Land-air dual-purpose vehicle with vertical and skating dual take-off and landing modes

Abstract

The utility model provides an air-ground dual-purpose traffic tool with a vertical take-off and landing mode and a skating take-off and landing mode, and the air-ground dual-purpose traffic tool can fly and run on the land by changing the shape of the air-ground dual-purpose traffic tool. The power of the vehicle is driven by a plurality of tilting rotors and a ducted fan, and the vehicle has two take-off and landing modes of vertical take-off and landing and taxiing take-off and landing boosted by an autonomous traveling chassis. Due to the design of the folding fixed wings and the horizontal tail, the traffic tool can be reduced to the specified size of a road or a garage when running and parking on the land; the flight part adopts a hydrogen fuel cell containing a titanium alloy bipolar plate to provide power, the titanium alloy bipolar plate also serves as a bearing structure of a fuselage, wings, skin and the like, and the aircraft has the advantages of being light in weight, high in strength, large in voyage, high in load and the like.

Description

Technical Field

[0001] The utility model belongs to the technical fields of split aircraft and vehicle autonomous driving, and particularly relates to an air-land dual-purpose vehicle with dual vertical and takeoff / landing modes of vertical takeoff / landing and taxiing. Background Art

[0002] At present, with the advocacy and promotion of the national low-altitude economy, a number of relatively small and advanced aircraft have emerged rapidly. The ways to achieve takeoff / landing and flight mainly include: vertical takeoff / landing using tiltrotors or ducted fans, traditional takeoff / landing by taxiing using propellers + fixed wings, and combined takeoff / landing modes of tiltrotors / ducted fans + fixed wings. However, the lithium-ion power batteries used in many existing technologies are an important reason for the large volume and high weight of such vehicles. At the same time, there are serious deficiencies in lightweight design, and the takeoff / landing modes are relatively single, which is not helpful for increasing the range and payload. Therefore, how to further develop a flight solution that combines the advantages of the above various types of aircraft and weakens the disadvantages in various aspects as much as possible is one of the problems to be solved in this field. Summary of the Invention

[0003] In view of this, the utility model provides an air-land dual-purpose vehicle with dual vertical and takeoff / landing modes of vertical takeoff / landing and taxiing, which is composed of a compound-wing flight module and an autonomous driving chassis that can be combined with each other or separated and operate independently;

[0004] Among them, foldable fixed wings are installed on both sides of the fuselage of the compound-wing flight module. Side beams parallel to the fuselage are provided on the fixed wings, and vertically placed rotors are installed on the side beams; a vertical tail is provided at the rear end of each side beam. The horizontal two ends of a horizontal tail are respectively pivotally connected to the upper ends of the two vertical tails, and the middle part of the front end of the horizontal tail is pivotally connected to the middle vertical tail at the tail of the fuselage; the horizontal tail folds down during land travel or parking, unfolds during takeoff / landing by taxiing or level flight, and can be selected to be in the unfolded or folded-down state during vertical takeoff / landing; a pair of ducted fans are provided below the horizontal tail and are respectively located on both sides of the tail of the fuselage. Each ducted fan is respectively pivotally connected to the inner side surface of the vertical tail on the same side, and the two ducted fans and the middle vertical tail form a coaxial pivotable connection, which is used to provide upward thrust during vertical takeoff / landing, and provide thrust or deceleration reverse thrust during takeoff / landing by taxiing and level flight; a cargo hold for carrying passengers or goods is provided on the compound-wing flight module;

[0005] The autonomous driving chassis serves as a takeoff / landing platform for the compound-wing flight module, has an autonomous driving function, and can also drive autonomously or under the operation of a driver when combined with the compound-wing flight module; when the compound-wing flight module takes off, the autonomous driving chassis drives it to accelerate to obtain the main lift or auxiliary lift;

[0006] The compound-wing flight module uses a fuel cell as power. The fuel cell includes a titanium alloy bipolar plate, which also serves as the fuselage load-bearing structure of the compound-wing flight module.

