Computer Science
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.509s&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Computer Science
Scientific paper
system, solid rocket motor and control system must be examined jointly many times during the course of the flexible nozzle study. With the aim of acquiring the responses of flexible to different excitation, there is much experiment to be done. Those different excitation signals are accomplished when different forces applied to the supports in divergent section. While the deformation of the nozzle, especially the deformation of supports ,which attach control system to divergent section, relates directly to control problems. During the course of thrust vector control, the forces are applied in the shape of stronger impact force. In the condition of excitation force applied, the better we know about deformation of the divergent section, especially the local deformation of the supports in the divergent section, the more control is accurate. In fact, all control is accomplished in dynamic state. The information of swing angle not only includes displacement in the condition of control force applied but also includes velocity and acceleration where control force applied. Only all that deformation and deformation process are comprehend comprehensively, can control efficiency and control accuracy be improved. in which the flexible joint is simply treated as distributed spring. With finite element method, the dynamic responses of the flexible nozzle model is studied in condition of dynamic load applied in finite element method. The dynamic response Results are presented in this paper when triangular wave excitation, sine wave Excitation and arc sine wave excitation applied. displacement of sine wave and arc sine wave lag 0.025s than maximal load. Velocity response has also the property lagging than load, which is little than displacement hysteresis effect. Maximal velocity lag 0.005s than maximal load. in the condition of above three sorts load applied, acceleration response shows obvious property of oscillating. These results can play important in flexible nozzle structure design. Key words: flexible nozzle, dynamic response,finite element method
Hou Xiao
Shi Hongbin
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