摘要
针对液氧煤油运载火箭对箭上设备高功重比的苛刻要求,提出液动机引流式伺服机构的能源系统优化设计方法,建立液压能源和伺服作动器的联合仿真模型,计算得到满足典型工作剖面性能要求的动力组件设计参数和蓄能器的最小排油容积,建立极限工作温度范围内的蓄能器工作状态转移模型,计算满足最小排油容积的充气压力和最大容积的数值解集合,通过绘制二维平面图判断得到最优解。类似地,建立包含低温和蓄能器气体泄漏在内的极限工况的油箱工作状态转移模型,计算得到满足工作要求的油箱有效容积、油箱加注油面和蓄能器充气容积的数值解集合,通过绘制三维图判断得到最优解,获取了满足各极限工况应用需求的能源系统设计参数。此方法利用数值计算方法,解决了能源系统的优化设计问题,确保了新型液氧煤油运载火箭伺服机构的高功重比设计。
To meet the high power-to-weight ratio requirements of on-board devices in Liquid Oxygen-kerosene Launch Vehicles,a parameters optimization design method for the hydraulic motor driven power system of the servo-mechanisms is proposed. A simulation model that combines the hydraulic power and the servo actuator is built to derive the minimum oil-discharging volume of the accumulator and the design parameters of the power elements, which satisfy the performance specification in typical operation profiles. A state transfer model is further built for the accumulator operating in the specified temperature scope, to derive the valid numerical solution set to the gas-charging pressure and the total volume that satisfy the above minimum oil-discharging volume, and an optimal solution can be easily judged by drawing a two-dimension graph. Similarly, a state transfer model is built for the reservoir operating in the operation limits, such as minimum temperature and accumulator failure,to derive the valid numerical solution set to the effective reservoir volume, the filling reservoir volume, and the gas-charging accumulator volume, and as well an optimal solution can be easily judged by drawing a three-dimension graph. The design parameters of energy system are obtained to meet the application requirements of each extreme working condition. The design approach provides a practical and effective parameter optimization method by a numerical solution and ensured the high power-to-weight ratio of the servo-mechanisms of our new generation Launch Vehicles.
引文
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