-off and landing vehicle includes a support element that includes a convex attachment portion.

[0051] On the other hand, the vertical take-off and landing vehicle includes a support element that includes a concave attachment portion.

[0052] On the other hand, the rotor protection device is a circumferential rotor protection device.

[0053] In the other case, the isolation element extends outward from at least one of the vertical takeoff and landing vehicle body and the rotor protection device.

[0054] On the other hand, the support components are integrated with the main body of the vertical take-off and landing vehicle.

[0055] On the other hand, the support components are integrated with the rotor protection device of the vertical take-off and landing vehicle.

[0056] On the other hand, vertical takeoff and landing vehicles are rotorcraft.

[0057] The features, functions, and advantages already discussed can be realized independently in each aspect or combined in other aspects, further details of which can be found in the following description and figures. Attached Figure Description

[0058] The variations of this disclosure have been described in such a general manner that reference will now be made to the accompanying drawings, which are not necessarily drawn to scale, and in which:

[0059] Figure 1 This is a perspective view of a vertical takeoff and landing vehicle (VTOL) based on this aspect;

[0060] Figure 2 This is a top view of a VTOL coupled with the currently disclosed device according to this aspect;

[0061] Figure 3A This is a diagram of a VTOL that is coupled to a currently disclosed device according to this aspect;

[0062] Figure 3B This is an illustration of a VTOL engaging with currently disclosed devices during takeoff. Figure 3B An example is also given of a VTOL that detaches from the currently disclosed device during takeoff, according to this aspect;

[0063] Figure 4A The mating arrangement of the first (concave) cooperative stabilizing element and the second (convex) cooperative stabilizing element in the joint structure according to this aspect is shown;

[0064] Figure 4B The diagram illustrates the mating arrangement of a first (concave) cooperative stabilizing element and a second (convex) cooperative stabilizing element in a joint configuration according to this aspect.

[0065] Figure 4C The diagram illustrates the mating arrangement of a first (concave) cooperative stabilizing element and a second (convex) cooperative stabilizing element in a joint configuration according to this aspect.

[0066] Figure 4D The diagram illustrates the mating arrangement of a first (concave) cooperative stabilizing element and a second (convex) cooperative stabilizing element in a joint configuration according to this aspect.

[0067] Figure 4E The diagram illustrates the mating arrangement of a first (concave) cooperative stabilizing element and a second (convex) cooperative stabilizing element in a joint configuration according to this aspect.

[0068] Figure 4F The diagram illustrates the mating arrangement of a first (concave) cooperative stabilizing element and a second (convex) cooperative stabilizing element in a joint configuration according to this aspect.

[0069] Figure 5A A perspective view, either a side view or a top view, of a support that may include a convex cooperative stabilizing element according to this aspect is shown.

[0070] Figure 5BA perspective view, either a side view or a top view, of a support that may include a convex cooperative stabilizing element according to this aspect is shown.

[0071] Figure 5C A perspective view, either a side view or a top view, of a support that may include a convex cooperative stabilizing element according to this aspect is shown.

[0072] Figure 5D A perspective view, either a side view or a top view, of a support that may include a convex cooperative stabilizing element according to this aspect is shown.

[0073] Figure 5E A perspective view, either a side view or a top view, of a support that may include a convex cooperative stabilizing element according to this aspect is shown.

[0074] Figure 5F A perspective view, either a side view or a top view, of a support that may include a convex cooperative stabilizing element according to this aspect is shown.

[0075] Figure 6A The mating arrangement of the first (convex) cooperative stabilizing element and the second (concave) cooperative stabilizing element in the joint structure according to this aspect is shown;

[0076] Figure 6B The diagram illustrates the mating arrangement of a first (convex) cooperative stabilizing element and a second (concave) cooperative stabilizing element in a joint configuration according to this aspect.

[0077] Figure 6C The diagram illustrates the mating arrangement of a first (convex) cooperative stabilizing element and a second (concave) cooperative stabilizing element in a joint configuration according to this aspect.

[0078] Figure 6D The diagram illustrates the mating arrangement of a first (convex) cooperative stabilizing element and a second (concave) cooperative stabilizing element in a joint configuration according to this aspect.

[0079] Figure 6E The diagram illustrates the mating arrangement of a first (convex) cooperative stabilizing element and a second (concave) cooperative stabilizing element in a joint configuration according to this aspect.

[0080] Figure 7A A top view of a bracket including a concave cooperative stabilizing element according to this aspect is shown;

[0081] Figure 7B A top view of a bracket including a concave cooperative stabilizing element according to this aspect is shown;

[0082] Figure 7C A top view of a bracket including a concave cooperative stabilizing element according to this aspect is shown;

[0083] Figure 7D A top view of a bracket including a concave cooperative stabilizing element according to this aspect is shown;

[0084] Figure 7E A top view of a bracket including a concave cooperative stabilizing element according to this aspect is shown;

[0085] Figure 7F A top view of a bracket including a concave cooperative stabilizing element according to this aspect is shown;

[0086] Figure 8A A top view of a bracket including a concave cooperative stabilizing element according to this aspect is shown;

[0087] Figure 8B A top view of a bracket including a concave cooperative stabilizing element according to this aspect is shown;

[0088] Figure 8C A top view of a bracket including a concave cooperative stabilizing element according to this aspect is shown;

[0089] Figure 9A A landing VTOL device close to the currently disclosed device according to this aspect is shown;

[0090] Figure 9B The landing VTOL of the device currently disclosed according to this aspect is shown;

[0091] Figure 9C This shows the results according to this aspect. Figure 9A and Figure 9B Top view of the device shown;

[0092] Figure 10A A landing VTOL device close to the currently disclosed device according to this aspect is shown;

[0093] Figure 10B The landing VTOL of the device currently disclosed according to this aspect is shown;

[0094] Figure 10C This shows the results according to this aspect. Figure 10A and Figure 10B Top view of the device shown;

[0095] Figure 11A The apparatus according to this aspect is shown;

[0096] Figure 11B This shows the results according to this aspect. Figure 11A Top view of the device shown;

[0097] Figure 12A Alternative devices according to this aspect are shown;

[0098] Figure 12B This shows the results according to this aspect. Figure 12A Top view of the device shown;

[0099] Figure 12C This shows the results according to this aspect. Figure 12A Top view of the device shown;

[0100] Figure 13 The apparatus according to this aspect is shown;

[0101] Figure 14A The apparatus according to this aspect is shown;

[0102] Figure 14B This shows the results according to this aspect. Figure 14A Top view of the device shown;

[0103] Figure 14C This shows the results according to this aspect. Figure 14A Top view of the device shown;

[0104] Figure 15A The apparatus according to this aspect is shown;

[0105] Figure 15B This shows the results according to this aspect. Figure 15A Top view of the device shown;

[0106] Figure 16A The apparatus according to this aspect is shown;

[0107] Figure 16B This shows the results according to this aspect. Figure 16A Top view of the device shown;

[0108] Figure 17 This is a flowchart outlining the method according to this aspect;

[0109] Figure 18 This is a flowchart outlining the method according to this aspect;

[0110] Figure 19 This is a flowchart outlining the method according to this aspect; and

[0111] Figure 20 This is a flowchart outlining the method according to this aspect. Detailed Implementation

[0112] This approach overcomes significant drawbacks associated with point-to-point delivery and transport of payloads (e.g., packages, devices, etc.) and personnel using vertical takeoff and landing vehicles (VTOLs), including major issues that arise during VTOL takeoff and landing, such as noise, excessive turbulence caused by ground effect pressure generated by the rotor, vehicle instability, safety issues, ground structure damage, and VTOL damage.

