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General specification for satellite propulsion system
1 Scope
1.1 Subject content
This specification specifies the requirements, quality assurance requirements and delivery preparation of satellite propulsion system (hereinafter referred to as propulsion system).
1.2 Application scope
This specification is applicable to the design, production, test and inspection of satellite propulsion system and its components and units using liquid and gas propellants, and also serves as a reference for the design, production, test and inspection of other spacecraft propulsion systems and their components and units.
2 Normative references
GB 190-90 Labels for packages of dangerous goods
GB 191-90 Packaging - Pictorial marking for handling of goods
GJB 145-86 Military specification preservation packaging method
GJB 151.3-86 Requirements for equipments and subsystems installed aboard spacecraft and launch vehicles, including associated support equipment (Class A2)
GJB 152-86 Measurement of electromagnetic emission and susceptibility requirements for military equipment and subsystems
GJB 190-86 Classification of characteristics
GJB 344-87 General design specification for insensitive electric-initiators
GJB 368.2-87 General specification for materiel maintainability - Basic requirements of maintainability
GJB 736.6-89 Method of initiating explosive device test - Determining the insulation resistance of electric initiating explosive device
GJB 736.7-89 Method of initiating explosive device test - Determining the DC resistance of bridge circuit of electric initiating explosive device
GJB 1027-90 Environmental test requirements for satellites
GJB 1307-91 General specification for pyrotechnic device of satellites
GJB 1391-92 Procedure for failure mode, effects and criticality analysis
GJB 1410-92 Requirement for satellite electrical checkout interface
GJB 1416-92 General specification for satellite attitude control system
GJB 2203-95 Cleanliness and its control requirements for satellite product
GJB/Z 35-93 Derating criteria for electrical, electronic and electromechanical parts
QJ 897-85 General specification for control of control for foreign object debris
QJ 1239.1-87 Environmental test conditions and methods for electronic equipment - General provisions
QJ 1239.13-87 Environmental test conditions and methods for electronic equipment - Impact test
QJ 1239.14-87 Environmental test conditions and methods for electronic equipment - Acceleration test
QJ 1357-88 Attitude control motor design procedures
QJ 1358-88 Attitude control motor thrust series
QJ 1579-88 Vibration test method for whole satellite
QJ 1666-95 Technical requirements for fusion welding of titanium and titanium alloy
QJ 1714.6-89 Management rules for design documents of space product - Part 6: Integrity of design documents
QJ 1842-95 Technical specification for fusion welding of structural steel and stainless steel
QJ 2053-91 Satellite leak detection test method
QJ 2137-91 Safety technical specification for production test of pyrotechnic devices used on space vehicles
QJ 2214-91 Cleanliness level and evaluation in clean room (zone)
QJ 2630.1-94 Space environment test method for satellite units - Thermal vacuum test
QJ 2630.3-94 Space environment test method for satellite units - Vacuum discharge test
3 Requirements
3.1 Relevant detailed specifications
Individual requirements for propulsion system of specific type shall comply with relevant detailed specifications. If the requirements of this specification conflict with those of relevant detailed specifications, the latter shall prevail.
3.2 Qualification
The propulsion system submitted according to this specification shall be a product that has been identified as qualified or approved.
3.3 Reliability
The reliability of propulsion system generally includes structural reliability and performance reliability. The reliability of propulsion system is related to factors such as function, in-orbit life, complexity, maturity of adopted technology, funds and development cycle, which are given in relevant detailed specifications.
The propulsion system submitted for the first flight test shall meet the reliability indicator requirements proposed by the whole satellite under the specified confidence level. With the development of the research work, the reliability of the propulsion system shall be gradually improved, and the requirements of relevant detailed specifications shall be met during the qualification or final approval.
The reliability design criteria include:
a. propulsion system configuration shall be simple;
b. the hardware and software that have been verified or flight-identified shall be used preferentially and maximally, and the inheritance shall be placed in a prominent position;
c. adequate and reasonable redundancy shall be available; when technically possible, single point failure shall be eliminated as far as possible; long-life propulsion systems require cross backup without single point failures;
d. electronic, electrical and electromechanical components shall be derated, and the derating level shall comply with Class I in GJB/Z 35, 4.2;
e. propellant consumption, total loading capacity and its margin shall comply with relevant detailed specifications, which are usually estimated according to Annex B (reference).
f. the failure mode, impact and harmfulness of propulsion system and its components shall be analyzed according to GJB 1391, and the characteristic classification of propulsion system and its components shall be specified according to the requirements of GJB 190 on the basis of analysis.
