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 various aspects of the present invention, a type of vertical takeoff and landing vehicle (VTOL) for point-to-point transport and delivery 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) include small, unmanned rotorcraft collectively referred to as "unmanned aerial vehicles" (UAVs), typically vertical takeoff and vertical descent vehicles, which 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 at 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. The methods, systems, and apparatus of this invention 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 an aspect of the invention, 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 adjacent 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, the vertical orientation support element including a first cooperative stabilizing element positioned adjacent to or integral with the second end, and a housing sized to substantially surround the at least one vertical takeoff and landing (VTOL) element. The method further includes: providing a VTOL vehicle including at least one second cooperative stabilizing element sized to engage with the first cooperative stabilizing element; and engaging the first cooperative stabilizing element of the vertical takeoff and landing 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 can include horizontal stabilization, angular stabilization, and combinations thereof, and can also 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 housing is directly connected to the vertically oriented support element.

[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 first end of the vertically oriented support element is attached to the base.

[0013] On the other hand, the method includes using a frame comprising at least one vertically oriented support element.

[0014] On the other hand, the second end of the vertically oriented support element is located at a distance from the first end, the distance ranging from about 4 feet to about 100 feet.

[0015] 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.

[0016] 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.

[0017] 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.

[0018] On the other hand, the second cooperative stabilizing element includes a support element configured to engage the first cooperative stabilizing element.

[0019] On the other hand, the second cooperative stabilizing element is configured to extend outward from the vertical takeoff and landing vehicle structure.

[0020] In addition, the support elements are configured to extend outward from the rotor protection device of the vertical take-off and landing vehicle.

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

[0022] On the other hand, the support components are integrated with the vertical take-off and landing rotor protection device.

[0023] On the other hand, vertical takeoff and landing vehicles are rotorcraft.

[0024] On the other hand, the frame is constructed to reside in a fixed position.

[0025] On the other hand, the frame can be moved to multiple locations.

[0026] On the other hand, the method also includes stabilizing the vertical takeoff and landing vehicle during at least one takeoff and landing.

[0027] On the other hand, the housing is directly connected to the vertically oriented support element.

[0028] In other respects, the housing includes at least one movable plate.

[0029] On the other hand, the housing includes at least one movable plate, which is configured to open and close.

[0030] On the other hand, at least one movable plate is located near the base.

[0031] On the other hand, at least one movable plate is located near the first end of the vertically oriented support element.

[0032] According to another aspect of the invention, a method for reducing air turbulence during the descent of a vertical takeoff and landing (VTOL) vehicle landing device is disclosed. The method includes providing a VTOL device that is at least partially enclosed. According to the method, the device includes at least one vertical orientation support element having a first end and a second end, the first end being positioned near a base and extending from the first end to the second end. The vertical orientation support element includes a first cooperative stabilizing element extending from the second end to the first end. The device also includes a housing sized substantially around the at least one vertical orientation support element, the housing including at least one movable housing plate positioned near or integral with the first end of the vertical takeoff and landing element. The method further includes lowering a VTOL vehicle into the VTOL landing device, the VTOL vehicle including at least one second cooperative stabilizing element sized to engage with the first cooperative stabilizing element. The method further includes: engaging a second cooperative stabilizing element of the vertical take-off and landing vehicle with a first cooperative stabilizing element of the vertical orientation support element; lowering the vertical take-off and landing vehicle within the at least partially enclosed vertical take-off and landing device from a second end of the vertical orientation support element to a first end of the vertical orientation support element; and opening at least one movable plate during the descent of the vertical take-off and landing vehicle to eliminate air turbulence within the housing.

[0033] In another aspect, the method further includes: detecting air pressure at least in a region of the housing; actuating at least one movable plate in response to the pressure detected by the detector; and opening at least one movable plate during descent of the vertical take-off and landing vehicle to eliminate air turbulence within the housing.

[0034] According to another aspect, a device for stabilizing the takeoff and landing of a vertical takeoff and landing vehicle is disclosed. According to an aspect of the invention, 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 device further includes at least one first cooperative stabilizing element positioned close to the second end. The device also includes a housing sized substantially around the at least one vertical orientation 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.

[0035] On the other hand, the second end is located at a distance from the first end, the distance ranging from about 4 feet to about 100 feet.

[0036] 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.

[0037] On the other hand, at least one first cooperative stabilizing element is configured to extend outward from the vertically oriented support element.

[0038] On the other hand, the first cooperative stabilizing element includes a convex attachment portion that is sized to accommodate a second cooperative stabilizing element that includes a concave attachment portion.

[0039] On the other hand, the first cooperative stabilizing element includes a concave attachment portion that is sized to accommodate a second cooperative stabilizing element that includes a convex attachment portion.

[0040] On the other hand, the concave 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.

[0041] On the other hand, the device also includes a guide that communicates with a vertically oriented support element and includes at least one first cooperative stabilizing element.

[0042] On the other hand, the device also includes a housing comprising a frame positioned close to the housing, a plurality of vertically oriented support elements spaced apart from each other, the frame also including at least one circumferential frame support communicating with one or more of the plurality of vertically oriented support elements, and wherein the dimensions of the housing are designed to substantially surround the plurality of vertically oriented support elements and the dimensions of the housing are designed to substantially surround the frame.

[0043] On the other hand, the device includes multiple horizontally oriented connectors.

[0044] On the other hand, at least one of the circumferential frame supports includes a horizontally oriented connector.

[0045] In another aspect, the frame is configured to support at least one of a plurality of vertically oriented support elements.

[0046] On the other hand, the device also includes a base that is configured as a support frame.

[0047] On the other hand, the base is connected to at least one of a plurality of vertically oriented support elements.

[0048] On the other hand, the housing includes at least one movable housing plate, wherein the at least one movable housing plate is positioned near the first end of the vertically oriented support element.

[0049] On the other hand, the device also includes at least one of a detector for detecting pressure at least in a local area of ​​the housing, a controller in communication with the detector, an actuator and a drive mechanism in communication with the controller, and a drive mechanism in communication with at least one movable housing plate.

[0050] 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 is also communicated with at least one first cooperative stabilizing element.

[0051] 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, which is equivalently referred to herein as a “guide inner surface channel”. The guide inner surface channel is sized to accommodate a second cooperative stabilizing element within the directional track, and the guide inner surface channel is in communication with the first cooperative stabilizing element.

[0052] On the other hand, the housing includes at least one movable housing plate, which is positioned near the first end of the vertically oriented support element.

[0053] On the other hand, at least one movable housing plate is configured to move from a closed position to an open position.

[0054] In another aspect, the frame includes at least one plate, at least one movable housing plate communicating with a plurality of vertically oriented support elements.

[0055] In another embodiment, the device further 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, the mesh material comprising mesh specifications 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 horizontally positioned platform.

[0056] In another aspect, an apparatus includes a horizontally positioned platform in communication with at least one of a plurality of vertically oriented support elements, wherein the horizontally positioned platform includes a rigid floor comprising a mesh material, and the mesh material includes mesh specifications selected to facilitate airflow through the rigid floor. The apparatus also includes a drive mechanism in communication with the horizontally positioned platform, wherein the drive mechanism is configured to raise and lower the horizontally positioned platform from a first position to a second position.

[0057] On the other hand, the horizontally positioned platform is connected to multiple vertically oriented support elements.

[0058] 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 a rotor guard designed to have a rotor guard diameter and a rotor guard radius exceeding the rotor length. The VTOL vehicle also includes a vehicle support element connected to at least one of the VTOL body and the rotor guard.

[0059] On the other hand, the vertical take-off and landing vehicle includes a support element that includes a convex attachment portion.

[0060] On the other hand, the vertical take-off and landing vehicle includes a support element that includes a concave attachment portion.

[0061] On the other hand, the rotor protection device is a circumferential rotor protection device.

[0062] In another aspect, the vehicle support element extends outward from at least one of the vertical takeoff and landing vehicle body and the rotor protection device.

