The analysis of transport opportunities of an oxygen-hydrogen chemical upper stage at insertion into a geostationary orbit for space system on the basis of a launcher Soyuz 2-1b

In this paper, the problem of minimum time multiple-burn optimization of an upper stage with a limited thrust, and engine restart capability for satellite injection into geostationary orbit are considered. The goals are to find thrust vector angle, times of the engine firings, and optimal duration of active phases of the upper stage to minimize fuel consumption and meet the desired boundary conditions. Various flight sequences with multiple burns, from two burns up to six burns, are considered. Also, the optimal trajectory for each sequence is derived. To solve the multi-point boundary value problem, an improved indirect shooting method with high performance is presented and used for an optimal solution. All in all, this novel method presented for multi-burn problem, not only with a very good accuracy, but also with a very fast convergence to the desired end conditions.

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MODEL FOR ASSESSING SITUATIONAL AWARENESS OF SPACE SYSTEM

Issues of radio electronics ◽

10.21778/2218-5453-2019-3-83-91 ◽

2019 ◽

pp. 83-91

Author(s):

V. I. Erokhin ◽

A. P. Kadochnikov ◽

S. V. Sotnikov ◽

A. A. Vaganov ◽

D. A. Valeryanov

Keyword(s):

Mathematical Model ◽

Numerical Experiment ◽

Control Region ◽

Situational Awareness ◽

Elliptical Orbit ◽

Geostationary Orbit ◽

Space System ◽

Numerical Example

The paper presents a mathematical model for assessing the situational awareness of the space system. The model includes a set of algorithms, the main ones being the algorithm for simulating the motion of a spacecraft in a highly elliptical orbit, the algorithm for determining the observability of a given controlled area by a given spacecraft in a highly elliptical orbit at a given time, and the algorithm for determining the observability of a given controlled area by a spacecraft in a geostationary orbit. The model allows the assessment of the information capabilities of a space system of various ballistic structures and compositions. A model numerical example is considered, which makes it possible to compare observability indices of a given control region with two possible variants of a ballistic construction of a spacecraft constellation. The results of the numerical experiment showed the correctness of the proposed mathematical model.

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HIGHLY ELLIPTIC SPACE SYSTEM FOR MONITORING OF GEOSTATIONARY ORBIT

Radio Industry (Russia) ◽

10.21778/2413-9599-2016-1-102-108 ◽

2016 ◽

pp. 102-108 ◽

Cited By ~ 1

Author(s):

N. N. Klimenko ◽

A. E. Nazarov

Keyword(s):

Geostationary Orbit ◽

Space System ◽

Elliptic Space

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An interferometer for high-resolution optical surveillance from geostationary orbit - space system study

International Conference on Space Optics — ICSO 2006 ◽

10.1117/12.2308169 ◽

2017 ◽

Author(s):

L. Bonino ◽

F. Bresciani ◽

G. Piasini ◽

C. Flebus ◽

J.-H. Lecat ◽

...

Keyword(s):

High Resolution ◽

Orbit Space ◽

Geostationary Orbit ◽

System Study ◽

Space System

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Development of method for selecting motion control laws of space optical system on based diffractive membranes during transfer into geostationary orbit

10.18287/1613-0073-2017-1966-35-42 ◽

2017 ◽

Author(s):

Gennadiy P. Аnshakov ◽

◽

Vadim V. Salmin ◽

Alexey S. Chetverikov ◽

Konstantin V. Peresypkin ◽

...

Keyword(s):

Optical System ◽

Trajectory Optimization ◽

Geostationary Orbit ◽

Pareto Optimal Solutions ◽

Terminal Control ◽

Low Thrust ◽

Space System ◽

Control Laws ◽

Control Programs ◽

And Control

The article presents a formulation of a problem of trajectory optimization using low-thrust engines for an optical space system based on diffractive membranes. A methodology, where first stage nominal trajectories and control programs are selected and then corrected at the longrange guidance, has been developed for solving the problem of optimizing the trajectories of a flight to a geostationary orbit. At the final stage, algorithms for terminal control are formed, which allows to deliver a cosmic optical system based on diffraction membranes to a given point in the geostationary orbit. The end result is acquisition of Pareto-optimal solutions in the coordinates "characteristic speed-duration of the flight", where each point of the set of solutions has a corresponding a measure of accuracy of payload delivery to a geostationary orbit at a given set of coordinates.

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