Aerial vehicle securing system and method

Technical Field The subject matter of the present disclosure relates to systems and methods for immobilizing objects, and more specifically for systems and methods for capturing and immobilizing aircraft.

Background Various aircraft, such as manned and unmanned VTOL (Vertical Takeoff and Landing) aircraft, have become more important in recent years to perform both military and civil operations where current runways are not available. In various scenarios, it is required that the aircraft land on the landing platform and restart from the landing platform. The landing platform can be located on or part of the deck of the ship, or can be any other mobile vehicle on land.

For example, U.S. Patent Application Publication No. 2015/0239578 discloses devices and systems for launching and recovering hovering aircraft. The device of the present disclosure captures a hovering aircraft between two or more fingers of an aircraft capture device, guides the captured aircraft for service and / or storage to a docking station, and launches the aircraft from the docking station. It is configured as follows. The device is configured to move the aircraft from an inaccurate and anomalous hovering state to a safe and well-controlled hibernation.

<p>Schematic Description According to one aspect of the subject matter of the present disclosure, an aircraft fixation system for sharing with the base of an aircraft is provided, which is at least one substantially flat platform. When the aircraft landed on the platform, at least one substantially flat platform supporting the base and at least one magnetization configured to be incorporated into one of the platform and the base. A possible element and at least one electric permanent magnet configured to be incorporated into the other of the platform and the base portion, the electric permanent magnet being configured to generate a magnetic field, wherein the aircraft is said to have said. In the process of landing on the platform, when the distance between the base and the platform reaches a predetermined value, the magnetic field attracts the at least one magnetizable element to the at least one electric permanent magnet. An electric permanent magnet and a power supply module configured to generate a current to the at least one electric permanent magnet in order to selectively generate or cancel the magnetic field. It includes a control module configured to control the supply of the current.</p><p> The aircraft fixation system of the subject matter of the present disclosure is configured to be used to capture and anchor an aircraft landing on a stationary or mobile platform. The platform can be attached to, placed on, or part of any known object on which the aircraft normally accretes. The object can be, for example, the landing deck of a ship, a land vehicle, or any other aircraft carrier known in the art. Aircraft fixation systems use the magnetic forces generated by electric permanent magnets to easily capture and fix the aircraft without human intervention or with minimal human intervention, based on their respective commands to counteract these magnetic forces. Easily release the aircraft.</p><p> The electric permanent magnet of the subject of the present disclosure is a type of permanent magnet capable of switching the external magnetic field on or off by passing a current pulse through a wire wound around a part of the magnet. The magnet consists of two sections, one is a "hard" (high holding force) permanent magnet material and the other is a "soft" (low holding force) permanent magnet material. The magnetization direction of the other piece can be switched by passing a current pulse through the wire wound around the piece. When the magnetic soft and hard materials are magnetized in opposite directions, the electric permanent magnet does not generate a net external magnetic field between its magnetic poles, while when the directions of magnetization are aligned, the electric permanent magnet creates a magnetizable element. Generates an external magnetic field that can be attracted. The magnetic field generated by the electric permanent magnet is generated independently of the electric current, which is a major difference from the electromagnet. At the same time, the electric permanent magnets are very strong, do not generate heat and have no moving parts. Electric permanent magnets use only current pulses to magnetize sections made of "soft" (low holding force) permanent magnet material in the desired direction. After switching the direction of magnetization, no current is needed. Therefore, electric permanent magnets are efficient in terms of energy consumption and most of the time do not require electrical energy to generate an external magnetic field. The use of electric permanent magnets is also convenient when used in areas susceptible to magnetic fields. For example, if the platform is mounted on the deck of a ship, the magnetic fields generated by the electric permanent magnets can be easily canceled when the aircraft does not need to be fixed. However, when the aircraft arrives, the magnetic field can be quickly and easily generated by the electric permanent magnets based on their respective commands. Electric permanent magnets can also be used by fixing different types of aircraft without making specific changes for each type of aircraft.</p><p> The aircraft fixation system allows the aircraft to be captured in close proximity to the aircraft fixation system without the use of any moving elements, sufficient to allow the aircraft to land and anchor at various locations in the aircraft fixation system. Can be widely constructed. This is the process of landing and fixing the aircraft without having to estimate the state of the platform and / or the aircraft at any given time to orient the landing aircraft currently approaching the platform. Can be simplified.