Shared chassis of hovercar

Abstract

The utility model provides a shared chassis of hovercars, which relates to the field of shared chassis of hovercars and comprises a shared chassis, a flight cabin is arranged at the top of the shared chassis, a landing groove is formed in the top of the shared chassis, and a supporting plate is mounted at the upper end of an inner cavity of the landing groove. The landing groove and the supporting plate are used for supporting the flight cabin, a buffer assembly is installed at the bottom of an inner cavity of the landing groove, the buffer assembly is used for buffering and energy absorption, and the buffer assembly comprises a damper, a lower base, an upper base, a hydraulic rod, a buffer spring, a baffle ring and an adjusting ring; under the synergistic effect of the damper, the lower base, the upper base, the hydraulic rod, the buffer spring, the baffle ring, the adjusting ring, the external thread, the supporting seat and the supporting spring, the impact energy in the landing and butt joint process of the flight cabin can be effectively absorbed, so that the shared chassis and the flight cabin can be protected, and the safety and stability of the hovercar are ensured.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the shared chassis field of flying car, specifically a shared chassis of flying car. BACKGROUND

[0002] The flying car shared chassis is an important component in flying car technology, which has the characteristics of split design, automatic driving function, mobile charging station and sharing property, provides flexibility of ground driving, air flight and seamless air-ground connection for flying car, the flying cabin is responsible for air flight, the chassis is responsible for ground driving and as a mobile charging station, multiple flying cabins can share the same chassis, and efficient utilization is realized through an intelligent scheduling system.

[0003] According to Chinese patent application No. 201922432433.5, a kind of whole split type unmanned flying car is disclosed, including chassis, passenger cabin connected with the upper end of the chassis, and aircraft connected with the top of the passenger cabin;The chassis and passenger cabin, and the passenger cabin and aircraft are all equipped with an automatic lock for realizing the connection and separation of the chassis and passenger cabin and the passenger cabin and aircraft;Wherein the chassis and passenger cabin, and passenger cabin and aircraft are all equipped with positioning device, by sharing a passenger cabin between the chassis and aircraft to reduce weight, thereby improving the endurance of aircraft, prolonging the loitering time, and the speed of automobile driving will not be affected;

[0004] The prior art effectively solves the problem of heavy weight of flying car, thereby leading to poor endurance of aircraft, and the speed of automobile driving is affected by aircraft, has the advantages of improving the endurance of aircraft and prolonging the loitering time, but when aircraft is docked with chassis, due to the speed difference or position deviation between the two, a certain impact energy will be generated, and currently the damping mechanism of shared chassis itself is mostly used to absorb the buffer energy, although it can reduce a certain buffer energy, but the effect is poor, so that the impact energy generated when aircraft and chassis contact can easily damage aircraft and chassis, thereby affecting the overall performance of flying car.

[0005] Therefore, the utility model provides a kind of shared chassis of flying car to solve the above problems. UTILITY MODEL CONTENTS

[0006] To solve the above technical problems, the utility model provides the following technical solutions:

[0007] The utility model provides a shared chassis of flying car, including shared chassis, the top of shared chassis is provided with flight cabin, the top of shared chassis is opened with landing groove, the upper end of landing groove inner chamber is installed with support plate, landing groove and support plate are used for providing support to flight cabin, the bottom of landing groove inner chamber is installed with buffer assembly, buffer assembly is used for buffering energy absorption, buffer assembly includes damper, lower base, upper base, hydraulic rod, buffer spring, fender ring and adjusting ring, the both ends of damper are fixedly connected with the inner wall of landing groove and the bottom of support plate respectively, lower base is fixed in the bottom of landing groove inner chamber, upper base is fixed with the bottom of support plate, the both ends of hydraulic rod are movably connected with lower base and upper base through movable pin, fender ring, buffer spring and adjusting ring are all set on the surface of hydraulic rod.

[0008] Further, in the utility model, the surface of the hydraulic rod is provided with external threads, the adjusting ring is threadedly connected with the external threads, and the fender ring is fixed to the output end of the hydraulic rod.

[0009] Further, in the utility model, one end of the buffer spring is fixedly connected with the fender ring, and the other end of the buffer spring is in contact with the adjusting ring.

[0010] Further, in the utility model, the bottom of the support plate and the bottom of the landing groove inner chamber are fixedly connected with support seats, and support springs are fixedly connected between the two support seats.

[0011] Further, in the utility model, the two ends of the top of the support plate are provided with limiting grooves, the two ends of the surface of the limiting grooves are fixedly connected with electric clamping jaws, the bottom bracket of the flight cabin extends into the inner cavity of the limiting groove and is movably connected with the inner cavity of the limiting groove, and the limiting groove and the electric clamping jaws are used for limiting the flight cabin.

