Method of test data processing for missile used turbojet - Part 3: Flight test
1 Scope
This part specifies the method of processing the data measured in flight test of missile used turbojet.
It is applicable to processing the data measured in flight test of missile used turbojet (hereinafter referred to as “turbojet”). It may also be referenced for processing the data measured in flight test of missile used turbofan engine.
2 Normative references
The following normative documents contain provisions which, through reference in this part, constitute provisions of this part. For dated references, subsequent amendments (excluding corrections), or revisions, of any of these publications do not apply to this part. However, parties to agreements based on this part are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated references, the latest editions apply to this part.
GJB 359 Specification for humidity correction of performance of turbojet and turbofan engines
GJB 366.3 Atmospheric humidity (0 ~ 10km)
GJB 378 Specification for temperature correction of performance of turbojet and turbofan engines
GJB 722 Specification for correction of test performance of turbojet and turbofan engines
QJ 3159.1-2002 Method of test data processing for missile used turbojet - Part 1: Stand bed test
3 Symbols
For the purpose of this part, the following symbols apply:
A——the intermediate parameter, 1/K;
A0——the sectional area of the air inlet of the intake, m2;
A3——the sectional area of straight sections such as combustion chamber, m2;
A5——the effective sectional area of the nozzle exit, m2;
——the sectional area of the nozzle exit, m2;
A50——the sectional area of the nozzle exit at 288.15K, m2;
a1——the empirical coefficient;
b1——the coefficient, J·min/(s·r);
b2——the coefficient, m3·min/(s·r);
b3——the coefficient, m3/s;
CHf——the correction coefficient of fuel btu;
CHgF——the humidity correction coefficient of total thrust;
CHn——the humidity correction coefficient of rotating speed;
CHpx——the humidity correction coefficient of total pressure;
CHqa——the humidity correction coefficient of air mass flow;
CHqf——the humidity correction coefficient of fuel mass flow;
CHtx——the correction coefficient of total temperature
Foreword i
1 Scope
2 Normative references
3 Symbols
4 General requirements
5 Measurement parameters
6 Steady-state calculation parameters
7 Reduced parameters
8 Calculation of steady-state characteristics of engine with telemetry parameters
9 Engine characteristics during starting acceleration
Method of test data processing for missile used turbojet - Part 3: Flight test
1 Scope
This part specifies the method of processing the data measured in flight test of missile used turbojet.
It is applicable to processing the data measured in flight test of missile used turbojet (hereinafter referred to as “turbojet”). It may also be referenced for processing the data measured in flight test of missile used turbofan engine.
2 Normative references
The following normative documents contain provisions which, through reference in this part, constitute provisions of this part. For dated references, subsequent amendments (excluding corrections), or revisions, of any of these publications do not apply to this part. However, parties to agreements based on this part are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated references, the latest editions apply to this part.
GJB 359 Specification for humidity correction of performance of turbojet and turbofan engines
GJB 366.3 Atmospheric humidity (0 ~ 10km)
GJB 378 Specification for temperature correction of performance of turbojet and turbofan engines
GJB 722 Specification for correction of test performance of turbojet and turbofan engines
QJ 3159.1-2002 Method of test data processing for missile used turbojet - Part 1: Stand bed test
3 Symbols
For the purpose of this part, the following symbols apply:
A——the intermediate parameter, 1/K;
A0——the sectional area of the air inlet of the intake, m2;
A3——the sectional area of straight sections such as combustion chamber, m2;
A5——the effective sectional area of the nozzle exit, m2;
——the sectional area of the nozzle exit, m2;
A50——the sectional area of the nozzle exit at 288.15K, m2;
a1——the empirical coefficient;
b1——the coefficient, J·min/(s·r);
b2——the coefficient, m3·min/(s·r);
b3——the coefficient, m3/s;
CHf——the correction coefficient of fuel btu;
CHgF——the humidity correction coefficient of total thrust;
CHn——the humidity correction coefficient of rotating speed;
CHpx——the humidity correction coefficient of total pressure;
CHqa——the humidity correction coefficient of air mass flow;
CHqf——the humidity correction coefficient of fuel mass flow;
CHtx——the correction coefficient of total temperature
Contents of QJ 3159.3-2002
Foreword i
1 Scope
2 Normative references
3 Symbols
4 General requirements
5 Measurement parameters
6 Steady-state calculation parameters
7 Reduced parameters
8 Calculation of steady-state characteristics of engine with telemetry parameters
9 Engine characteristics during starting acceleration
