Support device for an aircraft, safety system for an aircraft and aircraft comprising same

Abstract

This utility model relates to the field of unmanned vehicle support technology, specifically to a support device and safety system for aircraft. The support device includes multiple support frames located at the corners of the aircraft body. Each support frame houses a longitudinally sliding outrigger. A drive motor is located at the bottom of the support frame, and a helical groove is formed on the outer side of the support frame. The drive motor includes a stator and a rotor, with the inner side of the rotor meshing with the helical groove. This utility model, through the design of liftable outriggers, uses the rotation of the drive motor to raise the entire aircraft body, making the top turbofan and wings higher than adjacent objects, allowing the aircraft to park in existing parking spaces. In the event of an emergency landing or even a crash, the outriggers, upon impact, can reverse the rotation of the drive motor, generating emergency power to ensure the operation of necessary safety systems within the aircraft.

Description

Technical Field

[0001] This utility model relates to the field of unmanned vehicle support technology, specifically to support devices for aircraft, safety systems for aircraft, and aircraft. Background Technology

[0002] Aircraft represent a cutting-edge concept in urban air mobility, with numerous potential applications and advantages, and are expected to have a transformative impact on future transportation and lifestyles. Their future applications include urban air commuting, logistics delivery, and emergency rescue, utilizing low-altitude airspace to alleviate the heavy burden on urban road systems. Furthermore, aircraft are not limited or affected by ground road networks and congestion, enabling them to reach their destinations in a straight line at speeds far exceeding those of ground transportation.

[0003] However, the aircraft may have some limitations in future use. For example, the wings and turbofans of the aircraft occupy a lot of space. If a retractable design is adopted to reduce the overall volume of the aircraft, the space at both ends of the aircraft may be occupied by other vehicles or objects during parking, resulting in insufficient space for the wings and turbofans to unfold, causing the aircraft to be unable to take off or land, thus reducing the practicality and economy of the aircraft.

[0004] Therefore, it is necessary to invent a support device for aircraft and an aircraft thereof to solve the above problems. Utility Model Content

[0005] To address the shortcomings of existing technologies, the purpose of this utility model is to provide a support device and a safety system for aircraft, which mainly solves the technical problems of insufficient safety due to obstacles on both sides during the parking or takeoff process of aircraft.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: Aircraft support device: includes a support frame, inside which is a leg body that can slide longitudinally, the support frame is equipped with a drive motor, and the outer side of the leg body has a helical groove. The drive motor includes a stator and a rotor located inside the stator. The leg body passes through the rotor, and the rotor is driven by the external helical groove through a thread to realize the extension and retraction of the leg body relative to the support frame.

[0007] Preferably, in order to avoid the leg body rotating relative to the support frame and to achieve guidance, the aircraft support device of this embodiment is characterized in that the cross-section of the leg body is rectangular and the inner hole of the support frame is a rectangle that matches the leg body.

[0008] Preferably, the helix angle of the outer spiral groove is in the range of 15°-25°, and the spiral groove is opened at the corner of the leg body.

[0009] Specifically: The bottom of the outrigger body is provided with a support base for contacting and supporting the ground.

[0010] An aircraft safety system includes a gyroscope, a parachute, and an aircraft support device of any one of the aforementioned.

[0011] An aircraft includes an aircraft body, a battery pack and the aforementioned aircraft safety system, a support frame connected to the aircraft body, a parachute disposed at the upper end of the aircraft body, and an airbag disposed at the bottom of the aircraft body.

[0012] The aforementioned aircraft: The battery pack includes a battery pack body and an outwardly opening battery pack receiving cavity. The battery pack body is connected to the battery pack receiving cavity via a guide rail. The battery pack receiving cavity is driven by a battery pack quick-change mechanism to extend and retract relative to the battery pack receiving cavity.

[0013] To improve the aircraft's range, the top of the aircraft is equipped with retractable or foldable wings.

[0014] The technical effects and advantages provided by this utility model in the above technical solution are as follows: This utility model has the following advantages. First, through the design of the liftable outriggers, when there are other objects occupying space on both sides of the aircraft, the rotation of the drive motor drives the entire aircraft body to be raised, so that the top turbofan and wings are higher than the adjacent objects, giving them enough space to unfold, facilitating the take-off of the aircraft, and enabling the aircraft to be parked in existing parking spaces.

