Sliding plate chassis aircraft with multiple take-off modes

Abstract

The sliding plate chassis aircraft with multiple takeoff modes can change the vehicle form between an automobile and the aircraft and switch the flying state and the land running state, and has the advantages of being low in energy consumption, finally achieving large voyage and high load and the like. Power is provided by the tilting multi-rotor wings and the ducted fan, so that vertical take-off and landing can be realized, and short-distance taxiing take-off and landing can also be realized under the boosting of the self-traveling chassis. Due to the design of the folding fixed wings and the horizontal tail, the vehicle can be reduced to the specified size of a road or a garage when running and parking on the land.

Description

Technical Field

[0001] The utility model belongs to the technical fields of split aircraft and vehicle autonomous driving, and particularly relates to a skateboard chassis aircraft with multiple takeoff methods. Background Art

[0002] At present, with the advocacy and promotion of the national low-altitude economy, a number of relatively miniaturized advanced aircraft have emerged rapidly. The methods for realizing takeoff, landing and flight mainly include: vertical takeoff and landing methods using tilt-rotor or ducted fan, traditional takeoff and landing methods using propeller + fixed wing, and composite takeoff and landing methods using tilt-rotor / ducted fan + fixed wing. However, many existing technologies generally have disadvantages such as large volume, high energy consumption, short range, and single takeoff and landing method. Therefore, how to further develop a flight solution that combines the advantages of the above various types of aircraft and weakens the disadvantages in all 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 a skateboard chassis aircraft with multiple takeoff methods, which is composed of a composite 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 composite wing flight module. Side beams parallel to the fuselage are arranged on the fixed wings. A pair of tilt-rotors with locking mechanisms or non-tiltable coaxial contra-rotating rotors are arranged 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; A vertical tail is arranged 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 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 and landing by sliding or level flight, and can be selected to be in the unfolded or folded-down state during vertical takeoff and landing; A pair of ducted fans are arranged below the horizontal tail 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 its same side, and the two ducted fans and the middle vertical tail form a coaxial pivotable connection, which is used to provide ascending thrust during vertical takeoff and landing, and provide thrust or deceleration counter-thrust during takeoff and landing by sliding and level flight; A cargo hold for carrying passengers or goods is arranged on the composite wing flight module;

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

[0006] When the compound-wing flight module is combined with the autonomous driving chassis and is traveling or parked on land, the fixed wing and the horizontal tail are folded.

[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 a passenger transportation scenario, the cabin door can be optionally set on the side of the cargo compartment; in a freight transportation scenario, the cabin door can be optionally set in the front lower part or the rear lower part 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 optionally installed according to the lift index requirements; 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 including only 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 is provided, and the positioning during the combination of the compound-wing flight module and the autonomous driving chassis is achieved 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] The provided skateboard chassis aircraft with multiple takeoff methods can change the form of the transportation tool between an automobile and an aircraft, and switch between the flight and land travel states, has low energy consumption, and finally realizes advantages such as a large flight range and high payload. The present invention provides power through tiltable multi-rotors and ducted fans, can not only achieve vertical takeoff and landing, but also achieve short-distance takeoff and landing with the boost of the autonomous driving chassis. The foldable fixed wing and horizontal tail designs can reduce the size of the transportation tool to the size specified by the road or garage when traveling and parking on land. Description of the Drawings

[0014] Figure 1Schematic diagram of the land driving or parking mode of the skateboard chassis aircraft provided by the present utility model;

[0015] Figure 2 Schematic diagram of the vertical takeoff and landing mode of the skateboard chassis aircraft provided by the present utility model;

[0016] Figure 3 Schematic diagram of the level flight mode of the skateboard chassis aircraft provided by the present utility model;

[0017] Figure 4 Schematic diagram of the takeoff and landing mode by taxiing of the skateboard chassis aircraft provided by the present utility model;

[0018] Figure 5 Schematic diagram of the optional positioning combination structure of the compound wing flight module and the autonomous driving chassis;

[0019] Figure 6 Schematic diagram of the principle for realizing landing guidance and rough and fine positioning by using the positioning combination structure;

[0020] Figure 7 Preferred embodiment of arranging a tiltable propeller at the front end of the side beam. Detailed implementation manners

[0021] 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 some but not all of the embodiments of the present utility model. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.

