Patent Description:
Heat productivity is large during the working period of a lift motor and an electronic speed controller of an existing vertical takeoff and landing unmanned aerial vehicle, but an arm structure of the existing unmanned aerial vehicle is mostly a closed cavity structure which is not conducive to diffusion of hot air. There is generally no heat dissipation for equipment in the arm during the working period of the lift motor and the electronic speed controller of the existing vertical takeoff and landing unmanned aerial vehicle, which causes a certain influence on the equipment in the arm. There is no special equipment for the heat dissipation of the equipment in the arm during the working period of the lift motor and the electronic speed controller of the existing vertical takeoff and landing unmanned aerial vehicle. <CIT> relates to a rotor mounting boom assembly for a personal aircraft. <CIT> relates to a flying platform with detachable and interchangeable cabins.

The invention relates to a vertical takeoff and landing unmanned aerial vehicle and a cooling system for the unmanned aerial vehicle, which are used for solving the problem that an arm of the unmanned aerial vehicle is poor in heat dissipation.

The invention provides a vertical takeoff and landing unmanned aerial vehicle, which comprises:.

The opening is formed as a trumpet-shaped structure, wherein the radial sectional area of one end, toward the hollow interior, of the opening is less than the radial sectional area of one end, away from the hollow interior, of the opening.

In one embodiment of the invention, the unmanned aerial vehicle further comprises a fan which is arranged in the hollow interior of each of the left linear support and the right linear support.

In one embodiment of the invention, the fan is arranged close to the forward-facing opening to promote air circulation in the hollow interior.

In one embodiment of the invention, the fan is a ducted fan.

In one embodiment of the invention, the unmanned aerial vehicle further comprises motors of the first group of multiple lift propellers and the second group of multiple lift propellers, wherein the motors are arranged in the hollow interiors.

In one embodiment of the invention, the unmanned aerial vehicle further comprises an exhaust port provided at a position close to the tail end of each of the left linear support and the right linear support, thereby allowing air to flow from the hollow interior to an external environment.

In one embodiment of the invention, a plurality of exhaust ports are provided at the left linear support and the right linear support respectively, each exhaust port is in a shape of oblong, the plurality of exhaust ports on the left linear support are arranged around the axis of the left linear support in a spaced manner, and the plurality of exhaust ports on the right linear support are arranged around the axis of the right linear support in a spaced manner.

In one embodiment of the invention, the front end of each of the left linear support and the right linear support is of a circular truncated cone structure, and the opening is provided at the upper bottom face of the circular truncated cone structure; the tail end of each of the left linear support and the right linear support is of a conical structure, and the length directions of the exhaust ports are provided along a generatrix of the conical structure in a spaced manner.

In one embodiment of the invention, the unmanned aerial vehicle further comprises a detachable pod attached to the bottom face of the unmanned aerial vehicle.

In one embodiment of the invention, the pod is a passenger pod or a cargo pod.

In one embodiment of the invention, a rotating shaft of the fan is perpendicular to a rotating shaft of each lift propellers of the plurality of lift propellers.

In one embodiment of the invention, the unmanned aerial vehicle further comprises at least one propulsion propeller arranged on the unmanned aerial vehicle.

In one embodiment of the invention, a diameter of the forward-facing opening is greater than a radius of each of the left linear support and the right linear support.

The invention further provides a cooling system for an unmanned aerial vehicle, which comprises:.

In one embodiment of the invention, the fan is arranged at a position close to the front end of the linear support.

In one embodiment of the invention, the linear support is in a straight configuration.

In one embodiment of the invention, the cooling system further comprises at least one exhaust port which is further provided on the linear support to allow the air to escape from the interior of the linear support.

The invention provides a vertical takeoff and landing unmanned aerial vehicle according to claim <NUM>.

According to the vertical takeoff and landing unmanned aerial vehicle provided by the invention, by providing a forward-facing opening at the front end of each of the left linear support and the right linear support, the air may enter the interior of the left linear support from the opening at the front end of the left linear support and flows out from connection gaps between the left linear support and other components and parts in the forward flight process of the unmanned aerial vehicle, and may enter the interior of the right linear support from the opening at the front end of the right linear support and flows out from connection gaps between the right linear support and other components and parts in the forward flight process of the unmanned aerial vehicle, the heat in the interiors of the left linear support and the right linear support is taken away through the flowing of the air, and the heat dissipation in the arm, i.e., the linear support, of the unmanned aerial vehicle is realized, thereby achieving the purposes of lowering temperature in the arm and protecting equipment in the arm.

Many implementations have been described. However, it should be understood that various modifications may be made without departing from the scope of the appended claims.

For example, the example operations, methods, or processes described herein may comprise more steps or less steps than those described. In addition, the steps in these example operations, methods, or processes may be performed in different alternative ways than those described or illustrated in the figures.

The details of one or more implementations of a subject matter described in the invention are set forth in the accompanying drawings and the description below. Other features, aspects and advantages of the subject matter will become apparent in accordance with the specification, the accompanying drawings, and the technical solutions.

It should be noted that the accompanying drawings may be in simplified form and may not be precise in scale. With reference to the disclosure herein, for purposes of convenience and clarity only, directional terms such as top, bottom, left, right, up, down, upper side, above, beneath, below, rear portion, front portion, distal end, and proximal end are used with reference to the accompanying drawings. These directional terms should not be construed to limit the scope of the embodiments in any way.

