I would like for a fuzzy sliding mode controller to be developed that will position three satellites in a linear constellation and then align broadside to a stationary object for transmitting and receiving capabilities. The fuzzy sliding mode controller in this thesis paper [p.30] I believe will work ([login to view URL]) at the bottom of the paper a source code is given so it can be modified and tested.
The actuators I would prefer to use are 3 magnetorquers per satellite. This thesis paper has modeled 3 magnetorquers, 1 for each x,y,z axis ([login to view URL]) again at the bottom is source code to recreate this. The inertia matrix needs to be changed to a CubeSat.
This paper contains the type of satellite I would like to be modelled and shows the sensor and actuator modeling. Refer to Table 1: Magnetorquer Parameters to determine the max control torque that can be generated by the magnetorquers.([login to view URL]) and includes on [p.12] the simulation information with inertia matrix = [.002 .002 .002]kgm2. This paper includes a model for the magnet sensor, magnetometer, which needs to be modeled in the plant of the system.
The position estimates of the CubeSat will be provided by a StarTracker. This paper shows how the StarTracker can generate quaternion coordinates, and it shows how the extended Kalman filter (EKF) can remove the noise from the quaternion coordinates.([login to view URL]) I would like to have a plot showing the quaternion coordinates for all three satellites with noise generated by the StarTracker device and another plot showing the extended kalman filter successfully removing the noise so the quaternions can be used as accurate attitude information.
Please see this for a matlab script of an extended kalman filter ([login to view URL])
Please see this for matlab examples of satellite orbits modeled ([login to view URL])
Please see this for matlab script of determining position, velocity, and acceleration between the satellites ([login to view URL]) I think this will be useful to check if they are aligned linearly, i.e. the velocity's and acceleration will be the same and the position will be aligned on one of the axis in order to be linear.
please see the following links for the CubeSat parts talked about in the papers.
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** A thruster can be used if for some reason the magnetorquers don't provide enough control. [login to view URL]
I have attached my proposal for the design. I would like a simulink model for the overall system and plots that prove the satellites are aligned in a linear fashion and broadside to a stationary object while meeting the requirements of not exceeding control power available. The settling time is not of real importance, this is mainly a power and accuracy constraint. The key plots are the quaternion coordinates of all three satellites which will show their constellation becoming linearized and stabilized, this will yield them all having the same velocity and acceleration once they are in proper formation, and the control input that the sliding fuzzy controller generates being a feasible torque value that the magnetorquer explained above can provide. Please document any matlab scripts for easy readability and label all simulink blocks.
17 freelanceri licitează în medie 2345$ pentru acest proiect
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Hi Michael I saw this job post on [login to view URL] too and we did some discussion there too. I can help you out in this job. Do you have any reference paper which can give a complete picture of your idea. Hope to hear fr Mai multe
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I have worked orbit propagation and satellite positioning algorithms during my master's thesis. I also have experience in Simulink. We can further discuss about the project. thanks
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