منابع مشابه
Fuel-Optimal Spacecraft Rendezvous with Hybrid On–Off Continuous and Impulsive Thrust
J = cost function N = number of impulses NLT = number of low-thrust-independent thrusters p = primer-vector magnitude p = primer vector pm = primer-vector absolute maximum r = relative position vector rj = space collocation of the jth impulse tf = final time tint = intermediate time tj = time instant of the jth impulse application tm = midcourse time corresponding to the primer absolute maximum...
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Autonomous spacecraft rendezvous is an enabling technology for many future space missions, but anomalies in recent flight experiments suggest that safety considerations will play a critical role in mission success. This paper presents a method for online generation of safe, fuel-optimized rendezvous trajectories that guarantee passive collision avoidance for a large class of anomalous system be...
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We here approach the problem of designing a controller for automatic rendezvous and docking (AR&D). As a first step towards a fully reactive neurocontroller (based on state feedback), an artificial neural network is trained offline by a fitness based genetic algorithm to fulfill the docking task. Its performance using one specific docking case, with fixed initial and boundary conditions, is com...
متن کاملThe Laser Rangefinder on the near Earth Asteroid Rendezvous Spacecraft
In 1999, the Near Earth Asteroid Rendezvous (NEAR) mission will place a spacecraft with five facility instruments, including the NEAR Laser Rangefinder (NLR), into a low-altitude (-50 km) orbit about the asteroid 433 Eros. The NLR is a high-fidelity altimeter capable of 3 1.5cm resolution and c2-m accuracy, and will be operate-d continuously while at Eros. The NLR design is quite robust and is ...
متن کاملRobust H∞ Control for Spacecraft Rendezvous with a Noncooperative Target
The robust H(∞) control for spacecraft rendezvous with a noncooperative target is addressed in this paper. The relative motion of chaser and noncooperative target is firstly modeled as the uncertain system, which contains uncertain orbit parameter and mass. Then the H(∞) performance and finite time performance are proposed, and a robust H(∞) controller is developed to drive the chaser to rendez...
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ژورنال
عنوان ژورنال: Journal of the Japan Society for Aeronautical and Space Sciences
سال: 1991
ISSN: 0021-4663
DOI: 10.2322/jjsass1969.39.91