[0063] On the other hand, the support components are integrated with the main body of the vertical take-off and landing vehicle.

[0064] On the other hand, the support components are integrated with the vertical take-off and landing rotor protection device.

[0065] On the other hand, vertical takeoff and landing vehicles are rotorcraft.

[0066] According to another aspect of the invention, a method for assisting the takeoff of a vertical takeoff and landing (VTOL) vehicle is disclosed, the method comprising providing a VTOL device that is at least partially enclosed. The device includes at least one vertical orientation support element having a first end and a second end, the first end being close to a base, the second end extending 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 including a first cooperative stabilizing element positioned close to or integral with the second end. The device also includes a housing sized to substantially surround the at least one vertical orientation support element. The method further includes providing a VTOL vehicle including at least one second cooperative stabilizing element sized to engage with the first cooperative stabilizing element. The method further includes engaging a first cooperative stabilizing element of the vertical orientation support element with a second cooperative stabilizing element of the vertical takeoff and landing vehicle (VTOL vehicle) to increase pressure from ambient pressure to takeoff pressure, at least in a region of the hull, where the takeoff pressure is greater than the ambient pressure, said region of the hull is close to the VTOL vehicle. The method also includes maintaining the VTOL vehicle in a substantially fixed position within the hull during the pressure increase and releasing the VTOL vehicle from the substantially fixed position under takeoff pressure.

[0067] On the other hand, an apparatus for assisting the takeoff of a vertical takeoff and landing (VTOL) vehicle includes at least one vertical orientation support element having a first end and a second end, the first end being close to a base, the second end 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 apparatus also includes a housing sized to substantially surround the at least one vertical orientation support element. Optionally, the apparatus further includes a pressurization unit communicating with the housing, the pressurization unit being configured to increase pressure within the housing at least in a region inside the housing.

[0068] On the other hand, the pressurization required for assisted vertical takeoff and landing (VTOL) is supplied by the VTOL rotor, increasing the pressure within the casing from ambient pressure to takeoff pressure without the assistance of a separate pressurization unit. The device also includes a pressure detector and a controller, the controller being in communication with at least one of the pressure detector and a release mechanism. The release mechanism is configured to release the VTOL vehicle from a substantially fixed position within the casing, preferably at a selected and / or detected pressure.

[0069] On the other hand, the housing includes at least one movable housing plate positioned near the first end of the vertically oriented support element.

[0070] On the other hand, at least one movable plate is configured to move from a closed position to an open position, and is also configured to move from an open position to a closed position.

[0071] On the other hand, the device also includes at least one guide that is in communication with the second end of a plurality of vertically oriented support elements and is also in communication with at least one first cooperative stabilizing element.

[0072] On the other hand, the guide also includes an outer surface and an inner surface, the inner surface of which includes at least one inner surface channel, the dimensions of which are designed to accommodate the second cooperative stabilizing element and to communicate with the first cooperative stabilizing element.

[0073] 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

[0074] 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:

[0075] Figure 1 This is a perspective view of a vertical takeoff and landing vehicle (VTOL) according to an aspect of the present invention;

[0076] Figure 2 This is a top view of a VTOL that is coupled with a currently disclosed device according to an aspect of the present invention;

[0077] Figure 3A This is an illustration of a VTOL that is coupled with a currently disclosed device according to an aspect of the present invention;

[0078] Figure 3B This is an illustration of a VTOL engaging with currently disclosed devices during takeoff. Figure 3BAlso illustrated is a VTOL that detaches from the currently disclosed device during takeoff according to aspects of the invention;

[0079] Figure 4A The diagram illustrates the mating arrangement of a first (concave) cooperative stabilizing element and a second (convex) cooperative stabilizing element in a mating configuration according to an aspect of the invention.

[0080] 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 an aspect of the invention.

[0081] 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 an aspect of the invention.

[0082] 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 an aspect of the invention.

[0083] 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 an aspect of the invention.

[0084] 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 an aspect of the invention.

[0085] 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 an aspect of the invention is shown.

[0086] Figure 5B A perspective view, either a side view or a top view, of a support that may include a convex cooperative stabilizing element according to an aspect of the invention is shown.

[0087] 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 an aspect of the invention is shown.

[0088] 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 an aspect of the invention is shown.

[0089] 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 an aspect of the invention is shown.

[0090] 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 an aspect of the invention is shown.

[0091] Figure 6A The diagram illustrates the mating arrangement of a first (convex) cooperative stabilizing element and a second (concave) cooperative stabilizing element in a mating configuration according to an aspect of the invention.

[0092] 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 an aspect of the invention.

[0093] 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 an aspect of the invention.

[0094] 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 an aspect of the invention.

[0095] 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 an aspect of the invention.

[0096] Figure 7A A top view of a support including a concave cooperative stabilizing element according to an aspect of the invention is shown;

[0097] Figure 7B A top view of a support including a concave cooperative stabilizing element according to an aspect of the invention is shown;

[0098] Figure 7C A top view of a support including a concave cooperative stabilizing element according to an aspect of the invention is shown;

[0099] Figure 7D A top view of a support including a concave cooperative stabilizing element according to an aspect of the invention is shown;

[0100] Figure 7E A top view of a support including a concave cooperative stabilizing element according to an aspect of the invention is shown;

[0101] Figure 7F A top view of a support including a concave cooperative stabilizing element according to an aspect of the invention is shown;

[0102] Figure 8AA top view of a support including a concave cooperative stabilizing element according to an aspect of the invention is shown;

[0103] Figure 8B A top view of a support including a concave cooperative stabilizing element according to an aspect of the invention is shown;

[0104] Figure 8C A top view of a support including a concave cooperative stabilizing element according to an aspect of the invention is shown;

[0105] Figure 9A A landing VTOL device, close to that currently disclosed, is shown according to an aspect of the invention;

[0106] Figure 9B The landing VTOL of the device according to an aspect of the presently disclosed invention is shown;

[0107] Figure 9C An aspect according to the invention is shown Figure 9A and Figure 9B Top view of the device shown;

[0108] Figure 10A A landing VTOL device, close to that currently disclosed, is shown according to an aspect of the invention;

[0109] Figure 10B The landing VTOL of the device according to an aspect of the presently disclosed invention is shown;

[0110] Figure 10C An aspect according to the invention is shown Figure 10A and Figure 10B Top view of the device shown;

[0111] Figure 11A An apparatus according to an aspect of the invention is shown;

[0112] Figure 11B An aspect according to the invention is shown Figure 11A Top view of the device shown;

[0113] Figure 12A Alternative devices according to aspects of the invention are shown;

[0114] Figure 12B An aspect according to the invention is shown Figure 12A Top view of the device shown;

[0115] Figure 12C An aspect according to the invention is shown Figure 12A Side view of the device shown;

[0116] Figure 13An apparatus according to an aspect of the invention is shown;

[0117] Figure 14A An apparatus according to an aspect of the invention is shown;

[0118] Figure 14B An aspect according to the invention is shown Figure 14A Top view of the device shown;

[0119] Figure 14C An aspect according to the invention is shown Figure 14A and Figure 14B Side view of the device shown;

[0120] Figure 15A An apparatus according to an aspect of the invention is shown;

[0121] Figure 15B An aspect according to the invention is shown Figure 15A Top view of the device shown;

[0122] Figure 16A An apparatus according to an aspect of the invention is shown;

[0123] Figure 16B An aspect according to the invention is shown Figure 16A Top view of the device shown;

[0124] Figure 17A A VTOL takeoff and landing stabilization device with guides according to an aspect of the present invention is shown;

[0125] Figure 17B A VTOL takeoff and landing stabilization device with guides according to an aspect of the present invention is shown;

[0126] Figure 17C A representative block diagram according to an aspect of the invention is shown;

[0127] Figure 18A A VTOL takeoff and landing stabilization device with multiple guides according to an aspect of the present invention is shown;

[0128] Figure 18B A VTOL takeoff and landing stabilization device with guides according to an aspect of the present invention is shown;

