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Innovative Navigation Guidance and Control Technology for Mars Entry Descent and Landing

Author: PengYuMing
Tutor: LiShuang
School: Nanjing University of Aeronautics and Astronautics
Course: Navigation,Guidance and Control
Keywords: Mars Enter, fall and landing Navigation MRAC Neural Network Sliding Mode Variable Structure Control
CLC: V448.2
Type: Master's thesis
Year: 2011
Downloads: 172
Quote: 3
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Abstract


The current follows the Viking mission to Mars mission developed during the first generation of Mars EDL navigation, guidance and control, that is based on recursive navigation AVIC-bit mode and no lift control ballistic reentry way that leads to placement error ellipse radius of the order of hundreds of kilometers, unable to meet future Mars sample return mission and manned landing on the landing accuracy requirements. Therefore, it is necessary to develop a new generation of Mars EDL navigation, guidance and control techniques in order to achieve Mars precision landing. In this paper, precision landing of Mars exploration mission as the background, from the high-precision EDL navigation, trajectory optimization and guidance control three aspects of departure for the next generation of Mars EDL navigation, guidance and control technology for the in-depth study, the main research contents include: First, to analyze probe devices throughout the flight dynamics of the process, through reasonable assumptions and approximations were established Mars enters segment, descending and landing segment kinetic model for the back of the navigation, guidance and control system is designed to provide the necessary mathematical models . Secondly, based on the traditional IMU dead reckoning navigation accuracy is not high, the error accumulated over time this problem, this paper develops Mars EDL external measurement sensor / IMU integrated navigation system. Into segments using the orbiter and terrestrial radio beacon and probe for measurement and communication way to fix the error of inertial navigation, integrated navigation simulation results show that the accuracy of recurrence compared Navigational have increased significantly and substantially free from radio measurement disruptions . Descending height speedometer miniature combination with IMU navigation, although horizontal position status is not impressive, but still overcome the shortcomings of inertial navigation error divergence. Landing section of the navigation accuracy requirements are higher, so the falling section navigation sensor based on the increase with the navigation camera is used to estimate the level of movement. Then, enter the segment and landing segments of the nominal trajectory of advance planning. In this paper, trajectory optimization process fully considered the Mars probe limited ability to control this problem, a better solution to the trajectory of the nominal trajectory when the real difference is too large may occur due to control saturation can not track the nominal trajectory situation. Meanwhile, in the nominal trajectory optimization performance index added sensitivity to the state of uncertainty, and in the nearly optimal performance without changing the original while effectively reducing the atmospheric density, the detector status uncertain factors on the terminal state effects, thereby improving the control precision. Finally, in order to effectively overcome the uncertainty parameters on the adverse effects of guidance and control systems, according to the CGT-based direct adaptive control theory designed Mars enters adaptive guidance control law; kinetic model for the access segment exists unmodeled dynamics design issues the sliding mode controller and neural network nonlinear approximation ability good line estimation system uncertainties, so that guidance and control system has strong robustness.

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CLC: > Aviation, aerospace > Aerospace ( Astronauts ) > Space instrument,spacecraft devices,spacecraft guidance and control > Guidance and Control > Spacecraft guidance and control
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