АНАЛИЗ ВОЗМОЖНОСТИ ИСПОЛЬЗОВАНИЯ РАСТАЛКИВАЕМОЙ ДВУХМАССОВОЙ КОСМИЧЕСКОЙ СИСТЕМЫ С ПЕРИОДИЧЕСКИ ФОРМИРУЕМОЙ СВЯЗЬЮ ДЛЯ МЕЖОРБИТАЛЬНЫХ ПЕРЕЛЕТОВ

摘要

At present, methods for orbit parameters changing with cable system by periodical changing of its length for the case, when the cable is located in the plane orthogonal to the orbit plane, or when it lays in the orbit plane, are known. However, the orbit parameters changing is possible only in case of non-central gravity field. The presented paper offers the structure of interorbital transfer of the space system, consisting of two masses repulsed and retracted in the orbit plane by periodically formed coupling. The flight is considered in the central gravitational field. Originally, the system represents a single spacecraft, consisting of two parts of equal weight. Initially, the system s on a circular orbit. The mass repulsion occurs in the direction tangent to the trajectory. Hereafter, the masses being uncoupled move independently of one another over various trajectories. Performing a various number of turns around the attracting center, after a certain period of time they will turn up on the line coinciding with the radius vector. One of the masses herewith will pass the pericentre of its orbit, while the other - its apocentre. At this moment, the masses contraction occurs assisted by the formed coupling. Methods of coupling formation are not considered in this paper. The paper demonstrates that the eventually formed orbit differs from the original one. The authors obtained analytically the dependence of the system final velocity in the point of masses contraction after their contraction versus the speed of their repulsion △V The dependence of the masses contraction point radius vector versus the initial repulsion speed Л V for the final orbit. Here: V_(kon) - the speed on the final orbit after the masses contraction; V_(kr) - the speed of the system on the initial circular orbit; к - system of masses speed at start time to speed increment caused by their repulsion ratio; r_(kon) - radius-vector of the final orbit at the mass contraction point; μ - gravitational parameter of a planet, around which attracting center the orbital motion occurs; r_(kr) - radius-vector of the system of masses initial circular orbit prior to their repulsion. Solution of this problem revealed a theoretical possibility of orbit parameters changing for the system of a proposed type. The analytical dependence of the speed value at the time of contraction versus the initial masses repulsion velocity is obtained. The equation determining the radius vector in the point of masses contraction of the formed final orbit created.%Рассматривается модельная задача об изменении параметров орбиты космического аппарата, представляющего собой систему из двух масс, расталкиваемых и сближаемых периодически формируемой связью в плоскости орбиты. Расталкивание осуществляется на круговой орбите в противоположные стороны с относительной скоростью, меньшей начальной круговой. Стягивание системы масс происходит в противоположной относительно притягивающего центра точке. Полученная в результате орбита представляет собой эллипс с параметрами, отличающимися от исходных. Подобные устройства позволяют реализовать альтернативные реактивному способы изменения параметров орбиты. В рассматриваемом устройстве изменение параметров орбиты происходит без расходования запаса рабочего тела на борту. В ряде случаев это может помочь увеличить срок службы космических аппаратов.