Toy orbital vehicle

Abstract

The present disclosure discloses a toy orbital vehicle, including an orbit and a flying vehicle, wherein the vehicle has a first flight attitude of flying along the orbit and a second flight attitude of flying out of the orbit; Sliding cooperation of the taxiing connector on the orbit guide a flight direction of the flying vehicle, so that the flying vehicle can fly along the orbit. Thus, different flight trajectories can be simulated based on various structures of the orbit. The toy orbital vehicle has more playing methods, for example, flying across an obstacle or passing through a complicated orbit. Meanwhile, the flying vehicle can be separated relative to the taxiing connector and can directly take off after flying along the orbit and reaching a certain speed, thus really simulating land and air flights.

Description

CROSS-REFERENCE TO RELATED APPLICATION

The present disclosure claims the priorities of China Patent Applications No. CN202322042330.4 and No. CN202320963205.4, all contents of which are incorporated in the present disclosure.

TECHNICAL FIELD

The present disclosure relates to the technical field of toy air vehicles, and in particular, to a toy orbital vehicle.

BACKGROUND

Orbital toys usually use spliced orbits and powered or unpowered vehicle bodies, such as free-fall unpowered glider of the HOT SHEELS or a brush electric rail car of the Carrera. Mechanical kinetic energy is supplied to the vehicle body through electric energy drive, so that the vehicle body can run on the orbit; or, the vehicle body can be provided with a power supply to run autonomously on the orbit. All of these are traditional designs of toy orbital vehicles, where the vehicle body and the orbit form rolling friction to achieve motion, so that the vehicle still taxi on the orbit based on wheels.

SUMMARY

The present disclosure aims to provide a toy orbital vehicle, which achieves detachable connection between a vehicle and an orbit and can switch land and air modes and reduce usage of wheels.

In order to achieve the above objective, the present disclosure provides the following technical solutions:

A toy orbital vehicle includes an orbit and a flying vehicle, wherein the vehicle has a first flight attitude of flying along the orbit and a second flight attitude of flying out of the orbit; a taxiing connector is slidably arranged on the orbit; in the first flight attitude, the flying vehicle is connected to the taxiing connector; and in the second flight attitude, the flying vehicle is separated from the taxiing connector.

The flying vehicle can fly close to the ground or fly across the orbit. Sliding cooperation of the taxiing connector on the orbit guide a flight direction of the flying vehicle, so that the flying vehicle can fly along the orbit. Thus, different flight trajectories can be simulated based on various structures of the orbit. The toy orbital vehicle has more playing methods, for example, flying across an obstacle or passing through a complicated orbit. Meanwhile, the flying vehicle can be separated relative to the taxiing connector and can directly take off after flying along the orbit and reaching a certain speed, thus really simulating land and air flights.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic structural diagram of taxiing connection between a flying vehicle and an orbit according to an embodiment of the present disclosure;

FIG. 2 is a schematic diagram of a three-dimensional structure of a flying vehicle according to an embodiment of the present disclosure;

FIG. 3 is a schematic diagram of a three-dimensional structure of a top viewing angle of a flying vehicle according to an embodiment of the present disclosure.

FIG. 4 is a schematic diagram of an exploded structure according to an embodiment of the present disclosure;

FIG. 5 is a schematic structural diagram of a taxiing connector according to an embodiment of the present disclosure;

FIG. 6 is a schematic structural diagram of an orbit connecting part according to an embodiment of the present disclosure;

FIG. 7 is a schematic structural diagram of a straight orbit section according to an embodiment of the present disclosure;

FIG. 8 is a schematic structural diagram of a semicircular orbit section according to an embodiment of the present disclosure;

FIG. 9 is a schematic structural diagram of a curved orbit section according to an embodiment of the present disclosure;

FIG. 10 is a schematic structural diagram of a first kind of through gate according to an embodiment of the present disclosure;

FIG. 11 is a schematic structural diagram of a second kind of through gate according to an embodiment of the present disclosure; and

FIG. 12 is a schematic structural diagram of a third kind of through gate according to an embodiment of the present disclosure.

