作者: 評論性 時間: 2025-3-21 22:45
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作者: 健談的人 時間: 2025-3-22 01:58 作者: 貿易 時間: 2025-3-22 08:14
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作者: 改革運動 時間: 2025-3-22 11:21 作者: Communicate 時間: 2025-3-22 16:15
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.作者: 減去 時間: 2025-3-22 18:50
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作者: 航海太平洋 時間: 2025-3-22 22:37
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作者: 貪心 時間: 2025-3-23 02:54
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作者: 允許 時間: 2025-3-23 08:54
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作者: sed-rate 時間: 2025-3-23 10:28 作者: 小口啜飲 時間: 2025-3-23 14:59
,A Note on Dynamics About the Coherent Sun–Earth–Moon Collinear Libration Points,tudy both situations in the framework of a single, coherent model, the Hill restricted four-body problem. This model is presented in a Sun–Earth rotating reference frame to complement its earlier Earth–Moon frame formulation. We provide an overview of the planar quasi-periodic orbits that originate 作者: 歡笑 時間: 2025-3-23 18:15
The Trojan Problem from a Hamiltonian Perturbative Perspective,Starting from a representation of the Elliptic Restricted 3-Body Problem in terms of modified Delaunay variables, we propose a sequence of canonical transformations leading to a Hamiltonian decomposition in the three degrees of freedom (fast, synodic and secular). From such a decomposition, we intro作者: 我不死扛 時間: 2025-3-23 22:53 作者: 危險 時間: 2025-3-24 06:07
Formation Flying Guidance for Space Debris Observation, Manipulation and Capture,n-depth discussion of robotic arm based capture of debris. Guidance aspects of active debris removal missions are discussed. Mission phases for active debris removal missions are rendezvous, inspection, attitude synchronization and capture and de-tumbling. The need for attitude synchronization is dr作者: 歌曲 時間: 2025-3-24 09:56
Low Thrust Relative Motion Control of Satellite Formations in Deep Space,onsidered. A family of artificial Halo orbits with the same periods, around the .. and .. Lagrange points in the Earth-Sun system is found using the pseudo-arc-length continuation method. The orbits are used are reference trajectories for satellites to track. The problem of orbit stability, bounding作者: FLACK 時間: 2025-3-24 13:39
Efficient Modelling of Small Bodies Gravitational Potential for Autonomous Proximity Operations, Recent developments in on-board navigation paved the way for autonomous proximity operations. The missing elements for achieving this goal are a gravity model, simple enough to be easily used by the spacecraft to steer itself around the asteroid, and guidance laws that rely on a such an inherently 作者: Phagocytes 時間: 2025-3-24 17:08
Sun-Earth L1 and L2 to Moon Transfers Exploiting Natural Dynamics,der to assess the feasibility of future disposal or lifetime extension operations. With an eye to the probably small quantity of propellant left when its operational life has ended, the spacecraft leaves the libration point orbit on an unstable invariant manifold to bring itself closer to the Earth 作者: anthropologist 時間: 2025-3-24 22:06 作者: Commodious 時間: 2025-3-25 00:13
Formulating Poorly Water Soluble Drugspolynomials) is addressed, and a method for analytically estimating the minimum time of a manoeuvre is proposed. The method requires low computational capacity, and a comparison with optimal control solutions shows its relative performance.作者: Engaged 時間: 2025-3-25 04:18
Susanne Page,Reto Maurer,Nicole Wyttenbachies are estimated, among which the ‘halo’ orbits. Analytical results are compared with the numerical ones existing in the literature. Initial conditions for generating halos are found inverting this analytical process.作者: Hyaluronic-Acid 時間: 2025-3-25 10:49