[0113] For example, during typical VTOL landing and takeoff, the directional airflow generated by the VTOL during takeoff and landing creates air turbulence (including air turbulence known as the "ground effect"), which can disrupt stability and otherwise interfere with or complicate VTOL takeoff and landing protocols. For instance, when a VTOL is landing (e.g., descending from an air position to the ground or other solid structures, landing pads, etc., that may be above or below the ground plane), air pressure can be generated by manipulating the rotor in a directional airflow from the rotor, which initially "down" from the VTOL and then "out" and away from it. At a distance above the ground plane, the airflow from the rotor dissipates at least to some extent, and the return airflow from the rotor (which is directed back to the VTOL or otherwise affects it) is deflected little or not at all.

[0114] As the VTOL continues its descent and approaches the ground, the initial airflow pressure generated by the rotor impacts the ground and, as deflecting airflow pressure, is deflected back to the VTOL from the ground in at least an upward direction. In a typical VTOL landing, this airflow deflection gradually increases as the VTOL approaches its landing position (e.g., the ground, landing pad, etc.). Maximum airflow deflection typically occurs at the point when the VTOL is "landing" and impacting its landing position, and this deflection can cause the VTOL to become unstable, resulting in vibrations, flutter, turbulence, etc. Specifically, air turbulence increases because the directional airflow not only deflects vertically back to the VTOL from the ground (e.g., in an upward direction), but it also deflects in a non-vertical direction, which interrupts or "cuts off" the downward airflow from the rotor and causes instability in the VTOL. This, in turn, leads to increased lateral and vertical forces on the VTOL during landing (and takeoff) in other ways (e.g., an increase in forces associated with, for example, pitch, roll, and yaw, and an increase in forces that may otherwise contribute to pitch, roll, and yaw). Such forces can impede and otherwise lead to unpredictable and turbulent VTOL landings, rather than the desired smooth and turbulent VTOL landings (in the absence of such ubiquitous, variable, and potentially destabilizing vertical and lateral forces applied to the VTOL). The combined effects of the airflow generated by the rotor impacting and being deflected from the landing surface (e.g., the ground, landing pad, etc.), and the resulting air turbulence and forces shifting from the downward to the lateral direction, are collectively referred to in this paper as the "ground effect."

[0115] For example, during VTOL takeoff and / or landing, such undesirable forces affecting the VTOL can impede takeoff and / or landing and endanger ground structures, damage the VTOL, and injure ground personnel, as the deflection of airflow direction will have the maximum effect, and this will further destabilize the VTOL, resulting in vibration, flutter, turbulence, etc.

[0116] According to this aspect, the actuating rotating vehicle fixing device that provides the mechanical force required for the vertical lift of the VTOL can be a vertical propulsion unit, which includes, for example, jet engines, propellers, and rotors, wherein the vertical propulsion unit is referred to herein as equivalently and interchangeably as a "rotor." That is, as used herein, the term "rotor" includes propellers, vertical propulsion units, jet engines, and rotors.

[0117] According to this aspect, the apparatus, systems and methods significantly improve or substantially eliminate existing problems involving VTOL (including during VTOL takeoff and landing). Figure 1 The VTOL 20 according to this aspect is shown. The VTOL 20 includes a vehicle body 22, a battery 21 (which may be a rechargeable battery), wherein at least one rotor assembly 23 (in) Figure 1The rotor assembly 23 (shown as four rotor assemblies) is connected to the vehicle body 22. The rotor assembly 23 includes rotors 24 and rotor guards 26 circumferentially oriented to protect the rotors, wherein the radius of the rotor guards exceeds the length of the rotors, preventing the rotors from impacting the rotor guards during operation. When the VTOL uses a propeller, the rotor guards may be referred to as propeller guards, and the diameter of the circumferential propeller guards exceeds the length of the propellers. Figure 1 Also shown is a bracket 28 having a first bracket end 28a, which is attached to or integrated with the rotor protection device 26 and extends outward from the rotor protection device 26. Each bracket 28 also includes a second bracket end 28b, which terminates at a second cooperative stabilizing element 29.

[0118] The second cooperative stabilizing element 29 of the support 28 is configured to be attached to the first cooperative stabilizing element 34 of the vertical orientation support element 32 in the device 30, such as Figure 2 As shown. According to another aspect of this invention, the term "vertical orientation support element" is defined as a support element comprising an angle, measured at a first end of the vertical orientation support element, relative to a plane established by a substantially horizontal base or relative to a plane established substantially perpendicular to the first end of the vertical orientation support element, and the angle ranges from about 10° to about 90°, preferably from about 30° to about 90°, and more preferably from about 70° to about 90°.

[0119] Figure 2 It shows Figure 1 The VTOL 20 shown is a top view (e.g., a "top" view) of the following process, which includes the VTOL 20 being lowered and contacting the device 30 such that the second cooperative stabilizing element 29 of each of the various supports 28 extending from the VTOL 20 engages with the first cooperative stabilizing element 34 (shown as a "slot") of each of the four vertically oriented support elements 32 of the device 30. Figure 2 In the VTOL 20, the second cooperative stabilizing element 29 of the support 28 is shown as a "convex" fixing device, which engages with or is inserted into the first cooperative stabilizing element 34, which houses the vertically oriented support element 32. The remaining components of the VTOL 20 are as follows: Figure 2 As shown, and with Figure 1 The numbering is similar to the one provided in the document.

[0120] According to this aspect, the VTOL may include a bracket 28, which incorporates a second incorporating element 29. The second incorporating element 29 may be a convex fixing device configured to engage with a second mating feature on a vertically oriented support element and to be inserted into the second mating feature on the vertically oriented support element. The second mating feature may include, or be itself, a concave fixing device (which may be configured and sized to engage with the convex fixing device of the first cooperative stabilizing element 29 of the bracket 28 located on the VTOL). One arrangement of this type in… Figure 1 and Figure 2 As shown in the image.

[0121] In other aspects, for example, such as Figure 3A and Figure 3B As shown, the VTOL may include a bracket 28 incorporating a second mating element 49, which may be a concave fixing device configured to receive and engage with a first mating feature on the vertical orientation support element 42. The first mating feature may include, or may be itself, a convex fixing device (e.g., it may be configured and sized to engage with the concave fixing device of the second cooperative stabilizing element 49 of the bracket 28 located on the VTOL).

[0122] Figure 3A A simplified device 41a according to this aspect is shown for facilitating the takeoff (e.g., launch) and landing of a VTOL 40, wherein the VTOL 40 includes a vehicle body 22, wherein the vehicle body 22 has at least one rotor assembly 23 in communication with the vehicle body 22. Figure 3A (As shown in the diagram, there are four rotor assemblies). The only difference is the second cooperative stabilizing element located at the second end of the support. Figure 3A and Figure 3B The VTOL 40 shown also incorporates Figure 1 and Figure 2 The enumerated portion refers to VTOL 20. For example... Figure 1 and Figure 2 As shown, the bracket 28 includes a first bracket end 28a, which is attached to or integral with each rotor protection device 26 and extends outward from each rotor protection device 26. Each bracket 28 also includes a second bracket end 28b, which terminates at a second cooperative stabilizing element 29.

[0123] like Figure 3A and Figure 3B As shown, the second cooperative stabilizing element 49 of the support 28 is configured to be attached to the vertically oriented support element 42 in the device 41a, as... Figure 3AAs shown, the vertical orientation support element 42 has a first end 42a and a second end 42b. The vertical orientation support element 42 appears as a single element. Figure 3A In this context, the individual element may be, for example, a rod anchored to or otherwise connected to a base (not shown), the base (not shown) may be, for example, the ground or a fixing device in contact with the ground 16 at or near the ground plane.

[0124] The term "vertical orientation support element" does not necessarily imply that the pole is perfectly vertical. In some respects, the pole or vertical orientation support element may be at least 45 degrees to the base or ground from which the VTOL lands or takes off at an angle. In some respects, the pole or vertical orientation support element is nearly horizontal (e.g., at about 1 degree to the horizontal plane) and emanates from the side of the building, from which the VTOL can land or take off. In some respects, the vertical orientation support element is curved or otherwise non-linear. Therefore, the term "vertical orientation support element" should be interpreted to include poles or extensions from which the VTOL can be attached or detached from virtually any angle.

