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CN-121990167-A - Controllable magnetic suspension electric aircraft

CN121990167ACN 121990167 ACN121990167 ACN 121990167ACN-121990167-A

Abstract

The invention discloses a controllable magnetic suspension electric aircraft, which comprises a magnetic suspension driving system, a high-efficiency brushless direct current motor system, a solid battery energy system, a carbon fiber machine body structure, a three-axis gyroscope stabilizing system and a closed-loop control module, wherein the magnetic suspension driving system provides vertical lifting force and gesture control, the high-efficiency brushless direct current motor system provides horizontal propelling power, the solid battery supplies power for a whole system, the carbon fiber machine body is used as a bearing structure, the three-axis gyroscope detects flight gesture in real time, and the closed-loop control module receives gesture information and synchronously controls the magnetic suspension system and the motor system. The invention realizes main lifting force through magnetic suspension, combines electric propulsion, solves the problems of high energy consumption, high noise, poor wind resistance and short endurance of the traditional rotor craft, and realizes efficient, quiet, stable and long-endurance vertical take-off, landing and flying.

Inventors

  • Feng Dingze

Assignees

  • 冯定泽

Dates

Publication Date
20260508
Application Date
20260331

Claims (8)

  1. 1. The controllable magnetic suspension electric aircraft is characterized by comprising an aircraft (1), a magnetic suspension driving system (2), a high-efficiency brushless direct current motor system (3), a solid-state battery energy system (4), a carbon fiber airframe structure (5), a triaxial gyroscope stabilizing system (6) and a closed-loop control module (7), The magnetic suspension driving system (2) is fixedly arranged on a supporting arm structure of the aircraft (1) body and is used for generating controllable vertical suspension force and gesture control moment; the high-efficiency brushless direct current motor system (3) is used as a propeller to be installed in a cabin of an aircraft (1) and used for generating horizontal propulsion power; the solid-state battery energy system (4) is accommodated in a safety battery cabin which is close to the center of gravity and arranged in the body of the aircraft (1) and is used for providing electric energy for the magnetic suspension driving system (2) and the high-efficiency brushless direct current motor system (3); The carbon fiber engine body structure (5) forms a bearing main body and a shell of the aircraft (1), and the magnetic suspension driving system (2), the high-efficiency brushless direct current motor system (3) and the solid-state battery energy system (4) are all arranged on the bearing main body and the shell; The triaxial gyroscope stabilizing system (6) is arranged at the core position of the body of the aircraft (1) and is used for detecting the angular speed and the angular change of the aircraft (1) in three axial directions of pitching, rolling and yawing in real time; The closed-loop control module (7) is arranged in a control cabin of an aircraft (1) body, a signal input end of the closed-loop control module is electrically connected with the triaxial gyroscope stabilizing system (6), and a control output end of the closed-loop control module is electrically connected with control interfaces of the magnetic suspension driving system (2) and the high-efficiency brushless direct current motor system (3) respectively; The closed-loop control module (7) is configured to synchronously and independently send driving instructions to the magnetic suspension driving system (2) and the high-efficiency brushless direct current motor system (3) through control algorithm operation according to target flight instructions and real-time attitude information fed back by the three-axis gyroscope stabilizing system (6) so as to cooperatively realize accurate suspension, stable hovering, attitude adjustment and track flight of the aircraft (1).
  2. 2. The controllable magnetic levitation electric aircraft according to claim 1, wherein the magnetic levitation driving system (2) comprises at least one group of permanent magnet arrays and controllable electromagnet arrays corresponding to the permanent magnet arrays, and the closed-loop control module (7) realizes accurate closed-loop control of acting force between the magnetic levitation driving system and the permanent magnet arrays by adjusting the magnitude and the direction of current flowing through the controllable electromagnet arrays, so that the aircraft can realize ground-attached or near-ground levitation within a height range of 0-120 m, and stable hovering within a height range of 0-300 m.
  3. 3. A controllable magnetic levitation electric aircraft according to claim 2, characterized in that the magnetic levitation driving system (2) cooperates with the closed-loop control module (7) to enable the aircraft (1) to have stable hovering and flying capabilities against decimal wind power in real time in response to external wind disturbances.
  4. 4. The controllable magnetic levitation electric aircraft according to claim 1, wherein the high-efficiency brushless direct current motor system (3) is a contact part made of special tungsten alloy material, the designed service life is not less than 10 ten thousand hours, and the motor operation efficiency is not less than 96%.
  5. 5. A controllable magnetic levitation electric aircraft according to claim 4, characterized in that the high-efficiency brushless dc motor system (3) is capable of providing the aircraft (1) with a cruising speed of up to 150 km/h.
  6. 6. A controllable magnetic levitation electric aircraft according to claim 1, characterized in that the solid state battery energy system (4) is a high energy density solid state battery pack providing the aircraft (1) with a range of not less than 2000 km under standard conditions.
  7. 7. A controllable magnetic levitation electric aircraft according to claim 1, characterized in that the carbon fiber body structure (5) is integrally formed from carbon fiber composite material.
  8. 8. The controllable magnetic levitation electric aircraft according to claim 1, wherein the closed-loop control module (7) comprises a central processing chip and a peripheral driving circuit, and a flight control algorithm is embedded in the closed-loop control module and is used for processing sensor signals, resolving control quantities and generating driving instructions, so that precise closed-loop control of levitation force of the magnetic levitation driving system (2) and closed-loop control of rotation speed and thrust of the high-efficiency brushless direct current motor system (3) are realized.