[0007] Furthermore, the cargo compartment is a separate module that can be combined with or separated from the compound-wing flight module or the autonomous driving chassis; when the cargo compartment is separated from the compound-wing flight module, the compound-wing flight module can fly and take off and land autonomously; when the cargo compartment is combined with the autonomous driving chassis, it can be used as a vehicle for autonomous driving or driving under the operation of a driver; in the passenger transportation scenario, the cabin door can be selected to be set on the side of the cargo compartment; in the freight transportation scenario, the cabin door can be selected to be set in front of or below the lower rear of the cargo compartment.

[0008] Furthermore, each ducted fan can be tilted independently in the pitch direction to improve the maneuverability of the compound-wing flight module during flight.

[0009] Furthermore, the fixed wing includes a central wing and an outer wing in sequence from the fuselage to the distal end, and winglets that can be selected and installed according to the lift index requirements; the side beam is arranged at the connection between the central wing and the outer wing; the outer wing is provided with flaps and ailerons, or a simplified form that only includes ailerons.

[0010] Furthermore, elastic buffer and energy-absorbing materials are provided on the autonomous driving chassis to reduce the impact during the takeoff and landing of the compound-wing flight module.

[0011] Furthermore, precision positioning pins are provided below the compound-wing flight module or the cargo compartment, and corresponding precision positioning pin holes are provided on the autonomous driving chassis, and corresponding precision positioning pin holes are provided on the autonomous driving chassis, and a rough positioning guide block for positioning the nose of the compound-wing flight module, and the positioning during the combination of the compound-wing flight module and the autonomous driving chassis is realized through mutual cooperation.

[0012] Furthermore, landing gears are also provided on the compound-wing flight module for the compound-wing flight module to take off and land by itself or make an emergency landing on land or water, and a retractable hidden landing gear or an external landing gear can be selected according to actual needs.

[0013] Furthermore, a pair of tilt-rotors with locking mechanisms or non-tiltable coaxial contra-rotating rotors are provided on each side beam, symmetrically distributed on the front and rear sides of the fixed wing; a pair of tiltable propellers can be selected to be added at the front end of the side beam according to needs.

[0014] The above-mentioned land-air dual-purpose vehicle provided by the present utility model can achieve flight and land travel by changing its own form. The power of this vehicle is driven by tiltable multi-rotors and ducted fans, and it has two takeoff and landing methods: vertical takeoff and landing, and runway takeoff and landing assisted by an autonomous driving chassis. The foldable fixed wing and horizontal tail designs enable the vehicle to shrink to the size specified by the road or garage when traveling and parking on land; the flight part is powered by a hydrogen fuel cell containing titanium alloy bipolar plates, and the titanium alloy bipolar plates also serve as structural supports for the fuselage, wings, skins, etc., having many advantages such as lightweight, high strength, long range, and high load. Brief Description of the Drawings

[0015] Figure 1 Schematic diagram of the land travel or parking mode of the land-air dual-purpose vehicle provided by the present utility model;

[0016] Figure 2 Schematic diagram of the vertical takeoff and landing mode of the land-air dual-purpose vehicle provided by the present utility model;

[0017] Figure 3 Schematic diagram of the level flight mode of the land-air dual-purpose vehicle provided by the present utility model;

[0018] Figure 4 [[ID=I8]]Schematic diagram of the runway takeoff and landing mode of the land-air dual-purpose vehicle provided by the present utility model;

[0019] Figure 5 Schematic diagram of the optional positioning combination structure of the compound wing flight module and the autonomous driving chassis;

[0020] Figure 6 Schematic diagram of the principle of using the positioning combination structure to achieve landing guidance and rough and fine positioning;

[0021] Figure 7 Preferred embodiment of setting a tiltable propeller at the front end of the side beam. Detailed Description of the Invention

[0022] Next, the technical solutions of the present utility model will be clearly and completely described in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present utility model, rather than all of the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present utility model.

