检索结果-内蒙古大学图书馆

Resonant Control of Satellite Orbits

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2021年第12期44卷 2126-2142页

作者： Nie, Tao Gurfil, Pini Technion Israel Inst Technol Fac Aerosp Engn IL-32000 Haifa Israel

Low-thrust orbit control has been widely studied, mostly by using direct or indirect optimization to detect time-optimal and fuel-optimal orbit transfers. This paper proposes an alternative approach for designing efficient low-thrust orbit transfers. The main idea is to create an artificial resonance between the period of the control accelerations and a characteristic period of the orbital dynamics. To that end, Gauss's variational equations are written using a Fourier series expansion in the mean anomaly. The secular changes of the orbital elements are determined based on averaging theory. It is shown that an artificially created low-thrust resonance can save fuel compared with piecewise-constant thrust. A general resonant-control candidate for changing all mean orbital elements efficiently is proposed. Four simple decoupling control laws are designed for changing the semimajor axis, eccentricity, inclination, and right ascension of the ascending node separately. In addition, periodic corrections transforming between mean elements and osculating elements are derived. The proposed decoupling control laws are applied to a formation-keeping problem, illustrating the potential merit of the new control law compared with a fixed-thrust-magnitude feedback control.

关键词： Earth Satellites Highly Eccentric Orbit Feedback Control Right Ascension Orbital Eccentricity Fuel Consumption Numerical Simulation open loop controller Electric Propulsion Perturbation Theory

来源：评论

学校读者我要写书评

暂无评论

Quaternion-Based Bang-Bang Attitude Stabilizer for Rotating Rigid Bodies

引用

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2017年第6期40卷 1523-+页

作者： Serpelloni, Edoardo Maggiore, Manfredi Damaren, Christopher J. Univ Toronto Elect & Comp Engn Dept Toronto ON M5S 2J7 Canada Univ Toronto Inst Aerosp Studies Toronto ON M5S 2J7 Canada

The hybrid feedback is modified so as to take full advantage of the quaternion parametrization of the spacecraft attitude. The controller achieves practical stabilization of the spacecraft attitude assuming the full nonlinear dynamics of the spacecraft, while avoiding chattering and high-frequency switching of the actuators. An extensive Monte Carlo numerical analysis indicates that the result might be global. the attitude controller is the first bang-bang feedback controller with guaranteed stability properties and guaranteed bounded switching frequency, even in the presence of measurement noise.

关键词： Quaternions Attitude Stabilization open loop controller Hysteresis Spacecraft Attitude Rigid Spacecraft Pulse Width Modulation Bang Bang Control Spacecraft Configurations State Space Systems

来源：评论

学校读者我要写书评

暂无评论

Fuel optimal propulsive maneuver of an experimental structure exhibiting spacelike dynamics

引用

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1996年第1期19卷 141-149页

作者： Meyer, JL Silverberg, L North Carolina State Univ. Raleigh

The implementation of four fuel-optimal methods for propulsive maneuver of space structures is described. Toward this end, an experimental structure that possessed spacelike dynamics was fabricated and used to test the previously mentioned fuel optimal methods. The results given highlight the differences among fuel optimal methods for propulsive maneuver of space structures, their relative strengths and weaknesses, and the sources of errors.

关键词： Fuels Large Space Structures open loop controller Vibration Suppression Time Optimal Control Stiffness Matrices Power Spectral Density Data Acquisition Strain Gauge Out of Plane Maneuvers

来源：评论

学校读者我要写书评

暂无评论

AEROASSISTED ORBITAL MANEUVERING USING LYAPUNOV OPTIMAL FEEDBACK-CONTROL

引用

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1989年第2期12卷 237-242页

作者： LEE, B GRANTHAM, WJ Washington State University Pullman Washington

For advanced space transportation systems, such as the National Aerospace Plane or the Orbital Transfer Vehicle, the use of aeroassisted orbital transfer from a high Earth orbit to a low Earth orbit will require an optimizing closed-loop feedback controller, not only to achieve significant fuel savings, but also to compensate for large, unpredictable fluctuations in atmospheric density. The authors present a Lyapunov optimal function minimizing feedback control algorithm incorporating a preferred direction of motion at each state of the system, opposite to the gradient of a specified "descent function." Lyapunov optimal feedback control is compared to an approximate minimum-fuel calculus of variations open-loop optimal control algorithm based on the 1962 U.S. Standard Atmosphere.

