توجه: محتویات این صفحه به صورت خودکار پردازش شده و مقاله‌های نویسندگانی با تشابه اسمی، همگی در بخش یکسان نمایش داده می‌شوند.
۱Missiles Weapon Systems Identification and Design Based On Trajectory Waypoints via Genetic Algorithm
نویسنده(ها):
اطلاعات انتشار: سیزدهمین کنفرانس سالانه مهندسی مکانیک، سال
تعداد صفحات: ۸
One mission of the Defense Industry Research Center (DIRC) is the identification of foreign missile weapon systems. In the past, intuition and repeated runs of a missile performance model were required to converge to a solution compatible with observed flight characteristics. This approach can be time–consuming, as well as being subject to undesirable influences from the analyst’s biases. An alternative approach has been created to apply Genetic Algorithm (GA) techniques to allow automation of the process, wider exploration of the design space, and more optimal solutions matching the observational data. The GA, when interfaced with a missile performance model, was able to identify a set of missiles that very closely matched the observed performance of a given sample missile. The approach was able to provide the analyst with multiple candidate missiles for further analysis that would have been missed by the previous trial and error approach.<\div>

۲Evaluation of Airplane Image Quality Using Neural Networks
نویسنده(ها):
اطلاعات انتشار: چهاردهمین کنفرانس سالانه مهندسی مکانیک، سال
تعداد صفحات: ۱۲
We discuss the use of neural networks as an evaluation tool for the graphical algorithms to be used in training simulator visual systems. The results of a number of trial evaluation studies are presented in summary form, including the ‘calibration’ exercises that have been performed using human subjects.<\div>

۳Optimization of Cruise Missile Wing Airfoil Using Genetic Algorithm
نویسنده(ها):
اطلاعات انتشار: چهاردهمین کنفرانس سالانه مهندسی مکانیک، سال
تعداد صفحات: ۸
Airfoil design is very important for cruise missile performance, stability and control. Many optimization algorithms have been applied to airfoil shape design, but the use of local optimization tools like Gradient–Based methods may risk missing the best designs. The objective of this paper is to explore issues for global optimization of missile airfoil shapes in the transonic flow region by comparing a genetic algorithm with Gradient–Based optimization method. To determine the local optimum characteristics of the airfoil shape design space, different airfoil shapes are used as base or starting airfoils. The results showed that the GA generated nearly the same shape regardless of the different initial base airfoils, which suggests that these shapes are approaching the global optimum. Comparisons of the generated airfoil shapes, the airfoil shapes performance, and the computational effort expended as a result of the GA and GB methods are presented.<\div>

۴OPTIMAL INPUT DESIGN for Mig–29 FLIGHT TEST VALIDATION
نویسنده(ها):
اطلاعات انتشار: چهاردهمین کنفرانس سالانه مهندسی مکانیک، سال
تعداد صفحات: ۱۳
A technique for designing optimal inputs for aerodynamic parameter estimation was flight tested on the MIG–29 High Angle of Attack Research Aircraft (HARA). Model parameter accuracies calculated from flight test data were compared on an equal basis for optimal input designs and conventional inputs at the same flight condition. In spite of errors in the a priori input design models and distortions of the input form by the feedback control system, the optimal inputs increased estimated parameter accuracies compared to conventional 3–2–1–1 and doublet inputs. In addition, the tests using optimal input designs demonstrated enhanced design flexibility, allowing the optimal input design technique to use larger input amplitude to achieve further increases in estimated parameter accuracy without departing from the desired flight test condition. This work validated the analysis used to develop the optimal input designs, and demonstrated the feasibility and practical utility of the optimal input design technique.<\div>

۵Airplane Engine Failures Estimation Based On Kalman Filtering
نویسنده(ها):
اطلاعات انتشار: چهاردهمین کنفرانس سالانه مهندسی مکانیک، سال
تعداد صفحات: ۸
Airlines periodically collect engine data in order to evaluate the failure of the engine components. Kalman filters are often used to estimate the state variables of a dynamic system like an airplane engine. However, in the application of Kalman filters some known signal information is often either ignored or dealt with heuristically. For instance, state–variable constraints (which may be based on physical considerations) are often neglected because they do not fit easily into the structure of the Kalman filter. This paper develops an analytic method of incorporating state–variable inequality constraints in the Kalman filter. The resultant filter is a combination of a standard Kalman filter and a quadratic programming problem. The incorporation of state–variable constraints increases the computational effort of the filter but significantly improves its estimation accuracy. The improvement is proven theoretically and shown via simulation results obtained from application to a turbofan engine model. This model contains 16 state variables, 12 measurements, and 8 component health parameters. It is shown that the new algorithms provide improved performance in this example over unconstrained Kalman filtering.<\div>

۶Conceptual Design of Missile Guidance and Control via Six–Degree of Freedom Simulation
نویسنده(ها):
اطلاعات انتشار: چهاردهمین کنفرانس سالانه مهندسی مکانیک، سال
تعداد صفحات: ۱۱
A hardware control system framework is presented for both real–time and batch six–degree–of–freedom simulation. This framework allows stabilization and control with multiple command options, from body rate control to waypoint guidance. Also, Autopilot commands can be used to operate the simulation in a hardware in–the–loop environment. This control system framework is created by using direct missile state feedback with nonlinear dynamic inversion. A direct control allocation scheme is used to command missile effectors. Online B –matrix estimation is used in the control allocation algorithm for maximum algorithm flexibility. Primary uses for this framework include conceptual design and early preliminary design of missile, where missile models change rapidly and knowledge of missile six–degree–of–freedom performance is required. A simulated airbreathing hypersonic cruise missile and a simulated high performance air to air missile are controlled to demonstrate the flexibility and utility of the control system.<\div>
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