Description

Controllable magnetic suspension electric aircraft Technical Field The invention relates to the technical field of aircrafts, in particular to a controllable magnetic suspension electric aircraft. Background Vertical take-off and landing (VTOL) aircraft, particularly multi-rotor unmanned aerial vehicles, have been widely used in the fields of logistics distribution, aerial photography, facility inspection, and the like due to their flexible take-off and landing and hovering capabilities. However, the existing solutions rely mainly on aerodynamic forces (such as rotor wing to generate lift force) to realize motion control in the vertical direction, which brings about several inherent technical bottlenecks and problems to be solved: firstly, in terms of energy efficiency and noise, the rotor wing rotating at high speed is relied on to generate lifting force to overcome gravity to realize hovering, so that the energy consumption is extremely high, and the endurance time of the aircraft is severely limited. Meanwhile, the pneumatic noise generated by the high-speed air cutting of the rotor wing is very remarkable, and the pneumatic noise is limited in certain application scenes sensitive to the noise (such as urban communities, wild animal observations and the like). Secondly, in terms of stability and anti-interference capability, the hover stability of the traditional rotorcraft is seriously dependent on the rapid and accurate adjustment of the rotational speed of each rotor by a flight control system. Under complex meteorological conditions, particularly when suffering from gusts or continuous side winds, the attitude maintaining and position maintaining capabilities of the device can be greatly reduced, the hovering precision is difficult to ensure, and even the device is at risk of out of control. The wind resistance is generally limited, and the wind resistance is difficult to reliably work under severe weather conditions. Again, in terms of endurance and power system life, it is difficult for the operating radius and endurance of electric aircraft to meet the ever-increasing mission requirements, limited by the current energy density of lithium ion batteries. Meanwhile, the driving motor is in a high-load and high-rotation-speed working state for a long time, and the service life and reliability of the driving motor are key short plates for influencing the durability of the whole system. Finally, in terms of system complexity, multi-rotor systems require multiple motors, electric and propeller cooperation, increasing the complexity and potential failure point of the system. In order to solve the above problems, many studies have been made in the industry. Magnetic levitation technology has been used in the fields of rail transit, precision instruments, etc. due to its non-contact, low friction and high precision control characteristics. It is envisaged to introduce it into the field of aircraft, with magnetic forces replacing or assisting aerodynamic forces to achieve lift. However, how to integrate the magnetic levitation system with the propulsion, energy, structure and control system of the aircraft with high efficiency and reliability, and design an aircraft which can realize the full-flow controllable levitation and stable flight from the ground to the air and has practical performance indexes (such as sufficient voyage, wind resistance level and service life) is still lack of a public, effective and complete solution. Disclosure of Invention Aiming at the defects in the prior art, the invention aims to provide a controllable magnetic suspension electric aircraft so as to solve the problems in the prior art. In order to achieve the above objective, a specific embodiment of the present invention provides a controllable magnetic suspension electric aircraft, which includes an aircraft, a magnetic suspension driving system, a high-efficiency brushless dc motor system, a solid-state battery energy system, a carbon fiber body structure, a tri-axis gyroscope stabilizing system and a closed-loop control module, wherein the magnetic suspension driving system is fixedly installed on the support arm structure of the aircraft body, and is used for generating controllable vertical suspension force and gesture control moment; the high-efficiency brushless DC motor system is used as a propeller and is arranged in an aircraft cabin for generating horizontal propulsion power, the solid-state battery energy system is accommodated in a safety battery cabin which is arranged in the aircraft cabin and is close to the center of gravity and is used for providing electric energy for the magnetic suspension driving system and the high-efficiency brushless DC motor system, the carbon fiber aircraft body structure forms a bearing main body and a shell of the aircraft, the magnetic suspension driving system, the high-efficiency brushless DC motor system and the solid-state battery energy system are all arranged on the bearing