[0022] 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 accompanying drawings, and 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 cannot be construed as a limitation of 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.

[0023] In the description of the present utility model, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "connection", and "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 a direct connection or an indirect connection through an intermediate medium, and it can be the communication inside two components. 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.

[0024] The skateboard chassis aircraft provided by the present utility model with multiple takeoff methods, 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;

[0025] 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. A pair of vertically placed rotors 5 are installed at the front and rear of the side beams 4. A pair of tiltable propellers can be selectively added at the front end of the side beam as needed, such as Figure 7 shown; a vertical stabilizer 6 is provided at the rear end of each side beam 4. The horizontal two ends of a horizontal stabilizer 7 are respectively pivotally connected to the upper ends of the two vertical stabilizers 6, and the middle of the front end of the horizontal stabilizer 7 is pivotally connected to the middle vertical stabilizer 8 at the tail of the fuselage; the horizontal stabilizer 7 folds down during land travel or parking, unfolds during takeoff and landing by skidding or level flight, and can be selectively unfolded or folded down during vertical takeoff and landing.

[0026] This layout of high horizontal stabilizer + three vertical stabilizers is more conducive to increasing the flight 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-stabilizer layout can achieve a better balance between the strength and weight of the tail wing.

[0027] A pair of ducted fans 9 are provided below the horizontal stabilizer 7 on both sides of the tail of the fuselage respectively. Each ducted fan 9 is respectively pivotally connected to the inner side surface of the vertical stabilizer 6 on its same side, and the two ducted fans 9 and the middle vertical stabilizer 8 form a coaxial pivotable connection, which is used to provide upward thrust during vertical takeoff and landing, and provide thrust or deceleration reverse thrust during takeoff and landing by skidding and level flight; a cargo compartment for carrying passengers or goods is provided on the compound wing flight module 1;

[0028] The autonomous driving chassis 2 serves as the take-off and landing platform for the compound wing flight module 1. It has the function of autonomous driving 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 to obtain auxiliary lift. Through this design, the vehicle of the present utility model can freely select different take-off methods according to actual needs. For example, it can perform taxiing take-off and landing on open roads and suburban environments to save energy consumption, and perform vertical take-off and landing on congested urban roads. In this way, there is no need to carry out excessive renovation of existing roads. For special environments such as plateaus with thin air that are not conducive to vertical take-off, the autonomous driving chassis can also play a boosting role during the vertical take-off process, thereby greatly enriching the applicable environments and scenarios of the present utility model.

[0029] When the compound wing flight module 1 is combined with the autonomous driving chassis 2 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 range of the autonomous driving chassis 2 in the horizontal direction and meets the road height limit requirements during driving. This design not only enables the size of the present utility model on land to meet the requirements of existing urban road widths, heights, and relevant traffic safety regulations, but also can form a certain protection for the folded compound wing flight module by means of the front and rear anti-collision beam structures on the autonomous driving chassis, reducing losses in the event of a collision accident.

[0030] In a preferred embodiment of the present utility model, the cargo and passenger cabin is a separate module that can be combined with or separated from the compound wing flight module or the autonomous driving chassis (not shown in the figure); when the cargo and passenger cabin is separated from the compound wing flight module, the compound wing flight module can fly and take off and land autonomously; when the cargo and passenger cabin 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 set on the side of the cargo and passenger cabin; in the freight transportation scenario, the cabin door can be selected to be set in front of or below the cargo and passenger cabin. It is worth noting 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 and passenger cabin, flight power layout, and the size after folding of the compound wing flight module. Obviously, the above-mentioned multiple cargo and passenger cabin door and passenger and freight transportation function designs cannot be achieved in some prior arts with a low horizontal tail layout, and the size after folding and flight range also cannot reach the same indicators as the present utility model.

[0031] 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.

[0032] In a preferred embodiment of the present utility model, the fixed wing successively includes a central wing and an outer wing from the fuselage to the distal end, and winglets that can be optionally installed according to the lift index requirements, which can be omitted when the lift requirement is not high and 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.

[0033] In a preferred embodiment of the present utility model, a pair of tilt-rotor or non-tiltable coaxial contra-rotating rotors with locking mechanisms are arranged on each side beam 4, symmetrically distributed on the front and rear sides of the fixed wing Ⅲ 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 optionally added at the front end of the side beam, as Figure 7 shown. When in vertical takeoff, the rising thrust can be increased, and when in horizontal flight, it turns to horizontal to increase the horizontal thrust.