[0125] Figure 3B A device 41b according to this aspect for facilitating the takeoff (e.g., launch) and landing of a VTOL 40 is shown, wherein the VTOL 40 includes a vehicle body 22 having a plurality of rotor assemblies 23 in communication with the vehicle body 22. Figure 3A (As shown in the diagram, four rotor assemblies). One of the two second cooperative stabilizing elements 49 (in one of the two supports 28) is configured to be attached to the vertical orientation support element 42 in the device 41b, as... Figure 3B As shown, the vertical orientation support element has a first end 42a and a second end 42b. The vertical orientation support element 42 appears as two separate components. Figure 3B In this context, the two elements may be, for example, two rods anchored to a base (not shown) or otherwise connected to the base, which may be, for example, the ground or a fixing device in contact with the ground 16 at or near the ground plane.

[0126] like Figure 3A and / or Figure 3B As illustrated, during the VTOL descent procedure, as the VTOL 40 approaches the devices 41a, 41b, the second cooperative stabilizing element 49 of the VTOL support 28 engages, for example, the top of the vertically oriented support element 42 of the devices 41a, 41b. The VTOL can then descend, and during its descent to the ground plane, it experiences ground effects, resulting in turbulent energy 43 (from the ground effect)... Figure 3A and Figure 3B (The arrows in the diagram indicate) that the VTOL is transferred to the vertically oriented support element, making the VTOL descent very stable because the ground effect on the VTOL is significantly minimized or eliminated. Although not in... Figure 3A , Figure 3B As shown, however, the vertical orientation support element 42 of devices 41a and 41b can be anchored to the ground 16, or can be attached to or otherwise fixedly connected to the base, which is connected to the ground or to a structure that may be, for example, close to the ground.

[0127] Note that the term "vertical orientation support element" does not necessarily mean that the rod or vertical orientation support element is perfectly vertical. In some aspects, the rod or vertical orientation support element is at least at a 45-degree angle to the base or ground, where the VTOL can land at or take off from the base or ground at an angle. In some aspects, the rod or vertical orientation support element is nearly horizontal (e.g., at about 1 degree to the horizontal plane) and extends from the side of the building, where the VTOL can land or take off from the side of the building or nearly horizontally. In some aspects, the vertical orientation support element is curved or otherwise non-straight (although the vertical orientation support element is generally parallel). Therefore, the term "vertical orientation support element" should be interpreted as including rods or extensions or components that can be attached or detached from the VTOL from virtually any angle to support and / or stabilize the VTOL.

[0128] According to this aspect, the bracket integrated with or attached to the VTOL may include a "convex" or "concave" second cooperative stabilizing element at the end of the second end of the bracket, wherein the selection is made based on whether the selected feature is incorporated into, attached to, or integrated with the vertical orientation support element of the device. That is, the first cooperative stabilizing element on the vertical orientation support element and the second cooperative stabilizing element of the VTOL bracket are selected to be "mate" or interlocked.

[0129] Figures 4A to 4F This is a representative and enlarged top or "top" view of the components 50a, 50b, 50c, 50d, 50e, and 50f of the first and second cooperative stabilizing elements, wherein the varying first cooperative stabilizing elements 52a, 52b, 52c, 52d, 52e, and 52f (respectively in...) Figure 4A , Figure 4B , Figure 4C , Figure 4D , Figure 4E , Figure 4F(As shown) The vertical orientation support elements 54a, 54b, 54c, 54d, 54e, 54f of the VTOL take-off and landing device are integral with or attached to the vertical orientation support elements 54a, 54b, 54c, 54d, 54e, 54f, or otherwise communicated with the vertical orientation support elements 54a, 54b, 54c, 54d, 54e, 54f, and the first cooperative stabilizing elements 52a, 52b, 52c, 52d, 52e, 52f are shown as “concave” fixing devices. Figures 4A to 4F Also shown is a second cooperative stabilizing element engaged with a VTOL bracket 28, which is connected to or integrated with a second cooperative stabilizing element 29 shown as a “convex” fixing device, the “convex” fixing device being sized to engage with “concave” first cooperative stabilizing elements 52a, 52b, 52c, 52d, 52e, 52f of associated and corresponding vertically oriented support elements 54a, 54b, 54c, 54d, 54e, 54f. Figures 4A to 4F The geometry of the fixing devices and elements shown is representative and non-exhaustive, having additional geometry (including, for example, cross-sectional geometry, mating geometry, etc.) for vertically oriented support elements, as well as the first and second cooperative features considered in this aspect.

[0130] More specifically, Figure 4A Component 50a is shown, wherein the VTOL bracket 28 is connected to or integrated with a second cooperative stabilizing element 29, which is shown as a “convex” fixing device, the dimensions of which are designed to engage the “concave” first cooperative stabilizing element 52a of the associated vertical orientation support element 54a. Figure 4B Component 50b is shown, wherein the VTOL bracket 28 is connected to or integrated with a second cooperative stabilizing element 29, which is shown as a “convex” fixing device, the dimensions of which are designed to engage the “concave” first cooperative stabilizing element 52b of the associated vertical orientation support element 54b. Figure 4CComponent 50c is shown, in which the VTOL bracket 28 is connected to or integrated with a second cooperative stabilizing element 29, shown as a "convex" fixing device. This "convex" fixing device is sized to engage a "concave" first cooperative stabilizing element 52c of an associated vertically oriented support element 54c. A spring element 53 is positioned between the "concave" first cooperative stabilizing element 52c and the associated vertically oriented support element 54c and is connected to both. The spring element 53 represents an element capable of flexing, absorbing, and / or dissipating vibrational forces or other forces that may accompany ground-effect turbulence. The spring element can be, for example, an internal compression spring, a shock absorber, a telescopic extender, or combinations thereof.

[0131] Figure 4D The component 50d is shown, wherein the VTOL bracket 28 is connected to or integrated with the second cooperative stabilizing element 29, which is shown as a “convex” fixing device. The “convex” fixing device is sized to engage the associated vertically oriented support element 54d with the “concave” first cooperative stabilizing element 52d, wherein the vertically oriented support element 54d is shown as including an “I” beam construction. Figure 4E The component 50e is shown, in which the VTOL bracket 28 is connected to or integrated with the second cooperative stabilizing element 29, which is shown as a “convex” fixing device, the dimensions of which are designed to engage the “concave” first cooperative stabilizing element 52e of the associated vertical orientation support element 54e. Figure 4F Component 50f is shown, in which the VTOL bracket 28 is in communication with or integrated with a second cooperative stabilizing element 29, which is shown as a “convex” fixing device, the dimensions of which are designed to engage the associated vertically oriented support element 54f with a “concave” first cooperative stabilizing element 52f. The terms “bracket” and “bracket element” are equivalent and interchangeable herein. Furthermore, the terms “first end of bracket” and “first end of bracket element” are equivalent and interchangeable herein. Similarly, the terms “second end of bracket” and “second end of bracket element” are equivalent and interchangeable herein. When a bracket element protrudes from or is otherwise associated with a part of the VTOL structure, the bracket element may be equivalently referred to as a “vehicle bracket element,” “vehicle bracket,” or “VTOL bracket.”

[0132] like Figures 4A to 4FAs shown, the second cooperative stabilizing element 29 can extend longitudinally along the length of the associated vertical orientation support elements 54a, 54b, 54c, 54d, 54e, and 54f. As the VTOL continues to descend during the landing operation, when the second cooperative stabilizing element 29 engages with the first cooperative stabilizing elements 52a, 52b, 52c, 52d, 52e, and 52f—that is, when the second cooperative stabilizing element 29 is connected to or integrated with the vertical orientation support elements 54a, 54b, 54c, 54d, 54e, and 54f—the slotted function of the first cooperative stabilizing elements 52a, 52b, 52c, 52d, 52e, and 52f can serve as a guide to assist the descent of the VTOL down along the length of the vertical orientation support elements 54a, 54b, 54c, 54d, 54e, and 54f to the ground plane during VTOL descent. Furthermore, Figure 4A , Figure 4B , Figure 4C , Figure 4D , Figure 4E and Figure 4F Vertically oriented support elements 54a, 54b, 54c, 54d, 54e, 54f (e.g., rods) are shown that are in direct or integral contact with the first cooperative stabilizing elements 52a, 52b, 52c, 52d, 52e, 52f.

