Requirement for flight software simulation of trajectory missile and launch vehicle
1 Scope
This standard specifies the basic requirements, input conditions, items and contents of flight software simulation test of trajectory missile and launch vehicle.
This standard is applicable to the flight software simulation test verification of trajectory missile and launch vehicle. It may be used as reference for other types of missiles.
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) to, 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 latest editions of the normative standards indicated below. For undated references, the latest edition applies.
GB/T 11457 Software engineering terminology
3 Terms
For the purposes of this document, the terms and definitions given in GB/T 11457, as well as the following apply.
3.1
flight software
software that completes the real-time flight control function of the trajectory missile or launch vehicle control system in missile (or launch vehicle)-borne computer, also known as flight control software. Generally, it includes three major functions: guidance system, attitude control system, and integrated (timing) control system
4 Test objectives
After the flight software design and compilation are completed, simulation test verification must be carried out in the real operating environment (target aircraft). The purpose of the flight software simulation test is to verify the correctness of the design and implementation of the flight software, the completeness of functions, and the compatibility of the software and hardware environment. There are three kinds of flight software simulation tests:
a) flight software simulation test of guidance system;
b) flight software simulation test of attitude control system;
c) joint simulation test of guidance and attitude control systems.
5 Test system composition and main test equipment
5.1 Test system composition
5.1.1 Flight software simulation test system composition for guidance system
The flight software simulation test of the guidance system includes open-circuit simulation test and closed-circuit simulation test. The block diagram for the flight software open-circuit simulation test system composition for guidance system is shown in Figure 1, and that for the flight software closed-circuit simulation test system composition for guidance system is shown in Figure 2. When the guidance system adopts the combined
Foreword II
1 Scope
2 Normative references
3 Terms
4 Test objectives
5 Test system composition and main test equipment
6 Test conditions
7 Test items
8 Test contents
9 Test states
10 Evaluation of test results
11 Test report
Requirement for flight software simulation of trajectory missile and launch vehicle
1 Scope
This standard specifies the basic requirements, input conditions, items and contents of flight software simulation test of trajectory missile and launch vehicle.
This standard is applicable to the flight software simulation test verification of trajectory missile and launch vehicle. It may be used as reference for other types of missiles.
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) to, 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 latest editions of the normative standards indicated below. For undated references, the latest edition applies.
GB/T 11457 Software engineering terminology
3 Terms
For the purposes of this document, the terms and definitions given in GB/T 11457, as well as the following apply.
3.1
flight software
software that completes the real-time flight control function of the trajectory missile or launch vehicle control system in missile (or launch vehicle)-borne computer, also known as flight control software. Generally, it includes three major functions: guidance system, attitude control system, and integrated (timing) control system
4 Test objectives
After the flight software design and compilation are completed, simulation test verification must be carried out in the real operating environment (target aircraft). The purpose of the flight software simulation test is to verify the correctness of the design and implementation of the flight software, the completeness of functions, and the compatibility of the software and hardware environment. There are three kinds of flight software simulation tests:
a) flight software simulation test of guidance system;
b) flight software simulation test of attitude control system;
c) joint simulation test of guidance and attitude control systems.
5 Test system composition and main test equipment
5.1 Test system composition
5.1.1 Flight software simulation test system composition for guidance system
The flight software simulation test of the guidance system includes open-circuit simulation test and closed-circuit simulation test. The block diagram for the flight software open-circuit simulation test system composition for guidance system is shown in Figure 1, and that for the flight software closed-circuit simulation test system composition for guidance system is shown in Figure 2. When the guidance system adopts the combined
Contents of QJ 2187A-2008
Foreword II
1 Scope
2 Normative references
3 Terms
4 Test objectives
5 Test system composition and main test equipment
6 Test conditions
7 Test items
8 Test contents
9 Test states
10 Evaluation of test results
11 Test report