[0015] Secondly, when the aircraft makes an emergency landing or even crashes, the outriggers, when impacted, can reverse the rotation of the drive motors to generate emergency power, ensuring that necessary safety systems in the aircraft function, such as deploying airbags.

[0016] In the event of a crash, if the aircraft is at a high altitude, the parachute located at the top can deploy to cushion the impact. At a lower altitude, the gyroscope, in conjunction with the turbofan's rotation, can rapidly adjust the aircraft's attitude, allowing the wings to act as a buffer and ensuring that the outriggers make initial contact with the ground upon landing. The airbags at the bottom serve as a final safety measure. When crashing into water, the airbags provide buoyancy, preventing the aircraft from sinking. Furthermore, due to the presence of airbags, in certain situations, the aircraft can choose to make an emergency landing on water, avoiding damage from a hard landing.

[0017] When the battery pack itself catches fire, the corresponding battery pack can be quickly ejected through the battery pack quick-change mechanism to prevent the fire from spreading further and to further improve safety performance. Attached Figure Description

[0018] Figure 1This is a schematic diagram of the overall structure of the aircraft of this utility model; Figure 2 This is a schematic diagram of the structure of the airbag in the deployed state of this utility model; Figure 3 This is a schematic diagram of the structure of the support frame and the leg body of this utility model; Figure 4 This is a schematic diagram of the connection structure between the drive motor and the outrigger body of this utility model; Figure 5 This is an enlarged schematic diagram of the internal structure of the battery pack housing cavity of this utility model.

[0019] Explanation of reference numerals in the attached drawings: 1-Aircraft body; 2-Turbofan; 3-Wing; 4-Leg body; 5-Battery pack; 6-Drive motor; 601-Stator; 602-Rotor; 603-Bearing; 604-Permanent magnet; 7-Support base; 701-Connecting bolt; 41-Helical groove; 9-Parachute; 10-Leg frame; 51-Battery pack body; 52-Battery pack cavity; 53-Guide rail; 54-Battery pack quick-change mechanism; 11-Airbag. Detailed Implementation

[0020] The present invention will be further described below with reference to the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present invention, and should not be used to limit the scope of protection of the present invention.

[0021] This utility model provides, for example Figure 1-4 The aircraft support device shown includes a support frame 10, inside which a leg body 4 capable of sliding longitudinally is disposed. A drive motor 6 is disposed in the support frame 10, and an external helical groove 41 is formed on the outer side of the leg body 4. The drive motor 6 includes a stator 601 and a rotor 602 located inside the stator 601. The leg body 4 passes through the rotor 602, and the rotor 602 is threaded into the helical groove 41 for transmission, thereby enabling the extension and retraction of the leg body 4 relative to the support frame 10. In this embodiment, the stator 601 includes magnets and coils as in the prior art, and a permanent magnet 604 is provided on the outer ring of the rotor 602. The rotor 602 and the stator 601 are fixed together by at least two bearings 603. Considering that the drive motor 6 needs to withstand a certain axial thrust, the bearings 603 in this embodiment can be angular thrust bearings or thrust bearings as in the prior art.

[0022] The cross-section of the outrigger body 4 is preferably rectangular, and the inner hole of the support frame 5 is also rectangular, matching the outer contour of the outrigger body 4. The stator 601 is preferably fixedly mounted to the bottom end of the aircraft body 1, and the rotor 602 is sleeved on the outside of the outrigger body 4, with an internal thread on the inner side of the rotor 602 that matches the helical groove 9. As the rotor 602 rotates, the aforementioned internal thread engages with the helical groove 9, thereby adjusting the axial position of the outrigger body 4.

