Based on the structural characteristics of solid-annular aerospike nozzle,a thrust vector control scheme by means of the deflection of gas rudders was proposed.Utilizing Fluent simulation calculations,a method for calculating the axial thrust of the aerospike nozzle was presented.The influence of the gas rudder design and working factors on the thrust vector performance of the aerospike nozzle was investigated.The results indicate that shifting the axial position of the gas rudder rearward enhances the distur-bing effect of the rudder on the gas,so as to increase the thrust vector angle and lateral force.However,there is approximately 1.12%of thrust loss.Increasing the deflection angle of the gas rudder leads to significant changes of vector angle.A gas rudder deflection from 0° to 20° results in a change of the vector angle by 5.46° with a maximum thrust loss of 3.24%.The work height of the aero-spike nozzle significantly affects the vector performance.Beyond a certain altitude,gas inundates the rudder surface,weakening the disturbance effect and resulting in a notable decrease in thrust vector angle compared to ground conditions.To achieve the optimal thrust vector control scheme for the aerospike nozzle gas rudder,it is necessary to comprehensively consider design criteria,working conditions,and structural dimension constraints,perform finetuning and optimization of the gas rudder parameters.
aerospike nozzlethrust vectorgas rudderssolid rocket motor
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