Yoonhyuk Choi

Collision Avoidance Using Linear Quadratic Control in Satellite Formation Flying

This paper proposes a linear system control algorithm with collision avoidance in multiple satellites. Consideration of collision avoidance is augmented by adding a weighting term in the cost function of the original tracking problem in linear quadratic control (LQC). Because the proposed algorithm relies on a similar solution procedure to the original LQC, its inherent advantages, including gain-robustness and optimality, are preserved. To confirm and visualize the derived algorithm, a simple example of two-vehicle motion in the two-dimensional plane is illustrated. In addition, the proposed collision avoidance control is applied to satellite formation flying, and verified by numerical simulations.

Terrain Aided Inertial Navigation for Precise Planetary Landing

This study investigates Terrain Aided Inertial Navigation(TAIN) which consists of Inertial Navigation System (INS) with the optical sensor for precise planetary landing. Image processing is conducted to extract the feature points between measured terrain data and on-board implemented terrain information. The navigation algorithm with Iterated Extended Kalman Filter(IEKF) can compensate for the navigation error, and provide precise navigation information compared to single INS. Simulation results are used to demonstrate the feasibility of integration to accomplish precise planetary landing. The proposed navigation approach can be implemented to the whole system coupled with guidance and control laws.

Kalman Filtering for Spacecraft Attitude Estimation by Low-Cost Sensors

In this paper, fine attitude estimation using low-cost sensors for attitude pointing missions of spacecraft is addressed. Attitude kinematics and gyro models including bias models are in general utilized to estimate spacecraft attitude and angular rate. However, a linearized model and a transition matrix are derived in this paper from nonlinear spacecraft dynamics with external disturbances. A Kalman filtering technique is applied and offers relatively high estimation accuracy under dynamic uncertainties. The proposed approach is demonstrated using numerical simulations.

Impulsive Control of Satellite Formation Flying using Orbital Period Difference

Abstract This paper is mainly concerned with impulsive control of satellite formation flying using orbital period difference. Gausss Variational Equation is used as a main equation and corresponding six orbital elements represent satellite status. Schaub and Alfriends three-impulse algorithm constitutes a basic algorithm of this paper. In three-impulse algorithm, required impulses are determined by orbit element difference between current and desired orbit. Among orbit element difference, mean anomaly difference is an only time-varying term, and it comes from orbital period difference. In this paper, we analytically derive an impulse time which minimizes required impulse magnitude using orbital period difference, based on three-impulse algorithm. In addition, considering a case when proposed delayed impulse maneuver is not useful, alternative impulse maneuver is suggested. Finally, simulation studies are presented with artificial mission examples.

Efficient Control Torque Distribution Approach for Spacecraft Attitude Control

Two methods are proposed to maximize torque distribution efficiency for low capability reaction wheel assembly. First, to find the solution with a constraint, a weighted control allocation strategy is suggested instead of general control allocation method called pseudoinverse. The second method is proposed to enlarge torque capacity during maneuvers by determination of initial wheel angular momentum. Two approaches are applied to large angle maneuvers of satellite for improvement of control performance, and possibility for application to actual satellite system(STSAT-3) is demonstrated by numeric simulations.

Mechanism Modeling and Analysis of Deployable Satellite Antenna

Large number of SAR(Synthetic Aperture Radar) satellites, one type of earth observation satellite, have been developed as they have the advantage of not being affected by surrounding environment during the earth image acquisition. In order to gain high image quality, SAR antenna should have large diameter. However, internal space of satellite launch vehicle is limited and this leads SAR antenna to be designed deployable so that it can be folded in launch vehicle and unfolded in space. In this research, values of various design factors of deployable satellite antenna were chosen considering satellite`s target mission. Configuration of deployable satellite antenna was designed by applying the chosen values of design factors, and variation in deployable satellite antenna during satellite maneuver was observed through simulation.