[0133] Figures 5A to 5F The figures are enlarged side, top, or bottom views of a support structure that can be integrated into or otherwise connected to a VTOL structure, and can extend outward from the VTOL structure, such as (and as shown in the figures) rotor guards. The figures are exemplary and non-exhaustive regarding the shape and construction of the support. For example, although... Figure 5A , Figure 5B , Figure 5C , Figure 5D , Figure 5E and Figure 5FThe support shown is substantially linear (e.g., following a single axis along its length), but according to this aspect, the support may deviate angularly from the linear orientation. Alternatively, the second cooperative stabilizing element 29 may comprise a solid object of a different shape. Alternatively, the second cooperative stabilizing element 29 may comprise a circular object (e.g., like a wheel, roller, or bearing) that rotates or rolls within the concave first cooperative stabilizing element of the vertically oriented element. Furthermore, the inner surfaces of the second cooperative stabilizing element 29 and / or the first cooperative stabilizing elements 52a, 52b, 52c, 52d, 52e, 52f may comprise a low-friction coefficient material or material coating (e.g., polytetrafluoroethylene (PTFE)) to facilitate relative movement of the second cooperative stabilizing element 29 along and within the length of the first cooperative stabilizing elements 52a, 52b, 52c, 52d, 52e, 52f.

[0134] Figure 5A A bracket 58a is shown, which includes a second end 28b terminating at a second cooperative stabilizing element 29, the second cooperative stabilizing element 29 having a function for, for example, engaging with... Figures 4A to 4F The concave first cooperative stabilizing element on the vertical orientation element of the type shown engages with a "convex" structure. Figure 5B A bracket 58b is shown, comprising a second end 28b terminating at a second cooperative stabilizing element 29 having a "convex" configuration for engaging a concave first cooperative stabilizing element. The bracket 58b also includes a spring element 57, which can, in this respect, dissipate vibrational forces and other forces, including impacts and contact, that may occur during VTOL landing and takeoff. By dissipating or "absorbing" forces during VTOL takeoff and landing, the addition of the spring element 57 can further stabilize the VTOL during takeoff and landing, thus benefiting the performance of the apparatus, system, and method.

[0135] Figure 5C A bracket 58c is shown, which includes a second end 28b of the bracket terminating at a second cooperative stabilizing element 29 having a “convex” configuration for engaging with a concave first cooperative stabilizing element. The bracket 58c also includes a spring element 57 disposed within a spring housing 56.

[0136] Figure 5DThe bracket 58d is shown, which includes a second end 28b of the bracket terminating at a second cooperative stabilizing element 29 having a “convex” configuration for engaging with a concave first cooperative stabilizing element. The bracket 58d also includes a shock absorber 55, which can, in this respect, dissipate vibrational forces and other forces, including impacts, contact, etc., that may occur during VTOL landing and takeoff.

[0137] Figure 5E A support 58e is shown, comprising a second end 28b terminating at a second cooperative stabilizing element 29 having a “convex” configuration for engagement with a concave first cooperative stabilizing element. The support 58e also includes a telescopic portion 59, which can be adjusted to change the length of the support to customize the VTOL for use with existing landing and takeoff devices that have different sizes and / or (e.g., different distances between vertically oriented support elements to which the VTOL support will engage during takeoff and landing).

[0138] Figure 5F A bracket 58f is shown, comprising a second end 28b terminating at a second cooperative stabilizing element 29 having a “convex” configuration for engagement with a concave first cooperative stabilizing element. The bracket 58f also includes a telescopic portion 59 in communication with a telescopic motor 59a, which can be driven (e.g., remotely, in real-time, when the VTOL is in flight) to change the length or otherwise adjust the bracket to further customize and enhance the versatility and compatibility of the VTOL for use with existing landing and takeoff devices that have different sizes and / or (e.g., different distances between vertically oriented support elements to which the VTOL bracket will engage during takeoff and landing).

[0139] Figures 6A to 6E This is a representative enlarged top view of components 60a, 60b, 60c, 60d, and 60e of the first and second cooperative stabilizing elements, wherein the variations of the first cooperative stabilizing elements 62a, 62b, 62c, 62d, and 62e (respectively in...) Figure 6A , Figure 6B , Figure 6C , Figure 6D , Figure 6E(As shown) The vertical orientation support elements 64a, 64b, 64c, 64d, 64e of the VTOL take-off and landing system are integral with, attached to, or otherwise communicated with the vertical orientation support elements 64a, 64b, 64c, 64d, 64e. The first cooperative stabilizing elements 62a, 62b, 62c, 62d, 62e are shown as a "convex" fixing device. Figures 6A to 6E Also shown is a second cooperative stabilizing element engaged with the VTOL bracket 28, which is connected to or integrated with a second cooperative stabilizing element 69 shown as a “concave” fixing device, the “concave” fixing device being sized to engage with the associated and corresponding vertically oriented support elements 64a, 64b, 64c, 64d, 64e of the “convex” first cooperative stabilizing elements 62a, 62b, 62c, 62d, 62e. Figures 6A to 6E The geometry of the fixing devices and elements shown is representative and non-exhaustive, having additional geometries (including, for example, cross-sectional geometry, mating geometry, etc.) for vertically oriented support elements, as well as the first and second cooperative features considered in this aspect. Note that additional reinforcements (not shown) may be added to increase the ability of the cooperative stabilizing elements to roll or slide between each other, such as ball bearings, wheels, rollers, lubricants, etc.

[0140] More specifically, Figure 6A Component 60a is shown, wherein the VTOL bracket 28 is connected to or integrated with a second cooperative stabilizing element 29, shown as a “concave” fixing device, which is sized to engage the “convex” first cooperative stabilizing element 62a of the associated vertically oriented support element 64a. Figure 6B Component 60b is shown, in which the VTOL bracket 28 is connected to or integrated with a second cooperative stabilizing element 29, shown as a “concave” fixing device, which is sized to engage the “convex” first cooperative stabilizing element 62b of the associated vertically oriented support element 64b. Figure 6CComponent 60c is shown, in which the VTOL bracket 28 is connected to or integrated with a second cooperative stabilizing element 29, shown as a "concave" fixing device, which is sized to engage a "convex" first cooperative stabilizing element 62c of an associated vertical directional support element 64c. A spring element 63 is positioned between the "convex" first cooperative stabilizing element 62c and the associated vertical directional support element 64c and is connected to both. The spring element 63 represents an element capable of absorbing or dissipating vibrational forces or other forces that may accompany ground-effect turbulence, etc. The spring element can be, for example, an internal compression spring, a shock absorber, a telescopic extender, etc., or combinations thereof.

[0141] Figure 6D The component 60d is shown, in which the VTOL bracket 28 is connected to or integrated with a second cooperative stabilizing element 29, shown as a “concave” fixing device, which is sized to engage with the associated vertically oriented support element 64d, which is shown as including an “I” beam construction. Figure 6E The component 60e is shown, in which the VTOL bracket 28 is connected to or integrated with a second cooperative stabilizing element 29, shown as a “concave” fixing device, which is sized to engage the “convex” first cooperative stabilizing element 62e of the associated vertically oriented support element 64e.

[0142] According to this aspect, regarding Figures 6A to 6E The components shown include a first cooperative stabilizing element that extends outward from and is integral with the vertical orientation support element. When the first cooperative stabilizing element of the vertical orientation support element engages with the second cooperative stabilizing element of the VTOL support, during operation and according to this aspect, as the VTOL continues to descend during the descent operation, the slotted function of the second cooperative stabilizing element can serve as a guide to assist the descent process along the length of the vertical orientation support element down to the ground plane during the VTOL's descent.

