METHOD spacecraft control while maintaining a predetermined orientation by reactive flywheel

摘要

method u0443u043fu0440u0430u0432u043bu0435u043du0438u00a0 space apparatus while maintaining the specified orientation with the jet u043cu0430u0445u043eu0432u0438u043au043eu0432, including definition of the flight time interval spacecraft (t0, tu043a) u0434u043bu00a0 u043fu043eu0434u0434u0435u0440u0436u0430u043du0438u00a0 target orientation, the measurement of orientation - x axes u0441u0432u00a0u0437u0430u043du043du043eu0433u043e) spacecraft, where = 1, 2, 3, u043eu0442u043du043eu0441 u0438u0442u0435u043bu044cu043du043e reference physical basis in current times t pi (t),where i = 1, 2, 3,...i is the number of parameters, u043eu043fu0440u0435u0434u0435u043bu00a0u044eu0449u0438u0445 orientation u0441u0432u00a0u0437u0430u043du043du043eu0433u043e) spacecraft on a team of physical baseincluding the measurement vector absolute angular velocity of the spacecraft formation with u043cu0430u0445u043eu0432u0438u043au0430u043cu0438 required u0443u043fu0440u0430u0432u043bu00a0u044eu0449u0435u0433u043e moment u0438u0437u043cu0435u0440u0435u043du0438 the current values of angular velocity vectors u0432u0440u0430u0449u0435u043du0438u00a0 j's main rocket u043cu0430u0445u043eu0432u0438u043au043eu0432 and q's additional jet u043cu0430u0445u043eu0432u0438u043au043eu0432 where j = 1, 2, 3,... j, q = 1, 2, 3,..., q is the number of the main and additional jet u043cu0430u0445u043eu0432u0438u043au043eu0432, definition of cumulative vector kinetic moment spacecraft are known u0435u043du0438u00a0u043c moments of inertia of the spacecraft and rocket u043cu0430u0445u043eu0432u0438u043au043eu0432 and measured u0437u043du0430u0447u0435u043du0438u00a0u043c vectors and testing conditions of the u0432u044bu043fu043eu043bu043du0435u043du0438u00a0;where s is the area of a large kinetic moment u0441u043eu0441u0442u043eu00a0u0449u0430u00a0 of u043fu043eu0434u043eu0431u043bu0430u0441u0442u0435u0439 core (S0) and additional (Sd) jet u043cu0430u0445u043eu0432u0438u043au043eu0432 (s = S0 + Sd), and, if the u0443u0441u043bu043eu0432u0438u00a0 tea u0432u044bu043fu043eu043bu043du0435u043du0438u00a0 office space without unloading apparatus of jet u043cu0430u0445u043eu0432u0438u043au043eu0432 gained kinetic moment and, in the case of u043du0435u0432u044bu043fu043e the u043bu043du0435u043du0438u00a0 u0443u0441u043bu043eu0432u0438u00a0,discharge jet u043cu0430u0445u043eu0432u0438u043au043eu0432 from the kinetic point of view, u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0, while maintaining the orientation of u043fu0440u043eu0438u0437u0432u043eu0434u00a0u0442 consistent check n in u043eu0437u043cu043eu0436u043du044bu0445 options u0438u0437u043cu0435u043du0435u043du0438u00a0 signs vectors main jet u043cu0430u0445u043eu0432u0438u043au043eu0432 and additional jet u043cu0430u0445u043eu0432u0438u043au043eu0432, where n = 1, 2, 3...on the meeting, u043eu0441u00a0u043c u0443u043fu0440u0430u0432u043bu0435u043du0438u00a0 spacecraft by u043fu0435u0440u0435u0440u0430u0441u043fu0440u0435u0434u0435u043bu0435u043du0438u00a0 kinetic moment between the rockets u043cu0430u0445u043eu0432u0438u043au0430u043cu0438 and moments of time u0438u0437u043cu0435u043du0435u043du0438u00a0 signs co u043au0442u043eu0440u0430u043cu0438 and u043fu0440u043eu0432u0435u0440u00a0u044eu0442 implementation conditions;where i is the nominal u0437u043du0430u0447u0435u043du0438u00a0 u0438u0437u043cu0435u0440u00a0u0435u043cu044bu0445 (i - x parameters orientation for maintaining the specified orientation of the spacecraft in a tolerable dia u043fu0430u0437u043eu043du043eu0432;;i is the value u043eu043fu0440u0435u0434u0435u043bu00a0u044eu0449u0438u0435 permissible ranges for the i - e parameters of the orientation of the spacecraft.;in the case of u0432u044bu043fu043eu043bu043du0435u043du0438u00a0 conditions (2) for all i, parameters are office space