Spacecraft Attitude Estimation by Unscented Filtering

Spacecraft attitude estimation using the nonlinear unscented filter is addressed to fully utilize capabilities of the unscented transformation. To release significant computational load, an efficient technique is proposed by reasonably removing correlation between random variables. This modification introduces considerable reduction of sigma points and computational burden in matrix square-root calculation for most nonlinear systems. Unscented filter technique makes use of a set of sample points to predict mean and covariance. The general QUEST(QUaternion ESTimator) algorithm preserves explicitly the quaternion normalization, whereas extended Kalman filter(EKF) implicitly obeys the constraint. For spacecraft attitude estimation based on quaternion, an approach to computing quaternion means from sampled quaternions with guarantee of the quaternion norm constraint is introduced applying a constrained optimization technique. Finally, the performance of the new approach is demonstrated using a star tracker and rate-gyro measurements.

통신해양기상위성의 영상위치유지 성능평가 프로그램 개발 및 분석

이 연구는 통신해양기상위성의 영상위치유지 (Image Navigation and Registration, INR) 시스템의 시뮬레이션을 위한 프로그램을 개발하고, 영상오차보상(Image Motion Compensation, IMC) 알고리즘의 성능을 비교분석 하였다. 통신해양기상위성 궤도와 자세 요소를 모델링 하고 궤도오차와 자세오차를 계산하여 이러한 궤도 및 자세오차가 영상왜곡에 미치는 영향을 분석하였다. 또한 영상오차보상을 하지 않았을 경우와 GOES 위성의 영상오차보상 알고리즘을 적용하였을 경우, 그리고 선행 연구를 통해 개발되었던 개량된 영상오차보상 알고리즘을 적용하였을 경우의 영상들을 비교하여 각 알고리즘의 성능을 확인하였다. 개량된 영상오차보상 알고리즘은 GOES위성의 알고리즘보다 효율적으로 영상왜곡을 보상하였다. 이러한 연구는 통신해양기상위성의 INR시스템을 효과적으로 운용하고 그 성능을 향상시킬 수 있는 기술적 토대를 마련하는데 기여할 것이다. 【We developed a software for simulations and analyses of the Image Navigation and Registration (INR) system, and compares the characteristics of Image Motion Compensation (IMC) algorithms for the INR system. According to the orbit errors and attitude errors, the capabilities of the image distortions are analyzed. The distortions of images can be compensated by GOES IMC algorithm and Modified IMC (MIMC) algorithm. The capabilities of each IMC algorithm are confirmed based on compensated images. The MIMC yields better results than GOES IMC although both the algorithms well compensate distorted images. The results of this research can be used as valuable asset to design of INR system for the Communication, Ocean, Meteorological Satellite (COMS).】

Coordinated Simultaneous Attitude Pointing for Multiple Satellites Under Formation Flying

In this paper, attitude control laws for simultaneous pointing of multiple spacecrafts are considered under a formation flying scenario. The basic approach lies in adaptive feedback gains using relative attitude information or maneuver time approximation for coordinated attitude control. Each control law is targeted to balancing mean motion or to correcting system response to the slowest satellite. The control gain adaptation is constructed by two approaches. The first one is using variable damping gain to manipulate speed of a fast system response, and the second one uses alternate natural frequency of the system under control. The validity and stability of the proposed approaches are examined analytically and tested through numerical simulations.

Spacecraft Attitude Determination Study using Predictive Filter

Predictive filter theory proposed recently can be characterized by inherent advantages of estimating modelling error and overcoming the disadvantage of the Kalman filter theory. A one-step ahead error is minimized to produce optimized filter performance in the form of the predictive filter. The main advantage of this filter lies in the ability to estimate both state vector and system model error. In this paper, attitude estimation results based upon the predictive filter theory is addressed. Mathematical formulation for estimating bias signal is peformed by using the predictive filter theory, and attitude estimation based upon vector observation is presented. From the results of this study, the potential applicability of the predictive filter is highlighted.