Flight experience system of manned aircraft

Abstract

The utility model relates to a manned aircraft flight experience system, which comprises more than two supports, a bearing cable, a power supply module, a tracking hanging module and an aircraft, the bearing cable is connected with two adjacent supports, the power supply module provides electric energy for the manned aircraft flight experience system, and the tracking hanging module is connected with the aircraft through a cable. The tracking and hanging module comprises a cable winding and unwinding device and a tracking device, the cable winding and unwinding device is used for automatically winding and unwinding a cable, the tracking device is rigidly connected with the cable winding and unwinding device, and the tracking device moves on the bearing cable along with the aircraft and tracks operation of the aircraft; through the accurate tracking and following technology of the cable take-up and pay-off device and the tracking device, it is guaranteed that the aircraft cannot be pulled, the flight safety is remarkably improved, the unmanned aerial vehicle can be applied to amusement places in the field of commercial operation, flight experience activities are provided, and the safety guarantee problem and the application scene problem of the unmanned aerial vehicle in the flight process are effectively solved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and particularly relates to a flight experience system for a manned aircraft. Background Art

[0002] During the flight test of an aircraft, a mechanical device with a certain degree of freedom or a safety rope connecting the ground to the aircraft is often adopted to restrict the flight freedom and provide protection, preventing the aircraft from being damaged due to failure. Firstly, their design and application scenarios are relatively limited, mainly applicable to specific test or test environments, and it is difficult to adapt to complex and changeable actual flight conditions. Secondly, the non-retractable cables or steel cables limit the flexibility and adaptability, and cannot be dynamically adjusted according to the flight state, speed, altitude of the aircraft and changes in the external environment, which may cause unnecessary pulling or restriction on the aircraft in extreme cases and affect flight safety.

[0003] With the rapid development of domestic tourism and the continuous improvement of people's living standards, more and more people go out for sightseeing during holidays. Most domestic scenic spots are mainly for outdoor nature appreciation (mountain scenery, islands, canyons, grasslands) and urban sightseeing. Among these scenic spots, high and low altitude sightseeing is becoming more and more popular due to its extraordinary experience and is a key project for the future development of scenic spot tourism. At present, the high altitude experience projects in scenic spots are mostly realized by manned helicopters or fixed-wing aircraft, and these aircraft need to be equipped with pilots with flight qualifications. Given the shortage of domestic general aviation flight pilots and the high training costs, the pilot cost remains high, resulting in high prices for low and high altitude sightseeing experience projects and making it difficult to promote them on a large scale. Most scenic spots with low and high altitude sightseeing needs are in mountainous areas, canyons, etc., where the terrain is relatively complex, making it difficult to build professional aircraft runways and airports with sufficient area. At the same time, most existing mountainous and canyon scenic spots use cable cars for tourist sightseeing and passenger transportation, with a poor experience. More and more people like extreme sports, and how to improve the safety factor of extreme sports has always been the focus of people's attention. Summary of the Utility Model

[0004] The technical problem to be solved by the utility model is to provide a flight experience system for a manned aircraft, aiming to solve the flight technical problems such as low flight safety factor, high noise, only having a riding experience without a driving experience, low safety guarantee and limited application scenarios in the prior art.

[0005] To solve the above technical problems, the technical solution adopted by the present utility model is to provide a flight experience system for a manned aircraft, which includes a bracket, a load-bearing cable, a power supply module, a tracking suspension module and an aircraft. The number of the brackets is more than two. The load-bearing cable connects adjacent brackets. The power supply module provides electrical energy for the flight experience system of the manned aircraft. The tracking suspension module is connected to the aircraft through a cable. The tracking suspension module includes a cable retracting device and a tracking device. The cable retracting device is used for automatically retracting and releasing the cable. The tracking device is rigidly connected to the cable retracting device, and the tracking device moves on the load-bearing cable following the aircraft.

[0006] Further, a top connection device is also provided on the upper end surface of the aircraft. The top connection device includes a first connecting rod, a second connecting rod and a universal joint. One end of the first connecting rod is fixed on the upper end surface of the aircraft, and the other end is connected to the second connecting rod through the universal joint. The cable is connected to the universal joint through the second connecting rod.

