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1.
用脉冲星钟作航天器时间标准 总被引：3，自引：0，他引：3
在介绍参考坐标系和时间标准的基础上,讨论了用脉冲星为航天器导航的时间标准问题。利用X射线脉冲星实现航天器自主导航,星载钟的任何误差都会直接影响航天器位置测量。脉冲星钟具有较高的长期频率稳定度,适合用作各类航天器的时间标准。重点讨论了时间标准误差对航天器定位的影响;给出了用脉冲星钟作航天器时间标准的物理实现方法。 相似文献
2.
利用脉冲星钟模型能高精度地预报脉冲星脉冲到达太阳系质心的时间。基于脉冲星时、空参考架可实现各类空间飞行器的自主导航。讨论了脉冲星钟的模型和脉冲星导航系统的框架结构,描述了脉冲星导航的基本原理和算法。指出脉冲星导航系统对脉冲星脉冲到达探测器时刻的测量精度,是决定空间飞行器位置解算精度的关键因素。脉冲星导航观测采用的原子钟如果足够稳定,则空间飞行器位置的解算方法可以简化。在脉冲星导航系统计时观测精度达到或优于几十微秒量级时,脉冲星视差、相对论效应的影响是不可忽略的。对脉冲星导航系统开发设计中的关键技术和进一步研究的主要问题进行了初步分析和讨论。 相似文献
3.
The disturbance of an electrostatic probe, by the spacecraft carrying it, in the intermediate altitude regime from about 3000 km to the plasmapause, is discussed. Three kinds of disturbance are studied: loss of symmetry of the probe sheath due to the presence of the spacecraft; creation of potential barriers around the probe; and particle removal, or shadowing, by the spacecraft. The first of these effects is shown to be nonexistent for a spherical probe if it is operated under orbit-limited conditions. Methods are given for estimating the magnitudes of the other two effects in any given situation. The electrostatic probe experiment on the Explorer 31 spacecraft is discussed as an example. 相似文献
4.
The effect of micrometeorite impacts upon the surface of a spacecraft on the accuracy of astrometric measurements made by scanning with instruments onboard the spacecraft is considered. This effect is shown to be marginal for HIPPARCOS measurements. However, disregarding this kind of effect for all the currently projected spacecraft may result in the declared measurement accuracy being unachievable. Spacecraft maintaining constant spatial orientation during measurements are essentially not subject to the errors caused by collisions with micrometeorites. 相似文献
5.
《New Astronomy》2020
The purpose of this paper is to make a numerical search for natural orbits that can be used for a spacecraft to study a possible small moon of Pallas. There are many speculations about the existence of a small companion around this large asteroid, so finding and classifying orbits around this possible celestial body is an interesting problem in astrodynamics and that can be used for a spacecraft to observe this body. It is assumed that this moon has a radius that can vary from 0.125 to 1 km and that is located 750 or 500 km away from the center of Pallas. The idea is to show the effects of this parameter in the orbits around this moon. It means that the moon is much smaller than Pallas, so Keplerian orbits are not possible around it. To solve this problem, it is possible to find some special orbits that are called "Quasi Satellite Orbits" (QSO). They are orbits dominated by the gravity of Pallas, but that use the smaller perturbation from the moon to keep the spacecraft close to it. The present work searches for orbits that make the spacecraft to remain at given limits in its distance from the moon, like in the range from 3 to 50 km, the values used as an example in the present paper. This value is used because it is a good range to observe the body without getting to close to it, so reducing the risks of collisions. Each trajectory can be identified by the initial conditions of the spacecraft with respect to the moon, which means its initial position and velocity. The dynamics considers the restricted three-body problem and the influence of the solar radiation pressure, because some spacecraft may have higher values for the area-to-mass ratio, which gives a non-negligible effect in the trajectory of the spacecraft. 相似文献
6.
