Sharif Digital Repository

The collision of moderately large asteroids and comets also referred to as Near-Earth Objects (NEO's) with earth would have catastrophic consequences. Such events have occurred in the past and may occur again in the future. However, for the first time in known history, humanity may have the technology required to counter this threat. Methods studied for mitigation of this hazard are based on deflecting asteroid's trajectory and are normally divided into two basic categories: high energy impulsive methods, and long-duration low-thrust methods. Two parts of mission to be optimized are the trajectory of spacecraft to reach the target and the deflection strategy which could be analyzed by the... 

Chaotic and resonant Dynamics of full two body problem are investigated through the sphere-ellipsoid and ellipsoid-ellipsoid models. The fourth-order mutual gravitational potential function is derived in terms of the first-order moment of inertia for both models. Employing Hamiltonian formulation and elliptical expansion, the resonant angles appear in the equations which include secondary’s attitude and mean anomaly for sphere-ellipsoid model and attitude of both bodies and mean anomaly for ellipsoid-ellipsoid model. In first step, resonances overlapping criteria is applied to the first-order resonances of sphere-ellipsoid model and the effect of the asphericity and orbital eccentricity on... 

The aim of this project is to design an optimal mission for the Apophis asteroid hazardous rendezvous problem using continuous thrusters. The simulation time was considerably reduced using a suitable modeling of the time process. Meanwhile, numerical analyzing of the dynamical model reduced the escape phase simulation time. The gravity of the Earth, Moon, Sun and five other major planets was exploited in the escape and heliocentric phases, respectively and the results were compared with those of the two body problem. Also, the mission start and flight time together with initial mass in the park orbit were optimized. It was shown that the Sun and the Moon effects in the escape phase led to an... 

In this thesis, the optimal trajectories of a spacecraft in the binary asteroids system is studied. The objective functions of optimal trajectories in these system are the maximum coverage of the asteroids surface and minimum time and fuel consumption. For this purpose, the dynamic of binary system is modeled. The binary system of 1999 KW4 is selected as a case study. The ellipsoid-sphere model is a good approximation for the case of this study. In this model, the asteroids orbit in a circular orbit around each other in a spin-spin-orbit resonance configuration, in which the asteroids’ rotational velocity is equal to orbital mean motion. Then, the equations of motion of the spacecraft as the... 

In this work the problem of optimal spacecrafts reconfiguration and formation keeping is investigated for Asteroid attraction. Due to potential impact probability of the Apophis asteroid with Earth in 2036, the study is focused on optimal intercept avoidance via gravity attraction of multiple spacecrafts suitably arranged on halo orbits of Apophis. In this regard, a space mission is defined in which initially several spacecrafts are optimally reconfigured onspecial Halo orbits of the asteroid via several techniques that include pseudospectral, linear quadratic regulator as well as the integral sliding mode control. The utility of three methods is for verification purposes as well as... 

Studying of binary asteroids because of achieving data of existence sources in the world persuades to investigate about tethered satellite formation around binary asteroids in future missions. About 20 percent of asteroids around the sun are binary asteroids. It is going to analyse dynamics of tethered satellite around Didymos binary asteroid. Light mass of the asteroid is good reason to consider gravitational harmonic perturbation, and leads to attention about solar radiation pressure depends on distance in modelling of the dynamical system. It will be zonal harmonics up to second order and sectoral. Satellites are such a particle as an assumption; that is why attitude motion of satellites... 

This dissertation investigates the Multiple-Horizon Multiple-Model Predictive Control method and its application in soft landing problem on an irregular-shaped asteroid. In this way, a predictive framework including a heuristic guidance law named Predictive Path Planning and Multiple-Horizon Multiple-Model Predictive Control (MHMM-PC) as the control scheme is introduced for soft landing on an asteroid. Obviously, reducing the fuel consumption is a priority in space missions. Thus, the employed control framework should minimize the required control effort. Furthermore, the control method should be robust enough to deal with the effects of model uncertainties and disturbances. The unique...