[0007] Further, the cable retracting device includes a winch and a motor. The winch is used for retracting and releasing the cable, and the motor provides power for the winch.

[0008] Further, the cable retracting device includes an electromagnetic brake, a locking device and a slip ring. The slip ring is arranged on the outer end surface of the winch. The cable passes through the slip ring and is connected to the winch. An electromagnetic brake and a locking device are arranged at one end of the motor.

[0009] Further, the tracking device includes an electric wheel set and a main control unit. The electric wheel set moves linearly on the load-bearing cable. The main control unit is used to track the position of the aircraft to drive the electric wheel set to move following the aircraft.

[0010] Further, the tracking device further includes an anti-disengagement mechanism, and the anti-disengagement mechanism closes and wraps the electric wheel set up and down.

[0011] Further, the power supply module includes an external power supply and / or an internal power supply to provide electrical energy for the flight experience system of the aircraft.

[0012] Further, the power supply module is an external power supply. The external power supply includes a power supply cabinet, and the power supply cabinet supplies power to the tracking suspension module and the aircraft through a power supply line.

[0013] Further, the power supply module is an internal power supply. The internal power supply is a rechargeable battery, and the rechargeable batteries are separately arranged in the tracking suspension module and the aircraft to provide electrical energy.

[0014] Further, a power supply line retracting device is also provided on any one of the brackets. The length of the power supply line changes with the movement of the tracking module, and the power supply line retracting device is used for retracting and releasing the power supply line.

[0015] The beneficial effect of the utility model is to provide a manned aircraft flight experience system, including a bracket, a load-bearing cable, a power module, a tracking suspension module and an aircraft, wherein the tracking suspension module is connected to the aircraft through a retractable cable, and the tracking device of the tracking suspension module follows the movement of the aircraft on the load-bearing cable to track the operation of the aircraft. While protecting the aircraft, the cable retractable device and the tracking device accurately track and follow the technology to ensure that the aircraft will not be pulled, which significantly improves the flight safety. The utility model fundamentally solves the problem of pulling or excessive pulling existing in traditional protection schemes, reduces the safety risks during flight, provides a more solid guarantee for the safe flight of the aircraft, and enhances operational flexibility and adaptability. The integration of the cable retractable function and the power supply / non-power supply function enables the utility model to easily adapt to the needs of various operational scenarios. Through the set bracket, whether it is normal flight, special mission execution, or commercial operation, the system can provide stable and reliable support and protection, showing a high degree of flexibility and adaptability. Compared with the previous protection scheme that is only applicable to specific test environments, the utility model has successfully broadened the application scenarios with its excellent performance and wide applicability. In the field of commercial operations, it can be used in amusement parks to provide flight experience activities, effectively solving the safety and application scenario issues of drones during flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0017] Figure 1 This is a schematic diagram of the application of the manned aircraft flight experience system of the utility model;

[0018] Figure 2 This is a schematic diagram of the structure of the manned aircraft flight experience system of the utility model;

[0019] Figure 3 This is a schematic diagram of the manned aircraft flight experience system of the utility model being powered by an external power supply;

[0020] Figure 4 This is a schematic diagram of the operation of two aircrafts in the manned aircraft flight experience system of the utility model;

[0021] Figure 5 This is a schematic diagram of the operation of multiple brackets of the manned aircraft flight experience system of the utility model;

[0022] Figure 6Schematic diagram of the internal power supply for the flight experience system of the manned aircraft of the present utility model;

[0023] Figure 7 Schematic diagram of the structure of the cable retracting and releasing device of the flight experience system of the manned aircraft of the present utility model;

[0024] Figure 8 Schematic diagram of the structure of the tracking device of the flight experience system of the manned aircraft of the present utility model;

[0025] Figure 9 Schematic diagram of the internal power supply for the tracking device of the flight experience system of the manned aircraft of the present utility model.

