Responsibilities:

1. Carry out demonstration of the launch vehicle attitude system scheme according to the overall requirements.

2. Responsible for carrying out research on attitude control technology and algorithm design for the powered flight segment of the launch vehicle.

3. Responsible for the launch vehicle attitude dynamics model modeling and attitude control model modeling, to provide reference for the control system design and accuracy analysis.

4. Responsible for the whole process design of the launch vehicle attitude control system, mainly including the attitude control design based on the overall ballistic small deviation equation and the attitude control parameter optimization design based on the six-degree-of-freedom model, adapting to the launch conditions and launch process of the launch vehicle, and meeting the overall index requirements of attitude control stability margin, attitude tracking accuracy, attitude start control, etc.

5. Carry out the performance and function of the attitude control system based on the limit error combination to provide the basis for the overall decision-making.

6. Carry out the design of the thrust adjustment scheme of the liquid rocket engine, and provide the decision-making basis for the overall engine thrust adjustment.

Requirements:

1. Master degree or above in navigation, guidance and control, control theory, aircraft design and other related majors in aerospace field;

2. At least 3 years working experience in design of launch vehicle or ballistic missile guidance and attitude control system;

3. Basic theoretical knowledge of advanced mathematics, control theory, theoretical mechanics, material mechanics, signal and system, automatic control principle, numerical analysis, etc. With flight mechanics, track mechanics and other professional knowledge;

4. Professional knowledge in control theory, control engineering, computational simulation and other fields. Familiar with the basic performance and application of inertial navigation, servo, angular momentum flywheel and other measurement and attitude control execution equipment.