Low-Thrust Fuel-Optimal Rendezvous Mission to Near Earth Asteroids

2013 ◽  
Vol 816-817 ◽  
pp. 778-781
Author(s):  
Hao Huang ◽  
Zhong Xing Tang ◽  
Chao Han
Keyword(s):  
Indirect Method ◽  
Pseudospectral Method ◽  
Initial Guess ◽  
Low Thrust ◽  
Earth Asteroid ◽  
Optimal Rendezvous ◽  
Near Earth Asteroids

Indirect method combined with homotopy approach is used to solve low-thrust fuel-optimal problem. To start the homotopy progress, pseudospectral method is used to solve energy-optimal problem to generate the initial guess. The proposed approach is applied to Earth to a near earth asteroid rendezvous mission. The performance of such approach is demonstrated through simulation.

scholarly journals Design Of Lunar-Gravity-Assisted Escape Trajectories

2020 ◽  
Vol 67 (4) ◽  
pp. 1374-1390
Author(s):  
Lorenzo Casalino ◽  
Gregory Lantoine
Keyword(s):  
Lunar Gravity ◽  
Gravity Assist ◽  
Analytical Treatment ◽  
Direct Optimization ◽  
Earth Asteroid ◽  
Combined Use ◽  
Escape Trajectories ◽  
Gravity Assists ◽  
Lunar Gravity Assist ◽  
Near Earth Asteroids

AbstractLunar gravity assist is a means to boost the energy and C3 of an escape trajectory. Trajectories with two lunar gravity assists are considered and analyzed. Two approaches are applied and tested for the design of missions aimed at Near-Earth asteroids. In the first method, indirect optimization of the heliocentric leg is combined to an approximate analytical treatment of the geocentric phase for short escape trajectories. In the second method, the results of pre-computed maps of escape C3 are employed for the design of longer Sun-perturbed escape sequences combined with direct optimization of the heliocentric leg. Features are compared and suggestions about a combined use of the approaches are presented. The techniques are efficiently applied to the design of a mission to a near-Earth asteroid.

scholarly journals The Near Earth Asteroid associations

2012 ◽  
Vol 10 (H16) ◽  
pp. 474-475 ◽  
Author(s):  
Tadeusz J. Jopek
Keyword(s):  
Cluster Analysis ◽  
Analysis Approach ◽  
Earth Asteroid ◽  
Extensive Search ◽  
The Earth ◽  
Near Earth Asteroids

AbstractWe have made an extensive search for grouping amongst the near Earth asteroids (NEAs). We used two D- functions and rigorous cluster analysis approach. We have found several new groups (associations) among the NEAs: the objects moving on similar orbits with small minimum orbital intersection distances (MOID) with the Earth trajectory. Reliability of some of these groups is quite high.

scholarly journals Radar reconnaissance of near-Earth asteroids

2006 ◽  
Vol 2 (S236) ◽  
pp. 143-150 ◽  
Author(s):  
Steven J. Ostro ◽  
Jon D. Giorgini ◽  
Lance A. M. Benner
Keyword(s):  
Physical Properties ◽  
Powerful Source ◽  
Earth Asteroid ◽  
Near Earth Asteroids ◽  
Source Of Information

AbstractRadar is a uniquely powerful source of information about near-Earth asteroid (NEA) physical properties and orbits. This review consists largely of edited excerpts from Ostro and Giorgini (2004).

scholarly journals Novel 3U Stand-Alone CubeSat Architecture for Autonomous Near Earth Asteroid Fly-By

Aerospace ◽  
2020 ◽  
Vol 8 (1) ◽  
pp. 9
Author(s):  
Stefano Casini ◽  
Iosto Fodde ◽  
Bert Monna ◽  
Angelo Cervone ◽  
Eberhard Gill
Keyword(s):  
Fast Growth ◽  
Small Satellite ◽  
Earth Asteroid ◽  
Performance Requirements ◽  
Component Selection ◽  
Space Industry ◽  
Commercial Off The Shelf ◽  
And Performance ◽  
Near Earth Asteroids ◽  
Scientific Return

The purpose of this work is to present a novel CubeSat architecture, aimed to explore Near Earth Asteroids. The fast growth in small satellite commercial-off-the-shelf technologies, which characterized the last decade of space industry, is exploited to design a 3U CubeSat able to provide a basic scientific return sufficient to improve the target asteroid dataset. An overview of the current available technologies for each subsystem is presented, followed by a component selection driven by the mission constraints. First a typical asteroid fly-by mission is introduced together with the system and performance requirements. Then each characterizing subsystem is critically analyzed, and the proposed configuration is presented, showing the mission feasibility within only 3.9 kg of wet mass and 385 m/s of total ΔV.

scholarly journals The Multiobjective Trajectory Optimization for Hypersonic Glide Vehicle Based on Normal Boundary Intersection Method

2016 ◽  
Vol 2016 ◽  
pp. 1-8 ◽  
Author(s):  
Zhengnan Li ◽  
Tao Yang ◽  
Zhiwei Feng
Keyword(s):  
Trajectory Optimization ◽  
Optimization Problem ◽  
Pseudospectral Method ◽  
Optimization Method ◽  
Initial Guess ◽  
Programming Algorithm ◽  
Trajectory Design ◽  
Normal Boundary ◽  
Vehicle Trajectory ◽  
Intersection Method

To solve the multiobjective optimization problem on hypersonic glider vehicle trajectory design subjected to complex constraints, this paper proposes a multiobjective trajectory optimization method that combines the boundary intersection method and pseudospectral method. The multiobjective trajectory optimization problem (MTOP) is established based on the analysis of the feature of hypersonic glider vehicle trajectory. The MTOP is translated into a set of general optimization subproblems by using the boundary intersection method and pseudospectral method. The subproblems are solved by nonlinear programming algorithm. In this method, the solution that has been solved is employed as the initial guess for the next subproblem so that the time consumption of the entire multiobjective trajectory optimization problem shortens. The maximal range and minimal peak heat problem is solved by the proposed method. The numerical results demonstrate that the proposed method can obtain the Pareto front of the optimal trajectory, which can provide the reference for the trajectory design of hypersonic glider vehicle.

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