[0026] Label description:

[0027] 10. Bracket; 20. Load-bearing cable; 30. Tracking suspension module; 31. Cable retracting and releasing device;

[0028] 311. Slip ring; 312. Winch; 313. Motor; 314. Electromagnetic brake;

[0029] 315. Locking device; 32. Tracking device; 321. Electric wheel set; 322. Main control unit;

[0030] 323. Anti-disengagement mechanism; 40. Aircraft; 50. Cable; 60. Top connection device;

[0031] 61. First connecting rod; 62. Universal joint; 63. Second connecting rod; 70. Power cabinet;

[0032] 71. Power supply line; 72. Power supply line retracting and releasing device; 80. Internal power supply. Detailed implementation manners

[0033] The embodiments of the present utility model will be described in detail below. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present utility model, and should not be construed as a limitation of the present utility model.

[0034] In the description of the present utility model, it should be understood that the orientation or positional relationship indicated by the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present utility model.

[0035] In addition, the terms "first" and "second" are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present utility model, the meaning of "a plurality of" is two or more, unless otherwise specifically defined.

[0036] In the present utility model, unless otherwise clearly specified and defined, terms such as "mounted", "connected", "coupled", "fixed", etc. should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two components or the interaction relationship between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0037] As Figures 1-9 shown, an embodiment of the present utility model provides a flight experience system for a manned aircraft, including a bracket 10, a load-bearing cable 20, a power supply module, a tracking and hanging module 30, and an aircraft 40. The number of brackets 10 is two or more. The load-bearing cable 20 connects adjacent brackets 10. The power supply module provides electrical energy for the flight experience system of the manned aircraft. The tracking and hanging module 30 is connected to the aircraft 40 through a cable 50. The tracking and hanging module 30 includes a cable winding device 31 and a tracking device 32. The cable winding device 31 is used for automatically winding and unwinding the cable 50. The tracking device 32 is rigidly connected to the cable winding device 31. The tracking device 32 moves on the load-bearing cable 20 following the aircraft 40. Among them, the load-bearing cable 20 can also be a track, serving as the running carrier of the tracking device 32 and installed on adjacent brackets 10. The strength of the load-bearing cable 20 needs to meet the resultant force of the operating equipment under the action of external forces such as wind force, inertial force, frictional force, and impact force. The number of brackets 10 is two or more, preferably four, symmetrically arranged respectively, and can be made of steel frames or concrete, connecting and supporting the weight of the load-bearing cable 20.

[0038] The aircraft 40 involved in the present utility model is preferably an unmanned aircraft, which can be used for carrying people or goods, preferably for carrying people for flight experience, and has remote control and automatic navigation functions. It can fly freely within the preset three-dimensional space limit, that is, it has an electronic fence function. When used for carrying people, the aircraft can be controlled by the pilot within the constraint of the electronic fence, or can be flown by the remote crew manually or by planning a preset flight route. When used for carrying goods, the remote crew can complete the transportation task manually or by planning a preset flight route. The aircraft is linked and controlled with the tracking and hanging device to exchange information such as pose and state, and complete precise tracking and cable retraction and extension. The aircraft has all components for completing flight tasks, including an energy system, a power system, a control system, a navigation system, a communication system, a display and control system, an environment perception and obstacle avoidance system, etc. In an emergency state, the aircraft can start an emergency response program by the on-board personnel or the remote crew through a preset switch, such as returning to the landing point, landing in place, shutting down the propeller in the air, etc. The aircraft can complete functions such as automatic navigation, electronic fence, path planning and obstacle avoidance through GPS information, radar sensing, vision sensing, and / or external auxiliary positioning information, etc. The aircraft can establish real-time communication with other systems through wired and / or wireless communication methods, including but not limited to exchanging status information for necessary functions, videos, audios of on-board personnel or goods, etc.