In FIG. 1 to FIG. 12, correspondence relationships between names or lines of components and reference numerals are as follows:

1: orbit; 11: straight orbit section; 12: semicircular orbit section; 13: curved orbit section; 14: guide rail body; 15: first insertion part; 16: first insertion hole; 17: second insertion hole; 18: sliding limiting part; 2: flying vehicle; 21: positioning column; 22: fuselage; 221: machine seat; 222: housing; 23: upper rotor group; 24: lower rotor group; 25: rotor; 251: protective frame; 252: propeller; 253: motor; 26: guard beam; 27: taxiing wheel; 28: battery assembling groove; 29: modular battery; 3: taxiing connector; 31: taxiing seat; 32: clamping limiting part; 33: connecting part; 34: positioning hole; 4: magnet; and 5: metal structure.

DETAILED DESCRIPTION OF THE EMBODIMENTS

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention but not all of them.

Referring to FIG. 1, an embodiment of the present disclosure provides a toy orbital vehicle, including an orbit 1 and a flying vehicle 2, wherein the vehicle 2 has a first flight attitude of flying along the orbit 1 and a second flight attitude of flying out of the orbit 1; a taxiing connector 3 is slidably arranged on the orbit 1; in the first flight attitude, the flying vehicle 2 is connected to the taxiing connector 3; and in the second flight attitude, the flying vehicle 2 is separated from the taxiing connector 3. By the arrangement of the orbit 1, the taxiing connector 3 plays a role of guiding the flight of the flying vehicle 2, so that the flying vehicle 2 taxies along the orbit 1. After the flying vehicle 2 is separated from the taxiing connector 3, the flying vehicle can directly take off. The orbit 1 can be changed into an orbit 1 for taxiing according to an actual need or serves as an obstacle for the flying vehicle 2 to pass through.

As shown in FIG. 7 to FIG. 9, in order to reduce a quantity of parts that constitute the orbit 1 and facilitate formation of various structural forms, the orbit 1 is at least composed of one or more of a straight orbit section 11, a semicircular orbit section 12, and a curved orbit section 13. For example, the straight orbit section 11 and the semicircular orbit section 12 can be encircled into an elliptical orbit 1, as shown in FIG. 1, or into a vertical crossing door structure, which is specifically based on a change in the quantity of the straight orbit section 11 and the quantity of the semicircular orbit section 12. A circular orbit 1 can also be formed by the semicircular orbit section 12, and the straight orbit section 11, the semicircular orbit section 12, or the curved orbit section 13 can also be added to vertically arrange the circular orbit 1 to form a circular crossing door, as shown in FIG. 10. Of course, the specific crossing door structure that can be formed can also be of another shape, as shown in FIG. 11. As the orbit 1, by cooperation with the taxiing connector 3, the flying vehicle 2 can taxi along the orbit 1. As the crossing door, the flying vehicle can fly according to a flight obstacle. In addition, during simulation of orbital flight and a flight action of flying out of the orbit 1, the curved orbit section 13, the straight orbit section 11, or the semicircular orbit section 12 can also be formed into an orbit 1 with an opening, as shown in FIG. 12.

In general, specific structures that constitute the orbit 1 can be assembled according to the playing method of the flying vehicle 2 to form orbits 1 with different structures. Meanwhile, various flight manners such as taxiing flight or crossing flight can be achieved, thus forming a large-scale amusement scene for the flying vehicle 2 to avoid obstacles or taxi. Simultaneously using several orbit sections with higher universality can facilitate disassembling and assembling, thus facilitating packaging and transportation and increasing the fun of self-assembling of structures.