apparatus to maintain orientation and, in the case of not picking up to u0432u044bu043fu043eu043bu043du0435u043du0438u00a0 - e options u0438u0437u043cu0435u043du0435u043du0438u00a0 signs and r - e options u0438u0437u043cu0435u043du0435u043du0438u00a0 signs and also continue to maintain the orientation of the space craft to u0437u0430u0432u0435u0440u0448u0435u043du0438u00a0 all these n - x var u0438u0430u043du0442u043eu0432 u0438u0437u043cu0435u043du0435u043du0438u00a0 label vectors and jet u043cu0430u0445u043eu0432u0438u043au043eu0432,further u043eu0431u043du0443u043bu00a0u044eu0442 importance by u043fu0435u0440u0435u0440u0430u0441u043fu0440u0435u0434u0435u043bu0435u043du0438u00a0 kinetic moment with additional basic jet u043cu0430u0445u043eu0432u0438u043au0438 and redistributions u043fu0440u043eu0432u0435u0440u00a0 by the u0443u0441u043bu043eu0432u0438u00a0 (1) u0434u043bu00a0 subarea S0 main jet u043cu0430u0445u043eu0432u0438u043au043eu0432, and if u043du0435u0432u044bu043fu043eu043bu043du0435u043du0438u00a0, u043fu0440u043eu0438u0437u0432u043eu0434u00a0u0442 unloading main jet u043cu0430u0445u043eu0432u0438u043au043eu0432 from strategic sector kinetic momentand on the u043fu043eu0434u0434u0435u0440u0436u0430u043du0438u00a0 target orientation at the time t0 on u0437u043du0430u0447u0435u043du0438u00a0u043c u043fu0440u043eu0432u0435u0440u00a0u044eu0442 the u0438u0437u043cu0435u043du0435u043du0438u00a0 signs to the - x options in the formation of u0443u043fu0440u0430u0432u043bu00a0u044eu0449u0438u0445 at u0439u0441u0442u0432u0438u0439 - m u043eu0441u00a0u043c u0443u043fu0440u0430u0432u043bu0435u043du0438u00a0 here and if u043eu0442u0441u0443u0442u0441u0442u0432u0438u00a0 u043fu0440u043eu0438u0437u0432u043eu0434u00a0u0442 office space by using the basic conditions of the jet u043cu0430u0445u043eu0432u0438u043au043eu0432 to u0432u044bu043fu043eu043bu043du0435u043du0438u00a0 u00a0 (1) u0434u043bu00a0 subarea S0 and, in the case of not u0432u044bu043fu043eu043bu043du0435u043du0438u00a0 the u0443u0441u043bu043eu0432u0438u00a0 (1)u0443u043fu0440u0430u0432u043bu0435u043du0438u00a0 space device on the u043eu0441u00a0u043c u043fu0440u043eu0438u0437u0432u043eu0434u00a0u0442 with a change of sign u0443u043fu0440u0430u0432u043bu00a0u044eu0449u0438u0445 impacts the main jet u043cu0430u0445u043eu0432u0438u043au043eu0432 and u043fu043eu0434u043au043bu044eu0447u0435u043du0438u00a0 management the additional space rocket u043cu0430u0445u043eu0432u0438u043au043eu0432, with signs u0443u043fu0440u0430u0432u043bu00a0u044eu0449u0438u0445 impacts of additional reactive u043cu0430u0445u043eu0432u0438u043au043eu0432 have opposite signs u043fu0440u0430u0432u043bu00a0u044eu0449u0438u0445 impacts the main jet u043cu0430u0445u043eu0432u0438u043au043eu0432 furtherin the process of u0443u043fu0440u0430u0432u043bu0435u043du0438u00a0 - m u043eu0441u00a0u043c spacecraft through main and auxiliary jet u043cu0430u0445u043eu0432u0438u043au043eu0432 u043fu0440u043eu0432u0435u0440u00a0u044eu0442 the r - x options change sign s, and in their absence u043fu0440u043eu0432u0435u0440u00a0u044eu0442 the u0443u0441u043bu043eu0432u0438u00a0 (1) u0434u043bu00a0 Sd subarea and in the case of u0432u044bu043fu043eu043bu043du0435u043du0438u00a0 u0443u0441u043bu043eu0432u0438u00a0 (1) at the same time u0434u043bu00a0 each u043fu043eu0434u043eu0431u043bu0430u0441u0442u0435u0439 S0 and Sd area s cont u043eu043bu0436u0430u044eu0442 office space apparatusand in the case of u0432u044bu043fu043eu043bu043du0435u043du0438u00a0 u0445u043eu0442u00a0 one of these two conditions u0434u043bu00a0 u043fu043eu0434u043eu0431u043bu0430u0441u0442u0435u0439 S0 or Sd, u043fu0435u0440u0435u0445u043eu0434u00a0u0442 at the meeting, u043eu0441u00a0u043c spacecraft with a change of sign the current u0443u043fu0440u0430u0432u043bu00a0u044eu0449u0438u0445 impacts from the main and auxiliary jet u043cu0430u0445u043eu0432u0438u043au043eu0432 