[0039] The cable 50 can be composed of a tensile rope and / or a power supply line. The cable retraction and extension device 31 can retract and extend the cable 50. When an external power supply provides power, the power supply line provides the required electricity, and it can be made of metal materials with good electrical conductivity such as copper cores and aluminum cores; the cable 50 provides tensile strength guarantee and can be made of high-strength characteristic materials such as steel wires and fiber ropes. The power supply line and the tensile rope can be combined into one strand or remain separate. The cable 50 can be a cable or a steel cable made of high-strength and lightweight materials, and has a flexible retraction and extension function. Through a precise control system, precise adjustment of the length of the cable / steel cable is realized to ensure that it can closely follow the movement of the aircraft and make dynamic adjustments according to the flight state. Using tracking and following technology, integrating advanced tracking and following algorithms, and using data from multiple sensors such as GPS, RTK, and inertial navigation systems, the flight trajectory of the aircraft is calculated and predicted in real time to ensure that the cable / steel cable can accurately track and follow the movement of the aircraft. When the cable 50 integrates power supply and non-power supply functions, a power transmission line can be integrated inside the cable / steel cable to provide power support for electronic devices or other systems on the aircraft. At the same time, whether to enable the power supply function is selected according to actual needs to meet the requirements of different operation scenarios. In the non-power supply state, the cable / steel cable focuses on providing physical support and protection.

[0040] The most crucial concept of the present utility model lies in: providing a flight experience system for a manned aircraft, including a bracket, a load-bearing cable, a power supply module, a tracking and hanging module, and an aircraft. The tracking and hanging module is connected to the aircraft through a retractable cable. The tracking device of the tracking and hanging module moves on the load-bearing cable following the aircraft to track the operation of the aircraft. While protecting the aircraft, precise tracking and following technologies of the cable retracting device and the tracking device ensure that the aircraft will not be pulled, significantly improving flight safety. The present utility model fundamentally solves the problems of pulling or excessive pulling existing in traditional protection schemes, reduces the safety risks during flight, and provides a more solid guarantee for the safe flight of the aircraft.

[0041] As Figure 2 shown, a top connection device 60 is further provided on the upper end surface of the aircraft 40. The top connection device 60 includes a first connecting rod 61, a second connecting rod 63, and a universal joint 62. One end of the first connecting rod 61 is fixed on the upper end surface of the aircraft, and the other end is connected to the second connecting rod through the universal joint 62. The cable is connected to the universal joint through the second connecting rod. The top connection device 60 is used to connect the aircraft 40 and the cable 50. This device has a universal joint or a bearing, which can allow the aircraft 40 to move smoothly and freely in different motion modes, preventing the cable from getting entangled. At the same time, it has a certain rigidity to ensure the safe distance between the aircraft 40 and the cable, thus avoiding safety hazards such as entanglement of the aircraft. Further, this device can provide the transfer of the power supply circuit. For example, through slip ring connection, the aircraft can make continuous maneuvers. When the aircraft makes continuous yaw maneuvers, flexible components such as cables do not get entangled. The connection component between the cable and the aircraft has a certain strength, which can safely limit the movement distance, speed, and direction of the aircraft under the action of inertial force and impact force.

[0042] As shown in 7- Figure 9 shown, the cable retracting device includes a winch 312 and a motor 313. The winch 312 is used for retracting and releasing the cable 50, and the motor 313 provides power for the winch 312. The cable retracting device 31 is used to retract and release the cable 50 connected to the aircraft 40. The winch 312 for storing the cable 50 is provided inside the cable retracting device, which has the functions of rapid response and precise cable retracting and releasing. The winch 312 can be driven by a motor or a pure mechanical recovery force, and can accurately adjust the length of the cable 50 according to the current flight position and speed of the aircraft 40, so that the cable 50 always has a certain pre-tightening force to maintain a relatively safe distance from the aircraft.

[0043] As shown in 7- Figure 9As shown, the cable retracting device 31 also includes an electromagnetic brake 314, a stopper 315 and a slip ring 311. The slip ring 311 is arranged on the outer end surface of the winch 312. The cable 50 passes through the slip ring 311 and is connected to the winch 312. The electromagnetic brake 314 and the stopper 315 are arranged at one end of the motor 313. The electromagnetic brake is used for braking when the winch responds quickly. In the case of power failure, it is in a braking state to limit the speed of retracting and releasing the cable to ensure the safety of the aircraft 40; the stopper 315 is a purely mechanical emergency stop limiter, which is used to limit the length of the cable 50 to be retracted and released. In cooperation with the electromagnetic brake 314, it can further ensure the safe distance between the aircraft 40 and the ground in any fault.

