Rotor pod and vehicle
By designing a rotor cabin, the rotor is hidden inside the cabin when retracted, and opens the cabin door when deployed, solving the problem of flying car rotors interfering with the road surface and improving both safety and aesthetics.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- GUANGDONG HUITIAN AEROSPACE TECH CO LTD
- Filing Date
- 2022-07-01
- Publication Date
- 2026-05-12
AI Technical Summary
The external rotor structure of existing flying cars makes them prone to interfering with other vehicles and pedestrians on the road when traveling on land.
Design a rotor cabin including a cabin body, a first door and a second door. The rotor can be selectively retracted or deployed. When the rotor is retracted, it is retracted from the cabin body. When deployed, it drives the second door to open the cabin so that it protrudes out of the cabin body. The door and the rotor are linked. The state switching of the rotor and the door is controlled by a drive.
It effectively avoids interference from the rotor to other vehicles and pedestrians, improves the safety and aesthetics of the flying car on the ground, and simplifies the operation process.
Smart Images
Figure CN116946401B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of transportation technology, and more specifically, to a rotor cabin and a transportation vehicle. Background Technology
[0002] In vehicles using related technologies, such as flying cars, the flight structure is directly external to the fuselage, which makes it easy for flying cars to interfere with other vehicles and pedestrians on the road while traveling on land. Summary of the Invention
[0003] Embodiments of the present invention provide a rotor cabin or vehicle to improve at least one of the above-mentioned problems.
[0004] The embodiments of the present invention achieve the above objectives through the following technical solutions.
[0005] In a first aspect, embodiments of the present invention provide a rotor cabin, comprising a cabin body, a first door, a second door, and a rotor. The cabin body has a first compartment and a second compartment that are connected to each other. The first door is mounted on the cabin body and can selectively open or close the first compartment. The second door is mounted on the cabin body and can selectively open or close the second compartment. The rotor is mounted on the cabin body and can be selectively in a retracted state or an deployed state. The rotor is retracted from outside the cabin body through the first compartment into the cabin body in the retracted state. When the rotor switches from the retracted state to the deployed state, it causes the second door to open the second compartment and protrude from the second compartment out of the cabin body.
[0006] In some embodiments, the first door is hinged to the cabin body, and the rotor cabin also includes a telescopic actuator hinged between the cabin body and the first door. The telescopic movement of the telescopic actuator causes the first door to rotate relative to the cabin body, and enables the first door to selectively open or close the first cabin.
[0007] In some embodiments, the rotor cabin also includes a door lock body and a door latch, which are selectively locked or unlocked. One of the door lock body and the door latch is mounted on the cabin body, and the other is mounted on the first door.
[0008] In some embodiments, the second hatch is hinged to the cabin and slides with the rotor. When the rotor switches from the deployed state to the retracted state, it drives the second hatch to close the second cabin.
[0009] In some embodiments, the second door includes a hinged portion and a sliding portion, the hinged portion being opposite to the sliding portion, the hinged portion being hinged to the cabin body, and the sliding portion being slidably engaged with the rotor.
[0010] In some embodiments, the rotor cabin also includes a guide rail and a slider, the guide rail being mounted on the rotor and the slider being hinged to the sliding portion and slidably disposed on the guide rail.
[0011] In some embodiments, the rotor cabin also includes a resilient reset member fitted at the hinge between the second door and the cabin body, the resilient reset member being adapted to provide a resilient force for the second door to rotate in the direction of the second cabin.
[0012] In some embodiments, the rotor includes wing arms and propeller blades, the wing arms being hinged to the cabin and the propeller blades being rotatably mounted to the wing arms; the second cabin door includes a ball joint that is slidably abutting against the wing arm.
[0013] In some embodiments, the rotor also includes an elastic pad connected to the wing arm and abutting against the ball head.
[0014] In some embodiments, the volume of the second hatch is smaller than that of the first hatch; and / or, the second hatch has a hollow structure.
[0015] In some embodiments, the movement of the rotor relative to the cabin causes the second door to selectively open or close the second compartment. The rotor cabin also includes a processor, a door actuator, and a rotor actuator. The processor is signal-connected to both the door actuator and the rotor actuator. The door actuator drives the first door to selectively open or close the first compartment, and the rotor actuator drives the rotor to selectively be in a retracted or deployed state. The processor outputs an opening signal, and the door actuator responds to the opening signal and controls the first door to open the first compartment. The processor also outputs a rotor control signal, and the rotor actuator responds to the rotor control signal and controls the rotor to be in the corresponding state. The rotor control signal includes a rotor deployment signal and a rotor retraction signal. The rotor actuator controls the rotor to be in the deployed state according to the rotor deployment signal, and controls the rotor to be in the retracted state according to the rotor retraction signal. The processor also outputs a closing signal, and the door actuator responds to the closing signal and controls the first door to close the first compartment.