[0012] Beneficial effects, the utility model has the following beneficial effects:

[0013] The damper, the lower base, the upper base, the hydraulic rod, the buffer spring, the fender ring, the adjusting ring, the external threads, the support seats and the support springs are cooperated, so that the impact energy during the landing and docking of the flight cabin can be effectively absorbed, the shared chassis and the flight cabin can be protected, and the safety and stability of the flying car are ensured. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 It is the front view structure schematic diagram of the utility model;

[0015] Figure 2 It is the separation state structure schematic diagram of the shared chassis and the flight cabin of the utility model;

[0016] Figure 3is the separation state structure schematic diagram of shared chassis and support plate of the utility model;

[0017] Figure 4 is the front view cross section structure schematic diagram of shared chassis of the utility model;

[0018] Figure 5 is the connection state structure schematic diagram of hydraulic rod and lower base and upper base of the utility model.

[0019] In the figure,

[0020] 1, shared chassis;2, flight cabin;3, landing groove;4, support plate;5, buffer assembly;501, damper;502, lower base;503, upper base;504, hydraulic rod;505, buffer spring;506, blocking ring;507, adjusting ring;508, external thread;509, support seat;510, support spring;6, limiting groove;7, electric clamping jaw. DETAILED DESCRIPTION

[0021] In order to more understand the technical content of the utility model, specific embodiments are raised and the following is described with the attached drawings. In the present disclosure, the aspects of the utility model are described with reference to the attached drawings, and many illustrated embodiments are shown in the drawings. The embodiments of the present disclosure are not necessarily defined in all aspects including the utility model. It should be understood that the above-mentioned various concepts and embodiments, as well as those concepts and embodiments described in more detail below, can be implemented in any one of many ways, because the concepts and embodiments disclosed by the utility model are not limited to any implementation. In addition, some aspects of the utility model can be used alone, or used in any appropriate combination with other aspects of the utility model.

[0022] Embodiment 1

[0023] As Figures 1-5As shown, the first embodiment of the utility model provides a shared chassis of flying car, including shared chassis 1, the top of shared chassis 1 is provided with flight cabin 2, the top of shared chassis 1 is opened with landing groove 3, the upper end of landing groove 3 inner chamber is installed with support plate 4, landing groove 3 and support plate 4 are used to provide support for flight cabin 2, the bottom of landing groove 3 inner chamber is installed with buffer assembly 5, buffer assembly 5 is used to buffer energy absorption, buffer assembly 5 includes damper 501, lower base 502, upper base 503, hydraulic rod 504, buffer spring 505, retaining ring 506 and adjusting ring 507, the both ends of damper 501 are fixedly connected with the inner wall of landing groove 3 and the bottom of support plate 4 respectively, lower base 502 is fixed to the bottom of landing groove 3 inner chamber, upper base 503 is fixed with the bottom of support plate 4, the both ends of hydraulic rod 504 are movably connected with lower base 502 and upper base 503 through movable pin, retaining ring 506, buffer spring 505 and adjusting ring 507 are all set on the surface of hydraulic rod 504.

[0024] As Figures 1-5 shown, when flight cabin 2 lands and is docked with the landing groove 3 of shared chassis 1, first, part of impact energy is absorbed by damper 501, the transmission of impact is slowed down, then, hydraulic rod 504 is displaced under the action of impact, driving retaining ring 506 to move, and then compressing buffer spring 505, buffer spring 505 absorbs and stores impact energy through elastic deformation, the position of adjusting ring 507 can be adjusted as required to change the pre-tightening force and buffering effect of buffer spring 505, realizing accurate control of impact energy, support plate 4 and landing groove 3 jointly provide support for flight cabin 2, ensuring that it stably lands on shared chassis 1, through the synergistic effect of damper 501, lower base 502, upper base 503, hydraulic rod 504, buffer spring 505, retaining ring 506, adjusting ring 507, external thread 508, support base 509 and support spring 510, impact energy in the landing and docking process of flight cabin 2 can be effectively absorbed, so that shared chassis 1 and flight cabin 2 can be protected, ensuring the safety and stability of flying car.

[0025] Embodiment 2

[0026] Referring to Figures 1-5 , the second embodiment of the utility model, this embodiment is based on the previous embodiment.

[0027] In this embodiment, the surface of hydraulic rod 504 is provided with external thread 508, adjusting ring 507 is threadedly connected with external thread 508, and retaining ring 506 is fixed to the output end of hydraulic rod 504.

[0028] One end of buffer spring 505 is fixedly connected with retaining ring 506, and the other end of buffer spring 505 is in contact with adjusting ring 507.

[0029] The bottom of the support plate 4 and the bottom of the inner cavity of the landing groove 3 are fixedly connected with support seats 509, and the two support seats 509 are fixedly connected with support springs 510.

[0030] The two ends of the top of the support plate 4 are provided with limiting grooves 6, the two ends of the surface of the limiting groove 6 are fixedly connected with electric clamping jaws 7, the bottom support of the flight cabin 2 extends to the inner cavity of the limiting groove 6, and is movably connected with the inner cavity of the limiting groove 6, and the limiting groove 6 and the electric clamping jaw 7 are used for limiting the flight cabin 2.

