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Momentum wheel with adjustable center of mass and aircraft

A momentum wheel and quenching and tempering technology, which is applied in the direction of aerospace vehicle guidance devices, can solve the problems of inability to effectively weaken the disturbance moment of flight equipment and inconvenient adjustment of its own center of mass, achieve long life and reliable operation, improve attitude control accuracy, Effect of suppressing system vibration

Pending Publication Date: 2022-04-12
JIAXING UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] The object of the present invention is to provide a momentum wheel and an aircraft with an adjustable center of mass, which solves the technical problems in the prior art that the flight equipment is inconvenient to adjust its own center of mass and cannot effectively weaken various disturbance moments caused by internal and external factors of the flight equipment.

Method used

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  • Momentum wheel with adjustable center of mass and aircraft
  • Momentum wheel with adjustable center of mass and aircraft
  • Momentum wheel with adjustable center of mass and aircraft

Examples

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Effect test

Embodiment 1

[0037] refer to Figure 1-3 , the momentum wheel with adjustable center of mass provided in this embodiment includes an outer stator 1, a mover 2 and an inner stator 3, and a linear-rotational two-degree-of-freedom electromagnetic drive assembly 4, and the outer stator 1 and inner stator are sequentially sleeved from outside to inside. The sub-3s are all fixedly arranged with the external equipment, and the external equipment may be but not limited to a spacecraft. The linear-rotational double-degree-of-freedom electromagnetic drive assembly 4 is erected on the inner and outer sides of the mover 2, so that the mover 2 is suspended relative to the inner stator 3 and the outer stator 1, that is, the mover 2 can be suspended without contact, avoiding Mechanical friction enables the mover 2 to obtain a better speed, and the linear-rotational two-degree-of-freedom electromagnetic drive assembly 4 can drive the mover 2 to rotate in the circumferential direction and / or move along its...

Embodiment 2

[0039] refer to Figure 1-4 In this embodiment, on the basis of Embodiment 1, the linear-rotational two-degree-of-freedom electromagnetic drive assembly 4 is further defined. Among them, the linear-rotational two-degree-of-freedom electromagnetic drive assembly 4 includes a rotary support mechanism 5 and a linear motion mechanism 6, and the rotary support mechanism 5 is arranged between the mover 2 and the outer stator 1 to move in the outer circumferential direction of the follower 2 The whole of the mover 2 is supported by suspension, which is more stable, and can drive the mover 2 to rotate with a small driving force, which is more stable and convenient. The linear motion mechanism 6 is arranged between the mover 2 and the inner stator 3. By setting them on the inner and outer sides of the mover 2, the mutual interference between the linear motion mechanism 6 and the rotary support mechanism 5 can be greatly reduced, and the straight line and the inner stator 3 can be avoid...

Embodiment 3

[0055] The aircraft provided in this embodiment includes the above-mentioned momentum wheel with adjustable center of mass. By setting the momentum wheel with adjustable center of mass on the aircraft, when the position of the center of mass needs to be adjusted, the mover 2 can complete linear motion while rotating, so that The method of minimizing the disturbance arm weakens or even eliminates the influence of disturbance internal and external moments on the attitude of the spacecraft, so as to weaken the disturbance moment, suppress system vibration and improve the accuracy of attitude and orbit control. The novelty of the momentum wheel configuration and the diversity of functions of the present invention conform to the development trend of attitude-orbit control of spacecraft, and have strong practical engineering significance for the realization of high-precision, long-life and reliable operation of spacecraft.

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Abstract

The invention provides a momentum wheel with an adjustable mass center and an aircraft, relates to the technical field of flight equipment, and solves the technical problems that in the prior art, the mass center of the flight equipment is inconvenient to adjust, and various disturbance torques caused by internal and external factors of the flight equipment cannot be effectively weakened. The momentum wheel comprises an outer stator, a rotor, an inner stator, linear-rotary two-degree-of-freedom electromagnetic driving assemblies and a detection protection assembly, and the linear-rotary two-degree-of-freedom electromagnetic driving assemblies are erected on the inner side and the outer side of the rotor. The electromagnetic driving assembly can drive the mover to rotate in the circumferential direction and / or move in the axial direction of the mover, and when the position of the mass center needs to be adjusted, the mover can complete linear motion while rotating. The influence of internal and external disturbance torque on the attitude of the spacecraft is weakened or even eliminated in a mode of minimizing a disturbance force arm, so that the disturbance torque is weakened, the system vibration is inhibited, and the attitude and orbit control precision is improved.

Description

technical field [0001] The invention relates to the technical field of flight equipment, in particular to a momentum wheel with an adjustable center of mass and an aircraft. Background technique [0002] Space vehicles are all kinds of vehicles that basically operate in accordance with the laws of celestial mechanics in the space outside the earth's atmosphere. They are the main body of space missions and the main components of space systems. "Center of mass position" is a key physical quantity in high-precision attitude and orbit control of spacecraft. The influence becomes more and more prominent. [0003] Generally, disturbances related to the center of mass of a spacecraft originate from internal and external factors. Among them, the internal factor refers to the "active" change of the center of mass caused by the change of the configuration or operating state of the spacecraft. For example, changes in mass distribution caused by payload separation, space target captu...

Claims

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Application Information

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IPC IPC(8): B64G1/28
Inventor 陈军委
Owner JIAXING UNIV
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