https://doi.org/10.1057/9781137509857formations are considered. Suboptimal trajectories of formation attitude and relative position of a two-craft formation utilizing coulomb forces as well as thrusters is discussed. The effectiveness of the approaches as well as their comparison is demonstrated through numerical simulations.作者: ESPY 時間: 2025-3-25 14:42
https://doi.org/10.1057/9781137509888 smooth control performance is applied for formation flying of small spinning spacecraft while considering gravity gradient torques for the attitude dynamics. The performance of the formation flying is numerically demonstrated.作者: 的染料 時間: 2025-3-25 19:12
The EFT System and Regulatory Framework,uced to obtain suitable conditions that can be targeted such that the spacecraft impacts, or is weakly captured by, the Moon. Weak capture at the Moon is studied by method of these maps. Some results for planar Lyapunov orbits at .. and .. are given, as well as some results for the operational orbit of SOHO.作者: 裝入膠囊 時間: 2025-3-25 20:04
Leveraging Discrete Variational Mechanics to Explore the Effect of an Autonomous Three-Body Interacl as the corresponding natural parameters. Shape characteristics and structural changes are explained using the stability and existence of equilibrium points, enabling exploration of the effect of an additional three-body interaction and conditions for reproducibility in a natural gravitational environment.作者: 退出可食用 時間: 2025-3-26 02:32 作者: Supplement 時間: 2025-3-26 06:41 作者: consent 時間: 2025-3-26 10:56
Two ASRE Approaches with Application to Spacecraft Coulomb Formations,formations are considered. Suboptimal trajectories of formation attitude and relative position of a two-craft formation utilizing coulomb forces as well as thrusters is discussed. The effectiveness of the approaches as well as their comparison is demonstrated through numerical simulations.作者: 窒息 時間: 2025-3-26 15:56 作者: Canvas 時間: 2025-3-26 18:55 作者: 凌辱 時間: 2025-3-26 23:47
1570-6591 nference at the end of a Marie-Curie Research Training Netwo.These are the proceedings of the "AstroNet-II International Final Conference". This conference was one of the last milestones of the Marie-Curie Research Training Network on Astrodynamics "AstroNet-II", that has been funded by the European作者: chronicle 時間: 2025-3-27 02:08 作者: Inferior 時間: 2025-3-27 08:11 作者: anchor 時間: 2025-3-27 10:47 作者: 拋棄的貨物 時間: 2025-3-27 14:45 作者: Hyperopia 時間: 2025-3-27 21:30 作者: Morbid 時間: 2025-3-27 23:05
Terminal Entry Phase Trajectory Generator for Reusable Launch Vehicles, based on the concept of Energy Corridor management and it is composed of two main elements: a trajectory propagator and a ground track generator. Imposing a dynamic pressure profile as function of the altitude, a heading path is selected in order to steer the vehicle toward the runway, putting to zero cross and down track errors.作者: Locale 時間: 2025-3-28 05:54
,A Note on Dynamics About the Coherent Sun–Earth–Moon Collinear Libration Points,ing reference frame to complement its earlier Earth–Moon frame formulation. We provide an overview of the planar quasi-periodic orbits that originate from the .. and .. Lyapunov periodic orbits in Hill’s problem and the circular restricted three-body problem. The role of resonances is also discussed.作者: 闖入 時間: 2025-3-28 07:07 作者: 索賠 時間: 2025-3-28 12:53 作者: 載貨清單 時間: 2025-3-28 14:54
Low Thrust Relative Motion Control of Satellite Formations in Deep Space,seudo-arc-length continuation method. The orbits are used are reference trajectories for satellites to track. The problem of orbit stability, bounding and controlling the relative motion by means of nonlinear control is addressed.作者: 潰爛 時間: 2025-3-28 19:15 作者: 衰弱的心 時間: 2025-3-29 02:54
Conference proceedings 2016arch Training Network on Astrodynamics "AstroNet-II", that has been funded by the European Commission under the Seventh Framework Programme..The aim of the conference, and thus?this book,?is to communicate work on astrodynamics problems?to an international and specialised audience. The?results are?p作者: 防止 時間: 2025-3-29 03:28
