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.

In the view of the difficulty of digital coordination of coordination hole of the carrier rocket part, the influencing factors of digital coordination processing are analyzed and the main reasons are determined, and the influence of measurement error and positioning on the machining accuracy is analyzed through comparative test and theoretical analysis. On this basis, the digital coordinated machining control scheme is put forward, and the typical part is taken as the object to carry out coordinated hole test, the test results show that the digital quantity coordination machining hole position accuracy meets the requirements of assembly coordination, and the test coordination with the tooling platform, laying the foundation for the engineering application of the end-frame digital quantity coordinated machining.

In order to study the ability of laser-guided weapons to capture targets in various environments such as sea and land, mathematical models such as flight trajectory, backscatter and target diffuse reflection of laser-guided weapons are established, and whether the guided weapons could capture targets normally are judged by comparing the field of view, backscatter power density and target diffuse reflection power density of laser-guided weapons. Simulation calculations show that under the same conditions, the same laser weapon captures the target later at sea than in the land and other environments, the capture distance is closer, and the backscattering is more serious. Under normal circumstances, the backscattering effect of laser-guided weapons is more serious in the initial 4.4s time period of this projection, and the backscattering effect can be avoided by reducing the outlet energy of the laser irradiator or increasing the distance between the central axis of the laser-guided weapon and the optical path of the laser irradiator to more than 250m.

Focusing on the development of missile intelligent cooperation, the application of missiles in Unmanned Aerial Vehicle (UAV) swarms is focused on. The respective application characteristics of UAV swarm and missile systems are introduced, the application modes of missiles in UAV swarm are explored, the requirement on developing intelligent missile swam is analyzed. Based on the issues of observation, interaction, and collaboration in swarm intelligence, current challenges and key support technologies for missiles application in UAV swarm are analyzed. With the analysis on "MSET" and "Golden Horde" projects, the current situation and development of missiles in swam are analyzed, and the ability doubling points for the actualization of missile-UAV application are pointed out, which provides exploration for future research on intelligent missile system.

An improved ACO is proposed for two-dimensional path planning of flight vehicles to solve the problems such as slow convergence speed, easy to fall in stagnation and zigzag path with large angles in basic ACO. First, the improved algorithm optimizes extend method to accelerate convergence. Then, a new pheromone strategy is put forward to increase the utilization of pheromone information while preventing ant from falling into stagnation. At last, local optimization method is introduced to reduce the twists and turns in the searched path. According to the simulation results, the improved ACO has superiority in convergence, iteration number and quality of path. The result proves that the improved algorithm can increase the rate of convergence and path quality compared with basic ACO.

To address the reentry missions with different path constraints and range requirements, a conic based bank angle is designed to enhance the lateral maneuverability, and the predictor-corrector guidance method is used to revise the bank angle profile to satisfy the range requirements. The improved artificial potential field method is used to design the lateral guidance method to satisfy the path constraints. Finally, the guidance parameters are optimized by particle swarm optimization algorithm to obtain the trajectory with the best performance. Simulation results verify that the algorithm can adapt various range requirements and path constraints, and meet the terminal constraints with high accuracy.

The Model based Definition (MBD) technology digital process verification approach is examined. A process verification system for Design for Manufacture (DFM) is introduced. The system uses PMI, or product and manufacturing information, as a vehicle to express product processing information and dimensional information. In the concept design phase, the auto-matic process testing of the product geometry model is realized, and the viability of the product process is examined, thanks to the development of the model testing tool. The test's outcome is evaluated in accordance with the guidelines for producing liquid rocket engines. The designer can adjust and enhance the sketch of the geometry for the liquid rocket engine in light of the outcome. By using DFM, the process accessibility of the product in the design phase is improved, the design and process changes in the product manufacturing process are reduced, and the product development cycle is shortened.

The on-orbit refueling technologies of cryogen can reduce the total mass of propellants required in rocket vehicles, allowing a significant increase in the amount of payload delivered beyond low Earth orbit. It has great potential benefits in complex space transportation systems and deep space exploration tasks. A literature investigation on the key techniques of cryogenic propellant on-orbit refueling is conducted. The existing lab-scale and full-scale experimental studies are reviewed in detail. Moreover, advantages of using on-orbit refueling techniques comprehensive analysis in future space tasks are provided. Technical suggestions on the developments for on-orbit refueling of cryogenic propellants are proposed based on this research.

In order to improve the transpiration cooling efficiency at the stagnation point of the nose cone of the near space vehicle, a wedge-shaped porous nose cone with a gradient porosity layout is proposed and the phase change transpiration cooling is experimentally and numerically investigated under different coolant injection ratio. The experimental results indicate that the gradient porosity layout can effectively improve the cooling efficiency at the stagnation point and the overall temperature uniformity of the porous surface. When the coolant injection ratio $M$ is 0.125%, the cooling efficiency at the stagnation point is increased by 52.4%, and the overall cooling efficiency is increased by 31.7%. The numerical results indicate that the gradient porosity layout increases the coolant mass flux at the leading edge and optimizes coolant distribution by moving the maximum pressure value at the stagnation point downstream. When the coolant injection ratio $M ={0.15}\%$, the coolant mass flux at the stagnation point is increased 76%. In addition, the film formed by the coolant flows out of the porous structure is more uniform.

Iron loss occupies a large proportion of the losses of in-wheel motor for special vehicle, which directly affects the efficiency and temperature rise of the drive system. In order to accurately calculate the iron loss, time-stepping finite element analysis is adopted to analyze the flux density waveforms at different regions of the stator core by taking the in-wheel motor with rated power of ${70}\mathrm{\;{kW}}$ for example. Harmonic analysis of radial and tangential flux density waveforms at different regions of the stator core is carried out. The impact of rotating magnetic field and harmonic component on the stator iron loss is further studied. Three different iron loss calculation methods are adopted to calculate the stator iron loss after the flux density waveforms and harmonic analysis are carried out. The stator iron loss values separated from the efficiency and loss test of the in-wheel motor are compared with the calculation values of different calculation methods. The results show that the calculation method in consideration of the effect of rotating magnetic field and harmonic component has the highest accuracy and its calculation result is the closest to the test result, which verifies the validity of the calculation method.