[0023] In the description of the present utility model, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present utility model. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0024] In the description of the present utility model, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "connection", "coupling" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0025] The land-air dual-purpose vehicle provided by the present utility model, which has dual take-off and landing modes of vertical and taxiing, such as Figure 1-4 shown, is composed of a compound wing flight module 1 and an autonomous driving chassis 2 that can be combined with each other or separated and operate independently;

[0026] Among them, fixed wings 3 that can be folded are installed on both sides of the fuselage of the compound wing flight module 1. Side beams 4 parallel to the fuselage are provided on the fixed wings 3, and rotors placed vertically are installed on the side beams. A vertical tail 6 is provided at the rear end of each side beam 4. The horizontal ends of a horizontal tail 7 are respectively pivotally connected to the upper ends of the two vertical tails 6, and the middle part of the front end of the horizontal tail 7 is pivotally connected to the middle vertical tail 8 at the tail of the fuselage. The horizontal tail 7 folds down when driving or parking on land, unfolds when taxiing for take-off and landing or in level flight, and can be selectively unfolded or folded down according to needs during vertical take-off and landing.

[0027] This layout of high horizontal tail + three vertical tails is more conducive to increasing the range compared to other layouts, and also provides better redundancy and flexibility for the design of the wing and the cargo compartment. At the same time, compared with the prior art using a double tail strut form, the three-vertical-tail layout can achieve a better balance in terms of the strength and weight of the tail wing.

[0028] A pair of ducted fans 9 are arranged below the horizontal tail 7 and are respectively located on both sides of the tail of the aircraft. Each ducted fan 9 is pivotally connected to the inner side surface of the vertical tail 6 on its same side, and the two ducted fans 9 and the middle vertical tail 8 form a coaxial pivotable connection, which is used to provide upward thrust during vertical takeoff and landing, and to provide thrust or deceleration reverse thrust during takeoff and landing on the runway and during level flight; a cargo compartment for carrying passengers or goods is arranged on the compound wing flight module 1;

[0029] The autonomous driving chassis 2 serves as a takeoff and landing platform for the compound wing flight module 1, which has an autonomous driving function and can also drive automatically or under the operation of the driver when combined with the compound wing flight module 1. When the compound wing flight module 1 takes off, the autonomous driving chassis 2 drives it to accelerate and can obtain auxiliary lift. Through this design, the vehicle of the present utility model can freely choose different takeoff methods according to actual needs. For example, it can take off and land on the runway and save energy in open roads and suburban environments, and perform vertical takeoff and landing on crowded urban roads. In this way, there is no need for excessive renovation of existing roads. For special environments such as plateaus with thin air that are not conducive to vertical takeoff, the autonomous driving chassis can also play a boosting role during the vertical takeoff process, thereby greatly enriching the applicable environments and scenarios of the present utility model.

[0030] When the compound wing flight module 1 and the autonomous driving chassis 2 are combined and traveling or parked on land, the fixed wing 3 and the horizontal tail 6 are folded so that the outer periphery of the compound wing flight module 1 does not exceed the outer periphery of the autonomous driving chassis 2 in the horizontal direction and meets the road height limit requirements during driving.

[0031] The compound wing flight module uses a fuel cell as the power source. The fuel cell includes a titanium alloy bipolar plate, which also serves as the fuselage load-bearing structure of the compound wing flight module. In this way, it not only meets the power source requirements of the vehicle, but also can greatly improve the structural strength and lightweight index.

[0032] In a preferred embodiment of the present utility model, the cargo compartment is a separate module (not shown in the figure) that can be combined with or separated from the compound wing flight module or the autonomous driving chassis; when the cargo compartment is separated from the compound wing flight module, the compound wing flight module can fly and take off and land autonomously; when the cargo compartment is combined with the autonomous driving chassis, it can be used as a vehicle to drive automatically or under the operation of the driver; in the passenger transportation scenario, the cabin door can be selected to be arranged on the side of the cargo compartment; in the freight transportation scenario, the cabin door can be selected to be arranged in front of or below the cargo compartment. It should be noted that the layout of the high horizontal tail + three vertical tails of the present utility model is the optimal choice considering the design requirements of the independent cargo compartment, flight power layout, and the size after folding of the compound wing flight module. Obviously, the above-mentioned multiple cargo compartment door and passenger and freight transportation function designs cannot be realized in some existing technologies with a low horizontal tail layout, and the size and flight range after folding also cannot reach the same indicators as the present utility model.