[0016] Secondly, embodiments of the present invention also provide a means of transportation, the means of transportation including a fuselage and a rotor cabin of any of the above embodiments, the cabin being mounted on the fuselage.
[0017] In the rotor cabin and vehicle provided by the embodiments of the present invention, the rotor cabin has a first compartment and a second compartment that are connected to each other. A first door is installed on the cabin body and can selectively open or close the first compartment. A second door is installed on the cabin body and can selectively open or close the second compartment. The rotor is installed on the cabin body and can be selectively in a retracted state or an deployed state. The rotor is retracted from the cabin body through the first compartment into the cabin body in the retracted state, so as to facilitate the retraction of the rotor into the cabin body and help avoid interference with other vehicles, pedestrians, etc. When the rotor switches from the retracted state to the deployed state, it drives the second door to open the second compartment and protrude from the second compartment out of the cabin body, so that the vehicle can achieve flight by means of the rotor. Attached Figure Description
[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.
[0019] Figure 1 A schematic diagram of the rotor cabin provided in an embodiment of the present invention is shown.
[0020] Figure 2 It shows Figure 1 A schematic diagram of the rotor cabin with the rotor in the deployed state.
[0021] Figure 3 It shows Figure 1 A partial structural diagram of the rotor cabin.
[0022] Figure 4 It shows Figure 1 A schematic diagram of another part of the rotor cabin.
[0023] Figure 5 It shows Figure 1 A partial structural diagram of the first door of the rotor cabin.
[0024] Figure 6 It shows Figure 1 A schematic diagram of the structure in which the second door of the rotor cabin is connected to the rotor.
[0025] Figure 7 It shows Figure 1 A schematic diagram of the rotor cabin with the rotor in the deployed state from another perspective.
[0026] Figure 8 It shows Figure 1 A schematic diagram of the structure in which the rotor of the rotor cabin drives the second door to open the second compartment.
[0027] Figure 9 A schematic diagram of the structure of the second door of the rotor cabin and its cooperation with the rotor is shown in another embodiment of the present invention.
[0028] Figure 10 It shows Figure 1 A schematic diagram of the rotor cabin's processor, door actuator, and rotor actuator modules. Detailed Implementation
[0029] To enable those skilled in the art to better understand the present invention, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.
[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings.
[0031] Please see Figure 1 and Figure 2 This invention provides a rotor cabin 100, which can be applied to vehicles to enable them to fly. The vehicle can be an amphibious vehicle (land and air), a tri-amphibious vehicle (sea, land, and air), or similar types. This invention uses an amphibious vehicle as an example for illustration; for instance, the vehicle could be a flying car.
[0032] The rotor cabin 100 includes a cabin body 10, a first cabin door 20, a second cabin door 30, and a rotor 40, all of which are mounted on the cabin body 10.
[0033] The cabin 10 can be generally rectangular or other shapes. When the rotor cabin 100 is used in a flying car, the cabin 10 can be mounted on the vehicle body, for example, the cabin 10 can be mounted on the top of the vehicle body.
[0034] The hull 10 has a first compartment 11 and a second compartment 12, which are connected to each other. The sizes of the first compartment 11 and the second compartment 12 can be distinguished; for example, the space of the first compartment 11 can be larger than that of the second compartment 12.
[0035] The first hatch 20 can selectively open or close the first compartment 11. For example... Figure 2 As shown, the first hatch 20 can open the first compartment 11, allowing the first compartment 11 to communicate with the outside environment. For example... Figure 1 As shown, the first hatch 20 can close the first compartment 11, which facilitates the separation of the first compartment 11 from the outside environment.
[0036] The first hatch 20 is movably mounted to the hull 10 to allow selective opening or closing of the first compartment 11. For example, the first hatch 20 may be hinged to the hull 10, so that rotation of the first hatch 20 relative to the hull 10 can open or close the first compartment 11.
