Distributed nonlinear drive deployment method for large-diameter annular reflector

Abstract

The invention relates to a distributed nonlinear drive deployment method for a large-diameter annular reflector. The distributed nonlinear drive deployment method comprises the following steps of: (1), obtaining the nonlinear output torque of a hinge of an annular reflector by calculation, and obtaining the output torque Tfar of a far-end hinge and the output torque Tnear of a near-end hinge; (2), obtaining the corresponding relationship of the rotational angle of a driving gear at the far-end hinge and the rotational angle of a driven gear at the far-end hinge shown in the specification, and the corresponding relationship of the rotational angle of a driving gear at the near-end hinge and the rotational angle of a driven gear at the near-end hinge shown in the specification by calculation; (3), calculating a transmission ratio of the driven gear to the driving gear at the far-end hinge and a transmission ratio of the driven gear to the driving gear at the near-end hinge at any time; and (4), respectively obtaining corresponding gear trains by calculation according to the transmission ratio ifar and the transmission ratio inear. By means of the distributed nonlinear drive deployment method disclosed by the invention, energy distribution of a system in a deployment process is optimized; furthermore, the motor output energy in the deployment process is reduced; and thus, the deployment driving force is reduced.

Description

technical field [0001] The invention relates to a method for unfolding an annular reflector, in particular to a method for unfolding a large-aperture annular reflector with a non-linear driving method. Background technique [0002] In recent years, in order to detect micro-power signals, a new generation of mobile communication satellites, electronic reconnaissance satellites, data relay satellites, etc. have put forward an urgent need for large-diameter mesh deployable antenna reflectors. Among all kinds of mesh antenna schemes, the annular truss-type deployable antenna has become the current large-scale spaceborne deployable antenna due to its simple structure, high reliability, large expansion-to-retract ratio, light weight, and easy realization of a large-diameter reflective surface. the most ideal structure. The typical annular truss-type deployable antenna is the Astromesh configuration proposed by Northrop Grumman Company in the United States. figure 1 shown. Struc...

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Problems solved by technology

[0005] At the same time, from the perspective of energy utilization of the entire system, the input energy utilization rate of the current deployment scheme is low

Among them, in the spring driving stage, the initial output torque of the linear vortex spring is large, and at this time the mesh surface is loose and no unit is locked, the input energy required by the system is small, and most of the energy input by the vortex spring is wasted; stage, when the remote unit is deployed at the end of the deployment, the mesh surface is tensed, and concentrated input energy is required. At this time, the power transmission path of the motor through the power rope is long, and the friction causes the tension transmitted to the remote driving rope to be greatly reduced. The required deployment force is too large and the energy loss is large

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