On additional errors of float gyroscope during circulation of a carrier rocket

2009 ◽  
Vol 15 (6) ◽  
pp. 49-56
Author(s):  
V.V. Karachun ◽  
◽  
V.N. Mel’nick ◽  
Keyword(s):  
Carrier Rocket

REAL-TIME CARRIER ROCKET MISSION CONTROL USING SPACE RELAY SYSTEM

2019 ◽  
Vol 20 (3) ◽  
pp. 344-355
Author(s):  
D. A. Makhalov ◽  
◽  
M. P. Nikitina ◽  
S. B. Usikov ◽  
A. V. Manoilo ◽  
...  
Keyword(s):  
Real Time ◽  
Relay System ◽  
Mission Control ◽  
Carrier Rocket

In-orbit performance of the laser interferometer of Taiji-1 experimental satellite

2021 ◽  
pp. 2140004
Author(s):  
He-Shan Liu ◽  
Zi-Ren Luo ◽  
Wei Sha ◽  
Keyword(s):  
Laser Interferometer ◽  
Fused Silica ◽  
Test Mass ◽  
Frequency Range ◽  
Space Antenna ◽  
Satellite Platform ◽  
Laser Interferometer Space Antenna ◽  
Key Technologies ◽  
Carrier Rocket ◽  
Reference Sensor

Taiji-1, which is the first experimental satellite for space gravitational wave detection in China, relies on key technologies which include the laser interferometer, the gravitational reference sensor (GRS), the micro-thruster and the satellite platform. Similarly to the Laser Interferometer Space Antenna (LISA) pathfinder, except for the science interferometer, the optical bench (OB) of Taiji-1 contains reference and test mass (TM) interferometers. Limited by the lower mechanical strength of the carrier rocket and by the orbit environment, the OB of Taiji-1 is made of invar steel and fused silica, and it is aimed to achieve a sensitivity of the order of 100[Formula: see text]pm/[Formula: see text]. The experimental results from in-orbit tests of Taiji-1 demonstrate that the interferometer can reach a sensitivity of 30[Formula: see text]pm/[Formula: see text] in the frequency range of 0.01–10[Formula: see text]Hz, which satisfies the requirements of Taiji-1 mission.

Transformation of the soil-vegetation cover in carrier rocket first-stage impact areas

2011 ◽  
Vol 1 (1) ◽  
pp. 59-64 ◽  
Author(s):  
P. P. Krechetov ◽  
V. V. Neronov ◽  
T. V. Koroleva ◽  
O. V. Chernistova
Keyword(s):  
Vegetation Cover ◽  
Carrier Rocket

scholarly journals СОВРЕМЕННЫЕ ЗАДАЧИ СОЗДАНИЯ И УВОДА С ОРБИТЫ ГРУППИРОВОК КОСМИЧЕСКИХ АППАРАТОВ КЛАССА НАНО И ПИКО

2018 ◽  
pp. 20-35
Author(s):  
Эрик Александрович Лапханов ◽  
Александр Сергеевич Палий
Keyword(s):  
Permanent Magnet ◽  
Permanent Magnets ◽  
Formation Flying ◽  
Long Distance ◽  
Rocket Fuel ◽  
Effective Work ◽  
Satellite Systems ◽  
Magnetic Devices ◽  
Distributed Satellite ◽  
Carrier Rocket

The purpose of the present paper is the analysis of current tasks concerning with creation and deorbiting of the formation flying groups consist of nano- and picosatellites and the consideration of the possibility of using permanent magnet devices for the deorbiting of these groups. During research was determined that it is most expedient to use small standardized spacecraft and use them during the development of distributed satellite systems. It can be both formations, and groups of satellites spaced a long distance. The analysis of the current possibilities for the removal of nano- and pico- spacecraft into orbit is carried out. According to the characteristics and properties of super-small spacecraft because of their super-small size and saving of the rocket fuel, it was determined that these spacecrafts proposed to be launch as a passing payload when large, expensive spacecraft is launched into orbit.  To facilitate the integration of spacecrafts such as CubeSats with a carrier rocket, special multi-purpose dispensers were developed. The problems of controlling the configuration of the nano- and pico- satellites formations are shown. The analysis of deorbiting technologies of spacecrafts of the nano- and pico- satellites is carried out. The overview of modern well-known propulsion technologies of nano- and pico- satellites is carried out. The new method of creation and deorbiting of the formation flying groups from nano- and pico- satellites with using new constructive scheme “spherical dispensers” was proposed. The main axes of P-PODs are located along the radiuses of “spherical dispenser”. The technology of deploying and “clotting “of the formation flying groups from nano- and pico- satellites with using tether connection and hoist devices was proposed. The analysis of the possibility of implementation of devices with permanent magnets for nano- and pico- satellites is carried out. The low boundaries of effective work of the magnetic devices were determined. An alternative method for deorbiting nano- and pico- spacecrafts with the help of devices with permanent magnets using “clotting “technology is proposed

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