1 Scope
This specification specifies the basic requirements for the design, manufacture, performance, environmental adaptability, inspection and delivery preparation of the chamber grain of solid rocket motor (including liner and combustion-limiting layer, the same below).
This specification is applicable to the design, manufacture and inspection of composite solid propellant combustion chamber grain (hereinafter referred to as grain).
2 Normative references
The following documents contain provisions which, through reference in this text, constitute provisions of this code. For dated reference, subsequent amendments to (excluding any corrigendum), or revisions of, any of these publications do not apply. However, parties to agreements based on this specification are encouraged to investigate the possibility of applying the most recent editions of the documents indicated below. For undated references, the latest edition of the normative document referred to applies.
GJB 770A-1997 Propellant test method
GJB 772A-1997 Explosive test method
GJB 1026A-1999 General specification for solid propellant rocket motors
GJB 3387 Terms for rocket engine
GJB 3731 Parameter symbols of rocket engine
QJ 809 Determination of thermal conductivity and specific heat capacity of composite solid propellants—Quasi-steady-state method
QJ 917A-1997 Determination of density of composite solid propellant, lining and thermal insulation materials
QJ 1354-1988 General technical requirements for painting external marking and packing of solid rocket motors
QJ 1393A-2004 Thermodynamic calculation method and computer program of solid rocket motor
QJ 1468 Test method for initial thermal decomposition temperature and deflagration temperature of composite solid propellant
QJ 1469 Test method for electrostatic spark sensitivity of composite solid propellant and other explosives
QJ 1490 Determination of linear expansion factor of composite solid propellant
QJ 1617 Determination of glass transition temperature of composite solid propellant
QJ 2038.1A-2004 Test method for interface bonding strength of solid rocket motor chamber—Part 1: Unstick test for rectangular specimen
QJ 2038.2 Test method for interface bonding strength of solid rocket motor chamber—Shear method
QJ 2609 High energy X-ray flaw detection method for solid rocket motor chamber
QJ 2850-1996 Prevention and control for foreign object debris (FOD) space products
QJ 2913 Determination of friction sensitivity of composite solid propellant
QJ 3039 Test method for impact sensitivity of composite solid propellant by falling hammer
3 Requirements
3.1 General
The design, manufacture, test, acceptance and storage of grain shall meet the requirements of this specification and corresponding detailed specifications. In case of any inconsistency between the requirements of this specification and detailed specifications, the detailed specifications shall prevail.
3.2 Dimension
The dimension shall meet the following requirements:
a) The structure dimension and deviation of grain shall meet the requirements of detailed specifications;
b) The thickness and deviation of liner and combustion-limiting layer are allowed to be replaced by equivalent mass and deviation.
3.3 Mass
The mass and its deviation of grain shall meet the requirements of detailed specification.
3.4 Design
The grain design shall meet the requirements specified in the task book, and shall comply with the design documents, relevant standards and regulations.
1 Scope
This specification specifies the basic requirements for the design, manufacture, performance, environmental adaptability, inspection and delivery preparation of the chamber grain of solid rocket motor (including liner and combustion-limiting layer, the same below).
This specification is applicable to the design, manufacture and inspection of composite solid propellant combustion chamber grain (hereinafter referred to as grain).
2 Normative references
The following documents contain provisions which, through reference in this text, constitute provisions of this code. For dated reference, subsequent amendments to (excluding any corrigendum), or revisions of, any of these publications do not apply. However, parties to agreements based on this specification are encouraged to investigate the possibility of applying the most recent editions of the documents indicated below. For undated references, the latest edition of the normative document referred to applies.
GJB 770A-1997 Propellant test method
GJB 772A-1997 Explosive test method
GJB 1026A-1999 General specification for solid propellant rocket motors
GJB 3387 Terms for rocket engine
GJB 3731 Parameter symbols of rocket engine
QJ 809 Determination of thermal conductivity and specific heat capacity of composite solid propellants—Quasi-steady-state method
QJ 917A-1997 Determination of density of composite solid propellant, lining and thermal insulation materials
QJ 1354-1988 General technical requirements for painting external marking and packing of solid rocket motors
QJ 1393A-2004 Thermodynamic calculation method and computer program of solid rocket motor
QJ 1468 Test method for initial thermal decomposition temperature and deflagration temperature of composite solid propellant
QJ 1469 Test method for electrostatic spark sensitivity of composite solid propellant and other explosives
QJ 1490 Determination of linear expansion factor of composite solid propellant
QJ 1617 Determination of glass transition temperature of composite solid propellant
QJ 2038.1A-2004 Test method for interface bonding strength of solid rocket motor chamber—Part 1: Unstick test for rectangular specimen
QJ 2038.2 Test method for interface bonding strength of solid rocket motor chamber—Shear method
QJ 2609 High energy X-ray flaw detection method for solid rocket motor chamber
QJ 2850-1996 Prevention and control for foreign object debris (FOD) space products
QJ 2913 Determination of friction sensitivity of composite solid propellant
QJ 3039 Test method for impact sensitivity of composite solid propellant by falling hammer
3 Requirements
3.1 General
The design, manufacture, test, acceptance and storage of grain shall meet the requirements of this specification and corresponding detailed specifications. In case of any inconsistency between the requirements of this specification and detailed specifications, the detailed specifications shall prevail.
3.2 Dimension
The dimension shall meet the following requirements:
a) The structure dimension and deviation of grain shall meet the requirements of detailed specifications;
b) The thickness and deviation of liner and combustion-limiting layer are allowed to be replaced by equivalent mass and deviation.
3.3 Mass
The mass and its deviation of grain shall meet the requirements of detailed specification.
3.4 Design
The grain design shall meet the requirements specified in the task book, and shall comply with the design documents, relevant standards and regulations.
