不同载荷下瞬态放汽过程特性仿真

以美国某型弹射器为研究对象，建立蓄热器非平衡热力过程数学模型和基于牛顿定律和气体动力学的飞机力学模型，基于美军标实际数据进行了仿真验证。对不同飞机质量弹射过程进行动力学与热力学综合仿真研究，结果表明：当飞机质量为8、20、35 t时，弹射末速度均大于72 m/s，弹射最大加速度均小于6g，弹射时间均小于3 s；飞机质量越大，蓄热器放汽质量越多，蓄热器最终压力越小，开槽汽缸压力下降越缓慢，开槽汽缸漏汽质量越多

Transient simulation of steam discharge with differeat load

The mathematical model of non-equilibrium thermal process of steam accumulator and the mechanics model of aircraft based on Newton's law and gas dynamics for some thermal system was established. Based on the test date, the simulation result was tested and verified. The kinetic and thermodynamic comprehensive simulation of the steam process for different carrier-based aircraft mass was analyzed. The results was showed as follows:when the mass of the aircraft is 8, 20, 35 t, the end speed of aircraft is bigger than 72 m/s, the maximum acceleration is less than 6g and the time of catapult is less than 3 s. With the aircraft mass becoming greater, the steam discharging mass becomes larger, the end pressure of steam accumulator becomes lower,as while the down rate of the pressure of cylinder is small and the leaking quality of cylinder is bigger.