[0034] 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.

[0035] 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 hold. Corresponding precision positioning pin holes and rough positioning guide blocks for positioning the compound wing flight module are arranged 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.

[0036] In a preferred embodiment of the present utility model, landing gears are also arranged on the compound wing flight module 1. Concealable landing gears that can be retracted or external landing gears can be selected according to actual needs. The arrangement of the landing gears enables the present utility model to further serve as a three-in-one cross-medium vehicle for water, land and air, and also expands 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 gear 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 gear also provides the possibility of emergency landing in case of failures such as engine flameout in the air, significantly increasing the safety and survival probability of the crew and property on board compared with multi-rotor aircraft.

[0037] It should be understood that the magnitudes of the sequence numbers of the steps in the embodiments of the present utility model do not mean the order of execution. The execution order of each process should be determined according to its function and internal logic, and should not constitute any limitation to the implementation process of the embodiments of the present utility model.

[0038] 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. A skateboard chassis aircraft with multiple takeoff methods, characterized in that: It is composed of a composite wing flight module and an autonomous driving chassis that can be combined with each other or operate independently in a split form; Among them, foldable fixed wings are installed on both sides of the fuselage of the composite wing flight module. Side beams parallel to the fuselage are provided on the fixed wings. A pair of tilt-rotor 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 selectively added at the front end of the side beam as needed; A vertical tail is provided at the rear end of each side beam. The horizontal ends of a horizontal tail are pivotally connected to the upper ends of the two vertical tails respectively, 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 and landing on a runway or level flight, and can be selectively unfolded or folded down during vertical takeoff and landing; A pair of ducted fans are provided below the horizontal tail, located on both sides of the tail of the fuselage respectively. Each ducted fan is pivotally connected to the inner side surface of the vertical tail on its same side respectively, and the two ducted fans are coaxially pivotally connected to the middle vertical tail, used to provide upward thrust during vertical takeoff and landing, and provide thrust or deceleration reverse thrust during takeoff and landing on a runway and level flight; A carrier cabin for carrying passengers or goods is provided on the composite wing flight module; The autonomous driving chassis serves as a takeoff and landing platform for the composite wing flight module, which has an autonomous driving function and can also drive autonomously or under the operation of a driver when combined with the composite wing flight module; When the composite wing flight module takes off, the autonomous driving chassis drives it to accelerate to obtain the main lift or auxiliary lift; When the composite wing flight module is combined with the autonomous driving chassis and traveling or parked on land, the fixed wing and the horizontal tail fold.

2. The skateboard chassis aircraft with multiple takeoff methods according to claim 1, characterized in that: The carrier cabin is a separate module that can be combined with or separated from the composite wing flight module or the autonomous driving chassis; When the carrier cabin is separated from the composite wing flight module, the composite wing flight module can fly and take off and land autonomously; When the carrier cabin is combined with the autonomous driving chassis, it travels as a vehicle autonomously or under the operation of a driver.

3. The skateboard chassis aircraft with multiple takeoff methods as described in claim 1, characterized in that: Each ducted fan can be tilted independently in the pitch direction, used to improve the maneuverability of the composite wing flight module during flight.

4. The skateboard chassis aircraft with multiple takeoff methods as described in claim 1, characterized in that: 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 of the central wing and the outer wing; Flaps and ailerons are provided on the outer wing, or a simplified form containing only ailerons.

5. The skateboard chassis aircraft with multiple takeoff methods according to claim 1, characterized in that: Elastic buffer and energy absorption materials are provided on the autonomous driving chassis, used to reduce the impact during the takeoff and landing of the composite wing flight module.

6. The skateboard chassis aircraft with multiple takeoff methods according to claim 1, characterized in that: Precision positioning pins are provided below the composite wing flight module or the carrier cabin. Precision positioning pin holes corresponding to them and rough positioning guide blocks for positioning the composite wing flight module are provided on the autonomous driving chassis, and positioning during the combination of the composite wing flight module and the autonomous driving chassis is achieved through mutual cooperation.

7. The skateboard chassis aircraft with multiple take-off methods according to claim 1, characterized in that: Landing gears are also provided on the composite wing flight module, used for the composite wing flight module to take off and land by itself or make an emergency landing on land or water.

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