Where reference is made to components with reference numerals, like parts are denoted by the same reference numerals throughout the accompanying drawings of the specification:
<NUM>-unmanned aerial vehicle; <NUM>-flight platform; <NUM>-main body; 103A-left linear support; 103B-right linear support; 104A-left main wing; 104B-right main wing; 105A-left front wing; 105B-right front wing; 106A-left vertical stabilizer; 106B-right vertical stabilizer; <NUM>-propulsion propeller; 107A-left propulsion propeller; 107B-right propulsion propeller; 108A-first lift propeller; 108B-second lift propeller; 108C-third lift propeller; 108D-fourth lift propeller; 108E-fifth lift propeller; 108F-sixth lift propeller; 109A-left wingtip propeller; 109B-right wingtip propeller; 110A-left wingtip vertical stabilizer; 110B-right wingtip vertical stabilizer; 111A-left folding leg; 111B-right folding leg; 112A-first leaf spring; 112B-second leaf spring; 112C-third leaf spring; 112D-fourth leaf spring; <NUM>-vertical expander; <NUM>-central propulsion propeller; <NUM>-cargo pod; 135A-first pod leaf spring; 135B-second pod leaf spring; 135C-third pod leaf spring; 135D-fourth pod leaf spring; <NUM>-passenger pod; 145A-pod leg; 145B-pod leg; 145C-pod leg; 145D-pod leg; <NUM>-pod-attaching latch; <NUM>-electric wheel; <NUM>-shell; <NUM>-energy storage unit in flight platform; <NUM>-energy storage unit in pod; <NUM>-flotation device; <NUM>-fan; <NUM>-motor; <NUM>-opening; <NUM>-electronic speed controller; <NUM>-exhaust port; <NUM>-aileron; A-airflow direction; B-air inlet direction; C-air outlet direction.

Different aspects of various embodiments may now be better understood by turning to the following detailed description of the embodiments, which are presented as illustrative examples of the embodiments defined in the technical solutions. It is expressly understood that the embodiments defined by the technical solutions may be broader than the illustrated embodiments described below.

The words used in the specification to describe the various embodiments should be understood to not only have commonly defined meanings thereof, but, in structures, materials, or actions in the specification, to include special definitions beyond the scope of the generally defined meanings. Hence, if a component may be understood in the context of the specification to include more than one meaning, its use in the technical solution must be understood to be general for all possible meanings supported by the specification and the words themselves.

The term "unmanned aerial vehicle" is defined as a flight transportation system with at least one propeller as one propulsion source. The term "unmanned aerial vehicle" may comprise both "manned" and "unmanned" flight transportation systems. The "manned" unmanned aerial vehicle may refer to a flight transportation system that carries human passengers, none of which has right of control over the unmanned aerial vehicle. The "manned" unmanned aerial vehicle may also refer to a flight transportation system that carries human passengers, with some or one of the human passengers having a certain right of control over the unmanned aerial vehicle.

As the background, during the working period of a lift motor and an electronic speed controller of an existing vertical takeoff and landing unmanned aerial vehicle, there is no special equipment for heat dissipation of equipment in an arm, thus causing a certain influence on the equipment in the arm. To solve the problem that an arm of an unmanned aerial vehicle is poor in heat dissipation, the invention provides a vertical takeoff and landing unmanned aerial vehicle, which comprises: a left main wing and a right main wing; a left front wing and a right front wing; a main body which is engaged with the left main wing and the right main wing; a left linear support for connecting the left main wing with the left front wing; a right linear support for connecting the right main wing with the right front wing; the left linear support having a first group of multiple lift propellers arranged thereon; the right linear support having a second group of multiple lift propellers arranged thereon, wherein the left linear support and the right linear support each have a hollow interior; and a forward-facing opening which is provided at the front end of each of the left linear support and the right linear support.

The technical solutions of the invention will be described below in detail in conjunction with specific accompanying drawings.