[0129] Figure 18C An enlarged view of a slotted guide of a VTOL takeoff and landing stabilization device with a guide element according to an aspect of the present invention is shown;

[0130] Figure 19 A VTOL takeoff and landing stabilization device according to an aspect of the present invention is shown;

[0131] Figure 20A VTOL takeoff and landing stabilization device according to an aspect of the present invention is shown;

[0132] Figure 21 A VTOL takeoff and landing stabilization device according to an aspect of the present invention is shown;

[0133] Figure 22 A VTOL takeoff and landing stabilization device according to an aspect of the present invention is shown;

[0134] Figure 23 A VTOL takeoff and landing stabilization device according to an aspect of the present invention is shown;

[0135] Figure 24 A VTOL take-off and landing stabilization device near a residential area according to an aspect of the present invention is shown;

[0136] Figure 25A A VTOL take-off and landing stabilization device near a residential area according to an aspect of the present invention is shown;

[0137] Figure 25B A VTOL take-off and landing stabilization device near a residential area according to an aspect of the present invention is shown;

[0138] Figure 26A A VTOL takeoff and landing stabilization device near a residence is shown according to an aspect of the invention;

[0139] Figure 26B A VTOL take-off and landing stabilization device near a residential area according to an aspect of the present invention is shown;

[0140] Figure 27A A VTOL takeoff and landing stabilization device near a residence is shown according to an aspect of the invention;

[0141] Figure 27B A VTOL take-off and landing stabilization device near a residential area according to an aspect of the present invention is shown;

[0142] Figure 28 This is a flowchart outlining an aspect of the inventive method according to the present invention;

[0143] Figure 29 This is a flowchart outlining an aspect of the inventive method according to the present invention;

[0144] Figure 30 This is a flowchart outlining an aspect of the inventive method according to the present invention;

[0145] Figure 31 This is a flowchart outlining an aspect of the inventive method according to the present invention; and

[0146] Figure 32 This is a flowchart outlining an aspect of the method of the present invention. Detailed Implementation

[0147] The present invention overcomes the major drawbacks of using vertical takeoff and landing vehicles (VTOLs) for point-to-point transport of payloads (e.g., packages, devices, etc.) and personnel, including major problems that occur during VTOL takeoff and landing, such as noise, excessive turbulence caused by ground effect air pressure generated by the rotor, vehicle instability, safety issues, ground structure damage, VTOL damage, etc.

[0148] 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 flows "down" from the VTOL, then "out" and away from the VTOL. At a distance above the ground plane, the airflow from the rotor is at least partially neutralized, and the return airflow from the rotor (which is directed back to the VTOL or otherwise affects the VTOL) is deflected little or not at all.

[0149] 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."

[0150] 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.

[0151] According to an aspect of the invention, 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, a jet engine, a propeller, and a rotor, 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 a propeller, a vertical propulsion unit, a jet engine, and a rotor.

[0152] According to aspects of the invention, the apparatus, system, and method significantly improve or substantially eliminate existing problems involving VTOL (including during VTOL takeoff and landing). Figure 1 The illustration shows a VTOL 20 according to an aspect of the invention. 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 VTOL 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 VTOL bracket 28 also includes a second bracket end 28b, which terminates at a second cooperative stabilizing element 29.

[0153] The second cooperative stabilizing element 29 of the VTOL 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 the 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 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°.

[0154] 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.

[0155] According to an aspect of the invention, 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 is... Figure 1 and Figure 2 As shown in the image.

[0156] In other aspects of the invention, 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).

[0157] Figure 3A A simplified device 41a according to an aspect of the invention 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 VTOL bracket 28 includes a first bracket end 28a, which is attached to or integrated with each rotor protection device 26 and extends outward from each rotor protection device 26. Each VTOL bracket 28 also includes a second bracket end 28b, which terminates at a second cooperative stabilizing element 29.

[0158] like Figure 3A and Figure 3B As shown, the second cooperative stabilizing element 49 of the VTOL support 28 is configured to be attached to the vertical orientation support element 42 in the device 41a, as... Figure 3A As 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.

[0159] 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.

[0160] Figure 3B A device 41b according to an aspect of the invention is shown for facilitating the takeoff (e.g., launch) and landing of a VTOL 40, 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.

[0161] 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.

[0162] 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.

[0163] According to an aspect of the invention, a bracket integrated with or attached to the VTOL may include a "convex" or "concave" second cooperative stabilizing element at the end of a 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 "fitted" or interlocked.

[0164] 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 stabilization device are integral with or attached to the vertical orientation support elements 54a, 54b, 54c, 54d, 54e, 54f, or otherwise communicate with the vertical orientation support elements 54a, 54b, 54c, 54d, 54e, 54f, and the first cooperative stabilization 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 geometries (including, for example, cross-sectional geometry, mating geometry, etc.) for vertically oriented support elements, as well as first and second cooperative features considered in aspects of the invention.

[0165] 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 eliminating 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.

[0166] 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.”

[0167] 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.

[0168] 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 the support according to an aspect of the invention 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.

[0169] 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, according to aspects of the invention, can eliminate vibrational forces and other forces, including impacts and contact, that may occur during VTOL landing and takeoff. By eliminating or "absorbing" forces during VTOL takeoff and landing, the addition of the spring element 57 can further stabilize the VTOL during takeoff and landing, thereby improving the performance of the apparatus, system, and method.

[0170] 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.

[0171] Figure 5DA support 58d is shown, which includes a second end 28b of the support terminating at a second cooperative stabilizing element 29 having a “convex” configuration for engaging with a concave first cooperative stabilizing element. The support 58d also includes a shock absorber 55, which can eliminate vibrational forces and other forces, including impacts, contact, etc., that may occur during VTOL landing and takeoff according to aspects of the invention.

[0172] 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).

[0173] 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).

[0174] 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 directional support elements 64a, 64b, 64c, 64d, 64e of the VTOL takeoff and landing stabilization device are integral with, attached to, or otherwise communicated with, the vertical directional support elements 64a, 64b, 64c, 64d, 64e. The first cooperative stabilization 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 aspects of the invention. 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.

[0175] 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 eliminating 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.

[0176] 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.

[0177] According to an aspect of the invention, 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 aspects of the invention, as the VTOL continues to descend during the landing operation, the slotted function of the second cooperative stabilizing element can serve as a guide to assist the descent of the VTOL down the length of the vertical orientation support element to the ground plane during descent.

[0178] 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.

[0179] According to an aspect of the invention, 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.

[0180] Similar to Figures 5A to 5F According to an aspect of the invention, the support 28 is configured to eliminate vibration forces and other forces, including, for example, impacts and contact, that may occur during VTOL landing and takeoff.

[0181] According to aspects of the invention, the first and second cooperative stabilizing elements may include actuators and mechanisms to achieve a 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 having a “concave” configuration to facilitate entry and engagement of a cooperative stabilizing element having 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.

[0182] like Figure 8A As shown, the VTOL 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 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 VTOL support 28 is shown moved to the "partially closed" orientation (with...). Figure 8A (Compared to the "Open" orientation shown).

[0183] Figure 8C A second cooperative stabilizing element 69 is shown in the "closed" orientation of the VTOL support 28. According to an aspect of the invention, when the VTOL approaches the proposed takeoff and 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 actuation 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 an aspect of the invention, 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 in the VTOL is in communication with the gripping end, etc.

[0184] Figures 9A to 9C A VTOL participating in a landing operation according to an aspect of the invention is shown, wherein the VTOL descends and approaches the vicinity of the VTOL takeoff and landing stabilization device. For example... 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 two vertical orientation support elements 91, thereby placing the second cooperative stabilizing element 69 of the VTOL support 28 in a suitable position to engage with the first cooperative stabilizing element 92 located at the second end 91b of the vertical orientation 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.

[0185] Figure 9B The VTOL takeoff and landing stabilization 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.

