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在给定温度和加速度的条件下,用8次导轨试验的结果确定0.7-ES-6400(MK29 Mod 0)火箭发动机的动力性能。规定温度为-54℃,+21℃,+63℃的0.7-ES-6400火箭发动机放在专门设计的导轨滑撬上,并在海军武器试验室的158.5米的导轨上点火。用试验滑撬的结构重量控制燃烧结束时的速度,并由此建立要求的加速度和作用到发动机上相应的惯性力。在沿滑轨运动期间,8次发动机试验均经受了15～18g的平均加速度。发动机都成功地经受住了负担的过载,没有引起燃烧室的破裂和药柱的破碎。测得的性能数据与计算估计的数据很吻合。由达些试验结果可以推断:在温度为-54～+63℃,受到15～18g的加速度条件下,0.7-ES-6400(MK29 Mod 0)火箭发动机将满意地工作。可认为,发动机能承受在导轨上发射时所引起的横向与侧向颤震。对于使用像海军武器试验室的158.5米的短而速度为中等的导轨设备,推进系统需具备的特点是:发动机燃烧时间短,推力中等人小,以及推进剂重量与总重之比高。
The power performance of the 0.7-ES-6400 (MK29 Mod 0) rocket motor was determined using the results of eight rail tests given the temperature and acceleration conditions. The 0.7-ES-6400 rocket engine, rated at -54 ° C, +21 ° C and + 63 ° C, was placed on a specially designed guide rail and ignited on a 158.5-meter rail in the Naval Weaponry Laboratory. The structural weight of the test skid controls the speed at the end of the combustion and thus establishes the required acceleration and the corresponding inertial force acting on the engine. Eight engine tests all experienced an average acceleration of 15 to 18 g during movement along the slide. The engine successfully survived the overload of the load without rupturing the combustion chamber and breaking the pellets. The measured performance data is in good agreement with the estimated data. From the results of some experiments, it can be deduced that the 0.7-ES-6400 (MK29 Mod 0) rocket engine will work satisfactorily under the temperature of -54 ~ + 63 ℃ and acceleration of 15 ~ 18g. It can be considered that the engine can withstand lateral and lateral tremors caused when it is launched on a rail. For a short, medium-speed rail system that uses a 158.5 meter space like the Naval Weaponry Laboratory, the propulsion system must have features such as short engine burn times, low thrust, and a high ratio of propellant weight to gross weight.