</p><p> In the following, the term "aircraft" is configured to land on a support platform by its own landing system or an external landing support system, such as aircraft, VTOLs, helicopters, unmanned aerial vehicles, drones, spacecraft and land vehicles. Refers to any vehicle known in the art, which may be, etc. The base of the aircraft can be any of the following: skids, wheels, underside support members, legs, etc.</p><p> According to a particular example, at least one electric permanent magnet is incorporated into the platform, and at least one magnetizable element is incorporated into the base. According to a further specific example, the electric permanent magnet and the platform are incorporated into a single member.</p><p> The aircraft fixation system may further comprise the platform, the at least one magnetizable element and at least one shock absorbing member coupled to at least one of the at least one electric permanent magnet.</p><p> One or more shock absorbing members may be integral with the magnetizable element or platform.</p><p> The aircraft fixation system is connected to at least one of the at least one magnetizable element and the at least one of the electric permanent magnets, and the angle between the contact surface of the magnetizable element and the contact surface of each electric permanent magnet. Further, at least one pivot member configured to swivel spatially to minimize can be provided.</p><p> At least one pivot member can include the magnetizable element or the electric permanent magnet. In a particular example where an aircraft fixation system has one or more pivot members, each provided with a magnetizable element, in a scenario where the aircraft landed on the platform in an angled orientation, by turning. It is understood that magnetizable elements that come into contact with the platform can be easily and quickly magnetically attracted, which facilitates fixation of the entire aircraft to the platform.</p><p> The shock absorbing member and the pivot member can be incorporated into a single absorption-score member.</p><p> The control module may be configured to receive a release command, and upon receiving the release command, the control module may be configured to instruct the power supply module to generate an electric current in order to cancel the magnetic field. .. The release command can be sent wirelessly to the control module.</p><p> The release command may be configured to be generated when a predetermined threshold parameter indicating the number of revolutions per minute (RPM) of the aircraft motor is exceeded.</p><p> At least one magnetizable element may be composed of two or more magnetizable elements incorporated at the base and symmetrically on two opposite sides of the center of gravity of the aircraft or with respect to the longitudinal axis of the aircraft.</p><p> The platform can be folded.</p><p> The platform may include a moving mechanism that moves the platform with the aircraft while it is fixed to the platform.</p><p> At least one magnetizable element can be a ferromagnetic element or an electromagnet element.</p><p> At least one electric permanent magnet can be provided with an upper plane. The top plane can be substantially parallel to the bottom surface of the platform. The flatness of the top surface of the electric permanent magnet gives the aircraft the ability to land in any particular position without exactly landing in a particular given location or position, which is a real difficulty for the aircraft to land. It can be extremely important in conditions such as wind, rain, unstable platforms of ships at sea, limited visibility, etc.</p><p> At least one electric permanent magnet or said platform may include one or more range limiting portions extending from its top surface in order to limit the range of movement of the base portion.</p><p> The top surface of at least one electric permanent magnet can be characterized by a coefficient of friction greater than the coefficient of friction of the outer surface of the at least one magnetizable element.</p><p> According to another aspect of the subject matter of the present disclosure, a method of fixing an aircraft having a base portion by an aircraft fixation system is provided, wherein the method is at least one substantially flat platform, wherein the aircraft is said. When landing on the platform, at least one substantially flat platform for supporting the base and at least one magnetizable element configured to be incorporated into one of the platform and the base. , At least one electric permanent magnet configured to be incorporated into the other of the platform and the base portion, configured to generate a magnetic field in the electric permanent magnet, and the aircraft landing on the platform. At least one magnetizable element is attracted to the at least one electric permanent magnet by the magnetic field when the distance between the base and the platform reaches a predetermined value in the process of A step of providing the aircraft fixation system comprising an electric permanent magnet, a power supply module, and a control module. When the aircraft is fixed to the platform by the magnetic field, the control unit directs the power source to supply an electric current to the electric permanent magnet in order to cancel the magnetic field.</p><p> The method receives a release command in the control module, and upon receiving the release command, performs the step of instructing the power supply by the control unit to supply an electric current to the electric permanent magnet in order to cancel the magnetic field. Further steps can be provided.</p><p> The release command may be configured to be generated when a predetermined threshold parameter indicating the number of revolutions per minute (RPM) of the aircraft motor is exceeded.</p><p> In order to better understand the subject matter disclosed herein and to illustrate how the subject matter can be practiced in practice, embodiments may be made with reference to the accompanying drawings, using only non-limiting examples. It will be explained below.</p>