[0044] Such as 8. Figure 9 As shown, the tracking device 32 includes an electric wheel group 321 and a main control unit 322. The electric wheel group 321 moves linearly on the load-bearing cable 20, and the main control unit 322 is used to track the position of the aircraft 40 to drive the electric wheel group 321 to follow the movement of the aircraft. The tracking device 32 moves directly on the load-bearing cable 20 to follow the position of the aircraft, and is rigidly connected to the cable retracting device 30. It has a high strength to support the forces of the aircraft 40, the cable 50 and its retracting device 31 under inertia and impact. The tracking device 32 has an electric wheel group 321 and a main control unit 322. The electric wheel group 321 runs on the load-bearing cable 20, and is controlled by the main control unit 322 to quickly and accurately track the position of the aircraft 40; the main control unit 322 has necessary components such as corresponding controllers, communication systems and sensors to complete the coordinated control with the aircraft 40, and ensure that the tracking device 32 and the cable retracting device 31 accurately reach the predetermined position or preset length. Preferably, a power module is also included to be responsible for the corresponding internal and external power conversion and supply power to other units; it can be powered by an onboard power supply from a power cabinet 70, an internal power supply 80, or a battery in the device. The internal power supply can also be used as a backup power supply when the external power supply is lost. The main control unit adopts an intelligent monitoring and early warning system, which can monitor the state, tension, and changes in the surrounding environment of the cable 50 in real time. Once an abnormal situation or potential risk is found, an early warning signal is immediately issued and corresponding safety measures are taken to ensure the safe and stable operation of the aircraft.

[0045] Furthermore, the tracking device further includes an anti-slip mechanism 323, which is closed up and down and covers the electric wheel set 321. An anti-slip mechanism is provided between the electric wheel set 321 and the load-bearing cable 323, which can be protected by the anti-slip mechanism closed up and down or an additional anti-slip mechanism can be added to prevent the electric wheel set from detaching from the load-bearing cable when it moves violently.

[0046] like Figure 3 , Figure 6As shown in the figure, the power supply module includes an external power supply and / or an internal power supply to provide electrical energy for the flight experience system of the aircraft. The aircraft can be powered by an internal power supply such as a rechargeable battery, hydrogen energy, or a hybrid energy source, or by an external power supply, or by a combination of partial external power supply and partial self-provided energy source to provide the required power to complete the flight mission. In addition, the on-board power supply can also supply power to external systems.

[0047] As Figures 3-5 shown in the figure, the power supply module is an external power supply, and the external power supply includes a power supply cabinet 70. The power supply cabinet 70 supplies power to the tracking suspension module 30 and the aircraft 40 through a power supply line 71. The power supply cabinet 70 can provide all the power during system operation, and generally adopts high-voltage transmission to reduce the cable diameter and improve the system operation efficiency.

[0048] As Figure 6 、 Figure 8 、 Figure 9 shown in the figure, the power supply module is an internal power supply, and the internal power supply is a rechargeable battery. The rechargeable batteries are separately arranged in the tracking suspension module and the aircraft to provide electrical energy.

[0049] As Figure 3 、 Figure 4 shown in the figure, a power supply line retracting and releasing device 72 is also provided on any bracket 10. The length of the power supply line 71 changes with the movement of the tracking module 32. The power supply line retracting and releasing device 72 is used to retract and release the power supply line 71. The power supply line retracting and releasing device 72 is linked with the tracking device 32 to retract and release the power supply line to ensure that the power supply line 71 is not pulled or slack. When operating over a large span, a connecting piece can be provided between the power supply line and the load-bearing cable, which can be a cable tie or a hanging ring, etc. to support the power supply line and restrict the deflection of the power supply line.

