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The main goal of this paper is to analyze the flutter boundary and dynamic load of a supersonic fin. Reduced order mode (ROM) based on Volterra Series is presented to calculate the flutter boundary, and CFD/CSD coupling is used to compute the transient aerodynamic load. The Volterra-based ROM is obtained using the derivative of unsteady aerodynamic step-response, and the infinite plate spline is used...
This paper presents a method for constructing flow fields with proper orthogonal decomposition (POD) basis functions or modes with great reduction on the computational cost. Using this approach, it is possible to construct the entire aerodynamic flow fields from the knowledge of computed aerodynamic data or measured flow data specified on the aerodynamic surfaces, demonstrating a way to effectively...
Space rendezvous is the foundation of space operation and application. In this paper, mission planning of long distance guidance stage for space rendezvous is discussed. Two-impulse rendezvous is solved by analyzing Gauss problem. Based on Battin-Vaughan algorithm, ergodic calculation is performed for different combination of initial position and transfer time. To carry out the mission planning for...
The purpose of this paper is to develop a spacecraft collision warning expert system and apply to the spacecraft collision avoidance maneuver framework. Evasive maneuvering is one of key techniques for spacecraft actively protect. The warning system is an important part in the spacecraft collision avoidance maneuver framework. Expert system is a very successful approximate solution to the classic...
The main goal of present paper is to construct an efficient reduced order model (ROM) for unsteady aerodynamic force modeling. Balanced Truncation (BT) is presented to address the problem. For conventional BT method, it is necessary to compute exact controllability and observability grammians. Although it is relatively straightforward to compute these matrices in a control setting where the system...
The main objective of this paper is to numerically investigate the effects of a divert jet on the overall aerodynamic performance of a generic interceptor missile operating at moderate angle attack. A generic missile interceptor configuration consisting of a long, slender body containing tail fins is simulated in this study. Firstly, K-epsiv, K-omega and S-A turbulent model are evaluated in simulating...
Presented is an investigation into Advection Upstream Splitting Method (AUSM) family schemes. A newly improved version of the AUSM scheme, called AUSMPW+, was developed to increase the accuracy and computational efficiency of AUSM scheme in capturing oblique shock without compromising robustness. With a new definition of the numerical speed of sound at a cell interface, the ability of capturing an...
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