[0143] As is clear herein, the geometry of the first cooperative stabilizing element of the vertical orientation support element and the second cooperative stabilizing element of the VTOL bracket may include a “convex” or “concave” configuration such that the first and second cooperative stabilizing elements can engage together during ascent (e.g., takeoff) and descent (e.g., landing) from the currently disclosed support device to form a connection orientation and impart VTOL stabilizing characteristics.

[0144] According to this aspect, Figures 7A to 7F It shows the relationship with Figures 5A to 5FEnlarged views of similar supports 58a, 58b, 58c, 58d, 58e, and 58f depicted in the illustration, but with the second cooperative stabilizing element 69 located at the end of the second end 28b of the support, which is now shown as including a "concave" construction of the second cooperative stabilizing element (instead of as...). Figures 5A to 5F The “convex” second cooperative stabilizing element 29 shown is constructed.

[0145] Similar to Figures 5A to 5F According to this aspect, the support 28 is configured to dissipate vibration forces and other forces, including impacts and contact, that may occur during VTOL landing and takeoff.

[0146] According to this aspect, the first and second cooperative stabilizing elements may include actuators and mechanisms to achieve a certain degree of movement within the cooperative stabilizing elements to facilitate engagement of the first and second cooperative stabilizing elements, said movement including real-time movement and movement in response to a signal (e.g., movement of a cooperative stabilizing element with a "concave" configuration to facilitate entry and engagement of a cooperative stabilizing element with a "convex" configuration). For example, Figures 8A to 8C The progress of the second cooperative stabilizing element of the support is shown, for example, during the landing operation of a VTOL.

[0147] like Figure 8A As shown, the support 28 has a second cooperative stabilizing element 69 positioned near the second end 28b of the support, wherein the second cooperative stabilizing element 69 is shown being actuated to an "open" orientation (e.g., anticipated when the VTOL approaches the first cooperative stabilizing element of the vertical orientation support element during landing maneuvers). Figure 8B In the middle, the second cooperative stabilizing element 69 of the support 28 is shown moved to the "partially closed" orientation (with...). Figure 8A (Compared to the "Open" orientation shown).

[0148] Figure 8C A second cooperative stabilizing element 69 is shown in the "closed" orientation of the support 28. According to this aspect, when the VTOL approaches the proposed landing device, a signal is sent to and received by the VTOL (e.g., signals sent to the VTOL include signals remotely sent to the VTOL, signals sent from the VTOL itself to the actuating device, etc.) to actuate the second cooperative stabilizing element of the support to open or expand the "concave" fixing device of the second cooperative stabilizing element, thereby facilitating the engagement of the second cooperative stabilizing element with the first cooperative stabilizing element on the vertically oriented support element of the proposed landing (and takeoff) device. According to this aspect, Figures 8A to 8CThe second cooperative stabilizing element 69 shown may be in the form of an adjustable gripping end, which may also include a motor on the end, or the end may be in communication with mechanical attachments and linkages located on or within the support structure, including, for example, a solenoid that performs "gripping" and is responsible for operating the end to open and / or close to varying and selected degrees. Alternatively, the motor, mechanical linkage, wiring, etc., may be located in the VTOL, wherein the motor located in the VTOL is in communication with the gripping end, etc.

[0149] Figures 9A to 9C A VTOL participating in a landing operation according to this aspect is shown, wherein the VTOL descends and enters the vicinity of the VTOL takeoff and landing stabilization device. (As shown) Figure 9A As shown, as the VTOL 40 approaches the VTOL landing stabilization device 90a, the VTOL is oriented during landing in such a way that the two supports 28 on the VTOL 40 move to a position close to the first cooperative stabilizing element 92 located at the second end 91b of the directional support element 91, thereby placing the second cooperative stabilizing element 69 of the supports 28 in a suitable position to engage with the first cooperative stabilizing element 92 located at the second end 91b of the vertical directional support element 91. Figure 9A Also shown is a circumferential frame support 93a that engages with two vertically oriented support elements 91 near the second ends 91b of the two vertically oriented support elements, and also a circumferential frame support 93b that engages with two vertically oriented support elements 91 near the first ends 91a of the two vertically oriented support elements. Although the engagement can be a direct engagement, Figures 9A to 9C In the diagram, circumferential frames 93a and 93b are shown as independent attachments 95, which in turn engage or otherwise communicate with the first end 91a and the second end 91b of the two vertically oriented support elements. Note that the circumferential frame supports 93a and 93b shown are circular, but the shape of any frame support maintaining the form and / or shape of the VTOL stabilization device is acceptable. Alternatively, the VTOL stabilization device may be directly attached to the ground or some other structure.

[0150] Figure 9B The VTOL take-off and landing device 90b shown in the figure is ( Figure 9A Similar to the VTOL landing device 90a shown in the figure, device 90b shows an additional circumferential frame support 93c located approximately midway between circumferential frame support 93a and circumferential frame support 93b, and device 90b is shown at least for the purpose of implying that any number of circumferential frame supports may be included and present in the device currently considered. Figure 9BAlso shown is a reinforcement 94 that contacts the circumferential frame supports 93a, 93b, 93c and the vertical directional support element 91. Figure 9B The VTOLs shown as "dashed lines" represent VTOLs in the process of landing, while the VTOLs that have completed landing and are located on the ground 16 are shown and drawn as solid lines.

[0151] Figure 9C yes Figure 9B The top view of the VTOL take-off and landing device 90b shown has Figure 9B The numbering features shown. According to this aspect, Figures 9A to 9C The devices 90a and 90b shown can facilitate the landing and takeoff of the VTOL by increasing its stability during takeoff and landing, and by significantly improving and / or eliminating ground-effect turbulence and ground-effect-induced VTOL turbulent rotation. Furthermore, these devices promote the dissipation of recirculating eddies caused by the ground effect, where turbulent energy and effects are transferred from the VTOL to... Figures 9A to 9C Devices of the type shown.

[0152] According to another aspect, Figures 10A to 10C The VTOL involved in the landing operation is depicted, similar to... Figures 9A to 9C As shown, the VTOL 40 descends and approaches the vicinity of the VTOL takeoff and landing stabilization devices 100a, 100b, which have four vertically oriented support elements 91. Figure 10A As shown, VTOL 40 approaches VTOL landing stabilization device 100a, and VTOL 40 is oriented during landing in such a way that the four supports 28 on VTOL 40 are moved to an aligned position near the first cooperative stabilizing element 92 located at the second end 92b of the four vertical orientation support elements 91, and in a relative position between VTOL 40 and device 100a, so that the second cooperative stabilizing element 69 of the supports 28 is placed in a proper position for engaging the second end 91b of the vertical orientation support element 91. Figure 10A Also shown is a circumferential frame support 93a that engages with four vertically oriented support elements 91 near the second end 91b of the four vertically oriented support elements, and also shows a circumferential frame support 93b that engages with four vertically oriented support elements 91 near the first end 91a of the four vertically oriented support elements.

[0153] Figure 10B It shows the relationship with ( Figure 10AThe VTOL landing device 100a shown is similar to the landing device 100b, wherein device 90b shows an additional circumferential frame support 93c, which is located approximately midway between the circumferential frame support 93a and the circumferential frame support 93b, and device 100b is shown at least for the purpose of implying that any number of circumferential frame supports may be included and present in the device currently considered. Figure 10B Additional reinforcements in contact with the circumferential frame supports 93a, 93b, 93c and the vertical directional support element 91 are not shown. Considerations include devices 100a, 100b. Figures 9A to 9C Additional support components of the type shown. Figure 10B The VTOLs shown as "dashed lines" represent VTOLs in the process of landing, while the VTOLs that have completed landing and are located on the ground 16 are shown and drawn as solid lines.

