Khrunichev State Research Research Articles

Application of ERP-systems for increase of efficiency organization of high-tech production

The specificity of ERP-systems application in the production of high-tech products is described. The approaches to implementation in science-intensive industrial enterprises are described. The use of ERP systems by Russian manufacturing enterprises has been expanding in the last decade. The article describes approaches to implementation in high-tech industrial enterprises of the Federal state unitary enterprise “Khrunichev state research center”.

Results of the Komplast experiment on the long-term exposure of materials specimens on the ISS surface

The Komplast materials experiment was designed by Khrunichev State Research and Production Space Center together with Skobeltsyn Institute of Nuclear Physics, Lomonosov Moscow State University and other Russian scientific institutes, and has been carried out by Mission Control Moscow since 1998. The purpose of this experiment is to study the complex effect of the low Earth orbit environment on samples of various spacecraft materials. On November 20, 1998 the Komplast experiment began with the launch of the first International Space Station module Zarya, or Functional Cargo Block (FGB). Eight Komplast panels with samples of materials and sensors were installed on the outer surface of FGB module. Two of eight experiment panels were retrieved during Russian extravehicular activity in February 2011 after 12years of space exposure and were subsequently returned to Earth by Space Shuttle “Discovery” on the STS-133/ULF-5 mission in March 2011.The article presents the results obtained from this unique long-duration experiment on board of the International Space Station.

1st ACT Global Trajectory Optimisation Competition: Results found at Moscow Aviation Institute and Khrunichev State Research and Production Space Center

We discuss the general requirements for the solution of the problem given in the 1st ACT Global Trajectory Optimization Competition. We introduce some novel numerical methods used for multiple gravity-assist and low-thrust trajectory optimization, and in particular an original method to compute interplanetary conic trajectories and a novel continuation technique for low-thrust trajectory optimization. The application of these methods to the competition problem is discussed. The final trajectory has an objective function value of J = 1364042.86 kg km 2 / s 2 . It includes five swingbys in the inner Solar system and three thrusting arcs. An optimal direct Earth–asteroid trajectory is presented as a post-competition result.

L'Université sans profession (the University without profession): The Privilege of the Conflict of the Faculties

Jacques Derrida has institutionalized his belief that philosophy must be integral to the founding of any university. In 1982 he presented, with others, a report to the French government ‘to justify...

Earth Observation program at the khrunichev state research and production space center

This report represents the system of small satellites for remote sensing, based on the generic space bus. The main goals of the system are mapping, natural resource management, control of natural and man-induced risks, control of environment. The system of small satellites for remote sensing includes space/ground segments. The space segment is the orbital constellation of small satellites for remote sensing fit with optoelectronic, radar equipment and instruments to obtain natural resources data. The launch of the first satellite is scheduled for November, 2001. The deployment of the whole system is planned to be completed by 2006. The ground segment includes: ground control complex, mission management, data archiving and product generation facility, ground receiving station of the Khrunichev Space Center, federal and regional data receiving stations (functionally), data communication and transmission system. The purpose of the program is to provide Russian and foreign users with natural resource information.

The Rockot launch system—the commercial solution for low-cost planetary missions

EUROCKOT Launch Services GmbH was founded by DaimlerChrysler Aerospace of Germany and Khrunichev State Research and Production Space Center of Russia to offer worldwide cost-effective launch services on the flight proven and reliable Rockot launch system. Rockot can launch satellites weighting up to 1850 kg into low earth orbits (LEO) from around 50° up to high inclinations (e.g. SSO). The paper describes the design, the capabilities and the user interfaces of the Rockot launch vehicle which is based on the former Russian SS-19 strategic missile. The third stage “Breeze” has been newly developed and has multiple ignition capability. The extremely high flexibility of both the payload accommodation and the launch systems allows fast service, i.e. a mission integration period of 18 months from contract signature and a nominal launch campaign which lasts 19 working days. The launch site in Plesetsk has been modernised and adapted to fulfil all requirements of Western customers. The modifications will be verified by a launch of two satellite simulators in the second quarter of 2000. The first commercial launch (two IRIDIUM satellites) is foreseen for the third quarter of 2000. EUROCKOT is also in a position to offer high altitude orbits. In particular for payloads with a mass of up to approximately 320 kg even earth escape/planetary mission with reliable competitive and flight qualified systems can be offered by adding a solid boost stage to the Rockot launcher in co-operation with the major provider of these stages. In this paper the performance envelope, interfaces and potential design solutions will be discussed.

