USE OF INFORMATION ABOUT STATE VECTOR OF EXECUTIVE DEVICE IN STABILIZING SYSTEM OF A ROCKET ROTATION MOTION
DOI:
https://doi.org/10.15588/1607-3274-2018-3-19Keywords:
stabilization of motion, state vector, law of controlAbstract
Context. A method for obtaining estimates of the dependence of stability factor and reduced work during the transient processfor compensation of a constant disturbing acceleration on the presence in law of control data about current kinematic parameters of
the executive device under condition of ensuring a prescribed static error is developed. It will give a possibility to take decision about
level of complexity for appropriate units in stabilizing system.
Objective. The purpose of the research is to estimate the influence of the law of control reduction by means of exclusion from
one the data about state vector of the executive device on requirements to its power and stability factor.
Method. A linear stationary in the vicinity of a certain point of the trajectory model of a plane rotational motion of a rocket for
space purposes has been adopted, with taking into account the inertia of the executive device. Estimation of the stability factor is
carried out on the plane of the roots of the characteristic polynomial and two coefficients of the law of control. Divided to the square
of constant perturbation acceleration, the work of the executive device is determined by analytical solution of the differential
equations of perturbed rotational motion in one of the stabilization planes. For statically stable and unstable rocket the dependence
examples of the named performances on coefficients of the law of control by coordinates of the state vector are made.
Results. For the application of the rocket for space purposes for the first time the dependence of the named indices of stabilizing
system on availability in the law of control data about angle of rotation of steering gear and its velocity is established.
Conclusions. It is proven the ability of improvement the stabilizing system by means of inclusion in law of control kinematic parameters
of the executive device from the point of view of such performances as a stability factor and energy costs during transient
processes.
References
Igdalov I. M., Kuchma L. D., Poliakov N. V., Sheptun Ju.
D.; under the editorship by academician S. N. Konyukchov.
Dynamic designing of rockets. Dynamics problems of rockets
and space stages: monograph. Dnipro, ЛІРА, 2013,
p.
Avdejev V. V. Zapas ustojchivosti sistemy stabilizacii
vrashhatel'nogo dvizhenija rakety, Tehnicheskaja mehanika,
, No. 4, pp. 62–69.
Avdejev V. V. Kojefficienty oshibok stabilizacii vrashhatel'nogo dvizhenija rakety, Tehnicheskaja mehanika,
, No. 3, pp. 71–78.
Avdejev V. Law of control and characteristics of a stabilizing
system, 6th international conference “Space technologies:
present and future” 23–26 May 1917. Dnipro,
pp. 113–114.
Avdejev V. V. Kriterij jakosti perechidnogo processu i pokazniki totchnosti systemy stabilizazii obertalnogo ruchu
rakety, Aviazionno-kosmitcheskaja technika i technologia,
, No. 1 (136), pp. 4–10.
Rogers J., Castello M., Cooper G. Design consideration for
stability of liquid payload projectiles, Journal of spacecraft
and rockets, 2013, No. 1, Vol. 50, pp. 169–178. DOI:
2514/1.A32292.
Hrustaljov M. M., Halina A. S. Prostoj algoritm stabilizacii
orientacii sputnika s gibkim jelementom, Jelektronnyj zhurnal
«Trudy MAI», Vypusk No. 55, 2012. www.mai.ru/science/trudy.
Suhorebryj V. G., Cvetkova A. A., Shopina A. B. Optimizacija
parametrov sistemy stabilizacii raket-nositelej s pomoshh'ju
metoda variacij, Otkrytye informacionnye i komp'juternye
integrirovannye tehnologii, 2015, No. 68, pp. 5–
Rezhim dostupu: http://nbuv.gov.ua/UJRN/vikt_2015_68_3.
Chesi S., Gong O., Romano M. Aerodynamic three-axis
attitude stabilization of a spacecraft by center-of-mass
shifting, Journal of guidance, control, and dynamics, 2017,
No. 7, Vol. 40, pp. 1613–1626. DOI: 10.2514/1.G00246.
Celani F. Spacecraft attitude stabilization with piecewiseconstant magnetic dipole moment, Journal of guidance, control, and dynamics, 2016, No. 5, Vol. 39, pp. 1140–1146. DOI: 10.2514/1.G001388.
Chen C., Liang Y., Jhu W. Global stability of a system with
state-dependent Riccati equation controller, Journal of
guidance, control, and dynamics, 2015, No. 10, Vol. 38, pp.
–2054. DOI: 10.2514/1.G000989.
Avdejev V. V. Tochnіst' і zapas stіjkostі sistemi stabіlіzacії
obertal'nogo ruhu raketi, Radio Electronics, Computer Science,
Control, 2016, No. 3, pp. 93–98. DOI: 10.15588/1607-
-2016-3-12.
Downloads
How to Cite
Issue
Section
License
Copyright (c) 2018 V. V. Avdejev
This work is licensed under a Creative Commons Attribution-ShareAlike 4.0 International License.
Creative Commons Licensing Notifications in the Copyright Notices
The journal allows the authors to hold the copyright without restrictions and to retain publishing rights without restrictions.
The journal allows readers to read, download, copy, distribute, print, search, or link to the full texts of its articles.
The journal allows to reuse and remixing of its content, in accordance with a Creative Commons license СС BY -SA.
Authors who publish with this journal agree to the following terms:
-
Authors retain copyright and grant the journal right of first publication with the work simultaneously licensed under a Creative Commons Attribution License CC BY-SA that allows others to share the work with an acknowledgement of the work's authorship and initial publication in this journal.
-
Authors are able to enter into separate, additional contractual arrangements for the non-exclusive distribution of the journal's published version of the work (e.g., post it to an institutional repository or publish it in a book), with an acknowledgement of its initial publication in this journal.
-
Authors are permitted and encouraged to post their work online (e.g., in institutional repositories or on their website) prior to and during the submission process, as it can lead to productive exchanges, as well as earlier and greater citation of published work.