[0186] According to aspects of the invention, a frame support member can contact and provide support for a vertically oriented support element. When positioned together with the vertically oriented support element in an existing VTOL stabilization system, this frame support member provides the "frame" of the system. The frame support member can be deployed in the system as a horizontal support member directly connected to the vertically oriented support element. When the geometric orientation of the frame support member has a substantially circular geometry, the frame support member is referred to as a circumferential frame support member because the frame support member "defines" or "wraps" around a theoretical perimeter formed by a line drawn to include an area created within the region created by the vertically oriented support element, where the inner perimeter represents a value representing the outer perimeter capable of accommodating a VTOL configured to take off and land from the current VTOL stabilization system. Although shown as circular, aspects of the invention include other geometries for non-circular frame support members. For example, when four vertically oriented support elements are present, the frame support member can be circular, or it can be, for example, rectangular. If the four vertically oriented support elements are equidistant from each other, the frame support member can be square. According to aspects of the invention, the term "circumferential" frame support includes a frame support geometry that may not be circular. However, in all cases, as described herein, a selected perimeter formed by the "circumferential frame support" is chosen and its dimensions are designed to accommodate landing into and taking off from the VTOL, based on the dimensions of the VTOL. That is, aspects of the invention take into account a cross-sectional device perimeter that is larger than the outer perimeter of the VTOL taking off and landing from the device.

[0187] Figure 9C yes Figure 9B The top view of the VTOL takeoff and landing stabilization device 90b shown has Figure 9B The numbering features shown. According to an aspect of the invention, 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 VTOL turbulent rotation caused by the ground effect. Furthermore, these devices promote the elimination 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.

[0188] According to another aspect of the invention, 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 takeoff and 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 alignment 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 VTOL support 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.

[0189] Figure 10B It shows the relationship with ( Figure 10A The 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.

[0190] Figure 10C yes Figure 10B The top view of the VTOL takeoff and landing stabilization device 100b shown has Figure 10B The numbering features shown. According to an aspect of the invention, Figures 10A to 10CThe 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 elimination of recirculating eddies caused by the ground effect, where 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 aspects of the invention contemplate including a selected number of vertical orientation support elements in addition to the four.

[0191] In another aspect of the invention, methods, systems, and apparatuses employing currently disclosed VTOL takeoff and landing stabilization devices may include a platform to further enhance the stability imparted to the VTOL participating in landing or takeoff operations. According to an aspect of the invention, the platform may include a grid made of a material that may be rigid or tensioned, said material including a mesh material that may be a rigid mesh material and has an average mesh gauge, such that the grid includes a mesh material selected to be sufficiently robust to support the weight of the VTOL in contact with and supported by the grid.

[0192] Figure 11A The diagram shows a VTOL 40 that has completed its landing operation onto device 110, with the VTOL positioned appropriately on platform 112. According to an aspect of the invention, 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 mesh or grid 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. The invention contemplates platform 112 that can be made of metal, plastic, resin-based composite materials, ceramics, cloth, and combinations thereof. The platform can be made of a conductive material, or can be coated or impregnated with a conductive material or a conductive material coating, etc.

[0193] 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 11AAlso 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.

[0194] Figure 11B yes Figure 11A The top view of the VTOL takeoff and landing stabilization device 110 shown is illustrated, where the numbering features are also as follows: Figure 11A As shown and described herein. According to aspects of the invention, 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, VTOL turbulent rotation caused by the ground effect, and this device promotes the elimination of recirculating eddies caused by the ground effect, wherein turbulent energy and effects are transferred from the VTOL to the ground effect. Figure 11A , Figure 11B A device of the type shown. Although Figure 11A , Figure 11B Four vertical orientation support elements are shown, and aspects of the invention contemplate including a selected number of vertical orientation support elements in addition to the four.

[0195] According to other aspects of the invention, 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).

[0196] 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 12AA 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 extending from any rotor protection device and otherwise configured as engaging device 120. According to aspects of the invention, the retainer is equivalently referred to as a "release mechanism".

[0197] Figure 12B yes Figure 12A A top view of the device 120 shown, wherein VTOL 124 (still) Figure 12C (As shown in the side view) positioned near platform 112, platform 112 includes retainer 122, which is configured to engage the landing skid 128 of VTOL 120. Although in Figure 12B 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 The motion of the platform of the type shown.

[0198] 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 12CNot 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.

[0199] According to another aspect of the invention, 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 takeoff and landing stabilization device 130 can be combined with at least one Figures 11A to 11B , Figure 12A , Figure 12B , Figure 12C The 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 takeoff and landing stabilization device 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 the platform 112, where the unstable ground effect (generated by the VTOL rotor during takeoff and / or landing) on ​​the VTOL is significantly improved or substantially eliminated by transferring energy and force from, for example, the ground effect (at least partially) to the stabilizing device 130.

[0200] According to an exemplary takeoff operation, according to an aspect of the invention, 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(As shown) is located either directly connected to or otherwise integrated with platform 112. According to another aspect of the invention, at least a portion of the drive mechanism may be positioned remotely from the drive element positioned to communicate with platform 112, but still connected to said drive element. When the drive mechanism is activated, 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 platform 112 but still connected to it, wherein the drive mechanism is configured to raise or lower platform 112 along the length of device 130 to change the selected height. VTOL 40 may be positioned on platform 112, wherein a second cooperative stabilizing element 69 on 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 may be guided to a selected height along the length of 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.

[0201] According to an exemplary VTOL landing protocol, and according to aspects of the invention, when the VTOL is guided to device 130, power (e.g., electricity) from power source 132 can be activated and directed to drive mechanism 134 to raise platform 112 to a selected height within 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 VTOL support 28 with a first cooperative stabilizing element 92, which is positioned integral with or near the vertical orientation support element 91 of device 130. Once the controlled and stable landing is complete, the VTOL 40 will be safely positioned on platform 112, at which point, according to the landing protocol, drive mechanism 134 in 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 platform 112 (which may include, for example, the ground plane).

[0202] 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 aspects of the invention 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 currently disclosed VTOL takeoff and landing stabilization apparatus, system, and method.

[0203] like Figure 14A As shown, the VTOL takeoff and landing stabilization 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 142 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 142 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 14C A 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.

[0204] Figure 14B This is a top view of the VTOL landing stabilization 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 Device 100a, but 14A to Figure 14C The guide 142 shown herein is to be understood as applicable to many of the devices disclosed herein. When the VTOL takeoff and landing stabilization 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 stabilization device. For example... Figure 14A , Figure 14B , Figure 14CAs 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.

[0205] 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 stabilization device.

[0206] like Figure 14A , Figure 14B , Figure 14C As 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.

[0207] According to an aspect of the invention, when the device employs Figure 14A , Figure 14B , Figure 14CWhen using a guide of the type shown, a landing protocol for VTOLs is more advantageous. In an exemplary landing protocol using the VTOL landing stabilization 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 VTOL 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.

[0208] Furthermore, the external and / or internal geometry of the VTOL takeoff and landing stabilization device need not be approximately circular, approximately tubular, approximately cylindrical, etc., as long as the internal longitudinal dimension of the VTOL takeoff and landing stabilization device can be adapted to the external dimension of the VTOL, and the external dimension of the VTOL is designed for takeoff from or landing in a specific VTOL takeoff and landing device.

[0209] Although Figure 15A , Figure 15B , Figure 16A , Figure 16B Further exemplary and non-exhaustive constructions of a VTOL takeoff and landing stabilization device according to aspects of the invention 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 aspects of the invention 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 takeoff and landing stabilization device can be dimensionally adapted to the external dimensions of the VTOL, which are designed for takeoff or landing in a particular VTOL takeoff and landing stabilization device.

[0210] According to another aspect of the invention, Figure 15Aand Figure 15B A VTOL takeoff and landing stabilization 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).

[0211] 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.

[0212] Figure 15B This is a top view of the VTOL landing stabilization 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.

[0213] According to another aspect of the invention, Figure 16A and Figure 16B A VTOL takeoff and landing stabilization 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.