<FIG> is a top perspective view of an embodiment of a VTOL (vertical takeoff and landing) unmanned aircraft system in accordance with one aspect of an embodiment; <FIG> is a top perspective view of an embodiment of a VTOL unmanned aircraft system in accordance with still another aspect of an embodiment; <FIG> is a top perspective view of an embodiment of a VTOL unmanned aircraft system in accordance with still another aspect of an embodiment; <FIG> is a side view illustrating a forward-facing opening of an unmanned aircraft system in accordance with one aspect of an embodiment; <FIG> is a sectional view of a side portion of an unmanned aircraft system in accordance with one aspect of an embodiment; <FIG> is a sectional view of a side portion of an unmanned aircraft system in accordance with still another aspect of an embodiment; <FIG> is a top perspective view of an embodiment of a VTOL unmanned aircraft system in accordance with one aspect of an embodiment; <FIG> is a top rear perspective view of the unmanned aircraft system of <FIG>; <FIG> is a side view of the unmanned aircraft system of <FIG>; <FIG> is a top perspective view of another embodiment of a VTOL unmanned aircraft system with a flight platform and a detachably attached pod in accordance with one aspect of the embodiment; <FIG> is a top view of the unmanned aircraft system of <FIG> in accordance with one aspect of the embodiment; <FIG> is a front view of the unmanned aircraft system of <FIG> in accordance with one aspect of the embodiment; <FIG> is a top perspective view of an embodiment of a VTOL unmanned aircraft system with a flight platform and a detachably attached passenger pod in accordance with one aspect of the embodiment; <FIG> is a front view of the unmanned aircraft system of <FIG> in accordance with one aspect of the embodiment; <FIG> is a rear perspective view of the unmanned aircraft system of <FIG> in accordance with one aspect of the embodiment; <FIG> is a side perspective view of the unmanned aircraft system of <FIG> in accordance with one aspect of the embodiment, wherein the passenger pod is detached from the flight platform and parked on the ground; <FIG> is a rear perspective view of the embodiment of <FIG> in accordance with one aspect of the embodiment; <FIG> is a rear perspective view of another embodiment in accordance with one aspect of the embodiment; <FIG> is a side bottom perspective view of still another embodiment of an unmanned aircraft system in accordance with one aspect of the embodiment; <FIG> is a perspective view of one embodiment of an unmanned aircraft system in accordance with another aspect of the embodiment; <FIG> is a close-up view of an encircled region in <FIG> in accordance with another aspect of the embodiment; <FIG> is a side view of one embodiment of an unmanned aircraft system in accordance with another aspect of the embodiment; <FIG> is a front view of one embodiment of an unmanned aircraft system in accordance with another aspect of the embodiment; <FIG> is a rear view of one embodiment of an unmanned aircraft system in accordance with another aspect of the embodiment; <FIG> is an upward view of one embodiment of an unmanned aircraft system in accordance with another aspect of the embodiment; <FIG> is a perspective view of another embodiment of a flight platform in accordance with another aspect of the embodiment; <FIG> is a side view of another embodiment of a flight platform in accordance with another aspect of the embodiment; <FIG> is a front view of another embodiment of a flight platform in accordance with another aspect of the embodiment; <FIG> is a rear view of another embodiment of a flight platform in accordance with another aspect of the embodiment; <FIG> is an upward view of another embodiment of a flight platform in accordance with another aspect of the embodiment; <FIG> is a side view of another embodiment of a passenger pod in accordance with another aspect of the embodiment; <FIG> is a bottom perspective view of another embodiment of a passenger pod in accordance with another aspect of the embodiment; <FIG> is a front view of another embodiment of a passenger pod in accordance with another aspect of the embodiment; <FIG> is a rear view of another embodiment of a passenger pod in accordance with another aspect of the embodiment; <FIG> is an upward view of another embodiment of a passenger pod in accordance with another aspect of the embodiment; <FIG> is a side view of another embodiment of a flight platform attached to a cargo pod in accordance with another aspect of the embodiment; <FIG> is a perspective view of another embodiment of a flight platform without a propulsion propeller in accordance with another aspect of the embodiment; <FIG> is a side view of another embodiment of a passenger pod with a propulsion propeller in accordance with another aspect of the embodiment; <FIG> is a perspective view of still another embodiment of an unmanned aircraft system, wherein six flotation devices are inflated; <FIG> is a side view of the unmanned aerial vehicle of <FIG>; <FIG> is a side sectional view of an unmanned aerial vehicle with a cooling system in accordance with an embodiment of the invention; <FIG> is a view illustrating a configuration of an aileron of an unmanned aerial vehicle.

<FIG> is a top perspective view of an embodiment of a VTOL unmanned aircraft system in accordance with one aspect of an embodiment. The unmanned aerial vehicle <NUM> at least comprises: a left main wing 104A and a right main wing 104B; a left front wing 105A and a right front wing 105B; a main body <NUM> which is engaged with the left main wing 104A and the right main wing 104B; a left linear support 103A for connecting the left main wing 104A with the left front wing 105A; a right linear support 103B for connecting the right main wing 104B with the right front wing 105B, the left linear support 103A having a first group of multiple lift propellers 108A, 108B, 108C arranged thereon; the right linear support 103B having a second group of multiple lift propellers 108D, 108E, 108F arranged thereon; wherein the left linear support 103A and the right linear support 103B each have a hollow interior; and a forward-facing opening <NUM> which is provided at the front end of each of the left linear support 103A and the right linear support 103B.

By adopting a vertical takeoff and landing unmanned aerial vehicle provided by the invention, heat dissipation in an arm of the unmanned aerial vehicle is realized by providing a forward-facing opening at the front end of each of a left linear support and a right linear support, thereby achieving the purposes of lowering the temperature in the arm and protecting equipment in the arm.

Preferably, as shown in <FIG> and <FIG>, the radial sectional area of the right end of the opening <NUM>, i.e., one end toward the hollow interior, is less than the radial sectional area of the left end of the opening <NUM>, i.e., one end away from the hollow interior, that is, the opening <NUM> is formed as a trumpet-shaped structure. It may be understood by those skilled in the art that the sectional area gradually decreases as air passes through the opening <NUM> to enter the hollow interior, the volume of the air is compressed as it passes through the opening <NUM>, and a flow rate increases to increase the flow rate of the air in the hollow interior, thus increasing the cooling efficiency of the linear support.

<FIG> depicts an embodiment of a VTOL unmanned aerial vehicle <NUM> with a front wing configuration in general.

The various part features of the unmanned aerial vehicle <NUM> in the various embodiments shown in the accompanying drawings, which are illustrative only, may be flexibly combined to form an unmanned aerial vehicle with a new structure.

The unmanned aerial vehicle <NUM> in <FIG> may have two main wings 104A, 104B as a left main wing and a right main wing, and two front wings as a left front wing 105A and a right front wing 105B. The two main wings 104A, 104B and the two front wings 105A, 105B may be attached to a main body <NUM>, wherein the main body may be positioned along a central longitudinal line of the unmanned aerial vehicle <NUM>. The unmanned aerial vehicle <NUM> may also have a left linear support 103A arranged parallel to the main body <NUM>, which may connect the left main wing 104A to the left front wing 105A. Similarly, the unmanned aerial vehicle <NUM> may also have a right linear support 103B arranged parallel to the main body <NUM>, which may connect the right main wing 104B to the right front wing 105B. Wherein, the front wings of the unmanned aerial vehicle mainly control a flight attitude of an unmanned aerial vehicle during the flight period, such as controlling the pitch of the unmanned aerial vehicle. The main wings of the unmanned aerial vehicle, acting as the largest wings at two sides of a fuselage, are usually used for generating lift to support the unmanned aerial vehicle to fly in the air, and meanwhile, certain stabilization and manipulation effects are achieved.