In order to facilitate the straight orbit 11, the semicircular orbit section 12, and the curved orbit section 13 to have the same insertion connection structures and vertically erected connection structures, as shown in FIG. 6, the straight orbit section 11, the semicircular orbit section 12, and the curved orbit section 13 each include a guide rail body 14. First insertion parts 15 are arranged at two ends of the guide rail body 14; first insertion holes 16 corresponding to the first insertion parts 15 are also arranged at two ends of the guide rail body 14; meanwhile, at least two symmetrical second insertion holes 17 are also arranged on the guide rail body 14; and the first insertion holes 16 and the second insertion holes 17 have the same cross sections, and axial lines of the first insertion holes and axial lines of the second insertion holes are in a crossed state. The crossed state may be that axial lines in different planes are different, so that insertion directions of the first insertion holes 16 and the second insertion holes 17 are different, which conveniently achieves insertion supporting during vertical setting. The first insertion parts 15 and the first insertion holes 16 are cooperatively inserted, so as to connect the straight orbit section 11, the semicircular orbit section 12, and the curved orbit section 13 in sequence to form an annular orbit 1; the corresponding orbit sections are added and inserted into the second insertion holes 17 to vertically support the annular orbit 1, thus forming the crossing door structure, which is not limited to the above single structure. Particularly, the guide rail body 14 in the curved orbit section 13 may have various bent structures, thus forming more structural styles. Specifically, reverse buckles are arranged on the first insertion parts 15, and limiting slots matched with the reverse buckles are arranged on the first insertion holes 16 and the second insertion holes 17, which further prevents separation and improves the stability of insertion.

Specifically, a sliding limiting part 18 that extends outwards is arranged on the guide rail body 14. After sliding connection is performed on the taxiing connector 3 through the sliding limiting part 18, stable and smooth sliding of the taxiing connector 3 can be guaranteed, and meanwhile, the taxiing connector 3 can also be avoided from being separated from the sliding limiting part 18, which can ensure that the flying vehicle 2 drives the taxiing connector 3 to smoothly taxi along the orbit 1.

When the first insertion parts 15 are matched with the first connection holes 16 and the second connection holes 17, there can be an error-proof insertion method, which can ensure that the sliding limiting part 18 is spliced on the same side after connection or can normally form a stable vertical support. Cross-sections of the first insertion parts 15, the first insertion holes 16, and the second connection holes 17 are all L-shaped structures, so that the first insertion parts can only be inserted in a matching direction to achieve error prevention. Of course, other shapes can also be used.

When the taxiing connector 3 is used to drive the flying vehicle 2 to taxi along the orbit 1, the taxiing connector 3 specifically sleeves the orbit 1. Furthermore, the taxiing connector sleeves the orbit in advance in the splicing process of the orbit 1. After the orbit 1 is formed, the taxiing connector 3 can be prevented from being separated from the orbit 1. Specifically, as shown in FIG. 5, the taxiing connector 3 includes a taxiing seat 31. The taxiing seat 31 is provided with a clamping limiting part 32 half wrapped around the sliding limiting part 18. The clamping limiting part 32 can slide after being matched with the sliding limiting part 18, but will be separated from the sliding limiting part 18, thus achieving sliding connection and no separation of the entire taxiing connector 3. Meanwhile, the taxiing connector 3 is in a connected state when it is driven to slide by the flying vehicle 2. When the flying vehicle 2 flies freely, the taxiing connector 3 is in a separated state. Specifically, a connecting part 33 is arranged on the taxiing seat 31, and the connecting part 33 is provided with a positioning hole 34. As shown in FIG. 3, a positioning column 21 configured to be inserted into the positioning hole 34 is arranged on the flying vehicle 2; the positioning hole 34 and the positioning column 21 are provided with magnetic suction connecting parts that are mutually magnetically connected. The states in which the flying vehicle 2 is connected to and separated from the taxiing connector 3 are switched through the magnetic suction connecting parts.

The magnetic suction connecting parts include magnets 4 or metal structures 5 that mutually attract each other. For example, the positioning hole 34 and the positioning column 21 are both provided with the magnets 4 to achieve mutual attraction, or a magnet 4 is mounted in the positioning hole 34 and a screw (a metal structure 5) is mounted on the positioning column 21, or a screw is mounted in the positioning hole 34 and a magnet 4 is mounted on the positioning column 21 to achieve magnetic connection. Thus, it is possible to switch the state in which the flying vehicle 2 taxies on the orbit 1 or flies out of the orbit 1. After reaching certain take-off power, the flying vehicle 2 can be directly separated from the taxiing connector 3 and fly. Specifically, when the flying vehicle 2 is aligned with and connected to the taxiing connector 3, the flying vehicle 2 can be manually connected to the taxiing connector 3, or a feedback device with a positioning signal can be considered to be used to automatically locate the taxiing connector 3 and enable the flying vehicle 2 to land on the taxiing connector.

