ADJUSTABLE INTAKE-COLLECTOR FOR THE OPTIMUM PROPULSION EFFICIENCY OF AN AIR-BREATHING ELECTRIC THRUSTER

摘要

The invention relates to a novel intake system for an air-breathing electric thruster specially configured to operate in variable atmospheric conditions of a very low planetary orbit, comprising of both special geometric features and means of actuations to make the intake system more flexible in adjusting to the changing atmospheric conditions and from an operational perspective to the engine requirements, and thus making the overall architectural of the spacecraft electric propulsion system more effective. The aforementioned special geometric features comprise of angled longitudinal and radial collector walls with a preferred conical layout embodiment, that together form an intake device, whose surfaces may be partially curved and resistant to chemical reaction (in particular atomic oxygen bombing) due to the impinging high-speed particles. The proposed angled walls reduce the intake device outlet area, minimizing the potential for a collected particle to rebound back into space. To help further reduce this rebounding effect, a deflector cone is placed at the interface between the intake-collector and the ionization stage, deflecting the particle away from the line of sight of the intake device outlet. The means of actuation to orientate the sections of the intake device comprise of a series of motors powered by a source that can be solar panels or batteries. The motors adjust, independently or collectively, the sections of the intake device in terms of rotation and translation. A dedicated controller drives the motors to adjust the disposition of the intake device sections such that the collection effect of the high-speed atmospheric particle is optimized at every instance of the operation of the spacecraft. The sectioned conical intake device, the deflection cone, the thermalization chamber, the motors and the controller, all together form the novel intake system.