[0023] Since the support device in this embodiment is used for an aircraft, safety must be considered. This embodiment also discloses an aircraft safety system. If the aircraft using this safety system needs to make an emergency landing or even crash during flight, the outriggers must be able to provide a certain degree of cushioning. To achieve this, the outrigger body 4 in this embodiment can reversely drive the rotor 602 to rotate when subjected to a large impact or thrust. When the rotor 602 rotates, it can generate electricity through the drive motor 6, thus providing the necessary safety power for the aircraft. This safety power can sense the aircraft's attitude through the gyroscope, and then quickly adjust the aircraft's attitude through the operation of the turbofan 2, adjusting the outrigger body 4 to be below the aircraft body 1, ensuring that the outrigger body 4 is at the lowest point when the aircraft lands, thereby achieving cushioning. To further improve safety, the safety system described in this embodiment also includes a parachute 9 set at the top of the aircraft body 1, and an airbag 11 is also provided at the bottom of the aircraft body 1. Figure 2 (As shown). The airbag 11 is normally stored at the bottom of the aircraft body 1. It has two applications: one is to cushion the impact when the aircraft lands on the ground, and the other is to provide buoyancy support when the aircraft lands on water.

[0024] At the top of the aircraft body 1, there is also a retractable or foldable wing 3. By retracting the wing, the space occupied by the aircraft is reduced. By unfolding the wing 3, the aircraft can take off more easily. When the aircraft is flying horizontally, the wing 3 can increase horizontal lift and greatly reduce flight energy consumption. Furthermore, when the aircraft crashes, the wing 3 can also play a cushioning role when the aircraft's attitude is normal, which is also part of the safety system.

[0025] Since the cross-section of the outrigger body 4 is rectangular, the spiral groove 9 can only be opened at the corner of the outrigger body 4. The spiral groove 9 at the corner can ensure the lifting and lowering effect of the outrigger body 4, and the end face of the outrigger body 4 can play a guiding role within the support frame 5. The combination of the two reduces the complexity of the structure and facilitates the lightweighting of the aircraft.

[0026] According to mechanical design principles, and considering the influence of materials and lubrication, a bolt can drive the thread to rotate only if the helix angle is greater than the friction angle. For most engineering materials, the friction angle is between 5° and 10°, so theoretically, the helix angle usually needs to be greater than about 10°. In this embodiment, the helix angle of the helical groove 41 opened on the outer side of the leg body 4 ranges from 15° to 25°.

[0027] The bottom end of the outrigger body 4 is provided with a detachable support base 7, and the bottom end of the support base 7 is provided with anti-slip stripes or an anti-slip structure. The aircraft body 1 is a vertical takeoff and landing aircraft. Multiple rotating turbofans 2 are mounted on the top of the aircraft body 1. When the aircraft body 1 needs to take off, multiple outriggers 4 extend synchronously, ensuring that the top of the aircraft body 1 is higher than the top of adjacent vehicles, preventing collisions with adjacent vehicles after the wings 3 and turbofans 2 are deployed. A drive motor 6 is located at the bottom of the support frame 5. Through the rotation of the rotor 602, it drives the outriggers 4 to slide longitudinally. The square end faces of the outriggers 4 limit their movement, preventing rotation during longitudinal sliding and ensuring the stability of the support effect.

[0028] This embodiment also discloses an aircraft including the aforementioned aircraft safety system. The aircraft has at least four support devices. The drive motors 6 are hollow servo motors, and the rotors 602 of the multiple drive motors 6 rotate synchronously via a control module. By synchronously controlling the rotation of multiple rotors 602, the synchronous extension and retraction of multiple outrigger bodies 4 is achieved, ensuring the stability of the support.

[0029] Considering that the size of future small aircraft is about the size of a car, it is very likely that such aircraft will be parked in existing parking spaces. When vehicles are parked on both sides of the aircraft, the takeoff of the aircraft may be affected by the vehicles next to it. In this case, this utility model uses the liftable support leg body 4 to lift the entire aircraft body 1 to a certain height, so that the turbofan 2 and folding wings 3 at the top of the aircraft are higher than the adjacent objects, so that they have enough space to unfold, which is conducive to the flight of unmanned vehicles and avoids the problem of insufficient space hindering the takeoff and landing of the aircraft body 1.

[0030] like Figure 5As shown, the aircraft also includes a battery pack 5, which comprises a battery pack body 51 and an outwardly opening battery pack receiving cavity 52. ​​The battery pack body 51 is connected to the battery pack receiving cavity 52 via a guide rail 53. The battery pack receiving cavity 52 is driven to extend and retract relative to the battery pack body 51 via a battery pack quick-change mechanism 54. The battery pack quick-change mechanism 54 may include cylinders (hydraulic cylinders or electric cylinders) as used in the prior art, as well as battery pack locking, guide rails, and other structures. During flight, if the battery pack body 51 experiences high temperatures or catches fire, the corresponding battery pack can be quickly ejected via the battery pack quick-change mechanism 54, provided other external conditions permit, to prevent the fire from spreading further. "Other permitted external conditions" includes ensuring the safety of residents or property below. There are typically four battery packs 5, employing a redundant design. In actual use, if any one battery pack 5 fails, the other battery packs can continue to operate normally.