The flying vehicle 2 used in this implementation can fly close to the ground and the orbit 1 without wheels. Due to optimization of the specific structure of the flying vehicle, as shown in FIG. 2 to FIG. 4, the flying vehicle 2 includes a tilted fuselage 22. The fuselage 22 includes a machine seat 221 and a housing 222. The machine seat 221 can mount internal components, and the housing 222 can be disassembled relative to the machine seat 221 to assemble and maintain the internal components. Upper and lower ends of the fuselage 22 are respectively provided with an upper rotor group 23 and a lower rotor group 24 which are parallel to each other; and the upper rotor group 23 and the lower rotor group 24 each include rotors symmetrically arranged relative to the fuselage 22. That is, the upper rotor group 23 and the lower rotor group 24 each include two rotors. There are four rotors 25 in total. Rotating speeds of the rotors 25 at front, back, left, and right positions are controlled to make the flying vehicle move forward, move backward, turn left, and turn right. Particularly, the tilted fuselage 22 is shuttle-shaped, so that the fuselage 22 can be kept in flying in parallel to the ground or the orbit 1 when the upper rotor group 23 and the lower rotor group 24 rotate, and the fuselage can have balance power for flying in a flight direction.

Each rotor 25 includes a protective frame 251 integrated on the fuselage 22, a propeller 252, and a motor 253; the propeller 252 is rotatably mounted on the protective frame 251; the motor 253 drives the propeller 252 to rotate; and the motor 253 is independently controlled. The motor 253 of each propeller 252 is independently controlled, it is possible to achieve that the rotors 25 at different positions have different speeds, so that corresponding adjustment control can be controlled according to flight control. For example, when the speeds of the motors 253 in the upper rotor group 23 are less than the speeds of the motors 253 in the lower rotor group 24, the fuselage 22 is allowed to taxi close to the ground and the orbit 1. When the speeds of the rotors 25 on the left is less than the speeds the rotors 25 on the right, left turn is completed. When the speeds of the motors 253 in all the rotors 25 are the same, the entire fuselage 22 rises.

Meanwhile, in order to further combine the stable flight of the shuttle-shaped fuselage and provide good guidance for flowing of an air flow, an air deflector is arranged on one side of the protective frame 251 facing an upper end of the fuselage 22. That is, under the action of the air deflector, the fuselage 22 can be supported. The air flow generated by the rotation of the propellers 252 in the rotors 25 flows to a downwards tilted end of the fuselage 22 under the blocking action of the air deflector, thus pushing the fuselage 22 to taxi forwards. The terms front, back, left, and right mentioned in the above contents are all directions of observation based on a top view of the fuselage 22.

A speed difference of the motors 253 is mainly correspondingly controlled through a control circuit board integrated in the fuselage 22, and specific control instructions of the control circuit board can be transmitted through various interaction methods such as remote control, voice, and gestures, thereby achieving independent or comprehensive control on the entire flying vehicle 2 to move forward, move backward, turn left, and turn right.

Both the upper rotor group 23 and the lower rotor group 24 are provided with guard beams 26, and taxiing wheels 27 are arranged at two end portions of the guard beams 26. The guard beams 26 can be configured to protect the flying vehicle 2 from being damaged by collision and also have a certain protection effect during sliding. The taxiing wheels 27 can allow the flying vehicle 2 to taxi and be guided in the relatively closed orbit 1. For example, when flying in the invisible orbit 1, the flying vehicle can be guided by the taxiing wheels 27 to fly along an inner wall of the orbit 1, or can taxi on the ordinary orbit 1 with protective walls on both sides. This improves the protection on the flying vehicle 2 and improves flight requirements in more scenarios.