[0033] In a preferred embodiment of the present utility model, each ducted fan 9 can be tilted independently in the pitch direction to improve the maneuverability of the compound wing flight module 1 during flight.

[0034] In a preferred embodiment of the present utility model, the fixed wing includes a central wing and an outer wing in sequence from the fuselage to the distal end, and winglets that can be selected and installed according to the lift index requirements, which can be omitted when the lift requirement is not high and the takeoff and landing can be achieved only by using the central wing and the outer wing; side beams are arranged at the connection of the central wing and the outer wing; flaps and ailerons are provided on the outer wing, or a simplified form that only includes ailerons.

[0035] In a preferred embodiment of the present utility model, a pair of tiltable rotors with locking mechanisms or non-tiltable coaxial contra-rotating rotors are arranged on each side beam 4, symmetrically distributed on the front and rear sides of the fixed wing 3 to achieve better power redundancy. When the coaxial contra-rotating structure is adopted, greater thrust can be provided; a pair of tiltable propellers can be selectively added at the front end of the side beam, as Figure 7 shown, it can increase the ascending thrust when in the vertical takeoff state, and turn to the horizontal direction to increase the horizontal thrust during level flight.

[0036] In a preferred embodiment of the present utility model, elastic buffer and energy-absorbing materials are arranged on the autonomous driving chassis 2 to reduce the impact during the takeoff and landing of the compound wing flight module 1.

[0037] In a preferred embodiment of the present utility model, as Figure 5 shown, precision positioning pins are arranged below the compound wing flight module or the cargo compartment, precision positioning pin holes corresponding to the precision positioning pins are arranged on the autonomous driving chassis, and rough positioning guide blocks for positioning the compound wing flight module are provided, and the positioning during the combination of the compound wing flight module and the autonomous driving chassis is realized through mutual cooperation.

[0038] In a preferred embodiment of the present utility model, landing gears are also arranged on the compound wing flight module 1, and retractable hidden landing gears or external landing gears can be selected according to actual needs. The arrangement of the landing gears can further make the present utility model a water-land-air tri-media vehicle, and also expand its application scenarios. For example, in some disaster areas where land travel conditions are not available, the compound wing flight module needs to use the landing gears for takeoff and landing by itself; when performing rescue tasks for rescuing drowning people, a water landing gear can be equipped for the compound wing flight module to complete takeoff and landing on water. In addition, the arrangement of the fixed wing and the landing gears also provides the possibility for emergency landing in case of failures such as engine flameout in the air, significantly increasing the safety and survival probability of the on-board personnel and property compared with multi-rotor aircraft.

[0039] In a preferred embodiment of the present invention, a pair of vertically placed rotors 5 are installed before and after the side beam 4, and a pair of tiltable propellers can be selectively added at the front end of the side beam as needed. As Figure 7 shown, the driving force during takeoff / landing and level flight can be further increased.

[0040] It should be understood that the magnitudes of the sequence numbers of the steps in the embodiments of the present utility model do not imply the order of execution. The order of execution of each process should be determined by its function and internal logic, and should not constitute any limitation to the implementation process of the embodiments of the present utility model.

[0041] Although the embodiments of the present utility model have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present utility model. The scope of the present utility model is defined by the appended claims and their equivalents.