[0037] The first hatch 20 and the hull 10 can be hinged together via an intermediate structure. For example, please refer to [link / reference needed]. Figure 3 and Figure 4 The rotor cabin 100 may also include a first hinge 51, which is connected between the first door 20 and the cabin body 10. The first door 20 and the cabin body 10 can be hinged together by the first hinge 51.
[0038] The first hinge 51 may include a first hinge, a second hinge, and a first pivot. The first hinge may be connected to the hull 10, for example, by means of screws, bolts, rivets, or other fasteners. The second hinge may be connected to the first hatch 20, for example, by means of screws, bolts, rivets, or other fasteners. The first pivot is rotatably inserted through the first and second hinges, allowing the first and second hinges to rotate relative to each other, thereby enabling the first hatch 20 to rotate relative to the hull 10.
[0039] In other embodiments, the first hatch 20 and the cabin 10 may be hinged in other ways.
[0040] The first door 20 can be connected to a drive structure to move relative to the cabin 10 under the drive of the drive structure. For example, the rotor cabin 100 may also include a door actuator 61, which can be mounted between the cabin 10 and the first door 20. The door actuator 61 is used to drive the first door 20 to selectively open or close the first cabin 11.
[0041] The hatch actuator 61 can be a telescopic actuator, which can be hinged between the hull 10 and the first hatch 20. For example, the main body of the telescopic actuator can be hinged to the hull 10, and the telescopic end of the telescopic actuator can be hinged to the first hatch 20. In this way, the telescopic movement of the telescopic actuator can drive the first hatch 20 to rotate relative to the hull 10, and make the first hatch 20 selectively open or close the first compartment 11.
[0042] In this embodiment, the door actuator 61 can be an electric push rod. In other embodiments, the door actuator 61 can also be other types of actuators.
[0043] The first hatch 20 can be used in conjunction with a locking mechanism to improve the stability of the rotor cabin 100. (See, for example...) Figure 3 and Figure 5The rotor cabin 100 may further include a door lock body 71 and a door latch 72, which are selectively locked or unlocked. One of the door lock body 71 and the door latch 72 is fitted to the cabin body 10, and the other is fitted to the first door 20. Thus, when the first door 20 closes the first compartment 11, the door lock body 71 and the door latch 72 can be locked, thereby helping the first door 20 to be stably in the closed state of the first compartment 11. The door lock body 71 can be an electrically operated magnetic lock or other types.
[0044] The hatch latch 72 can be fitted to the first hatch 20, for example, at a position away from the hinged hatch 20 to the hull 10. Correspondingly, the hatch lock body 71 can be fitted to the hull 10. When the first hatch 20 is closed in the first compartment 11, the hatch lock body 71 can be opposite to the hatch latch 72 so that the hatch lock body 71 can cooperate with the hatch latch 72.
[0045] In other embodiments, the hatch lock body 71 can be fitted to the first hatch 20, and the hatch latch 72 can be fitted to the hull 10.
[0046] The first hatch 20 can be made of carbon fiber composite material, which helps to reduce the weight of the first hatch 20 and meet the lightweight design requirements of the rotor cabin 100. In other embodiments, the first hatch 20 can also be made of other materials.
[0047] The second hatch 30 can selectively open or close the second compartment 12. For example... Figure 2 As shown, the second hatch 30 can open the second compartment 12 to allow communication between the second compartment 12 and the outside environment. For example... Figure 1 As shown, the second hatch 30 can close the second compartment 12, making it easier to separate the second compartment 12 from the outside environment.
[0048] The second hatch 30 is movably fitted to the hull 10 to allow for the selective opening or closing of the second compartment 12. See, for example, [link to relevant documentation]. Figure 6 The second hatch 30 may include a hinge 31, which is hinged to the cabin 10. The rotation of the second hatch 30 relative to the cabin 10 can open or close the second cabin 12.
[0049] The second door 30 and the cabin 10 can be hinged together through an intermediate structure. For example, the rotor cabin 100 may also include a second hinge 52, which connects the second door 30 and the cabin 10. For example, the second hinge 52 can connect the hinge part 31 and the cabin 10, and the second door 30 and the cabin 10 can be hinged together through the second hinge 52.