[0031] As shown in the drawings, Figures 1-5 The adjusting ring 507 is screwed on the outer thread 508 of the hydraulic rod 504, the position of the adjusting ring 507 on the hydraulic rod 504 can be adjusted, the pre-tightening force and the buffering effect of the buffer spring 505 can be adjusted according to the weight and the landing speed of the flight cabin 2, more accurate buffering control can be realized, the support seats 509 and the support springs 510 provide additional support and buffering for the support plate 4, the support springs 510 can further absorb impact energy when the flight cabin 2 lands, the stability of the support plate 4 and the flight cabin 2 is ensured, the limiting groove 6 and the electric clamping jaw 7 are used for limiting and fixing the flight cabin 2, the bottom support of the flight cabin 2 extends to the limiting groove 6, and is movably connected with the limiting groove 6, the electric clamping jaw 7 clamps the flight cabin 2 after the butt joint is completed, and prevents the flight cabin 2 from shaking or falling off due to impact.

[0032] In use, when the flight cabin 2 lands and is butt jointed with the landing groove 3 of the shared chassis 1, first, part of the impact energy is absorbed by the damper 501, the transmission of the impact is slowed down, then the hydraulic rod 504 is displaced under the action of the impact, the blocking ring 506 is moved, and then the buffer spring 505 is compressed, the buffer spring 505 absorbs and stores impact energy through elastic deformation, the position of the adjusting ring 507 can be adjusted as needed to change the pre-tightening force and the buffering effect of the buffer spring 505, and accurate control of the impact energy is realized, the support plate 4 and the landing groove 3 jointly provide support for the flight cabin 2, and ensure that the flight cabin 2 stably lands on the shared chassis 1, the bottom support of the flight cabin 2 extends to the limiting groove 6, and is movably connected with the limiting groove 6, the electric clamping jaw 7 clamps the flight cabin 2 after the butt joint is completed, and prevents the flight cabin 2 from shaking or falling off due to impact.

[0033] The standard parts used in the present application file can be purchased from the market, and can be customized according to the description and the drawings, the specific connection mode of each part adopts the conventional means such as bolt, rivet and welding in the prior art, the machinery, parts and equipment adopt the conventional type in the prior art, the control mode is automatically controlled through the controller, the control circuit of the controller can be realized through simple programming by the person skilled in the art, which belongs to the common knowledge in the art, and the present application is mainly used to protect the mechanical device, so the control mode and the circuit connection are not explained in detail.

[0034] Although the utility model has disclosed as above with preferable embodiments, it is not used to limit the utility model. Those skilled in the art to which the utility model belongs can make various changes and decorations without departing from the spirit and scope of the utility model. Therefore, the protection scope of the utility model shall be subject to the definition of the claims.

Claims

1. A shared chassis of an air car, comprising a shared chassis (1), characterized in that: The top of the shared chassis (1) is provided with a flight cabin (2), the top of the shared chassis (1) is provided with a landing groove (3), the upper end of the inner cavity of the landing groove (3) is provided with a supporting plate (4), the landing groove (3) and the supporting plate (4) are used for supporting the flight cabin (2), the bottom of the inner cavity of the landing groove (3) is provided with a buffer assembly (5), the buffer assembly (5) is used for buffering energy absorption, the buffer assembly (5) comprises a damper (501), a lower base (502), an upper base (503), a hydraulic rod (504), a buffer spring (505), a blocking ring (506) and an adjusting ring (507), both ends of the damper (501) are fixedly connected with the inner wall of the landing groove (3) and the bottom of the supporting plate (4) respectively, the lower base (502) is fixed to the bottom of the inner cavity of the landing groove (3), the upper base (503) is fixed to the bottom of the supporting plate (4), both ends of the hydraulic rod (504) are movably connected with the lower base (502) and the upper base (503) through movable pins, the blocking ring (506), the buffer spring (505) and the adjusting ring (507) are all sleeved on the surface of the hydraulic rod (504).

2. The shared chassis for the flying car of claim 1, wherein: The surface of the hydraulic rod (504) is provided with external threads (508), the adjusting ring (507) is in threaded connection with the external threads (508), and the blocking ring (506) is fixed to the output end of the hydraulic rod (504).

3. The shared chassis of the flying car of claim 2, wherein: One end of the buffer spring (505) is fixedly connected with the blocking ring (506), and the other end of the buffer spring (505) is in contact with the adjusting ring (507).

4. The shared chassis of the flying car of claim 1, wherein: The bottom of the supporting plate (4) and the bottom of the inner cavity of the landing groove (3) are fixedly connected with supporting seats (509), and supporting springs (510) are fixedly connected between the two supporting seats (509).

5. The shared chassis of the flying car of claim 1, wherein: Both ends of the top of the supporting plate (4) are provided with limiting grooves (6), both ends of the surface of the limiting groove (6) are fixedly connected with electric clamping jaws (7), the bottom support of the flight cabin (2) extends into the inner cavity of the limiting groove (6) and is movably connected with the inner cavity of the limiting groove (6), and the limiting groove (6) and the electric clamping jaw (7) are used for limiting the flight cabin (2).

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