In still another embodiment, the unmanned aerial vehicle <NUM> may also not have the front wing configuration. Illustratively, the unmanned aerial vehicle <NUM> may have two main wings as a left main wing and a right main wing, and two ailerons as a left aileron and a right aileron, all of which are engaged together to form a flight platform.

In one embodiment, as shown in <FIG>, the aileron <NUM> of the unmanned aerial vehicle may be arranged at a rear side of the main wing 104B, there may be at least one aileron, preferably two, which is in a sheet-like configuration, and capable of moving up and down to control the roll of the unmanned aerial vehicle.

The left linear support 103A and the right linear support 103B are expected to improve the structural integrity of the unmanned aerial vehicle <NUM>. In other embodiments, the left linear support 103A and the right linear support 103B may accommodate a driving motor (not shown) for driving each of lift propellers 108A, 108B, 108C, 108D, 108E, 108F. Thus, the left linear support 103A and the right linear support 103B may be used for fixing the lift propellers to reduce usage of the parts of the unmanned aerial vehicle, and while simplifying structural parts of the unmanned aerial vehicle, the overall strength of the unmanned aerial vehicle may be improved due to the engagement of the left linear support 103A and the right linear support 103B with the two front wings and the two main wings. As will be disclosed later, the left linear support 103A and the right linear support 103B may also accommodate folding legs <NUM>, each of which may be retracted into the left linear support <NUM> A and the right linear support 103B.

In one embodiment, the left linear support 103A and the right linear support 103B are attached to the distal ends of the left front wing 105A and the right front wing 105B respectively. In still another embodiment, the left linear support 103A and the right linear support 103B extend beyond the front wings 105A, 105B.

In one embodiment, the left linear support 103A and the right linear support 103B are attached to positions near the middle portions of the left main wing 104A and the right main wing 104B respectively. In still another embodiment, the left linear support 103A and the right linear support 103B extend beyond the main wings 104A, 104B along a backwards direction.

The left linear support 103A is expected to be relative narrow in diameter, and may have a first group of multiple lift propellers 108A, 108B, 108C arranged at the top side, the bottom side, or both, of the left linear support 103A. In one feasible embodiment, these lift propellers 108A, 108B, and 108C may be driven by low profile motors arranged in the hollow interior of the left linear support 103A. In an embodiment shown in <FIG>, the lift propellers 108A, 108B, 108C are only arranged at the top side of the left linear support 103A. It should be noted that the number of the lift propeller shown in the figure is for illustrative purpose only, the invention is not intended to limit the number of the lift propeller, and the lift propeller may be increased or decreased according to the demand in actual. Likewise, the right linear support 103B is expected to be relative narrow in diameter, and may have a second group of multiple lift propellers 108D, 108E, 108F arranged at the top side, the bottom side, or both, of the right linear support 103B. In one feasible embodiment, these lift propellers 108D, 108E, 108F may be driven by low profile motors arranged in a hollow interior of the right linear support. In an embodiment shown in <FIG>, the lift propellers 108D, 108E, 108F are only arranged at the top side of the right linear support 103B. It should be noted that the number of the lift propeller shown in the figure is for illustrative purpose only, the invention is not intended to limit the number of the lift propeller, and the lift propeller may be increased or decreased according to the demand in actual.

In one embodiment, the left linear support 103A has at least one forward-facing opening provided thereon. Illustratively, referring to <FIG>, at least one forward-facing opening <NUM> may be provided at the front end of the left linear support 103A, thereby allowing air to enter the hollow interior of the left linear support 103A from an external environment. It should be noted that the forward-forcing opening shown in <FIG> is for illustrative purpose only, the invention is not intended to limit the shape and number of the forward-forcing opening, and the forward-forcing opening may be flexibly provided according to the demand in actual. In one embodiment, the right linear support 103B has a forward-facing opening (not shown) provided thereon, but may be similarly provided as shown in <FIG>, thereby allowing the air to enter the hollow interior of the right linear support 103B from the external environment; the forward-facing opening may be flexibly provided, for example, the forward-facing opening may likewise be provided at the front end of the right linear support 103B.

By providing the forward-facing openings, when the unmanned aerial vehicle starts to fly, the air enters from the openings <NUM> at the front ends of arms (i.e., the left linear support and the right linear support) and flows out from the connection gaps between the arms and other components and parts, such as motors, to form backward-flowing airflow in the arms, thereby accelerating heat dissipation.

As shown in <FIG> and <FIG>, one possible implementation is that the front end of each of the left linear support 103A and the right linear support 103B is of a circular truncated cone structure, and the opening <NUM> is provided on the upper bottom face of the circular truncated cone structure, preferably, the size of the opening <NUM> is same as that of the circular truncated cone structure. It may be understood by those skilled in the art that the front end of the linear support is formed as a circular truncated cone structure which may reduce resistance of the air to the linear support in the flight process of the unmanned aerial vehicle <NUM>, and thus the cruising ability of the unmanned aerial vehicle <NUM> is improved.

In one embodiment, the unmanned aerial vehicle <NUM> further comprises a fan <NUM> which is arranged in the hollow interior of each of the left linear support 103A and the right linear support 103B. The fan may accelerate air flow to make the heat in the arm to be taken away as quick as possible, thereby lowering the heat in the arm.

In one embodiment, the fan is arranged close to the forward-facing opening <NUM>, and forcibly promotes air circulation in the hollow interior, please referring to the illustrative arrangement of the fan <NUM> in <FIG> and <FIG>.

By installing a cooling fan in each of the left linear support 103A and the right linear support 103B of the unmanned aerial vehicle respectively, the cooling fan starts to work during the working period of a lift motor of the unmanned aerial vehicle, and hot airflow in the arm is exhausted through a flow field generated by the cooling fan, thereby achieving the purposes of lowering the temperature in the arm and protecting equipment in the arm.

