The guidance method for long range maneuvering vehicle is focused. The traditional proportional guidance method with falling angle in the terminal guidance phase is greatly affected by the geocentric angle of the flight range and cannot well adapt to the falling angle constraint of long range maneuvering vehicle. An optimal guidance law with falling angle constraint using geocentric angle is proposed. The simulation results show that the guidance method can make the falling angle of long range maneuvering vehicle content the falling angle constraint, and has certain robustness.

When launching missiles from oblique fixed launcher, the adapter is out of the canister launcher after the separation of the falling point problem. Through the test of the adapter falling point situation, the use of C programming recalculate the adapter throughout the motion process. The adapter in the exhaust flow field of the exhaust force and the adapter falling point are, predicted. The main causes of the falling point problem are determined. For the first time, the nitrogen-rich compounds (penta-amino tetrazolium) is first used as a boosting force source to realize the separation of the adapter instantaneous boost design,. Through the motion simulation and testing, the research validates that the application of the principle of the boosting device is correct and the validity of the separation.

To study the drag reduction characteristics of head opposing jet flow for the whole high-speed vehicle, a calculation model is established for sphere bicone, and flow field is solved by using multi-component axial symmetry Navier-Stokes equations. The influence laws of the opposing jet on the wave drag, friction drag, and base drag are studied by using the height of free stream, and the total pressure ratio of the jet and free stream. The calculation results show that the increase of the total pressure ratio reduces the wave drag and base drag by changing the flow field structure, and it leads to a temperature decrease and velocity gradient increase within the boundary layer. The dominant boundary velocity gradient can lead to an increase in friction drag. For high-altitude conditions, the friction drag has a high proportion of total drag and a better drag reduction effect, so it is better to choose an appropriate total pressure ratio. For low-altitude conditions, the base drag has a high proportion of total drag and a better drag reduction effect, so it is better to choose a high total pressure ratio. Considering the cost-effectiveness ratio of drag reduction and opposing jet mass flow, high-altitude flight conditions with a small total pressure ratio can be chosen.

In order to achieve the purpose of precision strike of reentry vehicle under complex electromagnetic interference conditions, a side window cover throwing technology for radar/infrared dual-model combined guidance is proposed. Through simulated analysis and ground tests, the rationality of heat seal structure of infrared window and the reliability of cover throwing scheme is verified, and the motion track and flight attitude of cover are obtained under high-Mach and high dynamic pressure conditions. The results show that the heat sealing performance of infrared window is effective, which can prevent the external heat flow into the interior of the vehicle successfully. The cover can be thrown successfully when it's needed, the cover can fly out the shock wave-affected zone and always move away from the vehicle continuously, which can not crash the vehicle. The infrared glass is in good condition, which is not broken and polluted. The research provides a technical support for the investigation on cover throwing technology for reentry vehicle.

To address the issues of scattered management, lack of standardization, and traditional analysis methods in the data of liquid rocket engine tests, a big data-based liquid propulsion test data analysis system has been designed. The system adopts an advanced big data architecture, combines data preprocessing technology, distributed storage, and data center modeling, forms a specialized data warehouse, optimizes data organization, retrieval, and analysis processing capabilities, and achieves comprehensive collection, efficient storage, fine management, and intuitive display of test data. Application results show that the system not only realizes the standard management and central storage of test data, but also provides functions for data analysis such as engine adjustment calculations, significantly improving data processing efficiency and analysis quality, which provides valuable exploration and practice for the digital transformation in the field of liquid propulsion and holds promising application prospects.

The satellite-rocket interface is an important factor affecting the success of rapid response launches. Rapid response solid rocket is taken as the research object. On the basis of proposing the general requirements of the satellite-rocket interfaces for rapid response rocket, the satellite-rocket interface is analyzed focusing on mechanical interface and electrical interface, the optimal mode of satellite-rocket interface for rapid response rocket is explored. It is concluded that the memory alloy-driven point satellite-rocket connection unlocking device and wireless charging do not reserve a charging interface. The research provides suggestions on how to promote the use of optimal model of satellite rocket interface for rapid response rocket, and provides reference for improving the reliability and efficiency of rapid response launches.

To investigate the effect of inducer blade thickness on cavitation performance, the liquid oxygen turbopump of a liquid rocket engine is taken as the research object. Four inducers with different blade thicknesses are designed by changing the thickness at the blade root, and the thickness at the blade tip changes accordingly with the change in blade root thickness. Strength verification and cavitation performance analysis are conducted for the inducers of these four schemes. The research results show that selecting thinner inducers can improve the cavitation performance of turbopumps while ensuring blade strength. Meanwhile, the thickness at the blade tip also has a significant impact on the cavitation performance of the turbopump.

Aiming at the trajectory optimization problem of the ascending stage of launch vehicle in the atmosphere with complex and multi constraints, a trajectory optimization method based on simultaneous method is proposed. The method adopts the direct method under the simultaneous framework, discretizes the state variables and control variables through the finite element orthogonal collocation method, and then solves the discrete nonlinear programming problem by the interior point method, so as to balance the calculation efficiency and solution accuracy, and improve the autonomy and task adaptability of trajectory optimization. Aiming at the problem that the larger the scale of the discrete nonlinear programming problem is, the more time-consuming the gradient matrix calculation is, making full use of the sparsity of the partial derivative matrix, the solution of the non-zero term in the NLP gradient is transformed into the solution of the partial derivative of the original optimal control problem, so as to further improve the efficiency of trajectory optimization. The simulation results show that this method can complete the flight mission well and meet constraints.

Heat exchangers are extensively used in rocket power system for gas supply and distribution. Three-dimensional numerical simulations of two different heat exchangers through straight and curve tubes, respectively, are performed by commercial software FLEUNT. Comparisons are made between numerical and empirical results. The investigation indicates that the total heat transfer coefficient obtained by FLUENT using the flow-heat coupled algorithm agrees well with that from the empirical formula. Moreover, compared with heat exchanger through straight tubes, the centrifugal force exerted on the hot air in the heat exchanger through curve tubes leads to higher heat transfer efficiency. As a result, the total heat transfer coefficient of heat exchanger through curve tubes is approximately 10% greater than that through straight tubes given other flow and geometry factors fixed.

In order to improve the efficiency of gas supply system in space launch, automatic charging technology of gas cylinders is proposed. Automatic charging schemes of gas cylinders based on PID control technology are designed, and the automatic control strategy is studied through the system simulation software AMESim. The results indicate that by setting the PID control module parameters reasonably, the schemes of gas charging can meet the automatic charging requirements of gas cylinders on launch vehicle. To improve the automatic charging control effect of gas cylinder, pressure sensor used in the control module should be installed close to the cylinders of launch vehicle.