[0154] Figure 10C yes Figure 10B The top view of the VTOL take-off and landing device 100b shown has Figure 10B The numbering features shown. According to this aspect, Figures 10A to 10C The devices 100a and 100b shown can enhance the stability of the VTOL during takeoff and landing, and facilitate the landing and takeoff of the VTOL by significantly improving and / or eliminating ground-effect turbulence and VTOL turbulent rotation caused by the ground effect. Furthermore, these devices promote the dissipation of recirculating eddies caused by the ground effect, wherein turbulent energy and effects are transferred from the VTOL to... Figures 10A to 10C A device of the type shown. Although Figures 10A to 10C Four vertical orientation support elements are shown, and this aspect considers including a selected number of vertical orientation support elements in addition to the four.

[0155] In another aspect of this invention, methods, systems, and apparatuses employing currently disclosed VTOL takeoff and landing devices may include a platform to further enhance the stability of the VTOL participating in landing or takeoff operations. According to this aspect, the platform may include a grid made of a material that may be rigid or tensioned, including a mesh material that may be a rigid mesh material with an average mesh gauge, such that the grid comprises a mesh material selected to be sufficiently robust to support the weight of the VTOL in contact with and supported by the grid.

[0156] Figure 11AThe diagram shows a VTOL 40 that has completed its landing operation onto device 110, with the VTOL positioned appropriately on platform 112. According to this aspect, platform 112 is made of a rigid and / or tensioning material. According to another aspect, the platform is configured to form a platform suitable for supporting the weight of the VTOL 40, wherein the rigid material is configured as a grid or mesh such that airflow from the VTOL 40 passes through the platform at a rate and extent substantially free of ground effects directed from the platform to the VTOL 40, at least during landing, and that the platform does not otherwise negatively impact the stability of the VTOL provided by device 112, at least during landing.

[0157] This aspect considers a platform 112 that can be made of metal, plastic, resin-based composite materials, ceramics, cloth, or combinations thereof. The platform can be made of conductive materials, or can be coated or impregnated with conductive materials or conductive material coatings, etc.

[0158] like Figure 11A As shown, the VTOL 40 includes multiple supports 28 (in Figure 11A The diagram shows four supports 28), and the second cooperative stabilizing elements 29 and 69 are positioned near the end of the second end 91b of the vertical directional support element 91. Figure 11A As further shown, the four second cooperative stabilizing elements 69 associated with the four VTOL supports 28 are engaged with the four first cooperative stabilizing elements 92 that are connected to the four vertically oriented support elements 91. Figure 11A Also shown is a circumferential frame support 93b engaging with four vertically oriented support elements 91, which are located near the first ends 91a of the four vertically oriented support elements and also near the ground 16. Note that the circumferential frame support 93b is shown as circular, but any shape of frame support that maintains the form and / or shape of a vertical take-off and landing stabilization device is acceptable.

[0159] Figure 11B yes Figure 11A The top view of the VTOL take-off and landing device 110 shown is illustrated, where the numbering features are also as follows: Figure 11A As shown and as described herein. According to this aspect, Figure 11A , Figure 11B The device 110 shown can facilitate the landing and takeoff of the VTOL by increasing the stability of the VTOL during takeoff and landing, and by significantly improving and / or eliminating ground effect turbulence, ground effect-induced VTOL turbulent rotation, and this device promotes the dissipation of recirculating eddies caused by the ground effect, wherein turbulent energy and effects are transferred from the VTOL to... Figure 11A , Figure 11B A device of the type shown. Although Figure 11A , Figure 11BFour vertical orientation support elements are shown, and this aspect considers including a selected number of vertical orientation support elements in addition to the four.

[0160] According to other alternative aspects, Figure 12A , Figure 12B and Figure 12C An alternative arrangement of the VTOL takeoff and landing stabilization device 120 is shown, which allows for the absence of a first cooperative stabilizing element at the first end of the vertical orientation support element, and further allows for assistance and facilitation of takeoff and landing of the VTOL without the support extending from the VTOL (e.g., the support extending from the rotor protection device).

[0161] Figure 12A The image shows a VTOL 124 parked on device 120. VTOL 124 includes components similar to... Figures 11A to 11B The elements shown and described herein include, in addition to the device 120 including platform 112, which may be a grid / mesh platform, and platform 112 also includes at least one retainer 122 in communication with platform 112, wherein retainer 122 is configured to releasably engage VTOL structures (e.g., VTOL landing struts, landing skids, landing gear) during VTOL landing, parking and / or takeoff operations. Figure 12A The VTOL that contacts platform 112 is also shown. Figure 12A A vertically oriented support element 91 with a second end 91b is also shown, which can be substantially flush with the upper surface of the platform and does not extend beyond the upper surface of the platform. Furthermore, Figure 12A The following VTOL 124 is shown, which does not include any support structure extending from any rotor protection device and otherwise configured to engage the device 120.

[0162] Figure 12B yes Figure 12A A top or top view of the device 120 shown, wherein VTOL 124 (also) Figure 12C (As shown in the side view) Positioned near platform 112, platform 112 includes retainer 122, which is configured to engage the landing carriage 128 of VTOL 120. Although in Figure 12BNot shown, in this alternative aspect, the retainer may also extend from the VTOL structure (e.g., landing skid, etc.) and be configured to securely and releasably engage the mesh of platform 112. Furthermore, motors, actuators, electronics, signal transmitters and receivers, mechanisms, etc., that impart a degree of movement to one or more retainers 122 may be associated with and / or communicate with device 120, and if one or more retainers (not shown) are integrated with the VTOL, the motors, actuators, electronics, signal transmitters and receivers, mechanisms, etc., may be located on the VTOL to control the movement of the retainers, said movement including releasably engaging such retainers on the VTOL with... Figure 12A , Figure 12B The motion of the platform of the type shown.

[0163] Figure 12C yes Figure 12A The side view of the device 120 is shown, in which the VTOL 124 (also shown in a side view) is positioned near the platform 112, which includes a retainer 122 configured to engage the landing carriage 128 of the VTOL 124. Although in Figure 12C Not shown, in this alternative aspect, the retainer may also extend from the VTOL structure (e.g., landing skid, etc.) and be configured to securely and releasably engage the mesh of platform 112. Furthermore, motors, actuators, electronics, signal transmitters and receivers, mechanisms, etc., that impart a degree of movement to one or more retainers 122 may be associated with and / or communicate with device 120, and if one or more retainers (not shown) are integrated with the VTOL, the motors, actuators, electronics, signal transmitters and receivers, mechanisms, etc., may be located on the VTOL to control the movement of the retainers, said movement including releasably engaging such retainers on the VTOL with... Figure 12A , Figure 12B and Figure 12C The motion of the platform of the type shown.

[0164] According to another aspect, Figure 11A , Figure 11B and / or Figure 12A , Figure 12B and Figure 12C The platform of the type shown may also include mechanical mechanisms to actuate the movement of the platform of the type described herein. For example... Figure 13 As shown, the VTOL take-off and landing device 130 can be combined with at least one Figures 11A to 11B , Figure 12A , Figure 12B , Figure 12CThe apparatus shown may include various aspects, and may also include a platform configured to move or transfer longitudinally along the length of the vertical orientation support element of the VTOL take-off and landing apparatus disclosed herein through various selected vertical positions and orientations. Figure 13 As shown, the VTOL 40, including the support 28 terminated in the second cooperative stabilizing element 69, is shown before takeoff or after landing, such that each of the second cooperative stabilizing elements 69 of the VTOL is engaged with the vertical orientation support element 91. The VTOL 40 is shown parked on a horizontally positioned platform 112, where the ground instability effects (generated by the VTOL rotor during takeoff and / or landing) on ​​the VTOL are significantly improved or substantially eliminated by transferring energy and force from, for example, the ground effect (at least partially) to the stabilizing device 130.