A brief description of the drawing<figref num="1A">FIG. 5 is a perspective view of an aircraft fixation system according to an example of the subject matter of the present disclosure, wherein the aircraft is anchored to the aircraft fixation system.</figref><figref num="1B">It is the bottom perspective view of the aircraft of FIG. 1A.</figref><figref num="2">It is a bottom perspective view of another aircraft fixed by the aircraft fixation system of FIG. 1A.</figref><figref num="3">It is a perspective view of an aircraft fixation system according to another example of the subject matter of the present disclosure, in which the aircraft is anchored to the aircraft fixation system.</figref>

Detailed Description of the Embodiment First, attention will be paid to FIGS. 1A and 1B, which are diagrams showing an example of the aircraft fixing system of the subject of the present disclosure shown in 1 as a whole together with the aircraft 10.

The aircraft fixation system 1 is configured to be used to anchor an aircraft 10 that has landed on a stationary or moving platform using magnetic force. The aircraft fixation system 1 comprises a substantially flat platform 20 that can be attached to, placed on, or part of any known object (not shown) on which the aircraft normally landed. .. The object can be, for example, the landing deck of a ship, a land vehicle, or any other aircraft carrier known in the art. According to the example in Figure 1A, platform 20 is located on the ship's landing deck 2. As described in detail below, the aircraft fixation system 1 uses the magnetic forces generated by the electric permanent magnets to easily capture and fix the aircraft 10, based on their respective commands to counteract these magnetic forces. Easily release the aircraft 10 without human intervention or with minimal human intervention.

Aircraft 10 shown in FIGS. 1A and 1B is a schematic representation of a UAV (unmanned aerial vehicle) having a base in the form of three legs 12. The platform 20 is configured to support the legs 12 when the aircraft 10 landed on the platform 20.

In addition to the platform 20, the aircraft fixation system has three magnetizable elements in the form of a ferromagnetic plate 16 (shown in FIG. 1B) connected to the tip 18 of the leg 12 and a single member platform 20. It further includes a built-in electric permanent magnet 22, a power supply module 30, and a control module 40.

As shown in FIG. 1A, the electric permanent magnet 22 has an upper plane 22'. The top plane 22 is parallel to the bottom surface of the platform 20. The flatness of the top surface 22'provides the ability of the aircraft 10 to land at any particular location without accurately landing at a particular location or location, which is a real difficulty for the aircraft to land. It can be extremely important in conditions (eg wind, rain, unstable platforms of ships at sea, limited visibility, etc.). The platform 20 has a range limiting portion 21 extending from its upper surface in order to limit the range of movement of the tip portion 18. According to a particular example, the top surface 22'can be characterized by a coefficient of friction greater than the coefficient of friction of the outer surface of the ferromagnetic plate 16.

The electric permanent magnet 22 is configured to magnetically attract the ferromagnetic plate 16 and thereby generate a magnetic field to secure the aircraft 10 to the platform 20. The magnetic field generated by the electric permanent magnet 22 causes the magnetic field to press the ferromagnetic plate 16 when the distance between the tip 18 and the platform 20 reaches a predetermined value of, for example, 5 mm during landing on the platform 20 of the aircraft 10. It is configured to be magnetically attracted to the electric permanent magnets 22, thereby facilitating the accretion process and the fixation of the aircraft 10 to the platform 20. The electric permanent magnet 22 of the subject of the present disclosure is a type of permanent magnet capable of switching on or off an external magnetic field by passing a current pulse through a wire wound around a part of the magnet. The magnet consists of two sections, one is a "hard" (high holding force) permanent magnet material and the other is a "soft" (low holding force) permanent magnet material. The magnetization direction of the other piece can be switched by passing a current pulse through the wire wound around the piece. When the magnetic soft and hard materials are magnetized in opposite directions, the electric permanent magnet 22 does not generate a net external magnetic field between its magnetic poles, while when the magnetization directions are aligned, the electric permanent magnet 22 is ferromagnetic. Generates an external magnetic field that can attract the plate 16. The magnetic field generated by the electric permanent magnet 22 is generated independently of the electric current, which is a major difference from the electromagnet. Therefore, the electric permanent magnet 22 is very strong, does not generate heat, and has no moving parts. The electric permanent magnet 22 uses only current pulses to magnetize a section made of "soft" (low holding force) permanent magnet material in the desired direction. After switching the direction of magnetization, no current is needed. Therefore, the electric permanent magnet 22 is efficient in terms of energy consumption and most of the time does not require electrical energy to generate an external magnetic field. The use of the electric permanent magnet 22 is also convenient when used in a region susceptible to a magnetic field. For example, platform 20 is mounted on the deck of a ship If so, the magnetic field generated by the electric permanent magnet 22 can be easily canceled when the aircraft does not need to be fixed. However, when the aircraft arrives, the magnetic field can be quickly and easily generated by the electric permanent magnets 22 based on their respective commands.