[0050] The second hinge 52 may include a third hinge, a fourth hinge, and a second pivot. The third hinge may be connected to the hull 10, for example, by using screws, bolts, rivets, or other fasteners. The fourth hinge may be connected to the second hatch 30, for example, by using screws, bolts, rivets, or other fasteners to connect the fourth hinge to the hinge portion 31. The second pivot is rotatably inserted through the third and fourth hinges, allowing the third and fourth hinges to rotate relative to each other, thereby enabling the second hatch 30 to rotate relative to the hull 10.
[0051] In other embodiments, the second hatch 30 and the hull 10 may be hinged in other ways.
[0052] The second door 30 can be made of carbon fiber composite material, which helps to reduce the weight of the second door 30 and meet the lightweight design requirements of the rotor cabin 100. In other embodiments, the second door 30 can also be made of other materials.
[0053] The rotor 40 can be selectively in a retracted state or an deployed state, and the rotor 40 is located in different positions depending on the state it is in.
[0054] The rotor 40 is retracted from the outside of the cabin 10 through the first compartment 11 into the cabin 10, thus facilitating its storage and helping to avoid interference with other vehicles and pedestrians. Since the rotor cabin 100, in its retracted state, does not experience wind noise, howling, or other sound quality issues due to the exposed rotor 40, it contributes to the flying car's safer operation on the ground, helping to meet land-based regulations and maintain an aesthetically pleasing overall design.
[0055] The rotor 40 can extend from inside the cabin 10 to the outside of the cabin 10 in an deployed state, so that the deployed rotor 40 protrudes outside the cabin 10, so that the vehicle can fly by means of the rotor 40.
[0056] Please see Figure 2 The rotor 40 may include a wing arm 41 and a propeller blade 42. The propeller blade 42 is rotatably mounted on the wing arm 41. The rotation of the propeller blade 42 relative to the wing arm 41 can provide propulsion for the flying car, so that the flying car can achieve flight.
[0057] The wing arm 41 can be hinged to the cabin 10 so that the rotor 40 can be in different states by rotating relative to the cabin 10. The hinge point between the wing arm 41 and the cabin 10 can be located inside the second compartment 12. Thus, when the rotor 40 is in the deployed state, the wing arm 41 can rotate relative to the cabin 10 to protrude from the cabin 10 outside the second compartment 12, so as not to occupy the space of the first compartment 11. This facilitates the closing of the first compartment 11 by the first door 20 and helps to reduce the airflow resistance of the first door 20.
[0058] In addition, when the rotor 40 is in the retracted state, a part of the structure of the wing arm 41 can be located in the second compartment 12, and another part of the structure can be located in the first compartment 11, and the propeller blade 42 can be located in the first compartment 11.
[0059] The number of propeller blades 42 can be multiple. For example, there can be two propeller blades 42, which are rotatably mounted on the upper and lower sides of the wing arm 41, thus facilitating the use of the rotor 40 as a twin-rotor structure.
[0060] The rotor 40 can be connected to a drive structure to move relative to the hull 10 under the drive of the drive structure. For example... Figure 2 and 7 As shown, the rotor cabin 100 may also include a rotor actuator 62, which can be mounted between the cabin 10 and the rotor 40. The rotor actuator 62 is used to drive the rotor 40 to be selectively in a retracted state or an deployed state.
[0061] The rotor actuator 62 can be a telescopic drive structure, and it can be hinged between the hull 10 and the rotor 40. For example, the main body end 621 of the rotor actuator 62 can be hinged to the hull 10, and the telescopic end 622 of the rotor actuator 62 can be hinged to the wing arm 41. In this way, the telescopic movement of the rotor actuator 62 can drive the rotor 40 to rotate relative to the hull 10, and allow the rotor 40 to be selectively in a retracted state or an deployed state.
[0062] In this embodiment, the rotor actuator 62 can be an electric actuator. In other embodiments, the rotor actuator 62 can also be other types of drive structures.
[0063] The rotor 40 can be linked and coordinated with the second hatch 30. For example, when the rotor 40 switches from the retracted state to the deployed state, it drives the second hatch 30 to open the second compartment 12. Figure 8 As shown. In this way, the second compartment 12 can be opened without additional operation of the second door 30, which helps to simplify the operation of the rotor cabin 100.
[0064] For example, when rotor 40 switches from the deployed state to the retracted state, it drives the second hatch 30 to close the second compartment 12, such as... Figure 6 As shown. In this way, the second compartment 12 can be closed without additional closing operation of the second door 30, which helps to simplify the operation of the rotor cabin 100.