Claims

1. An air-land dual-purpose vehicle with both vertical and takeoff / landing and taxiing takeoff / landing methods, characterized in that: It is composed of a compound-wing flight module and an autonomous driving chassis that can be combined with each other or operate independently in a separated state; Among them, foldable fixed wings are installed on both sides of the fuselage of the compound-wing flight module. Side beams parallel to the fuselage are provided on the fixed wings, and rotors placed vertically are installed on the side beams; a vertical stabilizer is provided at the rear end of each side beam. The horizontal ends of a horizontal stabilizer are respectively pivotally connected to the upper ends of the two vertical stabilizers, and the middle part of the front end of the horizontal stabilizer is pivotally connected to the middle vertical stabilizer at the tail of the fuselage; the horizontal stabilizer folds down during land travel or parking, and unfolds during takeoff and landing by taxiing or during level flight, and selects the unfolded or folded-down state according to needs during vertical takeoff and landing; a pair of ducted fans are provided below the horizontal stabilizer and are respectively located on both sides of the tail of the fuselage. Each ducted fan is respectively pivotally connected to the inner side surface of the vertical stabilizer on its same side, and the two ducted fans are pivotally connected coaxially with the middle vertical stabilizer, and are used to provide upward thrust during vertical takeoff and landing, and provide thrust or deceleration reverse thrust during takeoff and landing by taxiing and during level flight; a carrying cabin for carrying passengers or goods is provided on the compound-wing flight module; The autonomous driving chassis serves as a takeoff and landing platform for the compound-wing flight module. It has an autonomous driving function and can also drive autonomously or under the operation of a driver when combined with the compound-wing flight module; when the compound-wing flight module takes off, the autonomous driving chassis drives it to accelerate to obtain the main lift or auxiliary lift; The compound-wing flight module uses a fuel cell as power, and the fuel cell includes a titanium alloy bipolar plate, which also serves as the fuselage load-bearing structure of the compound-wing flight module.

2. The land-air dual-purpose vehicle with vertical and takeoff / landing in a gliding manner as claimed in claim 1, wherein: The carrying cabin is a separate module that can be combined with or separated from the compound-wing flight module or the autonomous driving chassis; when the carrying cabin is separated from the compound-wing flight module, the compound-wing flight module can fly and take off and land autonomously; when the carrying cabin is combined with the autonomous driving chassis, it acts as a vehicle and drives autonomously or under the operation of a driver.

3. The amphibious vehicle with both vertical and takeoff / landing and taxiing takeoff / landing modes as claimed in claim 1, wherein: Each ducted fan can be tilted independently in the pitch direction, and is used to improve the maneuverability of the compound-wing flight module during flight.

4. The land-air dual-purpose vehicle with both vertical and takeoff / landing and taxiing takeoff / landing modes as claimed in claim 1, wherein: The fixed wing successively includes a central wing and an outer wing from the fuselage to the distal end, and winglets optionally installed according to the lift index requirements; the side beam is arranged at the connection between the central wing and the outer wing; flaps and ailerons are provided on the outer wing, or a simplified form only including ailerons.

5. The land-air dual-purpose vehicle with vertical and takeoff / landing and taxiing dual takeoff and landing modes as claimed in claim 1, wherein: Elastic buffer and energy-absorbing materials are provided on the autonomous driving chassis to reduce the impact during the takeoff and landing of the compound-wing flight module.

6. The amphibious vehicle with vertical and takeoff / landing on runway double takeoff and landing modes as claimed in claim 1, characterized in that: Precision positioning pins are provided below the compound-wing flight module or the carrying cabin. Corresponding precision positioning pin holes and rough positioning guide blocks for positioning the compound-wing flight module are provided on the autonomous driving chassis, and positioning during the combination of the compound-wing flight module and the autonomous driving chassis is achieved through mutual cooperation.

7. The amphibious vehicle with both vertical and takeoff / landing and taxiing takeoff / landing modes as claimed in claim 1, wherein: Landing gears are also provided on the compound-wing flight module, and are used for the compound-wing flight module to take off and land by itself or make an emergency landing on land or water.

8. The amphibious vehicle with both vertical and takeoff / landing and taxiing takeoff / landing modes as claimed in claim 1, characterized in that: A pair of tiltable rotors with locking mechanisms or non-tiltable coaxial contra-rotating rotors are provided on each side beam, and are symmetrically distributed on the front and rear sides of the fixed wing; a pair of tiltable propellers can be optionally installed at the front end of the side beam according to needs.

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