关键词： Elliptical Orbit Feedback Control open loop controller Flight Path Angle Space Transportation System Characteristic Velocity Perigee Lift Coefficient Earth Boundary Value Problems

来源：评论

学校读者我要写书评

暂无评论

Modeling and Natural Mode Analysis of Tethered Multi-Aircraft Systems

引用

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2021年第6期44卷 1199-1210页

作者： Sanchez-Arriaga, Gonzalo Serrano-Iglesias, Jose Antonio Leuthold, Rachel Diehl, Moritz Carlos III Univ Madrid Bioengn & Aerosp Engn Dept Ave Univ 30 Leganes 28911 Spain Univ Freiburg Syst Control & Optimizat Lab Dept Microsyst Engn Georges Kohler Allee 102 D-79110 Freiburg Germany Univ Freiburg Dept Math Georges Kohler Allee 102 D-79110 Freiburg Germany

Two complementary simulators aimed at the dynamic analysis of airborne wind energy systems based on multi-aircraft configurations are presented. The first model considers a train of stacked aircraft linked among them by two inelastic and massless tethers with no aerodynamic drag. The architecture of the mechanical system in the second simulator is configurable, as long as the system is made of a set of aircraft linked by an arbitrary number of elastic tethers. In both cases, the aircraft are modeled as rigid bodies and the controller is incorporated in the aerodynamic torque through the deflections of control surfaces. An analysis of the symmetric equilibrium state and the corresponding natural modes of a train (stacked configuration) of aircraft was carried out. It revealed that the higher the position of the aircraft in the train, the more they participate in the modes. Tether inertial and aerodynamic drag effects increase the equilibrium angles of attack of the aircraft and the tether tension at the attachment points. The potential applications and computational performance of the two codes are discussed.

关键词： Aircraft Systems Aerodynamic Force Coefficients Airborne Wind Energy Control Surfaces Aircraft Configurations Dynamic Analysis Young's Modulus Training Aircraft Angle of Attack open loop controller

来源：评论

学校读者我要写书评

暂无评论

COVARIANCE CONTROL DESIGN FOR HUBBLE-SPACE-TELESCOPE

引用

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1995年第2期18卷 230-236页

作者： ZHU, GM GRIGORIADIS, KM SKELTON, RE PURDUE UNIV SCH AERONAUT & ASTRONAUTW LAFAYETTEIN 47907

To improve the response to unexpected thermally induced disturbances, two new controllers are designed for the Hubble Space Telescope (HST) using covariance control techniques. The first controller minimizes the required control effort subject to inequality constraints on the output covariance matrix. The second controller is designed to satisfy both output covariance constraints and controller covariance constraints. The importance of the controller covariance constraint is to properly scale the controller for digital implementation in the control computer using fixed-point arithmetic. We provide a technique to integrate modeling, control design, and signal processing (in HST's fixed-point control computer), since these problems are not separable. Covariance control can easily ac commodate the roundoff error and computational time delay. Compared with the existing HST controller design, the results show that the required pointing error specifications can be achieved with 85% less control effort and that the error due to the finite-wordlength implementation of the controller can easily be included in the optimal control design process.

关键词： Hubble Space Telescope Signal Processing Linear Quadratic Gaussian open loop controller Mathematical Models Reaction Wheels Cost Analysis Damping Coefficient Data Simulation Flexible Structures

来源：评论

学校读者我要写书评

暂无评论

ONLINE ANALYSIS CAPABILITIES DEVELOPED TO SUPPORT THE ACTIVE FLEXIBLE WING WIND-TUNNEL TESTS

引用

JOURNAL OF AIRCRAFT 1995年第1期32卷 39-44页

作者： WIESEMAN, CD HOADLEY, ST MCGRAW, SM NASA Langley Research Center Hampton Virginia 23681 Lockheed Engineering and Sciences Company Inc. Hampton Virginia 23666

A variety of on-line analysis tools were developed to support two active flexible wing (AFW) wind-tunnel tests. These tools were developed to verify control law execution, to satisfy analysis requirements of the control law designers, to provide measures of system stability in a real-time environment, and to provide project managers with a quantitative measure of controller performance. Descriptions and purposes of capabilities that were developed are presented in this article along with examples. Procedures for saving and transferring data for near real-time analysis. and descriptions of the corresponding data interface programs are also presented. Although much of the on-line analysis capabilities described herein are not technically new, the implementation for near real-time analysis to verify and evaluate controller performance is new, and is included in this special Journal if Aircraft issue for completeness in describing the AFW mind-tunnel testing. The on-line analysis tools worked well before, during, and after the wind-tunnel tests, and proved to be a vital and important part of the entire test effort.