Illustratively, one cooling fan is arranged below and in front of the lift motor, a wind field of the cooling fan blows towards the rear portion of the arm to form a backward-flowing airflow in the arm, and when the vertical takeoff and landing unmanned aerial vehicle is shifted to a level flight stage, the lift motor stops working, and the cooling fan stops working at the same time.

The invention is not intended to limit a specific structure of the fan <NUM>, illustratively, a ducted fan <NUM> may by adopted, an outer wall of the ducted fan <NUM> is fixedly connected to an inner wall of the linear support, and the ducted fan <NUM> is close to the front end of the linear support. It may be understood by those skilled in the art that, with a certain installation space for the fan <NUM>, the ducted fan <NUM> generates a greater thrust force on the air compared to the ordinary fan <NUM>, and the air flows at a greater speed in the hollow interior, and thus the cooling rate to the linear support is higher.

In one embodiment, the unmanned aerial vehicle further comprises motors <NUM> of the first group of multiple lift propellers 108A, 108B, 108C and the second group of multiple lift propellers 108D, 108E, 108F, the motors are arranged in the hollow interiors and used for driving the corresponding lift propellers, thereby achieving vertical takeoff and landing functions of the unmanned aerial vehicle.

In one embodiment, the unmanned aerial vehicle further comprises an exhaust port <NUM> provided at a position close to the tail end of each of the left linear support 103A and the right linear support 103B, thereby allowing the air to flow to the external environment from the hollow interior.

One possible implementation is that a plurality of exhaust ports <NUM> are provided at the left linear support 103A and the right linear support 103B respectively, the plurality of exhaust ports <NUM> on the left linear support 103A are arranged around the axis of the left linear support 103A in a spaced manner, and the plurality of exhaust ports <NUM> on the right linear support 103B are arranged around the axis of the right linear support 103B in a spaced manner. Illustratively, the exhaust port <NUM> may be in a shape of oblong. It may be understood by those skilled in the art that the shape of the exhaust port <NUM> is provided to be oblong, and on the premise of guaranteeing that the air in the hollow interior may smoothly flow out from the exhaust port <NUM>, the influence on the structural strength of the linear support due to excessive size of the exhaust port <NUM> is avoided.

Preferably, the tail ends of the left linear support 103A and the right linear support 103B are formed as a conical structure. It is easy to understand that the tail ends of the left linear support 103A and the right linear support 103B are formed as a tapered structure, and in the flight process of the unmanned aerial vehicle <NUM>, the conical structures at the tail ends of the left linear support 103A and the right linear support 103B may play a role in rectification, and thus the air resistance of the air to the left linear support 103A and the right linear support 103B is reduced. Illustratively, length directions of the exhaust ports <NUM> are arranged along a generatrix of the left linear support 103A and a generatrix of the right linear support 103B in a spaced manner.

In one embodiment, the unmanned aerial vehicle further comprises a detachable pod attached to the bottom face of the unmanned aerial vehicle, and the pod is a passenger pod or a cargo pod. By means of the arrangement mode as above, a structure of the unmanned aerial vehicle may be flexibly adjusted; in accordance with the actual conditions, the pod may be installed when needed, and may be detached when not needed, and therefore the unmanned aerial vehicle may be flexibly used in response to different requirements, and the adaptability of the unmanned aerial vehicle is improved.

In one embodiment, the main wing and the aileron are configured as a front wing configuration. As shown in <FIG> and the rest accompanying drawings showing the front wing configuration, the main wing and aileron may be a plate-like configuration of the main wing.

In one embodiment, a rotating shaft of the fan <NUM> is perpendicular to a rotating shaft of each lift propeller of the plurality of lift propellers 108A, 108B, 108C, 108D, 108E, 108F. Such arrangement makes cooling fan blades of the fan be perpendicular to propeller blades of the unmanned aerial vehicle, as shown in <FIG> and <FIG>, airflow A generated by rotation of the fan horizontally flows backwards in the linear support; the situation that, due to the fact that the fan is not arranged in such a way, the airflow A in the hollow interior is influenced by the inner surface of the arm and cannot flow through the hollow interior as quickly as possible to take away the heat is avoided.

In one embodiment, a diameter of the forward-facing opening <NUM> is greater than a radius of each of the left linear support 103A and the right linear support 103B. Such providing of the size of the forward-facing opening may make the air enter the interior of the linear support more easily, thereby facilitating the heat dissipation.

In one embodiment, the unmanned aerial vehicle <NUM> may have at least one propulsion propeller <NUM> to propel the unmanned aerial vehicle <NUM> in a forward direction. In the embodiments shown in <FIG>, <FIG> and <FIG>, there may be two propulsion propellers 107A, 107B. The two propulsion propellers 107A, 107B may be arranged at the distal ends of the rear portions of the linear support 103A, 103B.

In still another embodiment, such as an embodiment shown in <FIG>, a flight platform <NUM> may not have a propulsion propeller. In such embodiment, the flight platform <NUM> may be attached to a passenger pod or a cargo pod which is provided with the propulsion propeller. <FIG> illustrates an embodiment of a passenger pod having a propulsion propeller arranged at the rear end thereof. When the passenger pod is attached to the flight platform <NUM> of <FIG>, the propulsion propeller propels the flight platform <NUM> forwards.

In one embodiment, two vertical stabilizers 106A, 106B may be arranged at positions near the rear ends of the linear supports 103A, 103B respectively. Although the vertical stabilizers are shown pointing downward, there may have implementations possible in which the vertical stabilizers point upward.