Conference proceedings 2016bility of spacecraft and formation flying..The book addresses a readership across the traditional boundaries between mathematics, engineering and industry by offering an interdisciplinary and multisectorial overview of the field..作者: 一起平行 時間: 2025-3-29 10:38
John N. Williams,Eric W. K. Tsangmponents. The out-of-plane component is solved analytically while for the in-plane ones a Hamiltonian approximation is made.The novel procedure reduces the mathematical complexity and the computational cost of Lawden’s problem and gives also a different perspective about the optimisation of a transfer trajectory.作者: 象形文字 時間: 2025-3-29 12:07
Novel Approach on the Optimisation of Mid-Course Corrections Along Interplanetary Trajectories,mponents. The out-of-plane component is solved analytically while for the in-plane ones a Hamiltonian approximation is made.The novel procedure reduces the mathematical complexity and the computational cost of Lawden’s problem and gives also a different perspective about the optimisation of a transfer trajectory.作者: Gossamer 時間: 2025-3-29 18:34
Vision-Based Navigation Around Small Bodies,d analysis of absolute navigation with reference to the body surface is performed. The results section contains analysis of the positioning accuracy achieved by the presented algorithms on a set of images generated using PANGU software.作者: Pelago 時間: 2025-3-29 22:11 作者: membrane 時間: 2025-3-30 01:56
Formulating Poorly Water Soluble Drugsions) 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作者: intelligible 時間: 2025-3-30 05:27 作者: 膽大 時間: 2025-3-30 08:15 作者: Inertia 時間: 2025-3-30 14:38 作者: Adrenal-Glands 時間: 2025-3-30 17:21
Brian Fitzgerald,Debra HowcroftSolar 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.作者: 火光在搖曳 時間: 2025-3-30 21:46
John N. Williams,Eric W. K. Tsange 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作者: analogous 時間: 2025-3-31 04:42 作者: Mercantile 時間: 2025-3-31 06:27
John N. Williams,Eric W. K. Tsangoptimal 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作者: HEPA-filter 時間: 2025-3-31 11:52 作者: Redundant 時間: 2025-3-31 15:45
https://doi.org/10.1057/9781137509888ropellant. They can be used for missions studying astrophysics, heliophysics and planetary science. A formation flying system using solar radiation pressure is presented in this paper. The proposed formation flying mission uses sails due to the limited volume and power of small spacecraft. Station k作者: VOC 時間: 2025-3-31 17:44
Katja Zolper,Daniel Beimborn,Tim Weitzeltudy both situations in the framework of a single, coherent model, the Hill restricted four-body problem. This model is presented in a Sun–Earth rotating reference frame to complement its earlier Earth–Moon frame formulation. We provide an overview of the planar quasi-periodic orbits that originate 作者: AWE 時間: 2025-4-1 00:24 作者: ATRIA 時間: 2025-4-1 05:49 作者: 真 時間: 2025-4-1 08:31
An Integrated Multi-Disciplinary Approach,n-depth discussion of robotic arm based capture of debris. Guidance aspects of active debris removal missions are discussed. Mission phases for active debris removal missions are rendezvous, inspection, attitude synchronization and capture and de-tumbling. The need for attitude synchronization is dr作者: Predigest 時間: 2025-4-1 13:25
https://doi.org/10.1007/978-3-540-72047-8onsidered. A family of artificial Halo orbits with the same periods, around the .. and .. Lagrange points in the Earth-Sun system is found using the pseudo-arc-length continuation method. The orbits are used are reference trajectories for satellites to track. The problem of orbit stability, bounding作者: Junction 時間: 2025-4-1 16:13
https://doi.org/10.1007/978-3-540-72047-8 Recent developments in on-board navigation paved the way for autonomous proximity operations. The missing elements for achieving this goal are a gravity model, simple enough to be easily used by the spacecraft to steer itself around the asteroid, and guidance laws that rely on a such an inherently 作者: nutrition 時間: 2025-4-1 22:10
