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1.
Mingying Huo Giovanni Mengali Alessandro A. Quarta 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(10):2617-2627
Propellantless continuous-thrust propulsion systems, such as electric solar wind sails, may be successfully used for new space missions, especially those requiring high-energy orbit transfers. When the mass-to-thrust ratio is sufficiently large, the spacecraft trajectory is characterized by long flight times with a number of revolutions around the Sun. The corresponding mission analysis, especially when addressed within an optimal context, requires a significant amount of simulation effort. Analytical trajectories are therefore useful aids in a preliminary phase of mission design, even though exact solution are very difficult to obtain. The aim of this paper is to present an accurate, analytical, approximation of the spacecraft trajectory generated by an electric solar wind sail with a constant pitch angle, using the latest mathematical model of the thrust vector. Assuming a heliocentric circular parking orbit and a two-dimensional scenario, the simulation results show that the proposed equations are able to accurately describe the actual spacecraft trajectory for a long time interval when the propulsive acceleration magnitude is sufficiently small. 相似文献
2.
A new paradigm is suggested for 3D magnetic reconnection where the interaction of reconnection processes with current aligned
instabilities plays an important role. According to the new paradigm, the initial equilibrium is rendered unstable by current
aligned instabilities (lower-hybrid drift instability first, drift-kink instability later) and the non-uniform development
of kinking modes leads to a compression of magnetic field lines in certain locations and a rarefaction in others. The areas
where the flow is compressional are subjected to a driven reconnection process. In the present paper we illustrate this series
of events with a selection of simulation results.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
3.
Tommaso Pino Christian Circi Giovanni Vulpetti 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(11):3675-3690
A good model of solar-radiation pressure induced thrust is one of the key points in sailcraft trajectory design. The sail membrane’s local topographic deformations, i.e. wrinkles and creases, are among the main aspects that such a model should include. We have analyzed the influence of wrinkles/creases, as a whole, by measuring the related deformations on small samples of sail membrane, 2.5?μm thick, consisting of CP1 and physical-vapor-deposition Aluminum. Experimental outcomes from our laboratory facility have been processed, statistically investigated, and inserted into the lightness vector formalism. We have used such formalism for accurate sailcraft trajectory computation via a non-ideal reflection sail thrust model. Finally, we computed the deviations of wrinkled-sail sailcraft final orbital states with respect to the no-wrinkle sail final orbital ones for a circular to circular 2D inward transfer. The radii of the orbits are 1?AU and the semi-major axis of Mercury, respectively. It appears that sail wrinkles and creases are no longer negligible in the sailcraft trajectory design. 相似文献
4.
Chiara Toglia Marco Sabatini Paolo Gasbarri Giovanni B. Palmerini 《Acta Astronautica》2011,68(7-8):1031-1041
Space graspers are complex systems, composed by robotic arms placed on an orbiting platform. In order to fulfil the manoeuvres’ requirements, it is necessary to properly model all the forces acting on the space robot. A fully nonlinear model is used to describe the dynamics, based on a multibody approach. The model includes the orbital motion, the gravity gradient, the aerodynamic effects, as well as the flexibility of the links. The present paper aims to design, thanks to nonlinear optimization algorithms, a class of manoeuvres that, given the same target to be grasped, are characterized by different mission objectives. The grasping mission can be performed with the objective to minimize the power consumption. Collision avoidance constraints can be also added when the target is equipped with solar panels or other appendices. In some cases, large elastic displacements should be expected, possibly leading to an inaccurate positioning of the end-effector. Therefore, different design strategies can require that the manoeuvre is accomplished with minimum vibrations’ amplitude at the end-effector. Performance of the different strategies is analyzed in terms of control effort, trajectory errors, and flexible response of the manipulator. 相似文献
5.
Giovanni Vulpetti 《Acta Astronautica》2011,68(5-6):644-650
This paper is the second one of a research line whereupon the variations of the total solar irradiance are explicitly included in a large high-precision computer code for sailcraft trajectory optimization. Sailcraft-Mars rendezvous has been chosen for studying such effects. It turns out that irradiance-fluctuation perturbations are large in this trajectory type. 相似文献
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7.
It is shown that the digital-data-transition tracking loop, previouslydevised using physical reasonings, is actually a practical implementation of an optimum (maximum likelihood) self-bit synchronizer. 相似文献
8.
Rita Betta Salvatore Orlando Giovanni Peres Salvatore Serio 《Space Science Reviews》1999,87(1-2):133-136
We use a time-dependent hydrodynamic model to study the dynamics of siphon flows triggered by differences of pressure or heat
deposition asymmetries between the two footpoints of a coronal loop. We show that steady pressure driven flows in a uniformly
heated loop are unstable, whereas those driven by asymmetries in the heating function may be stable. We also show that, in
these cases, relatively cool loops might be filled far above their static pressure scale height.
This revised version was published online in June 2006 with corrections to the Cover Date. 相似文献
9.
This paper presents a theory for computing the signal acquisition time of a second-order tracing system operating in the frequency-search mode. In particular, a closed-form expression is obtained which relates the acquisition time to the relevant system parameters, to the initial loop detuning, and to the slope of the ramp that sweeps the voltage-controlled oscillator. Although the theory is only approximate and the resulting formula is exact only in the limit when the initial loop detuning ?F goes to infinity, it has been found that it gives quite accurate results as soon as ?F is some times greater than the equivalent noise bandwidth of the loop. 相似文献
10.
Over the past 40 years, the Lunar Laser Ranging Program (LLRP) to the Apollo Cube Corner (CCR) Retroreflector Arrays (ALLRRA) [1] has supplied almost all of the significant tests of General Relativity. The LLRP has evaluated the PPN parameters, addressed the possible changes in the gravitational constant and the properties of the self-energy of the gravitational field. In addition, the LLRP has provided significant information on the composition and origin of the moon. This is the only Apollo experiment that is still in operation. Initially the ALLRRAs contributed a negligible fraction of the ranging error budget. Over the decades, the ranging capabilities of the ground stations have improved by more than two orders of magnitude. Now, because of the lunar librations, the existing Apollo retroreflector arrays contribute a significant fraction of the limiting errors in the range measurements.The University of Maryland, as the Principal Investigator for the original Apollo arrays, is now proposing a new approach to the Lunar Laser Array technology [2]. The investigation of this new technology, with Professor Currie as Principal Investigator, is currently being supported by two NASA programs and by the INFN-LNF in Frascati, Italy. Thus after the proposed installation during the next lunar landing, the new arrays will support ranging observations that are a factor 100 more accurate than the current ALLRRAs.The new fundamental cosmological physics and the lunar physics [3] that this new Lunar Laser Ranging Retroreflector Array for the 21st Century (LLRRA-21) can provide will be described. In the design of the new array, there are three major challenges: (1) validate the ability to fabricate a CCR of the required specifications, which is significantly beyond the properties of current CCRs, (2) address the thermal and optical effects of the absorption of solar radiation within the CCR, reduce the transfer of heat from the CCR housing and (3) validate an accurate emplacement technique to install the CCR package on the lunar surface. The latter requires a long-term stable relation between the optical center of the array and the deep regolith, that is, below the thermally driven expansion and contraction of the regolith during the lunar day/night cycle. 相似文献