The Rockot launch system

EUROCKOT Launch Services GmbH has been founded by Daimler-Benz Aerospace of Germany and Khrunichev State Research and Production Space Center of Russia to offer world-wide cost effective launch services on the Rockot launch system. The Rockot commercial program is described. Rockot can launch satellites weighing up to 1850 kg into polar and other low earth (LEO) orbits. The Rockot launch vehicle is based on the former Russian SS-19 strategic missile. The first and second stages are inherited from the SS-19, the third stage named Breeze is newly developed and has multiple ignition capability. The Rockot launch system is flight proven. In addition to the currently adapted Rockot launch site Plesetsk for high inclinations, EUROCKOT is in the process to also adapt the Baykonur cosmodrome as their complementary Rockot launch site for lower inclinations. The wide range of Rockot performance is provided. The first commercial launch is foreseen in the middle of 1999. The expected launch capacity for Plesetsk and Baykonur will exceed 10 launches per year. The complete Rockot system including performance is presented.

German experiments developed for reentry missions

For the development of reentry technology it is essential that the knowledge gained from ground test facilities and numerical methods is tested and broadened in real reentry flights. The first of such projects was the space reentry capsule EXPRESS, which was designed as a German—Japanese enterprise for both microgravity research and reentry experiments. The capsule was built by the Russian company DB Saljut as part of the Khrunichev State Research and Production Space Center and modified by DASA. The capsule was launched from Kagoshima by a Japanese M-3 SII rocket in January 1995. Due to a failure of the rocket, the nominal orbital altitude could not be reached, which led to an early reentry of the capsule in Ghana after two and a half orbits. In the stagnation region of the reentry module an experiment was planned with a fibre reinforced ceramic tile of 300 mm in diameter integrated in the ablative heat shield. This experiment, called “CETEX”, was designed by the German Aerospace Research Establishment (DLR) in Stuttgart. The aim of CETEX is to qualify lightweight fibre reinforced ceramics and related structural concepts in terms of heat shield applications for space vehicles as well as to compare the erosion behaviour shown in flight experiments and ground tests. An integral part of the CETEX experiment is the PYREX experiment of the University of Stuttgart. With PYREX a pyrometer shall be qualified, which is designed for high precision temperature measurement of heat shield materials made of fibre reinforced ceramic compounds during the reentry phase of space vehicles and probes. A third German experiment, RAFLEX, projected by Hyperschall Technologie Göttingen (HTG), was also integrated in the CETEX tile. RAFLEX is designed for the measurement of dynamic and static pressures and heat transfer at various positions on the EXPRESS capsule. Two small SiC tubes are fed through the CETEX tile for the RAFLEX and RTEX experiments. RTEX is a Japanese spectroscopy experiment which uses the same SiC tube as RAFLEX. Other pressure measurement points and the heat transfer gauges are located in the conical flare of the reentry module. The aim of these pressure measurements is to verify theoretical flow field models for different flight altitudes and to determine the angle of attack of the capsule. In addition, the flight qualification of CETEX and the pressure tube integration are important technological experiments for future reentry experiments. In this paper the EXPRESS and the MIRKA missions will be described briefly. The three experiments, CETEX, PYREX and RAFLEX, in particular their qualification in ground tests, will be dealt with in detail.