[0165] According to an exemplary takeoff operation, in accordance with this aspect, power (e.g., electricity) from power source 132 can be activated and directed to drive mechanism 134, wherein drive mechanism 134 can (e.g.) Figure 13 The platform 112 (as shown) is located in direct communication with or otherwise integrated with the horizontally positioned platform 112. According to an alternative aspect of this invention, at least a portion of the drive mechanism may be positioned remotely from the drive element positioned in communication with the platform 112, but still in communication with said drive element. When the drive mechanism is activated, the platform 112 can be moved (e.g., lowered, raised, etc.) to a desired height (including the ground plane). The drive mechanism may be positioned remotely from the platform 112 but still in communication with it, wherein the drive mechanism is configured to raise or lower the platform 112 along the length of the device 130 to change the selected height. VTOL 40 may be positioned on the platform 112, wherein a second cooperative stabilizing element 69 on the support 28 engages a vertical orientation support element 91 (e.g., each second cooperative stabilizing element 69 engages one vertical orientation support element 91). If takeoff from a height beyond the ground plane is desired, the platform can be guided to a selected height along the length of the device 130, up to and including a height such that the platform approaches the maximum height of the device, wherein the platform is driven to a height close to the height occupied by the second end 91b of the vertical orientation support element. VTOL can then be activated for takeoff, where VTOL takeoff stability is significantly enhanced because undesirable takeoff ground effects are significantly improved and / or eliminated.

[0166] According to the exemplary VTOL landing protocol, and according to this aspect, when the VTOL is guided to the device 130, power (e.g., electricity) from the power source 132 can be activated and directed to the drive mechanism 134 to raise the platform 112 to a selected height within the device 130 to accommodate the landing VTOL in a stable landing manner, with improved or eliminated ground effects. In a manner similar to the landing protocol described herein, the VTOL is guided to align a second cooperative stabilizing element 69 on the VTOL support 28 with a first cooperative stabilizing element 92, which is positioned integral with or near the vertical orientation support element 91 of the device 130. Once the controlled and stable landing is complete, the VTOL 40 will be safely positioned on the platform 112, at which point, according to the landing protocol, the drive mechanism 134 in the platform 112 can be manually or automatically activated to lower the platform from, for example, a selected platform landing height to a selected height of the platform 112 (which may include, for example, the ground plane).

[0167] According to another aspect, the device disclosed herein may also include a guide that may be attached to, communicate with, or otherwise positioned near the second end 91b of the vertical orientation support element of the device. Figure 14A , Figure 14B , Figure 14C , Figure 15A , Figure 15B , Figure 16A , Figure 16B Exemplary variations of the guide according to this aspect are shown, which can be configured to further stabilize VTOL takeoff and landing and incorporated into the apparatuses, systems, and methods disclosed herein. The guide can be incorporated into any VTOL takeoff and landing apparatus, system, and method currently disclosed.

[0168] like Figure 14A As shown, the VTOL take-off and landing device 140 includes many features present in this device, including, for example Figure 10A The device 100a shown is as follows. Figure 14A As shown, guide 142 is located at the "top" of device 140, wherein the first end 142a of guide 142a is positioned in contact with or otherwise close to the second end 141c of vertical orientation support element, and the first end 142a of guide 142a has a first end diameter (d1) (see...). Figure 14C The diameter (d1) of the first end of the guide member can be substantially equal to the diameter of the circumferential frame support member 93a. The guide member 142 also includes a second end 142b having a second end diameter (d2) (see [reference]). Figure 14C The diameter of the second end of the guide (d2) is larger than the diameter of the first end of the guide (d1). See also Figure 14CA side view of the guide 140 shows that the diameter (d2) of the second end of the guide is larger than the diameter (d1) of the first end of the guide.

[0169] Figure 14B This is a top view of the VTOL takeoff and landing device 140, showing the first end 142a and the second end 142b of the guide, wherein the VTOL 20 is "nested" within the guide 140 and the VTOL 20 participates in the landing or takeoff protocol. Figure 14A and Figure 14B The components shown are labeled as being used for Figure 10A The device 100a in the middle, but Figures 14A to 14C The guide 142 shown herein is to be understood as applicable to many of the devices disclosed herein. When the VTOL take-off and landing device includes a circumferential frame support, for example, a substantially circular circumferential frame support 93a, as... Figure 14A The guide 142 shown may include a first guide end 142a and a second guide end 142b, which are also substantially circular in geometry. In this respect, and as... Figures 14A to 14C As shown, the guide can have an overall geometry of a truncated cone. According to another aspect, the guide geometry can "match" the geometry near the opening located adjacent to the first end 142a of the VTOL takeoff and landing device. For example... Figure 14A , Figure 14B , Figure 14C As shown, the guide 142 has a generally circular geometry, and the device 140 has a generally tubular geometry with a generally circular cross-section. The inner surface 142c of the guide 142 can be fitted with raised or embossed elements, as shown, which are used as... Figure 14A , Figure 14B , Figure 14C The “groove” or guide inner surface channel 142d shown (e.g., a guide inner surface channel configured to form a directional track, etc.) is shown in a conical and “funnel” shape.

[0170] The inner surface channel 142d of the guide can communicate with and be substantially aligned with the first cooperative stabilizing element, and the groove can facilitate the guidance of the VTOL from its position within the guide to the first cooperative stabilizing element by feeding at least one second cooperative stabilizing element of the VTOL from the inner surface channel 142d of the guide to the first cooperative stabilizing element which is in communication with the vertical orientation support element of the VTOL take-off and landing device.

[0171] like Figure 14A , Figure 14B , Figure 14CAs shown, the first cooperative stabilizing element may include grooves or protrusions configured to form a "directional track" or "directional channel" in the inner surface of the guide, such that the dimensions of the directional track can be designed to fit the dimensions of the second cooperative stabilizing element of the bracket. As the second cooperative stabilizing element of the VTOL bracket engages or otherwise contacts the directional track in the inner surface of the guide, the second cooperative stabilizing element (and the VTOL attached to the second cooperative stabilizing element) is guided downward from the guide into the first cooperative stabilizing element, which includes the track or channel.

[0172] According to this aspect, when this device adopts Figure 14A , Figure 14B , Figure 14C When using a guide of the type shown, a landing protocol for VTOLs is more advantageous. In an exemplary landing protocol using the VTOL takeoff and landing device 140, the VTOL 20 can approach an area near the top of the guide 142, and the VTOL can further be substantially centered in flight to hover above the guide. As the VTOL descends into the guide, a second cooperative stabilizing element 29 at the outer end of the support 28 can be associated with and otherwise at least partially inserted into recesses configured to form directional tracks or directional channels that are “feeded” into an internal track along the inner surface of the guide 142. The guide inner surface channel 142d formed by the recesses can be oriented along the guide inner surface 142c of the guide 142, wherein the guide inner surface channel 142d serves as a directional track that communicates with, is substantially aligned with, or is otherwise fed into the vertical directional support element channel 141c on the vertical directional support element 141. Once the second cooperative stabilizing element 29 of the VTOL is inserted into or otherwise oriented to the first cooperative stabilizing element, the VTOL can descend to the ground plane, where the ground disturbance effect that would otherwise occur is significantly improved or substantially eliminated, as the turbulent ground effect force is transferred from the descending VTOL to the device 140.

[0173] Furthermore, the external and / or internal geometry of the VTOL take-off and landing device need not be approximately circular, approximately tubular, approximately cylindrical, etc., as long as the internal longitudinal dimension of the VTOL take-off and landing device can be adapted to the external dimension of the VTOL, and the external dimension of the VTOL is designed for take-off from or landing in a particular VTOL take-off and landing device.

[0174] Although Figure 15A , Figure 15B , Figure 16A , Figure 16BFurther exemplary and non-exhaustive constructions of VTOL take-off and landing devices according to considerations of this aspect are depicted, wherein the overall geometry of the longitudinal “body” or “slide” of the device (e.g., generally rectangular or “square”) is shown to match the geometry of the guide, and it should be understood that, according to this aspect not shown, the geometry of the guide may differ from the geometry of the body or “slide” of the device, as long as the internal longitudinal dimensions of the VTOL take-off and landing device can be dimensionally adapted to the external dimensions of the VTOL, which are designed for take-off from or landing in a particular VTOL take-off and landing device.