In the more playing methods of the flying vehicle 2, it is possible to simulate a battle. Various battle modes such as land-land battle, land-air battle, and air-air battle are achieved through corresponding battle signal transmission. Combined with pre-programmed flight methods, the flying vehicle 2 can make various corresponding actions such as swinging, hovering, rotating, and landing, which further improves the playability and fun of the flying vehicle 2.

Specifically, two ends of the fuselage 22 are respectively provided with a signal transmitter and/or a signal receiver. For example, the signal transmitter and the signal receiver can use an infrared transmitter and an infrared receiver, and corresponding control can be achieved through an internal control circuit board. Specific control instructions can still be received through remote control, voice control, gesture control, or the like. The signal transmitter and the signal receiver can be respectively mounted at the two ends of the fuselage 22 or integrated at one end, or can be integrated simultaneously at the two ends of the fuselage 22 to achieve different battle states, such as pursue and attack, and attack from front and back.

Meanwhile, in order to facilitate control of the operability in the battle process, the signal transmitter and/or the signal receiver can be rotatably connected to the fuselage 22. Specifically, one of the signal transmitter and the signal receiver can be rotatably connected, or the signal transmitter and the signal receiver can be connected simultaneously. In the battle process, an angle of the signal transmitter can be adjusted by controlling a flight attitude of the flying vehicle 2. Another flying vehicle 2 also escapes from a signal after its flight attitude is adjusted, thereby increasing the difficulty of the battle to a certain extent. Rotation angles of the signal transmitter and the signal receiver can be relatively fixed after being manually adjusted, or automatic angle adjustment is further achieved using an internally integrated driving mechanism, or automatic adjustment and the like are performed according to the flight attitude of the flying vehicle 2.

In the above battle process, if an infrared signal transmitted by the signal transmitter of one flying vehicle 2 is received by the signal receiver of another flying vehicle 2, this is considered as a hit. At this time, hovering, swinging, rotating, landing, and other operations are achieved by controlling the speeds of the motors 253 of the rotors 25 at different positions, so as to simulate a battle effect more realistically.

Meanwhile, the flying vehicle 2 is powered by a battery. To achieve the sustainable playability of the flying vehicle 2, it is considered that the battery can be quickly replaced for charging, that is, quick mounting and removal of the battery need to be considered. Specifically, a battery assembling groove 28 is arranged below the fuselage 22, and a modular battery 29 is mounted inside the battery assembling groove 28. The modular battery 29 is mounted in and removed from the battery assembling groove 28. Specifically, a clamping slot is arranged in the battery assembling groove 28, and a clamping strip that is matched with the clamping slot is arranged on the modular battery 29. By the cooperation between the clamping slot and the clamping strip, the modular battery 29 is quickly fixed. Furthermore, a conductive contact on the modular battery 29 is conductively connected to a conductive contact on the fuselage 22, so that the flying vehicle will not fall off during the flight. When the modular battery 29 needs to be removed, the clamping strip needs to be separated from the clamping slot by a certain acting force. Specifically, reverse pushing is performed to release the clamping strip from the clamping slot, so as to ensure the stability of mounting of the modular battery 29 on the flying vehicle 2. It is convenient to quickly mount the modular battery 29 to achieve quick energy supplementation.

In the present disclosure, unless otherwise expressly specified and limited, the terms “mount”, “connect”, “connection”, “fix”, and the like should be understood in a broad sense, such as, a fixed connection, a detachable connection, an integrated connection, a mechanical connection, an electrical connection, a direct connection, an indirect connection through an intermediate medium, an internal communication of two elements, or interaction between two elements. For those of ordinary skill in the art, the specific meanings of the aforementioned terms in this disclosure can be understood based on specific conditions.

In the description of the present invention, it should be noted that orientations or positional relationships indicated by the terms “center”, “upper”, “lower”, “left”, “right”, “inner”, “outer”, and the like are orientations or positional relationships as shown in the drawings or orientations or positional relationships where this invention product is often located during use, and are only for the purpose of facilitating and simplifying the description of the present invention instead of indicating or implying that devices or elements indicated must have particular orientations, and be constructed and operated in the particular orientations, so that these terms are not construed as limiting the present invention. In addition, the terms “first”, “second”, and the like are only for the purpose of distinguishing, and may not be understood as indicating or implying the relative importance.

