Titlebook: Astrodynamics Network AstroNet-II; The Final Conference Gerard Gómez,Josep J. Masdemont Conference proceedings 2016 Springer International

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书目名称Astrodynamics Network AstroNet-II影响因子(影响力)




书目名称Astrodynamics Network AstroNet-II影响因子(影响力)学科排名




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书目名称Astrodynamics Network AstroNet-II网络公开度学科排名




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书目名称Astrodynamics Network AstroNet-II年度引用学科排名




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书目名称Astrodynamics Network AstroNet-II读者反馈学科排名

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An Efficient Sub-optimal Motion Planning Method for Attitude Manoeuvres,ions) is shaped by a polynomial, determined by matching prescribed boundary conditions and the manoeuvre time. This method allows constraints such as limits on velocity, acceleration, jerk, and torque to be evaluated via inverse dynamics. Pointing constraints are also considered. A spin-to-spin case

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Unconventional Solar Sailing,r has considered only a limited number of sail configurations. However solar sails do not have to be inertially-pointing squares, spin-stabilised discs or heliogyros: there is a range of different configurations and concepts that present some advantageous features. This chapter will show and discuss

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Communicate

Artificial Equilibria in the RTBP for a Solar Sail and Applications,Solar Radiation Pressure (SRP). The system has a family of “artificial” equilibrium points parameterised by the orientation of the sail. We show how to use the information on the natural dynamics of the system to navigate around the family of equilibrium points in a controlled way.

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Terminal Entry Phase Trajectory Generator for Reusable Launch Vehicles,e vehicle has to glide at low Mach to reach the point close to the runway where automatic approach and landing starts. The algorithm presented here is based on the concept of Energy Corridor management and it is composed of two main elements: a trajectory propagator and a ground track generator. Imp

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Two ASRE Approaches with Application to Spacecraft Coulomb Formations,equence of Riccati Equations (ASRE) methods. In the ASRE methods, the nonlinear problem is reduced to a sequence of linear-quadratic and time-varying approximating problems. For this purpose, the nonlinear equations are written in State Dependent Coefficient (SDC) factorization form. Two different A

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Novel Approach on the Optimisation of Mid-Course Corrections Along Interplanetary Trajectories,optimal with respect to propellant usage, within a two-body problem context. If the conditions are not satisfied, one or more potential intermediate impulses are performed along the transfer arc, in order to lower the overall cost. The method is based on the propagation of the state transition matri

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Vision-Based Navigation Around Small Bodies,on scenario is based on the latest guidelines for the ESA’s Phobos Sample Return mission (until recently known as Phootprint) and the focus of the presented research is placed on the body relative navigation methods that are applicable for use around asteroids and small moons. In particular, detaile