In another embodiment, as shown in <FIG> and <FIG>, the main wings 104A, 104B may be respectively provided with wingtip lift propellers 109A, 109B arranged at the distal ends thereof. This may be achieved by providing the wingtip vertical stabilizers 110A, 110B at the distal ends of the main wings 104A, 104B, respectively, and having lift propellers <NUM> A, 109B arranged at the upper tips of the wingtip vertical stabilizers 110A, 110B. These wingtip lift propellers 109A, 109B may be relatively smaller than the lift propellers arranged on the linear supports 103A, 103B.

These wingtip lift propellers 109A, 109B may be used for efficiently and effectively controlling the roll of the unmanned aerial vehicle <NUM>. These wingtip lift propellers 109A, 109B are located at the most distal positions away from the center axis of the unmanned aerial vehicle <NUM> and are effective in regulating the roll of the unmanned aerial vehicle <NUM>, and may do so with a diameter less than those of the other lift propellers.

As further shown in <FIG>, there is a pod <NUM> normally attached beneath the main body <NUM> of the unmanned aerial vehicle <NUM>.

Now referring to details in <FIG>, the unmanned aerial vehicle <NUM> is expected to use any type of landing gear. In one embodiment, the unmanned aerial vehicle <NUM> may have four single leaf springs 112A, 112B, 112C, 112D as the landing gears. The front two single leaf springs 112A, 112C are respectively arranged at the distal ends of folding legs 111A, 111B. During the flight, the folding legs 111A, 111B may be respectively retracted into interior spaces of the left linear support 103A and the right linear support 103B.

In one embodiment, the tail end of the landing gear of the unmanned aerial vehicle may be provided with the leaf spring as shown in <FIG>, or the tail end of the landing gear of the unmanned aerial vehicle may be provided with an electric wheel as shown in <FIG>.

The two single leaf left springs 112B, 112D at the rear side are expected to be respectively arranged at the distal ends of the bottom of the vertical stabilizers 106A, 106B.

The expected single leaf springs 112A, 112B, 112C, 112D may be made of appropriate materials to provide enough elasticity and integrity, the materials comprise natural and synthetic polymers, various metals and metallic alloy, natural materials, textile fibers, and all reasonable combination thereof. In one embodiment, carbon fibers are used.

Now turning to <FIG>, a pod used as a cargo pod <NUM> is illustrated. The cargo pod <NUM> may have single leaf springs 135A, 135B, 135C, 135D as landing gears thereof. Or, the cargo pod <NUM> may have other type of landing gear, for example, sliding rails, legs, and wheels.

In an expected embodiment, the cargo pod <NUM> may be detached from the other portion of the unmanned aerial vehicle <NUM>. The other portion of the unmanned aerial vehicle may be called a flight platform <NUM>. The flight platform <NUM> may fly without carrying the pod, and may interchangeably carry different pods. As will be described later, the flight platform <NUM> may also carry a passenger pod.

In an illustrated embodiment, all pods <NUM>, <NUM> are carried beneath the flight platform <NUM>. The pods <NUM>, <NUM> are expected to be loaded on the ground, and the loading process may be completed before or after attaching the flight platform <NUM> to the pods <NUM>, <NUM>.

<FIG> illustrates a top view of a flight platform <NUM>. The flight platform <NUM> may have a generally flat configuration, and capable of carrying a load therebelow or thereabove. During high-speed flight, all six lift propellers 108A, 108B, 108C, 108D, 108E, 108F may be locked in place, and thus each blade is parallel to the main body <NUM>.

<FIG> illustrates one embodiment of a flight platform <NUM>, wherein the length of each of the front wings 105A, 105B is not longer than a half of the length of each of the main wings 104A, 104B.

<FIG> depicts a front view of a flight platform <NUM> with a detachably attached cargo pod <NUM> in general. Whether the cargo pod <NUM>, the passenger pod <NUM>, or any other type of load, it is specifically expected that there may be an energy storage unit <NUM> arranged in the main body <NUM> of the flight platform. Stored energy may be used to power the other parts of the flight platform, such as lift propellers 108A, 108B, 108C, 108D, and propulsion propellers 107A, 107B. The stored energy may be electric power, and the storage unit is a battery. In another embodiment, the energy storage <NUM> may be used to power accessories in the pods <NUM>, <NUM>.

These batteries <NUM> may also be arranged in the other portions of the flight platform <NUM>, such as in the linear supports 103A, 103B.

Alternatively or preferably, there may be an energy storage unit <NUM> arranged in each of the pods <NUM>, <NUM>. Energy stored in the storage unit <NUM> may be used to power the lift propellers 108A, 108B, 108C, 108D, and the propulsion propellers 107A, 107B. The stored energy may be electric power, and the storage unit is a battery. By arranging the energy storage units <NUM> in the pods <NUM>, <NUM>, whenever the flight platform <NUM> is attached to a new pod <NUM> or <NUM>, the flight platform <NUM> will have a supplemental energy source. The flight platform <NUM> itself may be an emergency energy store or a battery <NUM> with smaller capacity to supply electric power to the flight platform <NUM> for a relatively short period of time when the flight platform <NUM> is in flight without the pods <NUM>, <NUM>. In one embodiment, the main power supply of the flight platform <NUM> is from the batteries <NUM> located in the pods <NUM>, <NUM>. In this way, the flight platform <NUM> or the entire VTOL unmanned aerial vehicle <NUM> will have a fully charged energy source when the flight platform <NUM> replaces the old pods <NUM>, <NUM> with the new pods <NUM>, <NUM>. This is a beneficial method without requiring the VTOL unmanned aerial vehicle to charge itself. In a preferred embodiment, the flight platform <NUM> may work/fly continuously for hours or even days to attach the cargo pod/passenger pod and detach the cargo pod/passenger pod without stopping to charge batteries thereof.

