ИСТИНА

Перемещение полезной нагрузки с лунного орбитального модуля на поверхность Луны при помощи тросовой системы.

This study intends to consider several problems associated with the movement of a payload between a spacecraft placed in lunar orbit and the lunar surface. The problems under consideration may arise within the framework of the theoretical study of the mission described below. A base spacecraft (BS) is launched into lunar orbit and will remain there permanently. After the completion of the process of orientation, stabilization and establishment of a stable connection with the Earth, a tether with a payload at the end begins to unwind from the BS. The payload can be a probe, or any other research equipment, supplies for a stationary module on the lunar surface. At the same time, the lunar landing point and the trajectory of the tether unwinding can either be stored in the on-board computer of the BS in advance, or calculated immediately before the start of the descent (for example, based on current data on environmental conditions and the topography of the descent area using computer vision technologies). Such a functional scheme eliminates fuel costs for the lunar landing process and simplifies the landing control mechanism (due to the fact that control is carried out from the BS, and not from the Earth). On the other hand, in such a scheme there will be problems associated with the joint dynamics of the flexible tether and the payload at its end. The process of unwinding a terher without additional control will, under certain conditions, be asymptotically unstable due to the influence of external forces and wave effects in the tether. Also, taking into account flexible coupling in the overall dynamics of the system entails a number of restrictions on the main characteristics of the system: the length of the maximum unwinding of the tether (and, consequently, on the altitude of the BS orbit), the value of the payload mass. Such a scheme for moving the payload is a way to solve the current problem of accurately landing spacecraft on the lunar surface. Recently, several missions (SLIM of the Japanese Space Agency; IM-1, Intuitive Machines, USA) have experienced problems associated with stable landing on the selected surface area: the vehicles turned over. The descent of such devices on a tether will make it possible to fend off this emergency situation without fuel costs (a device that has fallen on its side can be pulled back and another attempt at landing on the Moon can be made). The scientific novelty of the project lies in the study of the dynamics of the tether system, taking into account wave processes in the tether, applicable for operational missions in lunar orbit. In a formulation that takes into account the dynamics of a tether (as a flexible, tensile elastic thread), such problems were not considered.

1.Математическая модель тросовой транспортной системы, обеспечивающей моделирование различных вариантов перемещение нагрузки на окололунной орбите без топливных затрат. В модели должны быть учтены динамика подвижных частей системы, волновые эффекты в гибкой связи и факторы внешней среды; 2.Условия на основные характеристики системы, обеспечивающие ее устойчивое функционирование в рамках разработанной модели;

В качестве научного задела можно выделить следующие позиции: 1. Полученные для околоземной орбиты условия стабилизации размотки тросовой системы с оконечной массой; 2. Метод построения конфигурации системы при размотке в квазистатическом приближении для околоземной орбиты; 3. Анализ динамики троса с оконечной массы при превышении скорости размотки троса локальной скорости поперечной волны (для околоземной орбиты). Все указанные позиции рассмотрены в диссертации на соискание звания кандидата физико-математических наук руководителя проекта. Предполагается, что данные подходы и методы будут распространены и на условия окололунной орбиты.