关键词： Flexible Wings Wind Tunnel Models open loop controller Strain Gauge Time Domain Analysis Control Surfaces Dynamic Pressure Central Processing Unit Data Acquisition MATLAB

来源：评论

学校读者我要写书评

暂无评论

Predictive guidance for pursuit-evasion engagements involving multiple decoys

引用

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2007年第5期30卷 1277-1286页

作者： Dionne, D. Michalska, H. Rabbath, C. A. Lockheed Martin Canada Res & Dev Dept Quebec City PQ H4P 1K6 Canada McGill Univ Dept Elect Engn Montreal PQ H3A 2A7 Canada Def Res & Dev Canada Valcartier Quebec City PQ G3J 1X5 Canada McGill Univ Dept Mech Engn Montreal PQ H3A 2A7 Canada

A guidance law is developed for situations in which the pursuer's command is 1) conditioned on a multimodal probability density function of the target state, and 2) constrained by a bounded control effort. The novel law adopts a predictive control approach with two horizons: a fixed cost horizon, and a receding control horizon. The law performs a first optimization over the fixed cost horizon to deliver a novel control constraint. This control constraint is then employed in a new open-loop optimization procedure to deliver a piecewise-constant open-loop controller that is optimal over the receding control horizon. When the density function is unimodal, the novel law is proven to be equivalent to other approaches in feedback with the average of the density function (i.e., the minimum mean square error estimate, as suggested by the certainty equivalence principle), or the maximizer of the density function (i.e., the maximum a posteriori probability estimate). In an example engagement scenario with decoys, the novel law demonstrates a higher probability of interception than comparable laws in feedback with the minimum mean square error or maximum a posteriori probability estimates.

关键词： Guidance Laws open loop controller Probability Density Functions Kalman Filter Optimal Control Monte Carlo Simulation Power Spectral Density Proportional Navigation Cost Control Heading Angle

来源：评论

学校读者我要写书评

暂无评论

Rocket nozzle flow control using a reduced-order computational fluid dynamics model

引用

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2002年第3期25卷 449-454页

作者： Lucia, DJ Pachter, M Beran, PS USAF Inst Technol Dept Aeronaut & Astronaut Wright Patterson AFB OH 45433 USA USAF Inst Technol Dept Elect Engn Wright Patterson AFB OH 45433 USA USAF Res Lab Air Vehicles Directorate Wright Patterson AFB OH 45433 USA

The use of proper orthogonal decomposition-based reduced-order computational fluid dynamics models for multidisciplinary optimization are investigated. An open-loop optimal control problem is solved concerning the regulation of a rocket engine thrust profile. The control synthesis uses a numerical flowfield solver as the plant model. controllers are synthesized using both the full-order nonlinear fluid dynamics, which serves as a truth model, and a reduced-order model of the flowfield generated via proper orthogonal decomposition. The latter has been successfully applied to reduce the order of both steady and unsteady subsonic flowfield solutions obtained via computational fluid dynamics. Specifically, the application of reduced-order flowfield solvers to a rocket's thrust controller design is explored. A quasi-one-dimensional supersonic convergent-divergent nozzle with varying backpressure is used as a model problem. Treating the nozzle flow as one-dimensional, the reduced-order model is used to synthesize a nonlinear controller that controls thrust by varying nozzle throat area along an ascent trajectory. The performance of the reduced-order controller is quantified.

关键词： CFD Rocket Nozzle Flow Convergent Divergent Nozzles Rocket Engine Propellant open loop controller Chemical Rocket Optimization Algorithm Euler Equations Total Energy

来源：评论

学校读者我要写书评

暂无评论

Unified Velocity Control and Flight State Transition of Unmanned Tilt-Wing Aircraft

引用

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2017年第6期40卷 1348-1359页

作者： Hartmann, Philipp Meyer, Carsten Moormann, Dieter Rhein Westfal TH Aachen Inst Flight Syst Dynam D-52062 Aachen Germany

This paper presents an approach for velocity control of tilt-wing aircraft over their entire flight envelope, ranging from hovering flight to wing-borne flight. With their capability of vertical takeoff and landing operation in combination with efficient cruise flight, tilt-wing aircraft offer multiple benefits in unmanned aerial vehicle applications. Control of tilt-wing aircraft, in particular for fully automated flight, is challenging because along with their versatility comes significant variations in flight mechanics characteristics. Known approaches to this problem subdivide tilt-wing flight into discrete aircraft configurations. The presented control concept omits discrete configurations and instead allows for continuous flight state transitions over a unified flight configuration space. Actuation that is unique to tilt-wing aircraft, for example, tilt angle control, is not only used as an aircraft configuration parameter but also as a full-fledged motion control device. The concept includes a map-based feedforward controller to maintain trimmed straight-lined flight and uses virtual control devices for motion control independent of the flight state. Flight state transitions are conducted along state trajectories that are defined deterministically and safely with respect to flight envelope limitations. The controller is implemented for an unmanned tilt-wing demonstrator and evaluated in flight. Compared to prior results, velocity response is considerably improved.

关键词： VTOL Aircraft Aircraft Configurations Flight Envelope open loop controller Aircraft Flight Mechanics Unmanned Aircraft VTOL Flight Testing Control Surfaces Fixed Wing Aircraft

来源：评论

学校读者我要写书评

暂无评论

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案：

请选择收藏分类：

通借通还

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：