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O estetyce obiektów kosmicznych

Tomaszewski Mateusz, Wojewódka Jerzy

Systemy Wspomagania w Inżynierii Produkcji

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2023

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Vol. 12, iss. 2

57--70

PL

Ciekawość, która towarzyszy człowiekowi od narodzin jest niezwykłą siłą, która popycha ludzkość do przodu. To ona wywołuje swoistą potrzebę odkrywania tego co nieznane. Wielkie odkrycia geograficzne są już przeszłością, a tym co czeka na odkrycie jest kosmos. W tym celu ludzkość będzie musiała korzystać z obiektów pozwalających na przemieszczenie się w przestrzeni skrajnie niebezpiecznej dla człowieka. Niniejszy artykuł stanowi przegląd wybranych zagadnień dotyczących statków kosmicznych i ich estetki, oraz tego co ma wpływ na ostatecznie przyjętą formę takich obiektów. W spisanych rozważaniach analizowane są śmiałe wizje ukazane w pop-kulturze (kulturze popularnej), jak i informacje mogące wpłynąć w przyszłości na przyjęte rozwiązania formalne statków kosmicznych.

EN

The curiosity that has accompanied man since birth is an extraordinary force that drives humanity forward. It is what generates the peculiar need to discover the unknown. The great geographical discoveries are in the past, and what is waiting to be discovered is the cosmos. In order to do so, mankind will have to make use of facilities that allow it to move through space that are extremely dangerous for humans. This article reviews selected issues concerning spacecraft and their aesthetics, and what influences the final form of such objects. The written discussion examines the bold visions portrayed in pop culture, as well as information that may influence the formal solutions adopted for spacecraft in the future.

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Deployment of long-measured flexible structure in orbit

Zakrzhevsky A. E.

Vibrations in Physical Systems

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2014

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Vol. 26

335--342

EN

Dynamics of the spacecraft with giro-gravitational system of stabilisation, in which the pantograph design deployed in an orbit and containing on the end the concentrated mass is used as the gravitational stabilizer and the carrier of solar batteries, is investigated. The analysis of the obtained information is carried out and graphs that illustrate behaviour of characteristic variables are discussed.

3

Optimal reorientation of spacecraft orbit

Chelnokov Yu. N., Pankratov I. A., Sapunkov Y. G.

Archives of Control Sciences

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2014

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Vol. 24, no. 2

119--128

EN

The problem of optimal reorientation of the spacecraft orbit is considered. For solving the problem we used quaternion equations of motion written in rotating coordinate system. The use of quaternion variables makes this consideration more efficient. The problem of optimal control is solved on the basis of the maximum principle. An example of numerical solution of the problem is given.

4

Dynamics of spacecraft due to elastic ring antenna deployment

Khoroshilov V. S., Zakrzhevskii A. E.

Vibrations in Physical Systems

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2012

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Vol. 25

229--234

EN

This research deals with the study the dynamics of the spacecraft with the deployed flexible ring antenna. The deployment is performed after placing the spacecraft into orbit and completion of the preliminary damping by a special jet-propelled system, and after uncaging the gyros of the stabilization system. Primarily the antenna is a pre-stressed tape wound on a special drum. When the drum starts deploying the tape, it takes the shape of an elastic ring of variable diameter. The objective of the study is the mechanical and computational modelling of the spacecraft dynamics. The equations of motion are derived with the use of the Eulerian-Lagrangian formalism with the help of Mathematica 5©. Numerical simulations of the operational mode of the system are conducted. Numerical results indicate that the system used for attitude stabilization ensures the shape of the deployed design and prescribed accuracy of the orientation. Simulation results are presented for the spacecraft model in order to show the effectiveness of the spacecraft and deployment process stabilization.

5

New results on radiation effects on human health

Spurny F., Dachev T.

Acta Geophysica

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2009

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Vol. 57, no. 1

125-140

EN

Humans are exposed to ionizing radiation all the time, and it is known that it can induce a variety of harmful biological effects. Consequently, it is necessary to quantitatively assess the level of exposure to this radiation as the basis for estimating risks due to ionization radiation. During the Work Package 2400 of the COST-724/WG-2 action, a number of spacecraft and aircraft experiments have been performed with both active and passive detectors. A large data base has been created. In this contribution we would like to stress the results obtained and their importance in three particular directions: (i) Simultaneous investigation of galactic cosmic rays on aircraft and on the International Space Station (ISS); (ii) Onboard spacecraft neutron contribution as estimated on the basis of the comparison of results measured with MDU/Liulin equipment onboard ISS, foton capsule and a commercial aircraft flying at subsonic altitudes; (iii) Complex analysis of the results of long term measurements onboard a Czech Airlines aircraft. The results obtained are presented, analyzed, and discussed, and their complementary nature is underlined. The contribution represents a version of the Final Report of the Work Package 2400 of the COST-724/WG-2: Radiation Environment of the Earth.

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Probabilistic analysis of spacecraft separation from the launch-vehicle

Kibzun A.I., Shluinsky Y.T., Kan Y.S., Miroshkin V.L.

Zeszyty Naukowe Politechniki Rzeszowskiej. Mechanika

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1998

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z. 51[168], t.2

493-500

EN

The paper presents a methodology to analyse the probabilistic performance of separation process satelites and launch-vehicles (boosters). Models of spacecraftdynamics are considered with taking into account the liquid fluctuations in the fuel tanks. All the design uncertainties are modelled as random variables. The probabilistic characteristics of the critical separation parameters are estimated by the Monte Carlo method. The methodology allows to perform the statistical computer simulation of the separation and it is confirmed by the corespondence of the forecasted performances with data of real launches.