Now referring to the details of <FIG>, a passenger pod <NUM> is provided. The passenger pod <NUM> may use any type of landing gear, such as rigid legs 145A, 145B, 145C, 145D as shown in the figure.

<FIG> depicts one aspect of the invention in general, wherein a pod (whether a cargo pod or a passenger pod) is detachable. Here, the passenger pod <NUM> may be selectively detached from the flight platform <NUM>. The attachment and detachment between the flight platform <NUM> and the pod <NUM> may be autonomously executed (without simultaneous user intervention) by a computer and/or other sensors and a calculation device. Alternatively or preferably, a user may actively control and guide the attachment and detachment between the flight platform <NUM> and the pod <NUM>.

As will be recognized by those of ordinary skill in the art, various types of attachment mechanisms <NUM> may be used to fix the pod <NUM> to the flight platform <NUM>. For example, the attachment mechanism may be a mechanical latch, a magnetic latch, a track and groove, or a combination of any known engagement ways.

It is important to understand that, in addition to having two propulsion propellers 107A and 107B (as shown in <FIG>), alternatively or alternatively, there may be a central propulsion propeller <NUM> which is connected to the rear end of the main body <NUM> (as shown in <FIG>). As shown in <FIG>, the central propulsion propeller <NUM> is engaged to the rear end of the main body <NUM> through a vertical expander <NUM>. The vertical expander <NUM> may be any structure in any shape to physically engage with the propulsion propeller <NUM>, thereby making a rotating center of the propulsion propeller <NUM> perpendicularly deviate from the main body <NUM>. In still another embodiment, the propulsion propeller <NUM> perpendicularly deviates from the main body <NUM>, thereby making the rotating center of the propulsion propeller <NUM> be perpendicularly located at a position at the rear portion of the pod <NUM> or be perpendicularly flushed with the pod <NUM>. In another embodiment, the propulsion propeller <NUM> is perpendicularly flushed with the top of the pod <NUM>. In another embodiment, the propulsion propeller <NUM> is perpendicularly flushed with the middle portion of the pod <NUM>. In a further embodiment, the propulsion propeller <NUM> is perpendicularly flushed with the bottom of the pod <NUM>.

What is not shown in any figure of the embodiment is the absence of the propulsion propellers 107A, 107B at the end parts of the linear supports 103A, 103B respectively. Instead, there may only be one propulsion propeller <NUM> engaged with the rear end of the main body <NUM>.

It may also be contemplated that each of the linear support 103A, 103B may comprise more than three lift propellers, which may be achieved by providing a longer linear support to accommodate more lift propellers, by using a lift propeller with smaller diameter, or by placing lift propellers on both the top and bottom sides of the linear support. One embodiment is illustrated in <FIG>, wherein two additional lift propellers <NUM>, <NUM> are arranged at the front ends of the bottoms of the linear supports 103A, 103B.

Although the propulsion propellers 107A, 107B have been illustrated in the foregoing figures to be positioned at the distal ends of the rear portions of the linear support 103A, 103B, it is particularly expected that these propulsion propellers 107A, 107B may be arranged at a horizontal plane lower than the main wings 104A, 104B, as those shown in <FIG>. In one aspect, these propulsion propellers 107A, 107B may be arranged at a horizontal plane which is basically equal to the pods <NUM>, <NUM> carried by the flight platform. In another aspect, these propulsion propellers 107A, 107B may be arranged at the middles of the vertical stabilizers 106A, 106B. One expected reason for lowering the arrangement of the propulsion propellers 107A, 107B is to minimize head dipping effect during the flight, which may be caused by aerodynamic effects caused by the pods <NUM>, <NUM>.

<FIG> illustrate an embodiment in which a flight platform <NUM> or pods <NUM>, <NUM>, or both, may each have electric wheels <NUM> attached thereto. In an embodiment of <FIG>, the flight platform <NUM> is provided with the electric wheels <NUM>; and the pods <NUM>, <NUM> are also provided with the electric wheels. Now referring to an embodiment of the <FIG>, single electric wheel <NUM> unit may have a motor enclosed in a shell <NUM>, and the motor may be driven the electric power supplied by the energy storage unit <NUM> arranged in each of the pods <NUM>, <NUM>.

It is contemplated that the electric wheels <NUM> may enable the flight platform <NUM> or the pod <NUM> to move on the ground when the flight platform and the pod are parked on the ground. This allows the one of the pods <NUM>, <NUM> to move away from the flight platform <NUM> and allows the other of the pods <NUM>, <NUM> to move itself to the flight platform <NUM> for attachment.

Or, this may allow the flight platform <NUM> to be away from the pod <NUM> and to move towards another pod for attachment. In one embodiment, each of the pods <NUM>, <NUM> may have an energy storage unit <NUM>, and therefore, an energy source of the flight platform <NUM> is substantially supplemented when the flight platform <NUM> is engaged with a new and fully charged pod <NUM> or <NUM>.

In certain embodiments of the disclosed unmanned aircraft system, at least one flotation device <NUM> may be provided, which is engaged with at least one of the cargo pod <NUM>, the passenger pod <NUM>, and the flight platform <NUM>. The flotation device may be of the type that requires actuation, that is, active inflation with gas or through material when needed. In other words, in this particular embodiment, the flotation device <NUM> may remain in a deflated state and can expand only when the inflation is triggered at certain conditions. For example, the flotation device <NUM> may automatically inflate during emergency landing, may automatically inflate when landing on water, and may inflate when any landing gear fails in certain aspects.

Many known types of inflation mechanisms or airbag mechanisms may be implemented to achieve the needs and configuration of the disclosed flotation device <NUM>. The expected flotation device <NUM> may be of a type that may be repeatedly reused, re-inflated, and re-deflated. The expected flotation device <NUM> may be merely disposable.