A pulsar has the very stable rotation and can be used as the time standard. The astrometric parameters and astrophysical parameters of many pulsars, such as the spatial position, proper motion, distance, rotation period and its derivative, etc., can be all accurately determined. Since the pulsar can provide the time signal and the coordinates of its spatial position simultaneously, the pulsar navigation system installed on a spacecraft enables the autonomous navigation of the spacecraft to be realized. Firstly, the position of the spacecraft is predicted based on the equation of orbit dynamics of the spacecraft and then the Kalman filtering is applied to calculating the estimation error of the spacecraft position through the difference between the pulse arrival time observed on the spacecraft and the predicted pulse arrival time, thereby modifying the position of the spacecraft. Finally, the effects of the initial error, measuring accuracy of the pulse arrival time and number of pulsars on the navigation accuracy are analyzed. 相似文献
7.
V. M. Kulkov Yu. G. Egorov A. M. Krainov A. E. Shakhanov R. V. Elnikov 《Solar System Research》2016,50(7):533-539
Aspects of the design of small spacecraft with electric propulsion power plants for investigating minor bodies in the Solar System are examined. The results of design and ballistic analysis of transfer into an orbit of terrestrial asteroids using electric propulsion thrusters are given. The possible concept design of the spacecraft is determined and the structure of a small spacecraft with an electric propulsion power plant is presented. Parameters of the electric propulsion power plant of a small spacecraft for a flight to the minor bodies of the Solar System are estimated. 相似文献
8.
To send humans beyond Mars, a Human Outer Planet Exploration (HOPE) mission has been studied for new spacecraft concepts and technologies. In this paper, an interplanetary trajectory and a preliminary spacecraft design are presented for the HOPE visit to Callisto, one of Jupiter's moons. To design a round-trip trajectory for the mission, the characteristics of the spacecraft and its trajectories are analyzed. A detailed optimization approach is formulated to utilize a Variable Specific Impulse Magnetoplasma Rocket (VASIMR) engine with capabilities of variable specific impulse, variable engine efficiency, and engine on-off control. It is mainly illustrated that a 30 MW powered spacecraft can make the mission possible in a 5-year round trip constraint around the year 2045. Trajectories with different power and reactor options are also discussed. The results obtained in this study can be used for formulating an overall concept for the mission. 相似文献
9.
10.
Results and analysis are presented for a numerical simulation of solar radiation forces acting on the Spektr-RG spacecraft in operational orbit. The possibility is investigated of compensating the radiation pressure-induced perturbing torque without adding new units and assemblies into the spacecraft configuration. A rationale is given for ways of implementing the compensation techniques that enable 65% compensation of sufficiently large perturbing torques, thus considerably reducing (by 5–6 kg) the propellant consumption in the control system engines and increasing the lifetime of the spacecraft. 相似文献
11.
During the decay of solar cosmic-ray events cosmic-rays with kinetic energies of about 1 MeV are convected outward with the solar wind. It is shown that, with currently available observations it should be possible to demonstrate directly the energy losses which are occurring. Observations from two spacecraft on the same heliocentric radial line are required. In this paper observations from Venera-4 and Imp-F have been used. A simple and direct demonstration would be provided by the observation of nearly mono-energetic pulses convected between the two spacecraft, but no such pulses were found to be present. A second method depends upon observing the ratio of the integral fluxes at the two spacecraft and comparing this with the value predicted by theory. The relevant theoretical analysis has been given. It is shown that in order to discriminate between energy-loss processes the spacecraft must be well separated. For spacecraft at Earth's orbit and the orbit of Venus the integral-flux ratio predicted with energy loss due to adiabatic deceleration is a factor of three higher than that predicted with no energy loss. Comparisons of integral-flux ratios for two events observed on spacecraft separated by approximately 0.1 AU gave inconclusive results. In view of the importance of energy-loss processes in the propagation of cosmic rays it is suggested that others with access to relevant data might continue this investigation. 相似文献
12.