[0214] Figure 16B Is it like this? Figure 16A The diagram shows a top view of the VTOL landing stabilization device 160, and shows a first guide end 162a and a second guide end 162b, in which the VTOL 20 is "nested" within the guide 160, and the VTOL 20 participates in the landing or takeoff protocol. Figure 16A , Figure 16B The guide 162 shown is understood to be applicable to many of the devices disclosed herein.

[0215] 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 another aspect, a highly perforated material can be used as the material for guide 162.

[0216] The present invention considers guides 142, 152, and 162 that can be made of metal, plastic, resin-based composite materials, ceramics, cloth, or combinations thereof. The guides can be made of conductive materials, or can be coated or impregnated with conductive materials or conductive material coatings, etc.

[0217] According to aspects of the invention, VTOL takeoff and landing stabilization devices, systems, and methods can also facilitate aspects of VTOL takeoff and landing, including energy efficiency and stability during takeoff and landing, and noise reduction during takeoff and landing. According to another aspect of the invention, the enclosed device may include at least one housing that surrounds or may substantially surround and otherwise enclose a vertically oriented support element and a frame support, the frame support being a circumferential frame support and forming a device frame together with the vertically oriented support element.

[0218] For example, aspects of the invention also contemplate devices, systems, and methods for vertical takeoff and landing vehicles (VTOLs) comprising enclosed or substantially enclosed devices (collectively referred to herein as “enclosed devices”), from which such vehicles can take off and land, which can significantly improve or substantially eliminate ground effects on the vehicle, while improving the stability of the VTOL during takeoff and landing, and simultaneously saving energy and reducing operating decibel levels during takeoff and landing. According to aspects of the invention, an enclosed device may include fixing devices and components as specified herein, and such enclosed device additionally includes at least one movable plate that can be opened and closed (e.g., it can be moved from an open position to a closed position and from a closed position to an open position, including a partially open position and a partially closed position, etc.). According to aspects of the invention, in an enclosed device with the movable door in the open position, a vertical takeoff and landing vehicle can be accommodated within the enclosed device, which may also include guides and elevator-type platforms as described herein. Regarding the housing, the terms “plate” and “door” used herein are equivalent and interchangeable terms. Furthermore, the terms "movable housing plate" and "movable plate" are equivalent terms for the purposes of this application.

[0219] Focusing first on the VTOL descent operation in a currently disclosed enclosed VTOL takeoff and landing stabilization device, at least one movable plate can be moved directly or remotely, manually or automatically (e.g., from a closed position to an open position). During descent, the VTOL is positioned above and lowered into the device, including means that may include guides. Figure 17A and Figure 17B As shown, at least in Figure 1 and Figure 2 The VTOL 20 of the type shown has been lowered into the enclosed VTOL take-off and landing stabilization unit 170.

[0220] The enclosed VTOL takeoff and landing stabilization device 170 is similar in frame and structure to Figure 14A , Figure 14B The device shown in the middle (as VTOL take-off and landing stabilization device 140) significantly adds a housing 174 to the enclosed VTOL take-off and landing stabilization device 170, the housing 174 substantially surrounding or otherwise enclosing the VTOL take-off and landing stabilization device 170 to form a tubular region (e.g., when the housing is substantially cylindrical).

[0221] like Figure 17A and Figure 17B As shown, the enclosed VTOL takeoff and landing stabilization device 170 includes at least one ( Figure 17A , Figure 17BThe diagram shows multiple (four (4)) vertical orientation support elements 171, each support element 171 further including a first end 171a of the vertical orientation support element, a second end 171b of the vertical orientation support element, and a channel 171c of the vertical orientation support element.

[0222] The enclosed VTOL takeoff and landing stabilization device 170 also includes circumferential frame supports 173a and 173b that are connected to the vertical directional support element 171. Figure 17A , Figure 17B Guide 172 is also shown (in Figure 14A (shown as 142), which may include a first guide end 172a and a second guide end 172b that are also geometrically and substantially circular. Figure 17A and Figure 17B The enclosed VTOL takeoff and landing stabilization device 170 shown also includes an outer housing configured to form a housing 174 surrounding the enclosed VTOL takeoff and landing stabilization device 170 and a plurality of housing doors 176. Figure 17A Four (4) housing doors 176 are shown in the closed position, while Figure 17B Four (4) housing doors 176 are shown in the open position.

[0223] Figure 17A The diagram illustrates a VTOL 20 in a descent state, where the VTOL has oriented each of the four second cooperative (convex) elements 29 on the four supports 28 (one each) into the vertical orientation support element channel 171c, and as the VTOL descends within the VTOL stabilization device 170, the VTOL 20 is in a significantly enhanced stable descent state within the enclosed VTOL stabilization device 170. As the ground effect from the VTOL rotor generates a degree of air turbulence within the VTOL stabilization device 170, and as the VTOL 20 descends to a point near the ground 16, the influence of the ground effect turbulence region within a distance of the ground 16 affects the stability of both the VTOL 20 and the VTOL stabilization device 170. According to aspects of the invention, this ground effect turbulence within the enclosed VTOL stabilization device 170 can be controlled and significantly mitigated by triggering the opening of the housing door 176 within the enclosed VTOL stabilization device 170 to eliminate the ground effect turbulence.

[0224] like Figure 17B As shown, the housing door 176 is now in the open position, and the ground effect turbulence generated by the rotor of the VTOL 20 is eliminated at least by the open housing door 176 (as indicated by the arrow), and the forces commensurate with the generated ground effect turbulence are significantly reduced as the forces (including ground effect forces) are cleared from the closed VTOL takeoff and landing stabilization device 170 via the open housing door 176.

[0225] Figure 17B A control box 177 is shown, representing electrical and mechanical components for adjusting the position of the housing door 176. At least one control box 177 includes or is otherwise connected to a pressure detector 177a, which is configured to sense pressure in an area within the VTOL takeoff and landing stabilization unit 170. Figure 17C As shown in more detail in the block diagram, the control box 177 may include a controller 177b, a power supply 177c, and an actuator 177d in communication with at least one housing door. The actuator 177d is configured to receive signals from the controller 177b and / or the pressure detector 177a, and is configured to move the housing door according to a command.

[0226] Figure 18A and Figure 18B An alternative arrangement of the VTOL landing stabilization device 180 is shown, which differs from the VTOL landing stabilization device 170 in that each of the vertical orientation support elements 181 includes a plurality of individual guides 182 positioned adjacent to or on top of the second end 181b of the vertical orientation support element. In this respect, during descent and as the VTOL 20 approaches the VTOL landing stabilization device 180, the VTOL 20 aligns a second cooperative stabilization element 29 located on the VTOL support 28 with respect to the individual guides 182, and the second cooperative stabilization element 29 engages the individual guides 182, each individual guide 182 including an individual guide slot 182a, which is structurally configured to be fed into a groove located at the vertical orientation support element 181 associated with the individual guide 182 at the second end 181b of the vertical orientation support element. A housing 184 is shown as the body surrounding the VTOL landing stabilization device 180.

[0227] Figure 18B It shows Figure 18A The VTOL takeoff and landing stabilization device 180 shown is wherein the VTOL 20 is lowered into the main body of the VTOL takeoff and landing stabilization device 180. Figure 18C An enlarged representative top view of the individual guide 182 that houses the second cooperative stabilizing element 29 of the VTOL bracket 28 is shown. Figure 18C A second cooperative stabilizing element 29 that receives the VTOL support 28 is shown. Figure 18C A vertically oriented support element 181, which communicates with the guide 182 and the housing 184, is also shown.

[0228] Figure 19 and Figure 20Alternative existing aspects and alternative configurations of the VTOL takeoff and landing stabilization device are shown, which includes additional and / or alternative pressure relief elements that can assist in mitigating ground-effect air turbulence and otherwise eliminate increased pressure within the VTOL takeoff and landing stabilization device during VTOL descent according to aspects of the invention.