[0031] Compared with the prior art, this embodiment has the following advantages. First, this embodiment can use the design of the liftable outrigger body 4 to lift the entire aircraft body 1 by rotating the drive motor 6 when there are other objects occupying space on both sides of the aircraft. This makes the top turbofan 2 and wings 3 higher than the adjacent objects, so that they have enough space to unfold, which facilitates the take-off of the aircraft and allows the aircraft to be parked in the existing parking space.

[0032] When the aircraft makes an emergency landing or even crashes, the outrigger body 4 can reverse the rotation of the drive motor 6 when it is impacted, generating emergency power to ensure that the necessary safety systems in the aircraft work, such as deploying the airbag 11.

[0033] In the event of a crash, if the aircraft is at a relatively high altitude (e.g., above 30-50 meters), the parachute 9 located at the top can be deployed to cushion the impact. At a lower altitude, the aircraft's attitude can be rapidly adjusted using a gyroscope in conjunction with the rotation of the turbofan 2. This allows the wings 3 to act as a buffer and ensures that the outriggers 4 make contact with the ground first upon landing. The airbag 11 at the bottom serves as a final safety barrier. When crashing into water, the airbag 11 provides buoyancy, preventing the aircraft from sinking. Furthermore, due to the presence of the airbag 11, in certain situations, the aircraft can choose to make an emergency landing on water, avoiding damage from a hard landing.

[0034] When the battery pack body 51 catches fire, the corresponding battery pack can be quickly ejected through the battery pack quick-change mechanism 54 to prevent the fire from spreading further and to further improve safety performance.

[0035] The above are merely preferred embodiments of this utility model. It should be noted that, for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of this utility model, and these improvements and modifications should also be considered within the protection scope of this utility model.

Claims

1. A support device for aircraft, characterized in that: The system includes a support frame (10), inside which is a leg body (4) that can slide longitudinally. The support frame (10) is equipped with a drive motor (6). The outer side of the leg body (4) is provided with a spiral groove (41). The drive motor (6) includes a stator (601) and a rotor (602) located inside the stator (601). The leg body (4) passes through the rotor (602). The rotor (602) is driven by the thread and the outer spiral groove (41) to realize the extension and retraction of the leg body (4) relative to the support frame (10).

2. The aircraft support device according to claim 1, characterized in that, The cross-section of the outrigger body (4) is rectangular, and the inner hole of the support frame (10) is a rectangle that matches the outrigger body (4).

3. The aircraft support device according to claim 1, characterized in that: The helix angle of the outer helical groove (41) ranges from 15° to 25°.

4. The aircraft support device according to claim 1, characterized in that: The bottom end of the outrigger body (4) is provided with a support base (7) for contacting and supporting the ground.

5. The aircraft support device according to any one of claims 1 to 4, characterized in that: The spiral groove (41) is located at the corner of the leg body (4).

6. A safety system for aircraft, characterized in that: It includes a gyroscope, a parachute (9), and a support device for an aircraft as described in any one of claims 1 to 5.

7. An aircraft, characterized in that: The aircraft includes an aircraft body (1), a battery pack (5) and a safety system for an aircraft as described in claim 6. The support frame (10) is connected to the aircraft body (1), and the parachute (9) is disposed at the upper end of the aircraft body (1). An airbag (11) is also provided at the bottom of the aircraft body (1).

8. The aircraft according to claim 7, characterized in that: The battery pack (5) includes a battery pack body (51) and an outwardly opening battery pack receiving cavity (52). The battery pack body (51) is connected to the battery pack receiving cavity (52) via a guide rail (53). The battery pack receiving cavity (52) is driven by a battery pack quick-change mechanism (54) to extend and retract relative to the battery pack receiving cavity (52).

9. The aircraft according to claim 8, characterized in that: The top of the aircraft body (1) is also provided with a retractable or foldable wing (3).

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