[0065] As the rotor 40 switches to different states, the movement of the rotor 40 relative to the cabin 10 can selectively open or close the second cabin 12 via the second door 30, thus achieving linkage between the rotor 40 and the second door 30, which can effectively simplify the operation.
[0066] The rotor 40 can slide and engage with the second door 30 to achieve linkage between the two. For example, the second door 30 may also include a sliding part 32, which may be opposite to the hinge part 31. The sliding part 32 can slide and engage with the rotor 40, for example, the sliding part 32 can slide and engage with the wing arm 41. In this way, the sliding engagement method is relatively simple and helps to simplify the structure of the rotor 40 and the second door 30.
[0067] The sliding part 32 and the rotor 40 can achieve a sliding fit using an intermediate structure. For example... Figure 9 As shown, the rotor compartment 100 may further include a guide rail 73 and a slider 74, with the slider 74 slidably mounted on the guide rail 73. The guide rail 73 can be fitted to the rotor 40, for example, by fastening the guide rail 73 to the wing arm 41 with fasteners such as screws, bolts, or rivets. The slider 74 can be hinged to the sliding part 32, for example, by hinged to the sliding part 32 via a pivot. Thus, the sliding part 32 and the rotor 40 are connected by a sliding engagement of the guide rail 73 and the slider 74, which helps to stabilize the connection between the rotor 40 and the second compartment 30. In other embodiments, the sliding part 32 and the rotor 40 may also employ other structures to achieve a sliding engagement.
[0068] The rotor cabin 100 may also include a resilient reset member 80, which can be fitted at the hinge between the second door 30 and the cabin body 10. For example, the resilient reset member 80 can be fitted at the second hinge 52, or it can be sleeved on the second pivot and abut against the third and fourth hinges.
[0069] The elastic reset element 80 is adapted to provide an elastic force for the second hatch 30 to rotate in the direction of the second compartment 12. Thus, when the rotor 40 switches from the deployed state to the retracted state, the second hatch 30 always remains abutting against the rotor 40. The second hatch 30 can gradually close the second compartment 12 under the guidance of the rotor 40, thereby simplifying the sliding engagement between the second hatch 30 and the rotor 40. This eliminates the need for an additional sliding structure to connect the second hatch 30 and the rotor 40, simplifying the structure and number of parts of the rotor compartment 100. The elastic reset element 80 can be a return spring, a torsion spring, or other structures.
[0070] The structure of the second door 30 can be adapted and adjusted according to the elastic reset member 80. For example, the second door 30 may include a ball joint 33, which slidably abuts against the wing arm 41. This helps the second door 30 maintain good contact with the wing arm 41. The ball joint 33 can serve as the structure of the sliding part 32.
[0071] The structure of rotor 40 can be adapted and adjusted according to the structure of the second door 30. For example, rotor 40 may also include an elastic pad 43, which can be connected to wing arm 41 and abut against ball joint 33. In this way, elastic pad 43 can protect ball joint 33 and wing arm 41, helping to avoid direct friction contact between the two and ensuring their durability. Elastic pad 43 can be a rubber pad or a pad made of other materials.
[0072] Please see Figure 10 The rotor cabin 100 may also include a processor 90, which can be signal-connected to the door actuator 61 and the rotor actuator 62 respectively. The processor 90 can send different signals to control the rotor cabin 100 to be in different operating modes.
[0073] For example, when flight is required, the processor 90 can output a door opening signal, and the door actuator 61 responds to the signal and controls the first door 20 to open the first compartment 11. The processor 90 can also output a rotor control signal, and the rotor actuator 62 responds to the signal and controls the rotor 40 to be in the corresponding state. The rotor control signal includes a rotor deployment signal, and the rotor actuator 62 controls the rotor 40 to be in the deployed state based on the rotor deployment signal. The processor 90 can also output a door closing signal, and the door actuator 61 responds to the signal and controls the first door 20 to close the first compartment 11.
[0074] For example, when land travel is required, the processor 90 can output a door opening signal, and the door actuator 61 responds to the door opening signal and controls the first door 20 to open the first compartment 11. The processor 90 can also output a rotor control signal, and the rotor actuator 62 responds to the rotor control signal and controls the rotor 40 to be in the corresponding state. The rotor control signal also includes a rotor retraction signal, and the rotor actuator 62 controls the rotor 40 to be in the retracted state according to the rotor retraction signal. The processor 90 can also output a door closing signal, and the door actuator 61 responds to the door closing signal and controls the first door 20 to close the first compartment 11.