Alternatively or preferably, an inflation behavior may be activated by a user. For example, when an operator of the unmanned aircraft system determines that the flotation device <NUM> needs to be inflated, he or she may send a signal to start the inflation.

It should be particularly noted in certain embodiments that the flotation device <NUM> does not need the electric wheel <NUM>. In other embodiments, the flotation device <NUM> is a portion of a shell of the electric wheel <NUM>.

Referring to <FIG> as one example, a passenger pod <NUM> may have a lengthened type flotation device <NUM> arranged on any side of the pod <NUM>, which may be used as a water landing gear. In <FIG>, these flotation devices <NUM> are shown deflated. <FIG> illustrates a side view of a deflated flotation device <NUM>. As shown in <FIG>, the flotation device <NUM> engaged with the passenger pod <NUM> is shown inflated.

Referring <FIG> as another example, the flight platform <NUM> may have four flotation devices <NUM> respectively arranged on the tops of four electric wheels <NUM>. These flotation devices <NUM> may be alternatively attached to the electric wheels <NUM> or close to the electric wheels <NUM> at the other positions. In <FIG>, these flotation devices <NUM> engaged with the electric wheels are shown deflated. <FIG> illustrate an inflated flotation device <NUM> of a flight platform <NUM>.

As above, the forward-facing opening is provided at the front end of the arm of the unmanned aerial vehicle, further preferably, a cooling fan is installed in the arm of the unmanned aerial vehicle, during the working period of a lift motor of the unmanned aerial vehicle, hot airflow in the arm is exhausted through the forward-facing opening or further through a flow field generate by the cooling fan, thereby achieving the purposes of lowering temperature in the arm and protecting equipment in the arm.

According to the technical solutions of the invention, heat dissipation in an arm of an unmanned aerial vehicle is achieved by providing a forward-facing opening at the front end of each of a left linear support and a right linear support of the unmanned aerial vehicle, thereby achieving the purposes of lowering temperature in the arm and protecting equipment in the arm.

<FIG> is a side sectional view of an unmanned aerial vehicle with a cooling system in accordance with an embodiment of the invention. Please referring to <FIG>, a cooling system for an unmanned aerial vehicle provided by the invention comprises an opening (not shown) which is provided on a shell of a hollow linear support 103A; a plurality of lift propellers 108A, 108B, and 108C which are arranged on the hollow linear support 103A; a plurality of motors <NUM> which are configured to be used for the lift propellers 108A, 108B, and 108C in the plurality of lift propellers in the hollow linear support 103A; and a fan <NUM> which is arranged in the linear support 103A to supply air from an external environment to the interior of the hollow linear support.

Preferably, the openings may be provided at the front end and the rear end of the shell of the hollow linear support 103A according to an air inlet direction B and an air outlet direction C in <FIG>. The gas moves along an airflow direction A in the hollow linear support 103A.

In one embodiment, a fan is arranged at a position close to the front end of the linear support, thus airflow A in the linear support may flow through the linear support more quickly to take away all heat in the hollow interior more quickly.

In one embodiment, the linear support is in a straight configuration which is in favor of improving the overall strength of the unmanned aerial vehicle.

In one embodiment, the cooling system further comprises at least one exhaust port which is provided on the linear support to allow the air to escape from the interior of the linear support.

In one embodiment, the cooling system further comprises a pod which is detachably attached to the bottom face of the unmanned aerial vehicle, wherein the pod is a passenger pod or a cargo pod. By means of the arrangement mode as above, a structure of the unmanned aerial vehicle may be flexibly adjusted; in accordance with the actual conditions, the pod may be installed when needed, and may be detached when not needed, and therefore the unmanned aerial vehicle may be flexibly used in response to different requirements, and the adaptability of the unmanned aerial vehicle is improved.

The heat dissipation in the arm of the unmanned aerial vehicle may be achieved by adopting the cooling system for the unmanned aerial vehicle provided by the invention.

Many variations and modifications may be made by those of ordinary skill in the art without departing from the scope of the appended claims.

Thus, it must be understood that the illustrated embodiments are presented for the purpose of example only and should not be taken as limiting the embodiments defined by the appended technical solutions. For example, despite the fact that elements of the technical solutions are presented below in a certain combination, it must be expressly understood that the embodiment comprises other combinations of less, more or different elements, which are disclosed herein, even if such a combination is not initially defined.

Therefore, detailed embodiments and applications of a VTOL flight platform with interchangeable pods have been disclosed. However, it is apparent to those skilled in the art that more modifications in addition to those already described are possible without departing from the scope of the appended claims.

Claim 1:
A vertical takeoff and landing unmanned aerial vehicle, comprising:
a left main wing (104A) and a right main wing (104B);
a left front wing (105A) and a right front wing (105B);
a main body (<NUM>) which is engaged with the left main wing (104A) and the right main wing (104B);
a left linear support (103A) for connecting the left main wing (104A) with the left front wing (105A);
a right linear support (103B) for connecting the right main wing (104B) with the right front wing (105B);
the left linear support (103A) having a first group of multiple lift propellers (108A, 108B, 108C) arranged thereon;
the right linear support (103B) having a second group of multiple lift propellers (108D, 108E, 108F) arranged thereon;
wherein the left linear support (103A) and the right linear support (103B) each have a hollow interior suitable to arrange equipment therein; and
a forward-facing opening (<NUM>) which is provided at the front end of each of the left linear support (103A) and the right linear support (103B),
wherein the opening (<NUM>) is formed as a trumpet-shaped structure, wherein the radial sectional area of one end, toward the hollow interior, of the opening (<NUM>) is less than that of one end, away from the hollow interior, of the opening (<NUM>).