Thermodynamic calculation method and computer program of solid rocket motor
1 Scope
This standard specifies the thermodynamic calculation method and computer program of solid rocket motor and solid propellant.
It is applicable to the design of solid rocket motor and solid propellant.
2 Normative references
The following normative documents contain provisions which, through reference in this text, constitute provisions of this standard. For dated references, subsequent amendments (excluding corrections), or revisions, of any of these publications do not apply to this standard. However, parties to agreements based on this standard are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated references, the latest edition of the normative document referred to applies.
GJB 3387-1998 Terms for rocket engine
GJB 3731-1999 Parameter symbols of rocket engine
QJ 1814-1989 Standard mole formation enthalpy of related components of composite propellants
QJ 2036-1991 Temperature coefficient of propellant combustion products
3 Terms, definitions and symbols
3.1 Terms and definitions
For the purposes of this standard, the terms and definitions given in GJB 3387-1998, as well as the following apply.
3.1.1
component
all substances constituting a grain or a propellant, or all kinds of gas phase elements, gas phase compounds, condensed phase compounds, etc. constituting a combustion product
3.1.2
unit mass chemical formula
assuming 1kg solid propellant as a pure substance composed of the most basic chemical element Ak (k=1, 2, …1), and writing the calculated amount of various elements in the lower right corner of this element
3.1.3
independent component
a group of compounds in the combustion product (gas phase or condensed phase), which are independent of each other, have a large amount of substances, and can include all the elements in the propellant chemical formula at the same time
3.1.4
standard state
exact aggregation state of matter under arbitrarily selected standard pressure pθ
Internationally, 0.101325MPa is defined as standard state pressure, which is indicated by adding "θ" symbol to the upper right corner of parameter symbol. For example, indicates the standard mole entropy of the ith component
3.1.5
standard chemical power
in the mixed gas following the ideal gas state equation, the standard chemical power definition of the ith component at temperature T is shown in Equation (1):
Foreword i
1 Scope
2 Normative references
3 Terms, definitions and symbols
3.1 Terms and definitions
3.2 Symbols
4 Calculation methods
4.1 Calculation process
4.2 Main assumptions
4.3 Calculation of iterative accuracy
4.4 Calculation of the unit mass chemical formula and specific enthalpy of propellant
4.5 Determination of equilibrium components of combustion products
4.6 Calculation of combustion temperature in combustion chamber
4.7 Calculation of partial derivatives DT and Dp
4.8 Basic equations of nozzle area expansion process
4.9 Calculation of thermal performance parameters
4.10 Calculation of partial derivatives of thermodynamic function
5 Computer program
5.1 Computer input
5.2 Computer output
5.3 Computer program
5.4 Calculation of the standard molar formation enthalpy and the temperature coefficient of combustion products of propellant components
5.5 Program instructions
Annex A (Informative) Computer program
Thermodynamic calculation method and computer program of solid rocket motor
1 Scope
This standard specifies the thermodynamic calculation method and computer program of solid rocket motor and solid propellant.
It is applicable to the design of solid rocket motor and solid propellant.
2 Normative references
The following normative documents contain provisions which, through reference in this text, constitute provisions of this standard. For dated references, subsequent amendments (excluding corrections), or revisions, of any of these publications do not apply to this standard. However, parties to agreements based on this standard are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated references, the latest edition of the normative document referred to applies.
GJB 3387-1998 Terms for rocket engine
GJB 3731-1999 Parameter symbols of rocket engine
QJ 1814-1989 Standard mole formation enthalpy of related components of composite propellants
QJ 2036-1991 Temperature coefficient of propellant combustion products
3 Terms, definitions and symbols
3.1 Terms and definitions
For the purposes of this standard, the terms and definitions given in GJB 3387-1998, as well as the following apply.
3.1.1
component
all substances constituting a grain or a propellant, or all kinds of gas phase elements, gas phase compounds, condensed phase compounds, etc. constituting a combustion product
3.1.2
unit mass chemical formula
assuming 1kg solid propellant as a pure substance composed of the most basic chemical element Ak (k=1, 2, …1), and writing the calculated amount of various elements in the lower right corner of this element
3.1.3
independent component
a group of compounds in the combustion product (gas phase or condensed phase), which are independent of each other, have a large amount of substances, and can include all the elements in the propellant chemical formula at the same time
3.1.4
standard state
exact aggregation state of matter under arbitrarily selected standard pressure pθ
Internationally, 0.101325MPa is defined as standard state pressure, which is indicated by adding "θ" symbol to the upper right corner of parameter symbol. For example, indicates the standard mole entropy of the ith component
3.1.5
standard chemical power
in the mixed gas following the ideal gas state equation, the standard chemical power definition of the ith component at temperature T is shown in Equation (1):
Contents of QJ 1393A-2004
Foreword i
1 Scope
2 Normative references
3 Terms, definitions and symbols
3.1 Terms and definitions
3.2 Symbols
4 Calculation methods
4.1 Calculation process
4.2 Main assumptions
4.3 Calculation of iterative accuracy
4.4 Calculation of the unit mass chemical formula and specific enthalpy of propellant
4.5 Determination of equilibrium components of combustion products
4.6 Calculation of combustion temperature in combustion chamber
4.7 Calculation of partial derivatives DT and Dp
4.8 Basic equations of nozzle area expansion process
4.9 Calculation of thermal performance parameters
4.10 Calculation of partial derivatives of thermodynamic function
5 Computer program
5.1 Computer input
5.2 Computer output
5.3 Computer program
5.4 Calculation of the standard molar formation enthalpy and the temperature coefficient of combustion products of propellant components
5.5 Program instructions
Annex A (Informative) Computer program