Yawing maneuvering control method based on sinusoidal yawing guidance principle

Abstract

The invention discloses a yawing maneuvering control method based on a sinusoidal yawing guidance principle. The sinusoidal yawing guidance principle is designed in the yaw axis maneuvering method of an aircraft, thus, a yaw axis follows a sinusoid and the rotating speed of a sailboard is calculated based on the sinusoid at the same time, so as to ensure that an inclined angle between the sun direction and the normal of the sailboard is minimum in this mode. With the adoption of the sinusoidal yawing guidance principle, the energy of the aircraft is ensured, the demand of original yawing maneuvering mode to the capacity of an angular momentum exchange device is reduced, the demand on the capacity of the angular momentum of the aircraft is reduced, and a method is provided for reducing the weight of a control system.

Description

technical field [0001] The invention relates to a yaw maneuver control method using a sinusoidal yaw guidance law, which can realize sinusoidal yaw maneuvers on a satellite and is mainly used on satellites in non-sun synchronous orbits. Background technique [0002] Solar cells are laid on the satellite sailboard, and the stretched sailboard can greatly increase the area where the satellite can obtain solar energy. Therefore, the sailboard is an essential equipment for most satellites to obtain solar energy, and it is also the main energy source for satellites flying in orbit. At present, in addition to fixed-wing sailboards, most of the satellites in orbit in my country use single-degree-of-freedom sailboards. Satellites using single-degree-of-freedom sailboards usually choose sun-synchronous orbits with a small angle between the sun and the orbital plane when selecting orbits, so that the sailboard drive mechanism can rotate the sailboards in the direction perpendicular to...

AI Technical Summary

Problems solved by technology

[0003] In the existing yaw maneuver mode, with the decrease of the sun altitude angle, the change of yaw angle is more and more concentrated in the noon point of the orbit (the point where α is 0 degrees) and the midnight point (the point where α is 180 degrees ) in a range near noon and midnight, the yaw angular velocity is relatively large. When the jet control is adopted, the propellant consumption is large. When the angular momentum exchange device is used for control (this method is often used), the angular momentum capacity requirement is required. Large, the satellite needs to be equipped with a large-capacity angular momentum exchange device, and the problem of heavy weight

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