[0229] like Figure 19 As shown, the enclosed VTOL takeoff and landing stabilization device 190 includes, as follows: Figure 17A The enclosed VTOL landing stabilization device 170 shown comprises numerous components, in which an external shield 195 is added. The external shield 195 is located outside the housing and can extend from a first end 195a (e.g., near the ground 16) to a second end 195b. As the VTOL descends (e.g., during landing) or ascends (e.g., during takeoff) within the VTOL landing stabilization device 190, ground-effect air turbulence is allowed to exit from or otherwise be guided from the VTOL landing stabilization device housing 194 via a housing opening 196 defined by the housing 194. Figure 17A and Figure 17B An alternative embodiment of the lateral opening 176 of the housing shown is, in Figure 19 In this configuration, the housing opening 196 can open outward at the top while hinged at the bottom to conform to the shape of the outer shield 195. Then, ground-effect turbulent air at higher (above ambient) pressure escaping from the housing opening 196 can be guided against the inner surface 195c of the outer shield and escape to... Figure 19 In the lower-pressure atmosphere indicated by the middle arrow, and can otherwise be “released” into the air at a selected distance from the ground, which can be substantially equal to the height of the VTOL takeoff and landing stabilization device (e.g., the distance from the ground ranges from about 4 feet to about 100 feet, etc.).

[0230] Figure 20 Other alternative aspects of the VTOL takeoff and landing stabilization system 200 for improving ground effect during VTOL landing and takeoff are shown. For example... Figure 20 As shown, the enclosed VTOL takeoff and landing stabilization device 200 includes, as follows: Figure 17A The enclosed VTOL takeoff and landing stabilization device 170 shown comprises many components, but with the addition of multiple conduits 205, the conduits 205 being positioned such that the lower end 205a extends through the housing opening 206 in the housing 204. The second end 205b of the conduit extends a selected distance from the first end 205a to the second end 205b, the basic length of the conduit 205 (e.g., ...). Figure 20(As shown) The conduit 205 is located outside the housing 204 at the outer 204a and may be positioned close to the housing 204 or may be attached to or integral with the housing 204. Alternatively, the conduit 205 is inclined outward and away from the housing 204, such that the second end 205b of the conduit is horizontally farther away from the housing 204 than the first end 205a of the conduit.

[0231] As the VTOL descends (during landing) or ascends (during takeoff) within the VTOL stabilization unit 200 (e.g., during landing), ground-effect air turbulence is permitted to escape from or otherwise guide from the VTOL stabilization unit housing 204 via housing opening 196 defined by housing 194. The higher (above ambient) pressure ground-effect turbulent air escaping from housing opening 206 can then be directed into duct 205 and from duct 205 into a lower pressure atmosphere (e.g., at a selected distance away from the ground) Figure 20 (As indicated by the arrow in the image), this selected distance can be substantially equal to the height of the VTOL landing gear (e.g., the distance above the ground ranges from approximately 10 feet to approximately 200 feet, etc.). Figure 17A , Figure 17B , Figure 18A , Figure 18B , Figure 19 , Figure 20 In the VTOL takeoff and landing stabilization devices 170, 180, 190, 200, etc., there may be access doors to retrieve goods or passengers transported by the VTOL, or to load goods or passengers into the VTOL, etc.

[0232] The ground-effect turbulent air from the higher pressure VTOL landing stabilizers 190, 200 is eliminated substantially in real time during VTOL landing and / or takeoff. The VTOL is also stabilized within the device during landing and further facilitates landing operations by achieving pressure balance between the pressure inside the landing device and the ambient pressure outside the VTOL landing stabilizer.

[0233] According to another aspect of the invention, a VTOL takeoff and landing stabilization device is disclosed that improves or otherwise significantly reduces VTOL operating noise during takeoff and landing by incorporating sound insulation measures into the VTOL takeoff and landing stabilization device. Figure 21 , Figure 22 , Figure 23 This is a diagram showing the current state of sound insulation.

[0234] Figure 21 A cross-sectional view of the VTOL takeoff and landing stabilization device 210, including the housing 214, is shown. Figure 21 and Figure 22 The internal features of the device shown in the previous figure are omitted, although considering Figure 21 and Figure 22 The sound insulation aspects shown can be incorporated into a closed VTOL takeoff and landing stabilization device 210, which incorporates a housing 214 and includes at least, for example... Figure 17A , Figure 17B As shown in the current attached figure. Figure 21 The VTOL 20 is shown participating in takeoff maneuvers and ascending within the enclosed VTOL takeoff and landing stabilization device 210. Figure 22 This shows that VTOL 20 has risen to a height greater than that indicated by the second end 214b of the housing, such that VTOL 20 has exceeded the height of the enclosed VTOL take-off and landing stabilization device 210.

[0235] like Figure 21 and Figure 22 As shown, the VTOL takeoff and landing stabilization device includes a housing 214. The housing 214 includes a first end 214a located near the ground 16 or the base and a second end 214b located away from the ground 16 or the base. The housing 214 also includes an inner wall 214c, which is spaced apart from the outer wall 214d by a selected distance. An internal internal volume 215 is provided between the inner wall 214c and the outer wall 214d.

[0236] Sound reduction can include reflection, absorption, and diffusion. In aspects of the invention, sound reflection or diffusion is achieved by various treatments of the inner wall 214c of the housing, the walls in the internal volume 215, and the outer wall 214d of the housing. Furthermore, the internal volume 215 of the housing can be made of a single plate or multiple plates of material, or continuous or discrete materials, and can be otherwise combined or filled with single plates or multiple plates of material, or continuous or discrete materials. Examples of such materials with sound-absorbing capabilities include honeycomb materials, acoustic foam, phase-cancelling materials, active and passive noise cancellation panels, sound-absorbing tiles, other sound-absorbing materials and / or technologies, and combinations thereof. According to aspects of the invention, the housing 214 containing the internal volume 215 can reduce the decibel level of sound generated by VTOL takeoff and / or landing from, for example, an unattenuated level of about 68 dB (at 1 meter) for a relatively “quiet” drone to about 120 dB or higher (at 1 meter) for a flying vehicle. According to an aspect of the invention, these VTOL noise levels can be attenuated by different decibel amounts based on the material density, energy absorption characteristics, and the distance between the inner wall 214c and the outer wall 214d of the housing, depending on the material used in the walls and the internal volume 215. According to an aspect of the invention, various selected noise reduction amounts are obtained based on the chosen design.

[0237] According to an aspect of the invention, the dimensions of the VTOL takeoff and landing stabilization device can be designed relative to its width and height to take into account noise reduction at ground level by incorporating the device provided by the housing inner wall having an internal volume 215. That is, by selecting and combining the sound-absorbing material for the housing inner volume 215, together with the selected inner wall dimensions, and, for example, the height of the VTOL takeoff and landing stabilization device, an acceptable level of noise reduction at ground level can be selected to comply with, for example, local noise regulations, safety regulations, etc.

[0238] Figure 23 The enclosed VTOL takeoff and landing stabilization device 20 is shown (e.g. Figure 21 and Figure 22 As shown), an optional guy cable 218 is attached to the enclosed VTOL stabilization device 210 and anchored to, for example, the ground 16. For the purposes of this invention, the term "guy cable" includes any tension cable or rope selected to increase the stability of the stand-alone VTOL stabilization device according to aspects of the invention.

[0239] According to another aspect, the VTOL takeoff and landing stabilization device disclosed herein can be attached to a residential structure or positioned close to a residential structure. An exemplary residential structure 240 is in... Figure 24 The diagram shows an enclosed VTOL takeoff and landing vehicle assembly 244 positioned nearby. As considered herein, the VTOL can be sized to transport and deliver goods (e.g., parcels for delivery). The VTOL under consideration can also be sized to transport passengers, for example, in the case where the VTOL is an air vehicle (including vehicles designed for both land and air use (e.g., flying cars)), and in the case where the VTOL has a “hybrid” or multi-functional land, water, and air mode. In this respect, the enclosed VTOL takeoff and landing stabilization assembly 244 can serve as, for example, a “garage” that can be associated with and located near a residence (including integrated with the residence). For example, the VTOL takeoff and landing stabilization assembly 244 in such a “garage” configuration advantageously facilitates, for example, the takeoff and landing of a flying car VTOL.

