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41.
A new stochastic model considering satellite clock interpolation errors in precise point positioning
Shengli Wang Fanlin Yang Wang Gao Lizi Yan Yulong Ge 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(5):1332-1341
Precise clock products are typically interpolated based on the sampling interval of the observational data when they are used for in precise point positioning. However, due to the occurrence of white noise in atomic clocks, a residual component of such noise will inevitable reside within the observations when clock errors are interpolated, and such noise will affect the resolution of the positioning results. In this paper, which is based on a twenty-one-week analysis of the atomic clock noise characteristics of numerous satellites, a new stochastic observation model that considers satellite clock interpolation errors is proposed. First, the systematic error of each satellite in the IGR clock product was extracted using a wavelet de-noising method to obtain the empirical characteristics of atomic clock noise within each clock product. Then, based on those empirical characteristics, a stochastic observation model was structured that considered the satellite clock interpolation errors. Subsequently, the IGR and IGS clock products at different time intervals were used for experimental validation. A verification using 179 stations worldwide from the IGS showed that, compared with the conventional model, the convergence times using the stochastic model proposed in this study were respectively shortened by 4.8% and 4.0% when the IGR and IGS 300-s-interval clock products were used and by 19.1% and 19.4% when the 900-s-interval clock products were used. Furthermore, the disturbances during the initial phase of the calculation were also effectively improved. 相似文献
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This paper investigates the formation keeping problem for multiple spacecraft in the framework of networked control systems (NCSs). A continuous-time representation of the NCS is considered for the tracking control of relative translational motion between two spacecraft in a leader–follower formation in the presence of communication constraints and system uncertainties. Model-based control schemes are presented, which employ state feedback (when the relative position and velocity vectors are directly measurable) and output feedback (when velocity measurements are not available), respectively, to guarantee input-to-state stability (ISS) of the system. The stability conditions on network transfer intervals are derived as simple eigenvalue tests of a well-structured test matrix. The results are then extended to include network communication delay. Numerical simulations are presented to demonstrate the effectiveness of the control scheme ensuring high formation keeping precision and robustness to nonlinearities and system uncertainties. The proposed controllers are robust not only to structured uncertainties such as system parameter perturbations but also to unstructured uncertainties such as external disturbances and measurement noises. 相似文献
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《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2005,35(10):1795-1798
Based upon multi-wavelength observations outlined by Huang et al. [Solar Phys. 213 (2003) 341], especially the dynamic spectrum at 4.5–7.5 GHz, we study the physical nature of the radio fine structures (FS) during the flare on August 25, 1999 in AR 8674 (S28E21). The main results are: (1) the helical loop of the event related to the FS is unstable for m = 1 kink mode; (2) the time interval between the beginning of reconnection and relaxation of the unstable loop, inferred from the observation, is quantitatively consistent with the results of the numerical simulations on kink unstable loop; (3) the magnetic field strength estimated from the fast kink standing wave is basically of the same order as that estimated from the photospheric magnetic field, which provides strong support to our analysis. 相似文献
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This paper addresses the topic of damping of the spin dynamics of a spatial debris orbiting around the Earth. Such debris, which can consist of parts of heavy launchers such as the Ariane rocket under consideration in this article, are impacted by torques generated by eddy currents as their conducting non-ferromagnetic body orbits through the Earth magnetosphere. Several previous works have focused on describing this induction phenomenon and have proposed analysis of empirical observations of this particular and important effect which has attracted much attention since the number of spatial debris has emerged as a problem for the future of space programs, especially in low orbits. In this paper, we present a relatively comprehensive modeling of the induction phenomenon, by means of Maxwell's equations inside the conducting and non-ferromagnetic body. Through the generalized Ohm's law, we show how one can obtain a partial differential equation with Neumann's boundary conditions problem that, once solved, e.g. through a finite elements method, yields the values of induced currents and braking torques. The case of a depleted upper stage of a heavy launcher, having a cylindrical shape and thin walls is particularly studied. We show a methodology to estimate the decay-rate of the spinning velocity, which is proven to satisfy a first-order asymptotically stable linear dynamics. Special cases consisting of typical orbit of space debris are treated. 相似文献
46.
The method of controlling a spacecraft formation using mean relative states as the inputs is an effective technique if control actuation is sought to be reduced. In this paper, we extend the efficacy of this method by including the linearized J2 terms in the system dynamics and derive the linear mapping between the actual and the mean relative states. The resultant control equation has J2 related gains that are shown to improve the tracking of the states and increase system performance for a phase plane-based controller performing formation maneuvering. 相似文献
47.
《Air & Space Europe》2000,2(1):105-108
This article concerns the creation in the 90's of Aerospace Engineering degrees in Portugal, a country with a sustained tradition of aircraft operations since the 1910's, and a small aircraft industry. It addresses the issues of training Aeronautical engineers to an international standard in a small country in modern times. 相似文献
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《Air & Space Europe》2000,2(5):74-79
This article describes the key science objectives and system design aspects of the Ørsted satellite. It will also describe the integration and test activities performed to qualify the satellite for launch and present the first results obtained during the initial 6 months of the mission. The project is performed as a cooperative effort between a group of Danish universities, institutions and industries active in space activities. TERMA Elektronik AS manages the project. 相似文献
49.
A high cycle fatigue reliability analysis approach to helicopter rotor hub is proposed under working load spectrum. Automatic calculation for the approach is implemented through writing the calculating programs. In the system, the modification of geometric model of rotor hub is controlled by several parameters, and finite element method and S-N curve method are then employed to solve the fatigue life by automatically assigned parameters. A database between assigned parameters and fatigue life is obtained via Latin Hypercube Sampling (LHS) on toler- ance zone of rotor hub. Different data-fitting technologies are used and compared to determine a highest-precision approximation for this database. The parameters are assumed to he independent of each other and follow normal distributions. Fatigue reliability is then computed by the Monte Carlo (MC) method and the mean-value first order second moment (MFOSM) method. Results show that the approach has high efficiency and precision, and is suit- able for engineering application. 相似文献
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