[0175] According to another aspect, Figure 15A and Figure 15B A VTOL takeoff and landing device 150 is shown, which includes a guide 152 that can be positioned "on top" of the device 150. A first end 152a of the guide contacts or is otherwise positioned near a second end 151b of a vertically oriented support element, and the first end 152a has a guide first end width (w1) that can be substantially equal to the diameter of the circumferential frame support element. The guide 152 also includes a second end 152b having a guide second end width (w2), wherein the guide second end width (w2) is greater than the guide first end width (w1).

[0176] The inner surface 152c of the guide 152 can be combined with a raised element or an embossed element, which serves as such as Figure 15A , Figure 15B The “groove” or guide inner surface channel 152d shown. The guide inner surface channel 152d can be formed by grooves, recesses, raised relief areas, etc., which can be oriented along the guide inner surface 152c of the guide 152, wherein the guide inner surface channel 152d communicates with, is substantially aligned with, and is otherwise fed into the vertical orientation support element channel 151c on the vertical orientation support element 151.

[0177] Figure 15B This is a top view of the VTOL takeoff and landing device 150, showing the first end 152a and the second end 152b of the guide, in which the VTOL 20 is "nested" within the guide 150 and the VTOL 20 participates in the landing or takeoff protocol. Figure 15A , Figure 15B The guide 152 shown is understood to be applicable to many of the devices disclosed herein.

[0178] According to another aspect, Figure 16A and Figure 16BA VTOL takeoff and landing device 160 is shown, which includes a guide 162 that can be positioned "on top" of the device 160. A first end 162a of the guide is positioned in contact with or otherwise close to a second end 161b of a vertical orientation support element. The first end 162a has a first end dimension that can be substantially equal to the geometry formed by the positions of the plurality of second ends 161b of the vertical orientation support elements, such that the first end 162a is supported by the second ends 161b of the vertical orientation support elements. The guide 162 also includes a second end 162b having a second end width, wherein the second end width is greater than the first end width.

[0179] Figure 16B Is it like this? Figure 16A The diagram shows a top view of the VTOL takeoff and landing device 160, and shows a first end 162a and a second end 162b of the guide, in which the VTOL 20 is "nested" within the guide 160, and in which the VTOL 20 participates in a landing or takeoff protocol. Figure 16A , Figure 16B The guide 162 shown is understood to be applicable to many of the devices disclosed herein.

[0180] Figure 16A , Figure 16B Guide 162 is also shown as comprising guide mesh material 164, which may be a rigid or tensioned mesh material. The guide mesh material can be selected such that, at least during VTOL takeoff and landing, as the VTOL enters the mesh guide, the airflow from the VTOL rotor passes through the guide mesh at a rate and extent with substantially no ground effect directed back from the guide surface toward the VTOL 40, and at least during VTOL takeoff and landing, the guide does not otherwise negatively affect the stability of the VTOL 20 provided by guide 162. According to a further aspect, a highly perforated material can be used as the material for guide 162.

[0181] This aspect considers guides 142, 152, and 162 that can be made of metals, plastics, resin-based composites, ceramics, fabrics, and combinations thereof. The guides can be made of conductive materials, or coated or impregnated with conductive materials, or have conductive material coatings, etc.

[0182] Figure 17 , Figure 18 , Figure 19 and Figure 20 This is a flowchart outlining the methods used in this area.

[0183] like Figure 17The diagram illustrates a method 1000 for launching and landing a vertical takeoff and landing (VTOL) vehicle. The method 1000 includes providing a 1002 vertical orientation support element having a first end and a second end. The first end of the vertical orientation support element is located near a base, and the vertical orientation support element extends from the first end to the second end, the second end being located at a selected distance away from the first end. The vertical orientation support element includes a first cooperative stabilizing element positioned near the second end. The method 1000 further includes providing a 1004 VTOL vehicle including at least one second cooperative stabilizing element, the second cooperative stabilizing element being sized to engage with the first cooperative stabilizing element, and engaging a 1006 first cooperative stabilizing element of the vertical orientation support element with the second cooperative stabilizing element of the VTOL vehicle.

[0184] Figure 18 It includes Figure 17 The flowchart of the elements of the method for launching and landing vertical takeoff and landing vehicles described in the document 1000 Figure 18 Method 1100 also includes stabilizing the vertical takeoff and landing vehicle during at least one of takeoff and landing 1102.

[0185] Figure 19 It includes Figure 17 The flowchart of the elements of the method for launching and landing vertical takeoff and landing vehicles described in the document 1000 Figure 19 The method 1200 shown also includes limiting the angular and / or lateral movement of the vertical takeoff and landing vehicle 1202 toward and away from the vertical orientation support element during takeoff and landing.

[0186] Figure 20 It includes Figure 17 The flowchart illustrates the elements of a method 1000 for launching and landing a vertical takeoff and landing vehicle, wherein method 1300 further includes substantially eliminating the effects of ground effect on the VTOL at least during takeoff and landing, and transferring the energy and force generated by the ground effect to the VTOL takeoff and landing apparatus of this disclosure.

[0187] Of course, the aspects presented may be implemented in ways different from those specifically set forth herein without departing from the essential features of this disclosure. These aspects are to be considered illustrative rather than restrictive in all respects, and all variations in the meaning and scope of the appended claims are intended to be incorporated herein.

Claims

1. A device for stabilizing the launch and landing of a vertical takeoff and landing vehicle, the device comprising: A vertically oriented support element, the vertically oriented support element comprising: The first end of the vertically oriented support element; and A second end of a vertically oriented support element extends from the first end of the vertically oriented support element to the second end of the vertically oriented support element. The second end of the vertically oriented support element is located at a selected distance away from the first end of the vertically oriented support element. The vertically oriented support element includes at least one first cooperative stabilizing element, which is positioned close to the second end of the vertically oriented support element. Wherein, the at least one first cooperative stabilizing element includes at least one of the following: a convex attachment portion and a concave attachment portion, The spring element is positioned between the first cooperative stabilizing element and the vertical orientation support element and is in communication with both the first cooperative stabilizing element and the vertical orientation support element.

2. The apparatus of claim 1, wherein, The second end of the vertical orientation support element is located at a distance from the first end of the vertical orientation support element, the distance ranging from 4 feet to 100 feet.

3. The apparatus of claim 1 or 2, wherein, The first cooperative stabilizing element includes a convex attachment portion, the dimensions of which are designed to accommodate a second cooperative stabilizing element, the second cooperative stabilizing element including a concave attachment portion.

4. The apparatus of claim 1, wherein, The first cooperative stabilizing element includes a concave attachment portion, the size of which is designed to accommodate a second cooperative stabilizing element, the second cooperative stabilizing element including a convex attachment portion.

5. The apparatus of claim 4, wherein, The concave attachment portion includes a groove located at the second end of the vertical orientation support element, the groove extending longitudinally from the second end of the vertical orientation support element along the length of the vertical orientation support element for a selected distance.

6. The apparatus of claim 1, further comprising a guide member in communication with a second end of the vertical orientation support element, the guide member including the at least one first cooperative stabilizing element.

7. The apparatus according to claim 1, further comprising: The framework includes: Multiple vertically oriented support elements, wherein the multiple vertically oriented support elements are spaced apart from each other by a certain distance; At least one circumferential frame support member, the at least one circumferential frame support member being in communication with one or more of the plurality of vertically oriented support elements.

8. The apparatus of claim 7, further comprising a base configured to support the frame.

9. The apparatus according to claim 7, further comprising: The guide is connected to the second end of the vertical orientation support element of the plurality of vertical orientation support elements, and the guide is also connected to the at least one first cooperative stabilizing element.

10. The apparatus of claim 9, wherein, The guide also includes: The inner surface of the guide includes at least one inner surface channel, the dimensions of which are designed to accommodate a second cooperative stabilizing element, the inner surface channel being in communication with the first cooperative stabilizing element.

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