[0050] In summary, a flight experience system for a manned aircraft provided by the present utility model broadens the application scenarios of drones. By introducing the technology of retractable cables, it provides safety guarantees for any potential faults faced by drones during flight. Compared with the previous cable or wire rope protection solutions that were only applicable to specific test environments and non-retractable, the present utility model realizes a more extensive and flexible safety protection mechanism, ensuring stable and reliable support and protection for drones in various operation scenarios. At the same time, continuous flight power can be provided through the cables, thus significantly improving flight safety and operation efficiency. It effectively solves the problems of safety guarantee and application scenarios of drones during flight. Through one or more retractable cables, and the cables can track the operation of the aircraft, while protecting the aircraft, it ensures that the aircraft will not be pulled or over-pulled. The present utility model fundamentally solves the problem of pulling or over-pulling existing in traditional protection solutions, significantly reducing the safety risks during flight and providing a more solid guarantee for the safe flight of the aircraft. Enhance operation flexibility and adaptability: The integration of the cable retraction function and the power supply / non-power supply function enables the present utility model to easily adapt to the requirements of various operation scenarios. Whether it is normal flight, special mission execution, or commercial operation and other scenarios, the system can provide stable and reliable support and protection, demonstrating high flexibility and adaptability. With its excellent performance and wide applicability, the present utility model has successfully broadened the application scenarios. In the field of commercial operation, it can play an important role, improving operation efficiency and reducing operation costs.

[0051] The above are only the embodiments of the present utility model, and do not limit the patent scope of the present utility model accordingly. Any equivalent transformation made by using the content of the specification and drawings of the present utility model, or directly or indirectly applied in the relevant technical fields, shall be similarly included in the patent protection scope of the present utility model.

Claims

1. A manned aircraft flight experience system, characterized in that: It includes a bracket, a load-bearing cable, a power module, a tracking and hanging module and an aircraft, the number of the brackets is more than two, the load-bearing cable connects two adjacent brackets, the power module provides power for a manned aircraft flight experience system, the tracking and hanging module is connected to the aircraft through a cable, the tracking and hanging module includes a cable retracting device and a tracking device, the cable retracting device is used for automatic cable retracting, the tracking device is rigidly connected to the cable retracting device, and the tracking device follows the aircraft to move on the load-bearing cable.

2. A manned aircraft flight experience system according to claim 1, characterized in that: The upper end surface of the aircraft is also provided with a top connection device, which includes a first connecting rod, a second connecting rod and a universal joint. One end of the first connecting rod is fixed to the upper end surface of the aircraft, and the other end is connected to the second connecting rod through a universal joint. The cable is connected to the universal joint through the second connecting rod.

3. A manned aircraft flight experience system according to claim 1, characterized in that: The cable retracting and releasing device comprises a capstan and a motor, wherein the capstan is used for retracting and releasing the cable, and the motor provides power for the capstan.

4. A manned aircraft flight experience system according to claim 3, characterized in that: The cable retracting and releasing device comprises an electromagnetic brake, a locking device and a slip ring, wherein the slip ring is arranged on the outer end surface of the capstan, the cable passes through the slip ring and is connected to the capstan, and an electromagnetic brake and a locking device are arranged at one end of the motor.

5. The manned aircraft flight experience system according to claim 1, characterized in that: The tracking device comprises an electric wheel set and a main control unit. The electric wheel set moves linearly on the load-bearing cable. The main control unit is used to track the position of the aircraft to drive the electric wheel set to follow the movement of the aircraft.

6. A manned aircraft flight experience system according to claim 5, characterized in that: The tracking device also includes an anti-slip mechanism, which is closed up and down and covers the electric wheel set.

7. A manned aircraft flight experience system according to claim 1, characterized in that: The power supply module includes an external power supply and / or an internal power supply to provide electrical energy for the aircraft flight experience system.

8. A manned aircraft flight experience system according to claim 7, characterized in that: The power supply module is an external power supply, and the external power supply includes a power supply cabinet. The power supply cabinet supplies power to the tracking suspension module and the aircraft through a power supply line.

9. A manned aircraft flight experience system according to claim 7, characterized in that: The power supply module is an internal power supply, and the internal power supply is a rechargeable battery. The rechargeable battery is separately arranged in the tracking suspension module and the aircraft to provide electrical energy.

10. The manned aircraft flight experience system according to claim 8, characterized in that: A power supply line retracting device is also provided on any of the brackets. The length of the power supply line changes with the movement of the tracking module. The power supply line retracting device is used to retract the power supply line.

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