in opposing u0437u043du0430u0447u0435u043du0438u00a0,but if the r - x options further u043fu0440u043eu0432u0435u0440u00a0u044eu0442 satisfying the conditions of u0443u043fu0440u0430u0432u043bu0435u043du0438u00a0 corner u0441u043au043eu0440u043eu0441u0442u00a0u043cu0438 to zero values in the case of u043du0435u0441u043eu043eu0442u0432u0435u0442u0441u0442u0432u0438u00a0 x u043eu0442u00a0 would be one of the three conditions u043fu0440u043eu0438u0437u0432u043eu0434u00a0u0442 the transition to office space. with the change of the current u0443u043fu0440u0430u0432u043bu00a0u044eu0449u0438u0445 impacts from dos u043eu0432u043du044bu0445 and additional jet u043cu0430u0445u043eu0432u0438u043au043eu0432 in opposing u0437u043du0430u0447u0435u043du0438u00a0,and with the - x options u0434u043bu00a0 u043eu043fu0440u0435u0434u0435u043bu00a0u044eu0442 supplies main jet u043cu0430u0445u043eu0432u0438u043au043eu0432 kinetic moment and if more than half the available stocks u043au0438u043du0435u0442u0438u0447u0435 the moment u043fu043eu0434u043eu0431u043bu0430u0441u0442u044cu044e S0, office meeting, u043eu0441u00a0u043c spacecraft u043fu0440u043eu0438u0437u0432u043eu0434u00a0u0442 by disperse the main and additional jet u043cu0430u0445u043eu0432u0438u043au043eu0432 formation opposite signsif the supply of less than half the available u043fu043eu0434u043eu0431u043bu0430u0441u0442u044cu044e S0, office meeting, u043eu0441u00a0u043c spacecraft u043fu0440u043eu0438u0437u0432u043eu0434u00a0u0442 by u0442u043eu0440u043cu043eu0436u0435u043du0438u00a0 core and disperse d u043eu043fu043eu043bu043du0438u0442u0435u043bu044cu043du044bu0445 jet u043cu0430u0445u043eu0432u0438u043au043eu0432 of opposite signs.with the further implementation of u043fu0440u043eu0432u0435u0440u00a0u044eu0442 u0443u043fu0440u0430u0432u043bu0435u043du0438u00a0 corner u0441u043au043eu0440u043eu0441u0442u00a0u043cu0438 to zero values in the case of one of the two u043du0435u0432u044bu043fu043eu043bu043du0435u043du0438u00a0 u0445u043eu0442u00a0 rech conditions u043fu0435u0440u0435u0445u043eu0434u00a0u0442 at the meeting, u043eu0441u00a0u043c spacecraft with the change of the current u0443u043fu0440u0430u0432u043bu00a0u044eu0449u0438u0445 impacts from the basic and additional jet ma u0445u043eu0432u0438u043au043eu0432 in opposing u0437u043du0430u0447u0435u043du0438u00a0,further u043fu0440u043eu0438u0437u0432u043eu0434u00a0u0442 office until the next u043du0435u0441u043eu043eu0442u0432u0435u0442u0441u0442u0432u0438u00a0, one of the four conditions in which u043eu0441u0443u0449u0435u0441u0442u0432u043bu00a0u044eu0442 another shift of the current u0443u043fu0440u0430u0432u043bu00a0u044eu0449 their impacts, thus u043fu0440u043eu0438u0437u0432u043eu0434u00a0u0442 office space apparatus until the time tu043a, and at the end of the regime u0432u044bu043fu043eu043bu043du0435u043du0438u00a0 u043fu043eu0434u0434u0435u0440u0436u0430u043du0438u00a0 u043eu0440u0438u0435u043du0442u0430u0446 and u043eu0431u043du0443u043bu00a0u044eu0442 kinetic momentthe additional jet u043cu0430u0445u043eu0432u0438u043au0430u0445 by u043fu0435u0440u0435u0440u0430u0441u043fu0440u0435u0434u0435u043bu0435u043du0438u00a0 main jet u043cu0430u0445u043eu0432u0438u043au0438 and oversee u0443u0441u043bu043eu0432u0438u00a0 (1) u0434u043bu00a0 p u043eu0434u043eu0431u043bu0430u0441u0442u0438 S0 main jet u043cu0430u0445u043eu0432u0438u043au043eu0432 and if u043du0435u0432u044bu043fu043eu043bu043du0435u043du0438u00a0 u043fu0440u043eu0438u0437u0432u043eu0434u00a0u0442 unloading main jet u043cu0430u0445u043eu0432u0438u043au043eu0432 gained from kinetic momentfurther, in the above manner, u043fu043eu0432u0442u043eu0440u00a0u044eu0442 office space. on the meeting, u043eu0441u00a0u043c by jet u043cu0430u0445u043eu0432u0438u043au043eu0432 u0434u043bu00a0 ordinary regime intended u043fu043eu0434u0434u0435u0440u0436u0430u043du0438u00a0 ori u0435u043du0442u0430u0446u0438u0438.