排序方式: 共有18条查询结果,搜索用时 15 毫秒
1.
V. Koblik E. Polyakhova L. Sokolov A. Shmyrov 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2002,29(12):4431-2088
We present results of numerical simulations of trajectories of a space probe with a flat solar sail which moves from a circular Earth orbit to near-Sun regions. We consider the upper limit of the sail temperature as the basic restriction. We also examine the planar (ecliptic) solar sail transfer with gravity-assist flybys around planets. 相似文献
2.
3.
Beklemishev N. D. Boguslavskii A. A. Belyaev M. Yu. Volkov O. N. Sazonov V. V. Sokolov S. M. Sofinskii A. N. 《Cosmic Research》2021,59(3):183-198
Cosmic Research - The results of the Sreda–MKS space experiment showed that visual data on the vibrations of the ISS structural elements allow one to acquire quantitative characteristics of... 相似文献
4.
5.
The problem of determining an estimation of current spacecraft motion parameters on the stage of its descent is solved on the basis of readings of an optoelectronic navigation system and additional information from the self-contained inertial navigation system at the most general assumptions on the nature of motion of the object and the statistical properties of the noise of the measuring devices. 相似文献
6.
The motion of a spherically symmetric balloon satellite near the equatorial plane is considered. Taking the Earth's oblateness and solar light pressure into account, the integral of motion can be obtained under certain simplifications. The eccentricity is related to the solar angle which represents an angle between pericenter and the Sun. This analytical approximation describes a large and complicated evolution of the eccentricity in corresponding areas of the phase space and the space of parameters. Phase portraits contain fixed saddle points and separatrices that divide different types of oscillations of the eccentricity. In the unsimplified problem, separatrices break down, and specific stochastic motions arise. The aims of the present study are (1) evaluation of the accuracy of analytical approximation with the help of numerical integration using a sufficiently complete model of motion and (2) numerical investigation of stochastic motions and dimensions of stochastic zones in the region of broken separatrices for an adequate model of motion. For a balloon satellite with a semimajor axis of 2.15 Earth's radii and a windage of 30 cm2/g the dimensions of a stochastic zone in eccentricity and solar angle are 10–5and 0.1°, respectively. The analytical approximation describes the orbit evolution in the right way, except for the cases of large eccentricities, e> 0.4, which corresponds to a pericenter height of less than 1400 km, where the atmospheric drag is already significant. 相似文献
7.
The method of improving the positional accuracy of the airborne vehicle that moves along a great circle path is considered due to the analytical three-dimensional projection of its current coordinate position, determined from the measurements of the satellite navigation system under the conditions of high-amplitude noise to the true guide path. 相似文献
8.
V. L. Levtov V. V. Romanov A. A. Boguslavsky V. V. Sazonov S. M. Sokolov Yu. N. Glotov 《Cosmic Research》2009,47(6):513-524
A space experiment aimed at determination of quasi-static microaccelerations onboard an artificial satellite of the Earth
using video images of the objects executing free motion is considered. The experiment was carried out onboard the Foton M-3 satellite. Several pellets moved in a cubic box fixed on the satellite’s mainframe and having two transparent adjacent walls.
Their motion was photographed by a digital video camera. The camera was installed facing one of the transparent walls; a mirror
was placed at an angle to another transparent wall. Such an optical system allowed us to have in a single frame two images
of the pellets from differing viewpoints. The motion of the pellets was photographed on time intervals lasting 96 s. Pauses
between these intervals were also equal to 96 s. A special processing of a separate image allowed us to determine coordinates
of the pellet centers in the camera’s coordinate system. The sequence of frames belonging to a continuous interval of photography
was processed in the following way. The time dependence of each coordinate of every pellet was approximated by a second degree
polynomial using the least squares method. The coefficient of squared time is equal to a half of the corresponding microacceleration
component. As has been shown by processing made, the described method of determination of quasi-static microaccelerations
turned out to be sufficiently sensitive and accurate. 相似文献
9.
V. Koblik E. Polyakhova L. Sokolov 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
Some modifications of solar sail radiation pressure forces on a plate and on a sphere for use in the numerical simulation of ‘local-optimal’ (or ‘instantaneously optimal’) trajectories of a spacecraft with a solar sail are suggested. The force model development is chronologically reviewed, including its connection with solar sail surface reflective and thermal properties. The sail surface is considered as partly absorbing, partly reflective (specular and diffuse), partly transparent. Thermal balance is specified because the spacecraft moves from circular Earth orbit to near-Sun regions and thermal limitations on the sail film are taken into account. A spherical sail-balloon can be used in near-Sun regions for scientific research beginning with the solar-synchronous orbit and moving outward from the Sun. The Sun is considered not only as a point-like source of radiation but also as an extended source of radiation which is assumed to be consequently as a point-like source of radiation, a uniformly bright flat solar disc and uniformly bright solar sphere. 相似文献
10.
The possibility to synthesize the attitude control for a gyrostabilized platform is investigated under the most general assumptions on its drifts, using the principle of maximum. The analytical form of the control vector, explicitly depending on all components of the state vector of a navigation system of a descent vehicle, is a specific feature of the found solution. 相似文献