[0075] In some implementations, the rotor cabin 100 can reduce airflow drag by adjusting the structure of the door. For example, in flight mode, the second door 30 opens the second compartment 12 to allow the rotor 40 to be deployed. The volume of the second door 30 can be designed to be smaller than that of the first door 20, which helps to reduce the airflow drag experienced by the second door 30.
[0076] In some embodiments, the second hatch 30 may have a perforated structure. This helps to reduce the weight of the second hatch 30 and also helps to reduce airflow resistance to the second hatch 30.
[0077] In some implementations, there can be multiple first compartments 11. For example... Figure 1 As shown, there are two first compartments 11. The two first compartments 11 can be symmetrically distributed on the body 10. For example, the two first compartments 11 can be symmetrically distributed on the left and right sides of the body 10, and can be used as the left first compartment and the right first compartment, respectively.
[0078] Correspondingly, the number of first hatches 20 is the same as the number of first compartments 11. There can also be two first hatches 20, with each first hatch 20 corresponding to one of the two first compartments 11. Each first hatch 20 can selectively open or close a corresponding first compartment 11. The hinge points of the two first hatches 20 to the hull 10 can be close to each other; for example, the hinge points of the two first hatches 20 to the hull 10 can be located in the middle of the hull 10, so that when the two first hatches 20 open their respective first compartments 11, they can form a European-wing opening configuration. The two first hatches 20 can be designated as the left first hatch and the right first hatch, respectively.
[0079] There can be multiple second compartments 12. For example, there can be four second compartments 12, which can be designated as the left front second compartment, the left rear second compartment, the right front second compartment, and the right rear second compartment, respectively. The left front second compartment and the left rear second compartment can be symmetrically distributed on the front and rear sides of the left first compartment, and the right front second compartment and the right rear second compartment can be symmetrically distributed on the front and rear sides of the right first compartment.
[0080] Correspondingly, the number of second hatches 30 is the same as the number of second compartments 12. There can also be four second hatches 30, with each of the four second compartments 12 corresponding to one of them. Each second hatch 30 can selectively open or close a corresponding second compartment 12. The four second hatches 30 can be designated as the left front second hatch, left rear second hatch, right front second hatch, and right rear second hatch, respectively.
[0081] The number of rotors 40 can be the same as the number of the second compartment 12, or there can be four rotors 40, which can serve as the left front rotor, left rear rotor, right front rotor, and right rear rotor, respectively. The hinge point between the left front rotor and the compartment 10 can be located in the left front second compartment, the hinge point between the left rear rotor and the compartment 10 can be located in the left rear second compartment, the hinge point between the right front rotor and the compartment 10 can be located in the right front second compartment, and the hinge point between the right rear rotor and the compartment 10 can be located in the right rear second compartment. The left first compartment can accommodate the left front rotor and the left rear rotor, and the right first compartment can accommodate the right front rotor and the right rear rotor. In this way, the rotor compartment 100 can be used as a four-shaft, eight-propeller rotor compartment.
[0082] This invention also provides a means of transportation, which can be an amphibious vehicle, a land-air amphibious vehicle, or a land-sea-air amphibious vehicle. The means of transportation includes a fuselage and a rotor cabin 100 as described in any of the above embodiments, with the cabin 10 mounted on the fuselage.
[0083] In the case of a flying car, the fuselage can be the vehicle body, and the cabin 10 can be mounted on top of the vehicle body. When the area around the top structure is complex and the space is limited, the entire rotor 40 can be housed within the top structure, helping to achieve full coverage of the overall design and effectively improving the overall vehicle quality. In other embodiments, the cabin 10 can also be mounted in other locations on the vehicle body.
[0084] In the vehicle provided by this embodiment of the invention, the rotor cabin 100 has a body 10 with a first compartment 11 and a second compartment 12 connected to each other. A first door 20 is mounted on the body 10 and can selectively open or close the first compartment 11. A second door 30 is mounted on the body 10 and can selectively open or close the second compartment 12. The rotor 40 is mounted on the body 10 and can be selectively in a retracted or deployed state. The rotor 40 is retracted from outside the body 10 through the first compartment 11 into the body 10 in a retracted state, which facilitates the retraction of the rotor 40 and helps to avoid interference with other vehicles, pedestrians, etc. When the rotor 40 switches from the retracted state to the deployed state, it drives the second door 30 to open the second compartment 12 and protrude from the second compartment 12 out of the body 10, so that the vehicle can fly by means of the rotor 40.
