火箭推进

为了研究预冷空气涡轮火箭发动机(PATR)的最大状态(最大推力和最大比冲状态)控制规律,建立了PATR的稳态变工况模型,研究了控制量对发动机性能参数的影响特性,给出了在总氢流量一定的前提下,发动机的最优性能状态(推力和比冲同时达到最大)控制规律,在此基础上进一步分别得到了发动机的最大推力状态和最大比冲状态的控制规律,并分别给出了发动机处于最大推力状态和最大比冲状态下的飞行包线。结果表明:当总氢流量一定时,PATR发动机的推力和比冲将随主燃室温度、氦涡轮入口温度、尾喷管喉部面积的增加而增大; 给定总氢流量下的PATR发动机的最优性能状态控制规律为:核心机余气系数之和等于1、氦涡轮入口温度、尾喷管喉部面积分别取得最大值,此时发动机的推力和比冲同时达到最大,发动机处于最优性能状态; 当主燃室温度、氦涡轮入口温度、尾喷管喉部面积一定时,推力随总氢流量的增加而增大,比冲与之相反; PATR发动机的最大推力状态控制规律为核心机余气系数之和等于1、氦涡轮入口温度、尾喷管喉部面积分别取得最大值,并要尽可能地增加总氢流量; PATR发动机的最大比冲状态控制规律为核心机余气系数之和等于1、氦涡轮入口温度、尾喷管喉部面积分别取得最大值,并要尽可能地减小总氢流量。

In order to study the control law of the maximum state(the maximum thrust state and the maximum specific impulse state)of the pre-cooling air turbine rocket engine(PATR), a steady state variable condition model of PATR was established, and the influence of the control parameter on the performance parameters of the engine was studied.The optimal performance state(maximum thrust state and specific impulse state at the same time)of the engine was given on the premise that the total hydrogen flow rate is proposed.On this basis, the control laws of the maximum thrust state and the maximum specific impulse state of the engine were proposed, and the flight envelope of the engine in the maximum thrust state and the maximum specific impulse state were given, respectively.The results show that the thrust of PATR engine will increase with the increase of main combustion chamber temperature, helium turbine inlet temperature and nozzle throat area when the total hydrogen flow rate is constant.When the temperature of the main combustion chamber, the inlet temperature of the helium turbine and the throat area of the nozzle are constant, the thrust increases with the increase of the total hydrogen flow.The optimal performance state control law of PATR engine with given total hydrogen flow rate is as follows: the sum of the residual gas coefficient of the precombustion chamber and the main combustion chamber is equal to 1, the inlet temperature of the helium turbine and the throat area of the tail nozzle get the maximum value, and the thrust and specific impulse of the engine reach the maximum at the same time, and the engine is in the optimal performance state.The maximum thrust state control rules of the PATR engine are as follows.The sum of the residual gas coefficient of the precombustion chamber and the main combustion chamber is equal to 1, the maximum value of the inlet temperature of the helium turbine and the throat area of the tail nozzle are obtained respectively.The total hydrogen flow rate should be increased as far as possible, when the total hydrogen flow rate is increased, the engine will touch the air compressor conversion speed or the maximum pressure boundary of the helium circuit.Safety boundary contact order is determined by engine characteristics and flow conditions.The maximum specific impulse state control law of PATR engine is as follows. The sum of the residual gas coefficient of the precombustion chamber and the main combustion chamber is equal to 1, the maximum of the inlet temperature of the helium turbine and the throat area of the tail nozzle are obtained, and the total hydrogen flow rate should be reduced as far as possible, when the total hydrogen flow rate is reduced, the engine will touch the surge boundary of the air compressor or the maximum temperature boundary of the precooler material.Safety boundary contact sequence is also determined by engine characteristics and incoming flow conditions.

引言
1 PATR发动机变工况模型
2 PATR发动机控制特性
3 PATR发动机最大状态控制规律
4 结论

图1 PATR发动机系统原理图<br/>Fig.1 Schematic diagram of PATR engine system

图1 PATR发动机系统原理图
Fig.1 Schematic diagram of PATR engine system

图2 发动机参数随主燃室氢流量的变化<br/>Fig.2 Variation of engine parameters with temperature of main burner

图2 发动机参数随主燃室氢流量的变化
Fig.2 Variation of engine parameters with temperature of main burner

图3 发动机性能参数随主燃室氢流量的变化<br/>Fig.3 Variation of performance parameters with hydrogen flow in main burner

图3 发动机性能参数随主燃室氢流量的变化
Fig.3 Variation of performance parameters with hydrogen flow in main burner

图4 发动机参数随氦涡轮入口温度的变化<br/>Fig.4 Variation of engine parameters with inlet temperature of helium turbine

图4 发动机参数随氦涡轮入口温度的变化
Fig.4 Variation of engine parameters with inlet temperature of helium turbine

图5 发动机性能参数随预燃室氢流量的变化<br/>Fig.5 Variation of performance parameters with hydrogen flow in preburner

图5 发动机性能参数随预燃室氢流量的变化
Fig.5 Variation of performance parameters with hydrogen flow in preburner

图6 发动机参数随尾喷管喉部面积的变化<br/>Fig.6 Variation of engine parameters with nozzle throat area

图6 发动机参数随尾喷管喉部面积的变化
Fig.6 Variation of engine parameters with nozzle throat area

图7 发动机性能参数随尾喷管喉部面积的变化<br/>Fig.7 Variation of performance parameters with nozzle throat area

图7 发动机性能参数随尾喷管喉部面积的变化
Fig.7 Variation of performance parameters with nozzle throat area

图8 发动机参数随总氢流量的变化<br/>Fig.8 Variation of engine parameters with total hydrogen flow

图8 发动机参数随总氢流量的变化
Fig.8 Variation of engine parameters with total hydrogen flow

图9 发动机性能参数随总氢流量的变化<br/>Fig.9 Variation of performance parameters with total hydrogen flow

图9 发动机性能参数随总氢流量的变化
Fig.9 Variation of performance parameters with total hydrogen flow

图10 最大推力状态下发动机可能触碰的安全边界<br/>Fig.10 Safety boundary that the engine may touch under maximum thrust

图10 最大推力状态下发动机可能触碰的安全边界
Fig.10 Safety boundary that the engine may touch under maximum thrust

图11 最大推力状态下发动机的飞行包线<br/>Fig.11 Flight envelope of the engine under maximum thrust

图11 最大推力状态下发动机的飞行包线
Fig.11 Flight envelope of the engine under maximum thrust

图12 最大比冲状态下发动机可能触碰的安全边界<br/>Fig.12 Safety boundary that the engine may touch under maximum specific impact condition

图12 最大比冲状态下发动机可能触碰的安全边界
Fig.12 Safety boundary that the engine may touch under maximum specific impact condition

图13 最大比冲状态下发动机可能触碰的安全边界<br/>Fig.13 Safety boundary that the engine may touch under maximum specific impact condition

图13 最大比冲状态下发动机可能触碰的安全边界
Fig.13 Safety boundary that the engine may touch under maximum specific impact condition

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备注

引言

1 PATR发动机变工况模型

2 PATR发动机控制特性

3 PATR发动机最大状态控制规律

4 结论

期刊信息