home Activities Products and services Contacts Site Map home>>Products and services>>Ballistic justification Ballistic justification The main products manufactured by JSC "EKA" in terms of ballistics are programs for solving problems of navigation and ballistic support (NBO) of spacecraft flight control for various purposes, combined into an automated program complex (ACP). The list of programs for solving NBO problems as part of the ACP is as follows: 1. System components Monitor (control program) of the complex; Complex administrator; Database administrator; Technological cycle monitor; Display and documentation system; Information and reference system. 2. Service components (programs, modules) Placement of the spacecraft for service (registration in the complex, input of service and technological information on the object); Formation of the initial conditions of spacecraft motion (input, viewing, editing, deletion of the SC, calculation of the SC for a given parameter value); Formation of a logical scale for modeling the spacecraft motion; Maintaining general constants (fundamental constants, tuning parameters, environment variables) of the complex; Formation of cyclograms of the propulsion system (creation of a CCLG for spacecraft, viewing, editing, merging, deleting); Registration and maintenance of ground measuring points; Maintaining the coordinates of measuring instruments of ground points; Registration of global objects of the complex, maintenance of vectors of the initial state of global objects; Registration and maintenance of ground objects; Registration and maintenance of launchers; Input of coordinates of ground areal objects (targets); Formation and maintenance of arrays of the astronomical yearbook; Maintenance of UTC-IAT time corrections; Formation, maintenance of the parameters of the Earth's rotation (PVZ); Formation of initial data on launch vehicles; Registration of refined (perturbed) parameters of global objects, formation of characteristics of refined parameters (a priori information, perturbations for calculating derivatives, etc.); Maintaining arrays of indices of geogeliophysical factors (input, processing, viewing, editing, statistical processing and forecasting of SA and GMV indices); Maintenance of arrays of coefficients of the atmospheric density model, testing the density model, issuing a table of control parameters; Registration of measured parameters (boundary conditions), maintenance of tolerances for measured parameters; Maintaining arrays of coefficients of the Earth's gravitational field model, testing the GPZ model; Maintenance of maps of links between objects; Input, formation of boundary conditions; Maintaining lists of alternatives for various purposes; Formation, maintenance of meteorological parameters of ground points; Maintenance of technological data of measuring instruments; Maintenance of the control program of the remote control; Editing global variables; Formation of lists of subscribers of the complex, duty shift, formation of a table for sending telegrams; Formation of delays of the standard of the navigation signal; Formation and maintenance of the catalog of stars; Maintenance of navigation frames of the GLONASS SPS (processing, writing to the database, viewing the catalog, testing the algorithm for restoring ephemeris and PVP according to NDT data); Maintenance of a posteriori ephemeris and PVP CNS GLONASS (processing, writing to the database, viewing the catalog, testing the model for calculating a posteriori ephemeris and PVP). 3. Components of information exchange Massive and per-codogram reception of measuring information (ITNP) received via communication channels (AKSZH, AKMS, ASOI); Maintenance of the ITNP archive, receiving measurements from files, issuing measurements to a file; Reception of telemetric information (TMI) received via communication channels; Complex exchange of forms of ballistic information (reception, processing, issue of forms). 4. Components of primary ballistics Pre-processing of measurements of radio engineering systems; Pre-processing of astrooptical measurements; Pre-processing of laser measurements in QUICK-LOOK and MERIT2 formats; Pre-processing of primary GLONASS measurements in RINEX format; Processing vectors with NAP data; Measurement quality assessment, measurement correction, including automatic and manual removal of abnormal measurements, systematization of quality assessments; Generalized assessment of the quality of measurements; Generation of agreed forms for abnormal ITNP sessions according to specified rejection criteria; Simulation of measurement information (simulation of a given sample of ITNP under given conditions, limitations and characteristics of measurement errors); Determination of the parameters of the object's motion by measurements (obtaining a zero approximation of the values of orbital parameters - rough filtering of measurements); Refinement of the parameters of models of motion of objects by measurements or boundary conditions (assessment of the state of the dynamic system by the measured output, refinement of motion control parameters in order to ensure the specified boundary conditions); Determination and refinement of the movement parameters and the launch vehicle control program (control of the DS state) in real time using navigation and telemetry data; Construction of reference orbits (reprocessing of the results of determining the motion parameters, updating the orbit parameters using orbital standardization methods); Coordination of parameters of motion models of objects (models of external factors) in a given space of controlled parameters (or measured parameters, taking into account given conditions and restrictions); Clarification (coordination) of the value of the ballistic coefficient based on deviations of the exit time at the time of the event (the beginning of the orbit, reaching the minimum distance to the observer, etc.), the formation of the ballistic coefficient; Coordination of the launch vehicle traffic control program; Control of the characteristics of the navigation field created by the GLONASS CNS; Formation of differential corrections. 