For those skilled in the art, it is apparent that the present disclosure is not limited to the details of the exemplary embodiments mentioned above, and can be implemented in other specific forms without departing from the spirit or basic features of the present disclosure. Therefore, in any perspective, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present disclosure is limited by the accompanying claims rather than the above description. Therefore, all changes within the meaning and scope of the equivalent conditions of the claims within the present disclosure. Any reference numerals in the claims should not be regarded as limiting the claims involved.

Claims

1. A toy orbital vehicle, comprising an orbit and a flying vehicle, wherein the vehicle has a first flight attitude of flying along the orbit and a second flight attitude of flying out of the orbit; a taxiing connector is slidably arranged on the orbit; in the first flight attitude, the flying vehicle is connected to the taxiing connector; and in the second flight attitude, the flying vehicle is separated from the taxiing connector.

2. The toy orbital vehicle according to claim 1, wherein the orbit is at least composed of one or more of a straight orbit section, a semicircular orbit section, and a curved orbit section.

3. The toy orbital vehicle according to claim 2, wherein the straight orbit section, the semicircular orbit section, and the curved orbit section each comprise a guide rail body; first insertion parts are arranged at two ends of the guide rail body; first insertion holes corresponding to the first insertion parts are also arranged at two ends of the guide rail body; at least two symmetrical second insertion holes are also arranged on the guide rail body;the first insertion holes and the second insertion holes have the same cross sections, and axial lines of the first insertion holes and axial lines of the second insertion holes are in a crossed state; andthe guide rail body is provided with a sliding limiting part that extends outwards.

4. The toy orbital vehicle according to claim 3, wherein the taxiing connector comprises a taxiing seat; the taxiing seat is provided with a clamping limiting part half wrapped around the sliding limiting part; the taxiing seat is provided with a connecting part; the connecting part is provided with a positioning hole; the flying vehicle is provided with a positioning column configured to be inserted into the positioning hole; and the positioning hole and the positioning column are provided with magnetic suction connecting parts that are mutually magnetically connected.

5. The toy orbital vehicle according to claim 4, wherein the magnetic suction connecting parts comprise magnets or metal structures that mutually attract each other.

6. The toy orbital vehicle according to claim 1, wherein the flying vehicle comprises an inclined fuselage; upper and lower ends of the fuselage are respectively provided with an upper rotor group and a lower rotor group which are parallel to each other; and the upper rotor group and the lower rotor group each comprise rotors symmetrically arranged relative to the fuselage.

7. The toy orbital vehicle according to claim 6, wherein each rotor comprises a protective frame integrated on the fuselage, a propeller, and a motor; the propeller is rotatably mounted on the protective frame; the motor drives the propeller to rotate; and the motor is independently controlled.

8. The toy orbital vehicle according to claim 7, wherein an air deflector is arranged on one side of the protective frame facing an upper end of the fuselage.

9. The toy orbital vehicle according to claim 6, wherein both the upper rotor group and the lower rotor group are provided with guard beams, and taxiing wheels are arranged at two end portions of the guard beams.

10. The toy orbital vehicle according to claim 6, wherein the fuselage is a shuttle-shaped fuselage.

11. The toy orbital vehicle according to claim 6, wherein two ends of the fuselage are respectively provided with a signal transmitters and/or a signal receiver.

12. The toy orbital vehicle according to claim 11, wherein the signal transmitter and/or the signal receiver are rotatably connected to the fuselage.

13. The toy orbital vehicle according to claim 6, wherein a battery assembling groove is arranged below the fuselage, and a modular battery is mounted inside the battery assembling groove.

14. The toy orbital vehicle according to claim 13, wherein a clamping slot is arranged in the battery assembling groove, and a clamping strip that is matched with the clamping slot is arranged on the modular battery.