[0240] Figure 25A , Figure 25B , Figure 26A , Figure 26B , Figure 27A and Figure 27B Various configurations for enclosed VTOL take-off and landing stabilization devices associated with residences are also shown, with a focus on functional elements on the top, which are movably configured, for example, to protect the enclosed VTOL device, and for the VTOL (e.g., a “parked” VTOL, etc.) to “open” from the elements in various ways and to accommodate the VTOL taking off and landing from the existing enclosed VTOL take-off and landing stabilization device as needed.

[0241] like Figure 25A As shown, the enclosed VTOL landing stabilization device 254 is configured in a “garage” that may be located near the residence 240. The enclosed VTOL landing stabilization device 254 includes a first end 254a of the VTOL landing stabilization device close to the ground plane and a second end 254b of the VTOL landing stabilization device located at a selected distance from the first end 254a. The distance between the first end 254a and the second end 254b of the VTOL landing stabilization device is expressed as approximately equal to the total height of the enclosed VTOL landing stabilization device 254. Figure 25A The top 256a is also shown in the closed top position, which can be moved to the open top position (in Figure 25A (Seen in dashed lines, with arrows indicating movement between the closed and open positions). When the top 256a is in the open position, the interior of the enclosed VTOL takeoff and landing stabilization device 254 is exposed.

[0242] like Figure 25A As shown, the top 256a can be designed to be flat, and the top can move between an open and closed position via, for example, pivoting about a top mechanism 255a, which can be, for example, an electric hinge. The top 256a can be engaged or otherwise connected to a mechanical actuator and a power source, which is connected to a controller, and the power source can be contained, for example, within a control box 257. The control box 257 may also include a receiver for receiving remote signals transmitted from the receiver to the controller, which is connected to the actuator, which is also connected to the top mechanism. For example, upon receiving a signal (e.g., a signal from a nearby VTOL, or a signal from a residence, or a signal from a VTOL waiting to take off within an enclosed VTOL landing stabilization device, etc.), the receiver in the control box 257 (e.g., a receiver that can be integrated with or communicate with the controller in the control box 257) can send a signal to the controller, and the controller can send a signal to the actuator to move the top 256a from the open position to the closed position or from the closed position to the open position. Figure 25A Also shown is a VTOL 252 positioned on the ground plane within an enclosed VTOL landing stabilization device, wherein the VTOL is not drawn to scale and is a cargo or passenger VTOL.

[0243] Figure 25B It shows Figure 25A An alternative aspect of the enclosed VTOL takeoff and landing stabilization device is shown. Figure 25B The dimensions of the top 256b shown are designed as a sloping top. Figure 25B The remainder of the aspects described and listed in the text, such as Figure 25A As shown.

[0244] Figure 26A It shows Figure 25A An alternative aspect of the enclosed VTOL takeoff and landing stabilization device 254 shown is... Figure 26A The top 256c shown is designed to be flat, the top mechanism 255b communicates with the top 256c, and the top mechanism is configured to apply a lateral force to the top 256c to, for example, rotate or “slide” the top from a closed position to an open position (e.g., Figure 26A As indicated by the arrow in the diagram, when the top 256c is in the open position, the interior of the enclosed VTOL landing stabilization device 254 is exposed. The support mechanism disclosed herein, which communicates with the top 256c, and related to... Figure 25A and Figure 25B The similarities disclosed in the aspects shown are understandable. Figure 26A and Figure 26B The top mechanism 255b shown is selected to transmit the force required for, for example, lateral movement of the top 256c and top 256d between an open position and a closed position. The top mechanism 255b includes, for example, necessary hydraulic, pneumatic, servo, piston, etc.

[0245] Figure 26B It shows Figure 26A An alternative aspect of the enclosed VTOL takeoff and landing stabilization device shown is... Figure 26B The top 256d shown is designed with a sloping top (similar to...). Figure 25B The top 256b) and top 256d shown herein include information about the text. Figure 26A The top mechanism 255b is shown and described as of type 255b. Figure 26A and Figure 26B It can also include Figure 25A , Figure 25B The control box 257 shown is configured to include mechanisms and electronics for operation as described herein.

[0246] Figure 27A This illustrates another alternative aspect of the invention, the VTOL takeoff and landing stabilization device 254, which has similar characteristics to... Figure 25A and Figure 26A The top shown (e.g., a top with a flat orientation, etc.), Figure 27A The top 256e shown includes a top mechanism 255c communicating with the top 256e, and the top mechanism 255c is configured to transmit force to the top 256e and otherwise engage guides or tracks to, for example, move the top 256e from a closed top position to an open top position, when the top 256e is in the open position, the interior of the enclosed VTOL takeoff and landing stabilization device 254 is exposed. The support mechanism that can communicate with the top 256e disclosed herein and related... Figure 25Aand Figure 26A The similarities disclosed in the aspects shown are understandable. Figure 27A and Figure 27B The top mechanism 255c shown is selected to transmit the force required to move the tops 256e, 256f, for example, along a guide or track arrangement to move the tops 256e, 256f between an open position and a closed position. The top mechanism 255c includes, for example, necessary hydraulic, pneumatic, servo, piston, guide, track, pulley, gear chain, etc.

[0247] Figure 27B It shows Figure 27A An alternative aspect of the enclosed VTOL takeoff and landing stabilization device 254, Figure 27B The top 256f in the middle is designed to be the same as Figure 25B , Figure 26B The sloping top type shown is similar to top 256f, and top mechanism 255c includes those described herein. Figure 27A The components described in the indicated aspect. Figure 27A and Figure 27B It can also include Figure 25A , Figure 25B , Figure 26A , Figure 26B The control box 257 shown is configured to include mechanisms and electronics for operation as described herein.

[0248] Figure 28 , Figure 29 , Figure 30 , Figure 31 and Figure 32 This is a flowchart outlining a method according to an aspect of the invention. (e.g.) Figure 28 As shown, a method 2000 for launching and landing a vertical takeoff and landing (VTOL) vehicle is disclosed. Method 2000 includes: providing 2002 a VTOL device that is at least partially enclosed, the VTOL device including at least one vertical orientation support element having a first end and a second end, the first end being close to a base, the second end extending 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 including a first cooperative stabilizing element positioned close to the second end. The device also includes a housing sized to substantially surround the at least one vertical orientation support element.

[0249] like Figure 28As shown, method 2000 further includes: providing 2004 a vertical take-off and landing vehicle, the vertical take-off and landing vehicle including at least one second cooperative stabilizing element, the second cooperative stabilizing element being sized to engage with a first cooperative stabilizing element, and engaging 2006 the first cooperative stabilizing element of the vertical orientation support element with the second cooperative stabilizing element of the vertical take-off and landing vehicle.

[0250] Figure 29 This is a flowchart outlining method 2100, which includes methods for launch and landing, such as... Figure 28 The elements of the method 2000 for a vertical takeoff and landing vehicle described herein, method 2100 further include: stabilizing the vertical takeoff and landing vehicle at least horizontally during at least one of takeoff and landing, and restricting the movement of the vertical takeoff and / or landing vehicle during takeoff and / or landing.

[0251] Figure 30 This is a flowchart outlining a disclosed method 2200 for launching and landing a vertical takeoff and landing vehicle. Method 2200 includes: providing 2202 a vertical takeoff and landing device that is at least partially enclosed, the device including at least one vertically oriented support element, wherein the at least one vertically oriented support element has a first end and a second end, the first end being near a base, the second end extending from the first end to the second end, the second end being located at a selected distance away from the first end, the vertically oriented support element including a first cooperative stabilizing element positioned near the second end. The device also includes a housing sized substantially around the at least one vertically oriented support element, the housing including at least one movable housing plate positioned near the first end of the vertically oriented support element.