The electric permanent magnet 22 communicates with the power supply module 30, and the power supply module 30 is configured to generate a current pulse to the electric permanent magnet 22 in order to selectively generate and cancel the external magnetic field. There is. The control module 40 telecommunications with the power supply module 30 to control the supply of current.

For example, control module 40 is configured to receive fixed commands from an operator or another source before aircraft 10 landed on platform 20. Upon receiving a fixed command, the control module 40 is configured to generate a current pulse to the electric permanent magnet 22 to generate an external magnetic field. As a result, the electric permanent magnet 22 is ready to accept the aircraft 10 in order to fix the aircraft by an external magnetic field when the aircraft 10 lands.

When the aircraft 10 is fixed to an electric permanent magnet 22, the control module 40 is configured to receive a release command from the operator or another source. Upon receiving the release command, the control module 40 is configured to instruct the power supply module 30 to generate a current pulse to cancel the external magnetic field, thereby allowing the aircraft to take off. Fixed commands and / or release commands can be sent wirelessly to the control module 40.

According to a particular example, the release command can be generated when a predetermined threshold parameter indicating the number of revolutions per minute (RPM) of an aircraft motor is exceeded. For example, if an aircraft is about to take off and its engine is running, a release command can be sent from the aircraft to control unit 40. The threshold parameter can be a particular engine force that takes off the aircraft 10 and disconnects it from the electric permanent magnet 22. If this engine power is greater than a certain threshold, the release command is automatically generated and can be received by the control unit 40, then cancels the external magnetic field.

According to another example not shown in the drawings, the electric permanent magnets 22 can consist of an array of electric permanent magnets. The electric permanent magnets can be arranged at equal intervals from each other.

Each one of the legs 12 has a shock absorbing member in the form of a pistol.

Each one of the tips 18 is a pivot member configured to rotate 3D with respect to the rest of the leg 12. Therefore, the tip 18 spatially swivels when the aircraft 10 landed on the electric permanent magnets 22 to create an angle between the contact surface of each ferromagnetic plate 16 and the top surface 22'of the electric permanent magnets 22. It is configured to be minimized.

According to the examples of FIGS. 1A and 1B, in a scenario where the aircraft 10 landed on the electric permanent magnet 22 in an angled orientation, the tip 18 swivels to facilitate the ferromagnetic plate 16 in contact with the platform. It is understood that it will be possible to quickly and magnetically attract, which will facilitate the fixation of the aircraft 10 to platform 20.

The ferromagnetic plate 16 is arranged such that the center of gravity of the aircraft 10 is located between them at equal distances from each one of the ferromagnetic plates 16. Placing the ferromagnetic plate 16 in such an manner with respect to the center of gravity of the aircraft 10 allows the aircraft 10 to be properly secured to the platform 20.

Although not shown, the platform 20 can be folded and housed in the body to which it is attached. As shown in FIG. 3, the platform 20 may also include a movement mechanism in the form of wheels 80 for moving the platform 20 with the aircraft while fixed to the platform. The moving mechanism further comprises a pulling member 85 for pulling the platform 20 to another location with the fixed aircraft.

According to another example, the magnetizable element can be an electromagnet element, which can be magnetically attracted to the permanent magnet 22 when an electric current is being applied.

Now refer to FIG. 2 where the aircraft 110 is shown. Aircraft 110 is a schematic of a helicopter having a base in the form of two skids 112. Platform 20 is configured to support the skid 112 when the aircraft 110 landed on platform 20.

Aircraft 110 also has 18 magnetizable elements in the form of ferromagnetic plate 116. Each of the nine ferromagnetic plates 116 is connected to each skid of the skid 112. Aircraft 110 is configured to land on platform 20 and be magnetically anchored to an electric permanent magnet 22 when an external magnetic field is generated. Therefore, both aircraft 110 and 10 can be shared with platform 20 and secured by electric permanent magnets 22. The ferromagnetic plate 116 can be arranged such that the center of gravity of the aircraft 110 is located between the ferromagnetic plates 116.

Placing the ferromagnetic plate 116 in such an manner with respect to the center of gravity of the aircraft 110 allows the aircraft 110 to be properly secured to the platform 20.