3.4 Materials and electrical, electronic and electromechanical parts
3.4.1 Selection
Materials and electrical, electronic and electromechanical parts for manufacturing propulsion system shall be preferentially selected from those complying with national standards, national military standards and professional standards, and meet the requirements of working performance, service environment, storage period, lifetime and manufacturing process of the propulsion system. The adoption of new materials and electrical, electronic and electromechanical parts shall be fully demonstrated, tested, identified or finalized at the development stage of mold and prototype, and pass the prescribed examination and approval procedures.
3.4.2 Compatibility
The metallic and nonmetallic materials in the propulsion system must be first-class compatible with the working medium in contact. Before use, each batch of non-metallic materials adopted shall be tested for compatibility according to the requirements of relevant detailed specifications, and provided with a material certificate issued by the quality inspection department.
For the propulsion system, the parts shall be corrosion resistant, and the pressure components shall be subjected to stress corrosion test to prove their corrosion resistance. Protective measures shall be taken on the surfaces of parts made of non-corrosion resistant materials, and shall remain effective throughout the lifetime.
3.4.3 Hairlines
The metallic materials of important components shall be free of hairlines.
3.5 Design
3.5.1 Composition
Generally, the propulsion system is a redundant system composed of tank, gas cylinder, various valves, sensor, thruster, pipeline and electronic circuit.
3.5.2 Functions
Generally, the functions performed by the propulsion system include orbit injection, orbit control, attitude control, de-orbit and return control, etc. Specific requirements are specified by relevant detailed specifications. The typical functions and requirements of propulsion system are given in Annex C (reference).
3.5.3 Propellants
Propellants adopted for the propulsion system shall be selected according to the functions and requirements of the propulsion system and comply with relevant detailed specifications.
3.5.4 Basic parameters of propulsion system design
The basic parameters of propulsion system design include:
a. satellite stabilization mode;
b. total impulse;
c. thrust of thruster;
d. working mode of thruster;
e. minimum impulse of thruster;
f. lifetime;
g. weight;
h. power consumption.
3.5.5 Interfaces
The interfaces of propulsion system are controlled by interface data sheet, which determines the mechanical, electrical and thermal characteristics of components, including the predetermined requirements of quality characteristics, telemetry, remote control and thermal characteristics. Please refer to Annex D (reference) for the details of filling in of interface data sheet.
3.6 Structure
3.6.1 Strength and rigidity
Components shall have sufficient strength and rigidity to withstand the stress of test, operation, transportation, launching and orbit running environment. Under the specified conditions, there shall be no elastic deformation or permanent deformation affecting their use.
3.6.2 Installation
Generally, components are connected with satellite structures through lugs, of which, the flatness shall be superior to 0.1mm/100mm. The contact area of the fixing point shall be clearly specified in the interface data sheet. For components with great heat generation, the number and position of fixing points shall be determined by thermal control requirements. The number of fixing points shall be determined according to the component structure. Generally, for box-shaped components, the following requirements shall be met:
a. take four fixing points when the weight is not greater than 12kg;
b. take six fixing points when the weight is greater than 12kg.
3.6.3 Calibration
Dowel pins or adjustment mechanisms may be adopted for components to be accurately installed in place. When the calibration accuracy is superior to 0.15°, it is necessary to set a calibration reference (usually an optical reflector) on the components. The position of the reflector shall be indicated in the assembly drawing and interface data sheet.
3.6.4 Pipe clamps
The tube of propulsion system shall be fixed with pipe clamps according to the requirements of detailed specification.
3.6.5 Fasteners and anti-loosening
Generally, fasteners are made of non-magnetic-conductive materials, and shall be equipped with effective locking devices to prevent loosening. Generally, rubber seals, spring washers and check washers are adopted. The net tightening torque C of the screw shall be within the following ranges:
a. M3: 1
Contents of GJB 2787-1996
1 Scope
2 Normative references
3 Requirements
4 Quality assurance requirements
5 Delivery preparation
6 Instructions
Annex A (Supplementary) Inspection of propulsion system components
Annex B (Reference) Estimation of propellant
Annex C (Reference) Typical functions and requirements of propulsion system
Annex D (Reference) Interface data sheet
Additional explanation