[0085] In this invention, unless otherwise explicitly specified or limited, the terms "installation," "connection," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, an integral connection, or a transmission connection; they can be a direct connection or an indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.
[0086] Furthermore, the terms "first," "second," etc., are used only for distinguishing descriptions and should not be construed as referring to specific or particular structures. The description of "some embodiments" means that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this invention, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. Furthermore, without contradiction, those skilled in the art can combine and integrate different embodiments or examples described in this invention, as well as the features of different embodiments or examples.
[0087] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be included within the protection scope of the present invention.
Claims
1. A rotor cabin, characterized in that, include: The cabin has a first compartment and a second compartment that are connected to each other; A first hatch and a second hatch, wherein the first hatch is fitted to the hull and can selectively open or close the first compartment, and the second hatch is fitted to the hull and can selectively open or close the second compartment; A rotor is mounted on the cabin and can be selectively in a retracted or deployed state. The rotor is retracted into the cabin from outside the cabin via the first compartment in the retracted state. When the rotor switches from the retracted state to the deployed state, it drives the second door to open the second compartment and protrudes from the second compartment out of the cabin. The movement of the rotor relative to the cabin causes the door to selectively open or close the second compartment. as well as The system includes a processor, a door actuator, and a rotor actuator. The processor is signal-connected to the door actuator and the rotor actuator, respectively. The door actuator is used to selectively open or close the first compartment by driving the first door, and the rotor actuator is used to selectively put the rotor into the retracted state or the deployed state. The processor is used to output a door opening signal, and the door driver responds to the door opening signal and controls the first door to open the first compartment; The processor is also configured to output a rotor control signal, and the rotor driver responds to the rotor control signal and controls the rotor to be in a corresponding state. The rotor control signal includes a rotor deployment signal and a rotor retraction signal. The rotor driver controls the rotor to be in the deployment state according to the rotor deployment signal, and the rotor driver controls the rotor to be in the retraction state according to the rotor retraction signal. The processor is also configured to output a door closing signal, and the door driver responds to the door closing signal and controls the first door to close the first compartment.
2. The rotor cabin according to claim 1, characterized in that, The first door is hinged to the cabin body. The rotor cabin also includes a telescopic actuator, which is hinged between the cabin body and the first door. The telescopic movement of the telescopic actuator causes the first door to rotate relative to the cabin body, and allows the first door to selectively open or close the first cabin.
3. The rotor cabin according to claim 1, characterized in that, The rotor cabin also includes a door lock body and a door latch. The door lock body and the door latch can be selectively locked or unlocked. One of the door lock body and the door latch is assembled to the cabin body, and the other is assembled to the first door.
4. The rotor cabin according to claim 1, characterized in that, The second hatch is hinged to the cabin body and slides with the rotor. When the rotor switches from the deployed state to the retracted state, it drives the second hatch to close the second cabin.
5. The rotor cabin according to claim 4, characterized in that, The second hatch includes a hinged part and a sliding part. The hinged part is opposite to the sliding part, the hinged part is hinged to the cabin body, and the sliding part is slidably engaged with the rotor.
6. The rotor cabin according to claim 5, characterized in that, The rotor cabin also includes a guide rail and a slider. The guide rail is mounted on the rotor, and the slider is hinged to the sliding part and slidably disposed on the guide rail.
7. The rotor cabin according to claim 4, characterized in that, The rotor cabin also includes a resilient reset member, which is mounted at the hinge between the second door and the cabin body. The resilient reset member is adapted to provide the second door with a resilient force for rotation in the direction of the second cabin.
8. The rotor cabin according to claim 7, characterized in that, The rotor includes a wing arm and a propeller blade. The wing arm is hinged to the cabin, and the propeller blade is rotatably mounted on the wing arm. The second cabin door includes a ball joint that slidably abuts against the wing arm.
9. The rotor cabin according to claim 8, characterized in that, The rotor also includes an elastic pad, which is connected to the wing arm and abuts against the ball head.
10. The rotor cabin according to claim 1, characterized in that, The volume of the second hatch is smaller than that of the first hatch; and / or, the second hatch has a hollow structure.
11. A means of transportation, characterized in that, include: body; as well as The rotor cabin according to any one of claims 1 to 10, wherein the cabin is mounted on the fuselage.