5. Components of secondary ballistics Calculation of predicted parameters of spacecraft motion at a given time interval (orbits); Calculation of spacecraft visibility zones from ground points; Calculation of spacecraft visibility zones by quantum-optical means; Calculation of the guidance parameters of the antenna systems of the LVCD; Calculation of spacecraft visibility zones of other spacecraft (NSA, SR); Calculation of the illumination of the object and the sub-satellite regions of the Earth, the intervals of the spacecraft being in the shadow of the Earth and the Moon; Calculation of altitude and flight path; Comparison of the parameters of the spacecraft orbits, calculation of the relative position of the spacecraft; Calculation of the conditions for the SC survey of the Earth's surface; Comprehensive calculation of standard ballistic information on spacecraft; A posteriori assessment of the forecasting accuracy of the orbit parameters (calculation of deviations of the orbit parameters from the reference or nominal ones, comparison of orbits, calculation of single and group realizations with recording the results in the database, statistical processing of the results); Calculation of illumination angles of PSB spacecraft by the Sun; Formation of tables of nodal values (tabular orbits, ephemeris tables), import of trajectories of ground, air and space objects; Calculation of the spacecraft lifetime in the orbit of the Earth satellite; Calculation of points of impact of spacecraft and their fragments, landing of spacecraft on the Earth's surface, assessment of dispersion of points of impact (landing); Calculation of the moments of time of the minimum and maximum distance between the spacecraft, the time intervals for being within a given distance; Calculation of the parameters of the state of the spacecraft system (parameters of the structure of the spacecraft system), estimation of the time of destruction of the system; Assessment of the conditions for communication between the consumer and the spacecraft in geostationary orbit; Calculation of the dynamics of changes in the actual parameters of the spacecraft motion based on the totality of orbital determinations; Calculation of the reference trajectory of the spacecraft flight; Calculation of angles Sun - Object - Earth (Sun - Object - Illuminated Edge of the Earth); Calculation of antenna retargeting parameters; Calculation of secondary ballistic information on the Molniya spacecraft (zones of mutual influence equal to the range, passing a given height); Calculation of the parameters of the position of the Sun relative to the orbit of the spacecraft, the intervals of the location of the Sun in a given range of angular positions, the moments of the passage of the Sun through the orbital plane of the spacecraft; Calculation of coordinates of celestial bodies; Calculation of the angular position of the spacecraft relative to the Earth, Moon, Sun and stars; Calculation of the density (relief) of the navigation field of the GLONASS CNS; Calculation of intervals of possible (stable) navigation of ground and orbital consumers using signals from the GLONASS station; Assessment of the state of the orbital constellation of the spacecraft (calculation and display of information on the composition and distribution of the orbital constellation of the spacecraft). 6. Components for calculating the parameters of motion control. Development of test connections of the spacecraft control system; Calculation of the geostationary spacecraft alignment program; Calculation of the geostationary spacecraft retention program; Calculation of the control program for the implementation of a given type of maneuver (interorbital transition): single-pulse test correction; one-pulse correction maneuver T with the maximum possible approximation of Hex, Vhex to the required values; one-pulse correction maneuver L with the maximum possible approach of hex, Vhex to the required values; single-pulse hex correction maneuver with the maximum possible approach of Vhex to the required value; one-two-pulse correction maneuver T, wp (reversal of the apse line); two-pulse correction maneuver T, hex, Vhex; two-pulse correction maneuver L, hex with the maximum possible approach of Vhex to the required value; two-pulse correction maneuver L, T with the maximum possible approach of hex, Vhex to the required values; three-pulse correction maneuver L, T, hex, Vhex; Calculation of the control program for the descent of the spacecraft (AO) to a given area on the Earth's surface; Optimization of descent trajectories according to the criterion of minimum angular descent range, longitudinal dispersion of landing points, costs of characteristic velocity for de-orbiting; The boundary value problem of choosing the time of deorbiting for landing on the line of sight, given by latitude on the ascending (descending) part of the orbit or by longitude in the northern (southern) hemisphere; A two-parameter boundary value problem for the choice of the de-orbit point and the optimal direction of the descent impulse; A posteriori estimate of the magnitude and direction of deviation of the actual landing point from the calculated one; Binding of the actual landing point to landmarks on the ground; Characteristic velocity pulse test; Calculation of the launch time of launch vehicles for launching a spacecraft into a sun-synchronous orbit. 7. Components of generation and processing of forms (UOF) Processing of forms of ballistic information; Calculation of forms with the initial conditions of spacecraft motion; Calculation of forms with the initial conditions of spacecraft motion in the sections of the cyclogram of the propulsion system. 8. Components of the a priori-a posteriori estimate. A priori linear estimate of the accuracy of determining the parameters of the spacecraft motion; Estimation of variations in atmospheric density as a function of a given argument, comparison of atmospheric density models; Assessment of the influence of errors in accounting for factors of the atmospheric group (aerodynamics, density models and geophysical factors) on the accuracy of predicting the parameters of the movement of a space object; Assessment of the influence of short-period and long-period (resonant) effects of the GPZ on the accuracy of predicting the parameters of the motion of a space object. 9. Components of information presentation (display) Calculation of the graphic flight path of the spacecraft with marking of the injection and propulsion sections; Display of the position of the spacecraft constellation on the GSO; Displaying the position of a given set of ground objects on a digital electronic map of a given scale; Display of spacecraft visibility zones from ground points; Display of the cut-off situation on the Earth's surface and in the spacecraft orbit; Display of spacecraft service areas for ground consumers; Display of the orbital motion of the spacecraft (spacecraft system) in three-dimensional space; Displaying the density (relief) of the navigation field of the GLONASS CNS; Display of fall areas of detachable parts and emergency objects; Calculation and display of generalized spacecraft visibility zones.