Riccardo Bevilacqua Jason S. Hall Marcello Romano 《Celestial Mechanics and Dynamical Astronomy》2010,106(1):69-88
A novel two-phase hybrid controller is proposed to optimize propellant consumption during multiple spacecraft rendezvous maneuvers
in Low Earth Orbit. This controller exploits generated differentials in aerodynamic drag on each involved chaser spacecraft
to effect a propellant-free trajectory near to the target spacecraft during the first phase of the maneuver, and then uses
a fuel optimal control strategy via continuous low-thrust engines to effect a precision dock during the second phase. In particular,
by varying the imparted aerodynamic drag force on each of the chaser spacecraft, relative differential accelerations are generated
between each chaser and the target spacecraft along two of the three translational degrees of freedom. In order to generate
this required differential, each chaser spacecraft is assumed to include a system of rotating flat panels. Additionally, each
chaser spacecraft is assumed to have continuous low-thrust capability along the three translational degrees of freedom and
full-axis attitude control. Sample simulations are presented to support the validity and robustness of the proposed hybrid
controller to variations in the atmospheric density along with different spacecraft masses and ballistic coefficients. Furthermore,
the proposed hybrid controller is validated against a complete nonlinear orbital model to include relative navigation errors
typical of carrier-phase differential GPS (CDGPS). Limitations of the proposed controller appear relative to the target spacecraft’s
orbit eccentricity and a general characterization of the atmospheric density. Bounds on these variables are included to provide
a framework within which the proposed hybrid controller can effect an extremely low propellant rendezvous of multiple chaser
spacecraft to a desired target spacecraft. 相似文献
13.
关于脉冲星脉冲到达时间转换方程 总被引：1，自引：0，他引：1
较详细地介绍了脉冲星脉冲到达时间（TOA）转换方程,讨论了脉冲星TOA转换方程在航天器导航算法中的具体应用问题。同时,对导航用的脉冲星脉冲TOA转换方程与地面射电计时观测用的脉冲星脉冲TOA转换方程进行了比较研究。 相似文献
14.
15.
A method and an algorithm for determining the coordinates of points on the planetary surface are described. The coordinates are determined using photographs. To solve the problem, the spacecraft coordinates need to be determined at five trajectory points. The spacecraft trajectory is considered to be a plane. The method is applicable for determining the coordinates of points on the Earth’s surface and on the surface of other planets. 相似文献
16.
Walter S. Kiefer 《Planetary and Space Science》2012,60(1):155-165
Reliable measurements of the Moon's global heat flow would serve as an important diagnostic test for models of lunar thermal evolution and would also help to constrain the Moon's bulk abundance of radioactive elements and its differentiation history. The two existing measurements of lunar heat flow are unlikely to be representative of the global heat flow. For these reasons, obtaining additional heat flow measurements has been recognized as a high priority lunar science objective. In making such measurements, it is essential that the design and deployment of the heat flow probe and of the parent spacecraft do not inadvertently modify the near-surface thermal structure of the lunar regolith and thus perturb the measured heat flow. One type of spacecraft-related perturbation is the shadow cast by the spacecraft and by thermal blankets on some instruments. The thermal effects of these shadows propagate by conduction both downward and outward from the spacecraft into the lunar regolith. Shadows cast by the spacecraft superstructure move over the surface with time and only perturb the regolith temperature in the upper 0.8 m. Permanent shadows, such as from thermal blankets covering a seismometer or other instruments, can modify the temperature to greater depth. Finite element simulations using measured values of the thermal diffusivity of lunar regolith show that the limiting factor for temperature perturbations is the need to measure the annual thermal wave for 2 or more years to measure the thermal diffusivity. The error induced by permanent spacecraft thermal shadows can be kept below 8% of the annual wave amplitude at 1 m depth if the heat flow probe is deployed at least 2.5 m away from any permanent spacecraft shadow. Deploying the heat flow probe 2 m from permanent shadows permits measuring the annual thermal wave for only one year and should be considered the science floor for a heat flow experiment on the Moon. One way to meet this separation requirement would be to deploy the heat flow and seismology experiments on opposite sides of the spacecraft. This result should be incorporated in the design of future lunar geophysics spacecraft experiments. Differences in the thermal environments of the Moon and Mars result in less restrictive separation requirements for heat flow experiments on Mars. 相似文献
17.
