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Energy-Optimal Waypoint-Following Guidance for Gliding-Guided Projectiles |
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Qiulin Yin, Qi Chen, Zhongyuan Wang(NanJing University of Science and Technology, China) |
| This paper addresses the problem of energy-optimal way-point-following guidance for Long-Range
Gliding-Guided projectiles with the consideration of velocity variation. This proposed guidance law is derived
as a solution of a linearized kinematics model. The algorithm integrates path planning and following into a
single step and can be applied to a general waypoint-following mission. Nonlinear numerical simulations clearly
demonstrate the effectiveness and superiority of the proposed formulations. |
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Integrated Inertial and Radio Based State and Parameter Estimation for Mars Entry Phase Spacecraft Navigation |
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Natnael Zewge, Hyochoong Bang(KAIST, Korea) |
| We address the entry phase navigation of Entry, Descent, and Landing (EDL) operation for future Mars spacecraft missions. The entry phase is characterized by a highly non-linear motion model and is influenced by various aerodynamic forces. Current entry phase navigation systems exclusively use Inertial Measurement Units (IMUs) from atmospheric entry to parachute deployment phase. This results in large error accumulation. Such systems cannot meet the precision landing requirements of future missions. We present an integrated navigation scheme using radio and IMU to give greatly enhanced navigation accuracy. We validate our method through extensive simulations using EKF and UKF. |
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An Instantaneous Impact Point Guidance for Rocket with Aerodynamics Control |
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Ki-Wook Jung(Korea Advanced Institute of Science and Technology, Korea), Chang-Hun Lee(KAIST, Korea), Junseong Lee, Sunghyuck Im, Keejoo Lee(Korea Aerospace Research Institute, Korea), Marco Sagliano, David Seelbinder(DLR Institute of Space Systems, Germany) |
| This paper aims to propose a new guidance algorithm for a rocket with aerodynamics control for launch operations, based on the concept of the instantaneous impact point (IIP). In this study, the rocket with aerodynamics control is considered with the purpose of reducing dispersion of the impact point after separation of the rocket for safety reasons. The proposed guidance algorithm is derived directly from the underlying principle of the guidance process: forming the collision geometry towards a target point. The key feature of the proposed guidance algorithm lies in its simple implementation and exact collision geometry nature. |
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The Influence of Trajectory Design Parameters on Miss Distance and Survivability of Anti-ship Missiles |
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Bui Quoc Dung(Le Quy Don Technical University, Viet Nam) |
| In this paper, we synthesize the sinusoidal biased proportional navigation guidance law for enhancing the survivability of anti-ship missiles against the interception of anti-air missiles. A closed-form solution for the command acceleration of the proposed guidance law is derived. The simulation is implemented based on the homing loop model which consists of the canonical fifth-order binomial dynamics and the proposed guidance law. The simulation results show that the magnitude, frequency, and time constants greatly influence the miss distance and survivability of the anti-ship missiles. |
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Nonlinear Three-Loop Autopilot Design for Spaceplanes |
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Dain Yoon(Korea Advanced Institute of Science and Technology, Korea), Chang-Hun Lee(KAIST, Korea) |
| This paper deals with the nonlinear autopilot design for spaceplanes based on the three-loop autopilot architecture. To this end, the nonlinear dynamics equations for spaceplanes during the reentry phase are first determined. The dynamic characteristics of the dynamics model are then investigated. The analysis results show that the time-scale separation is valid in the autopilot design for spaceplanes. Accordingly, based on the approximation of the time-scale separation, the proposed autopilot is designed by leveraging the feedback linearization control technique in conjunction with specific forms of the desired error dynamics. |
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