A Robust Control Algorithm of a Descent Vehicle Angular Motion in the Earth’s Atmosphere

A new approach to synthesize a robust controller for the angular motion of the Earth lander by decomposition method of output modal control is proposed. A universal analytical solution for the problem of stabilizing the angular position of the lander is obtained. A comparative analysis of the presented algorithm with the currently used onboard algorithm for descent control of the manned spacecraft Soyuz is carried out. The advantages of the new algorithm relative to the existing algorithm are presented, both in terms of stabilization accuracy and the consumption of the working fluid of the control motors.

Parametric Calculations of the Aerodynamics of a Descent Vehicle

We present the methodology and results of parametric aerodynamic studies of vehicles descending into the planet’s atmosphere. The proposed computational approach might serve as the basis for solving a number of problems such as predicting and optimizing the descent trajectory of the vehicle, the search for a rational aerodynamic layout of the vehicle, i.e., tasks requiring massive parametric calculations. The systematization of such calculations is the first step towards the creation of a specialized database that includes sets of input and output data (flight speed, angles of attack, drag and lift coefficients, aerodynamic pitching moment, etc.) and the corresponding three-dimensional fields of gas-dynamic quantities together with computational meshes of various granularity and parameters of the computational model. Additional information to each element of the database might be a set of variables, parameterizing the geometry of the vehicle, experimental data, etc. The probability of forming the information content of such a data-base using modern supercomputer systems is shown. The capabilities of the domestic supercomputer aerodynamic code NOISEtte are demonstrated in the field of multiparametric three-dimensional calculations of descent vehicles based on the numerical solution of the Navier --- Stokes equations on three-dimensional unstructured meshes

KEY ENGINEERING SOLUTIONS IMPLEMENTED IN ROCKET AND SPACE SYSTEM VOSTOK TO ASSURE CREW SAFETY DURING ASCENT (towards 60th anniversary of the first man in space)

The paper analyzes engineering and operational solutions implemented in rocket and space system Vostok to assure crew safety during ascent in view of the need to complete the work on an extremely short notice. It reviews the results of flight tests of launch vehicles belonging to the R7 family and the status of during prelaunch processing and ascent phase. The paper draws comparisons between work to develop a crew escape system by the time when the first manned mission of Vostok spacecraft took place. It provides an analysis of emergencies and measures to assure safety our country’s project Vostok and US project Mercury. Key words: rocket and space system, spacecraft, descent vehicle, crew safety.

KEY ENGINEERING SOLUTIONS IMPLEMENTED IN ROCKET AND SPACE SYSTEM VOSTOK TO ASSURE CREW SAFETY DURING ASCENT (towards 60th anniversary of the first man in space)

The paper analyzes engineering and operational solutions implemented in rocket and space system Vostok to assure crew safety during ascent in view of the need to complete the work on an extremely short notice. It reviews the results of flight tests of launch vehicles belonging to the R7 family and the status of work to develop a crew escape system by the time when the first manned mission of Vostok spacecraft took place. It provides an analysis of emergencies and measures to assure safety during prelaunch processing and ascent phase. The paper draws comparisons between our country’s project Vostok and US project Mercury. Key words: rocket and space system, spacecraft, descent vehicle, crew safety.

Emergency recovery of the crew of the manned transportation spacecraft Soyuz during ascent to orbit (towards a history of development of the unique space hardware)

The paper is dedicated to the development of the equipment for emergency recovery of the Soyuz spacecraft crew during ascent to orbit, and contains a summary of research, engineering, design and experimental studies, carried out by specialists of RSC Energia (formerly OKB-1), TsNIIMash (formerly NII-88), TsAGI and many other companies that were involved in the development of the emergency crew rescue equipment. The paper discusses layout arrangements for the emergency escape nose section, algorithms for the operation of the emergency rescue system, provides results of simulations of the motion of the emergency escape nose section and structural parts of the spacecraft in case of the launch vehicle failure, provides brief results of the analysis of actual cases of emergency crew rescue, including the failure of Soyuz-FG launch vehicle on October 11, 2018. Key words: descent vehicle, emergency escape nose section, separation equipment.

Simulation of landing vehicle dynamic motion in the final stage of landing

When designing promising spacecrafts and missions to explore the planets of the Solar system, preliminary testing of all the important systems affecting the success of the space mission is necessary. Among the other systems responsible for the functioning of the spacecraft, it is necessary to distinguish the landing system. The landing stage is important and complex, since this stage is accompanied by large overloads and forces of the stick-slip nature acting on the spacecraft, their effect can be critical for the spacecraft structure. When landing the descent vehicle, it is necessary to study separately the moment of approach to the surface and the movement in the ground. The purpose of this article is to describe the methodology for modeling the motion dynamics at the final stage of movement and perform numerical studies of the descent vehicle motion dynamics at the final stage of movement in the case of a hard landing. Studies were conducted for different initial conditions of approach to the surface. As a result, the values of the arising overloads acting on the descent vehicle were obtained. The data provided by the simulation allow making conclusions about the most dangerous landing options that should be considered for the successful completion of future missions.