应用X射线源的航天器姿态测量 总被引：1，自引：0，他引：1
在介绍X射线源和X射线探测器、准直器的基础上,重点描述了应用X射线源测量航天器姿态参数的原理和方法。对X射线星扫描仪的结构、扫描观测X射线源方法和矩形准直器响应函数等做了介绍,较详细地论述了应用单准直器X射线星扫描仪和差分准直器X射线星扫描仪确定航天器姿态参数的测量模型,并进行了二者间的比较和分析。简单讨论了X射线星扫描仪测量建模和应用测量模型拟合航天器姿态参数的算法问题。最后,对采用编码孔径系统确定航天器姿态参数的方法做了概括性介绍。 相似文献
18.
The theory of interactions between a probe and the surrounding plasma at rest is developed in a spherically and in a cylindrically symmetric model (probe theory). The theory is based on the Vlasov-Poisson system; a general numerical program was developed to solve this system by means of an iterative procedure. Various ambient plasma and charged particle emission properties are described by the complete set of boundary conditions for the distribution functions in the phase space. By use of this numerical method, potential and space charge density in the whole surroundings of the probe as well as the current densities of all plasma constituents are calculated self-consistently.Furthermore, the regions of the phase space with particle trajectories of the same kind can be approximated depending on the plasma properties. Then, the current densities can be estimated analytically. This approach to the problem yields self-consistent approximations and is the only stringent derivation of the thick sheath and of the thin sheath approximation of the classical Langmuir theory. These approximations are generalized with respect to the charged particle emission from the surface.The symmetric probe theory is applied to the following problems of spacecraft environment and spacecraft charging: (i) a spacecraft in the ionosphere with very negative surface potential, (ii) a spacecraft in the solar wind with strong photoelectron emission, and (iii) a spacecraft in the transition region of comet Halley with very strong secondary plasma emission. 相似文献
19.
Opitz A. Karrer R. Wurz P. Galvin A. B. Bochsler P. Blush L. M. Daoudi H. Ellis L. Farrugia C. J. Giammanco C. Kistler L. M. Klecker B. Kucharek H. Lee M. A. Möbius E. Popecki M. Sigrist M. Simunac K. Singer K. Thompson B. Wimmer-Schweingruber R. F. 《Solar physics》2009,256(1-2):365-377
The two STEREO spacecraft with nearly identical instrumentation were launched near solar activity minimum and they separate by about 45° per year, providing a unique tool to study the temporal evolution of the solar wind. We analyze the solar wind bulk velocity measured by the two PLASTIC plasma instruments onboard the two STEREO spacecraft. During the first half year of our measurements (March?–?August 2007) we find the typical alternating slow and fast solar wind stream pattern expected at solar minimum. To evaluate the temporal evolution of the solar wind bulk velocity we exclude the spatial variations and calculate the correlation between the solar wind bulk velocity measured by the two spacecraft. We account for the different spacecraft positions in radial distance and longitude by calculating the corresponding time lag. After adjusting for this time lag we compare the solar wind bulk velocity measurements at the two spacecraft and calculate the correlation between the two time-shifted datasets. We show how this correlation decreases as the time difference between two corresponding measurements increases. As a result, the characteristic temporal changes in the solar wind bulk velocity can be inferred. The obtained correlation is 0.95 for a time lag of 0.5 days and 0.85 for 2 days.
相似文献20.
The solar wind flow behind shock fronts on June 25–26 and August 11, 1967 was studied using data from two spacecraft. For the last event the spacecraft were separated by 0.1 AU. In both cases there is a high degree of correlation between plasma parameters observed from the two spacecraft indicating that the features retain their identity over radial distances of at least 0.1 AU. 相似文献