[0252] like Figure 30 As shown, method 2200 further includes: lowering a vertical takeoff and landing (VTOL) vehicle 2204 into a VTOL vehicle assembly, the VTOL vehicle including at least one second cooperative stabilizing element, and the second cooperative stabilizing element being sized to engage with a first cooperative stabilizing element; engaging 2206 the second cooperative stabilizing element of the VTOL vehicle with the first cooperative stabilizing element of a vertical orientation support element; and lowering the VTOL vehicle, which is at least partially enclosed within the VTOL assembly, from a second end of the vertical orientation support element 2208 to a first end of the vertical orientation support element. Figure 30 As shown, method 2200 further includes: opening 2210 at least one movable plate to eliminate air turbulence in the housing during VTOL landing.

[0253] Figure 31 This is a flowchart outlining method 2300, which includes methods for launch and landing, such as... Figure 30 The method 2200 for a vertical takeoff and landing vehicle described herein, method 2300 further includes: detecting 2302 air pressure in at least a region of the housing; actuating 2304 at least one movable plate in response to the detected air pressure detected by the detector within the housing; and subsequently opening 2210 at least one movable plate during VTOL descent to eliminate air turbulence in the housing.

[0254] According to another aspect, Figure 32 A method 2400 for assisting the takeoff of a vertical takeoff and landing (VTOL) vehicle is outlined. Method 2400 includes: providing 2402 a VTOL device that is at least partially enclosed, the VTOL device including at least one vertical orientation support element having a first end and a second end, the first end being near a base, the second end extending 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 including a first cooperative stabilizing element positioned near the second end. The device also includes a housing sized to substantially surround the at least one vertical orientation support element.

[0255] like Figure 32 As shown, method 2400 further includes: providing 2404 a vertical take-off and landing vehicle, the vertical take-off and landing vehicle including at least one second cooperative stabilizing element, the second cooperative stabilizing element being sized to engage with a first cooperative stabilizing element, and engaging 2406 the first cooperative stabilizing element of the vertical orientation support element with the second cooperative stabilizing element of the vertical take-off and landing vehicle.

[0256] Method 2400 further includes: increasing pressure 2408 in at least a region of the hull from ambient pressure to takeoff pressure, said takeoff pressure being greater than said ambient pressure, the region of the hull being close to the vertical takeoff and landing vehicle; maintaining the vertical takeoff and landing vehicle 2410 in a substantially fixed position within the hull; and releasing the vertical takeoff and landing vehicle 2412 from the substantially fixed position under takeoff pressure.

[0257] Of course, the aspects presented may be implemented in ways different from those specifically set forth herein without departing from the essential characteristics of this disclosure. The aspects of the invention are to be considered illustrative rather than restrictive in all respects, and all variations within the meaning and scope of the appended claims are intended to be included therein.

Claims

1. A device (32, 41a, 41b, 90a, 90b, 100a, 100b, 110, 120, 130, 140, 150, 160, 170, 180, 190) for stabilizing the takeoff and landing of a vertical takeoff and landing vehicle, said device comprising: Vertical directional support elements (42, 91, 141, 151, 161, 171, 181), wherein the vertical directional support element comprises: The first end of the vertically oriented support element (42a, 91a, 141a, 151a, 161a, 171a, 181a); and The second end of the vertical orientation support element (42b, 91b, 141b, 151b, 161b, 171b, 181b) extends from the first end of the vertical orientation support element to the second end of the vertical orientation support element, and the vertical orientation support element further includes at least one first cooperative stabilizing element near the second end of the vertical orientation support element. Housings (174, 194, 204, 214, 254), the dimensions of which are designed substantially around at least one vertically oriented support element. The at least one first cooperative stabilizing element includes at least one of the following: a convex attachment portion (62a, 62b, 62c, 62d, 62e) and a concave attachment portion (52a, 52b, 52c, 52d, 52e, 52f). The housing includes at least one movable housing plate (176, 196), which is positioned near the first end of the vertically oriented support element. The device further includes: A detector (177a) is used to detect pressure in at least a local area of ​​the housing; Controller (177b), the controller (177b) being connected to the detector; and An actuator (177d) is connected to the controller and also to a drive mechanism, which is also connected to the at least one movable housing plate.

2. The apparatus according to 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 about 4 feet to about 100 feet.

3. The apparatus according to claim 1 or 2, wherein, The at least one first cooperative stabilizing element is configured to extend outward from the vertically oriented support element.

4. The apparatus according to claim 1, further comprising guides (142, 152, 172, 182) communicating with the second end of the vertical orientation support element, and the guides also communicating with the at least one first cooperative stabilizing element.

5. The apparatus according to claim 1, further comprising: Frames (93a, 93b, 93c, 143a, 143b, 173a, 173b), the frames comprising: Multiple vertically oriented support elements (42, 91, 141, 151, 161, 171, 181), wherein the multiple vertically oriented support elements are spaced apart from each other by a certain distance; and At least one circumferential frame support (93a, 93b, 93c, 143a, 143b, 173a, 173b), said at least one circumferential frame support being in communication with one or more of the plurality of vertically oriented support elements. The dimensions of the housing are designed to substantially surround the frame.

6. The apparatus according to claim 5, wherein, The frame is configured to support at least one of the plurality of vertically oriented support elements.

7. The apparatus according to claim 5, further comprising: The base is configured to support the frame.

8. The apparatus according to claim 7, wherein, The base is connected to at least one of the plurality of vertically oriented support elements.

9. The apparatus according to claim 5, 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 according to claim 1, further comprising: A horizontally positioned platform (130) connected to the vertically oriented support element, the horizontally positioned platform including a rigid floor, the rigid floor including a mesh material, the mesh material including mesh specifications selected to facilitate airflow through the rigid floor; and A drive mechanism (134) is connected to the horizontally positioned platform. The drive mechanism is configured to raise and lower the platform at the horizontal setting.

11. The apparatus according to claim 5, further comprising: A horizontally positioned platform, the horizontally positioned platform being in communication with at least one of the plurality of vertically oriented support elements, the horizontally positioned platform including a rigid floor, the rigid floor including a mesh material, the mesh material including mesh specifications selected to facilitate airflow through the rigid floor; as well as The drive mechanism is connected to the horizontally positioned platform. The drive mechanism is configured to raise and lower the horizontally positioned platform from a first position to a second position.

12. A method (2400) for assisting the takeoff of a vertical takeoff and landing vehicle, the method comprising the following steps: Provided (2402) at least partially enclosed vertical take-off and landing (VTOL) device, said VTOL device comprising: At least one vertically oriented support element having a first end and a second end, the first end being close to a base, the second end extending from the first end to the second end, the second end located at a selected distance away from the first end, and the vertically oriented support element including a first cooperative stabilizing element positioned close to the second end; and The housing, the dimensions of which are designed substantially around the at least one vertically oriented support element. The housing includes at least one movable housing plate, which is positioned near the first end of the vertically oriented support element. The vertical take-off and landing device further includes: A detector for detecting pressure in at least a local area of ​​the housing; A controller, which is connected to the detector; and An actuator, which is connected to the controller and also connected to a drive mechanism, which is also connected to the at least one movable housing plate; Provided (2404) a vertical takeoff and landing vehicle, the vertical takeoff and landing vehicle including at least one second cooperative stabilizing element, the second cooperative stabilizing element being sized to engage with the first cooperative stabilizing element; The first cooperative stabilizing element of the vertical directional support element (2406) is connected to the second cooperative stabilizing element of the vertical take-off and landing vehicle; The pressure in at least a region of the housing is increased from ambient pressure (2408) to takeoff pressure, which is greater than the ambient pressure, and the region of the housing is close to the vertical takeoff and landing vehicle; During the pressure increase, the vertical take-off and landing vehicle is maintained (2410) in a substantially fixed position within the housing; and Under the takeoff pressure, the vertical takeoff and landing vehicle is released (2412) from the basically fixed position.

Images