For the final stage of a launch vehicle which cannot start multiple times, the main constraint of a highly ec-centric orbit launch mission is the argument of perigee, which is conditioned by the range. This paper studies the pay-load capacity at different launch sites for a highly eccentric orbit (e.g. GTO) and gives a method to improve the payload capacity with an argument of perigee constraint by increasing the sliding time before the final ignition and simultaneously adjusting the launch azimuth and yaw at the final stage. An example of launching to GTO orbit on a rocket from Hainan is given, which proves that the method has strong engineering value.

The divergence angle of laser beam used in space laser communication is usually no more than 100 μrad. Using laser beam with small divergence angle to achieve acquisition and tracking for space laser link has al-ways been a difficult problem. In addition, the random nature of the atmosphere will affect the satellite-ground laser link, which increases the difficulty of the acquisition and stable tracking for the laser link. Thus, taking into account the above challenges for satellite-ground laser communication, an acquisition and tracking scheme of using both beacon beam and signal beam was designed for the Laser Communication Terminal (LCT) of Shijian 20 satellite. In-orbit test results indicated that under the condition of moderate atmospheric turbulence (atmospheric coherence length r0≈3cm), the process of acquisition and tracking for the satellite-ground laser link can be completed within 1s after the initial pointing between the LCT and Optical Ground Station (OGS) is performed, and the tracking error was less than 1 μrad (3σ). In addition, the laser link can be re-established quickly once being interrupted by unsteady atmospheric turbulence, and can be maintained for a long time under moderate twurbulence conditions, which lays a foundation for future application of satellite-ground laser communication.

Large lift-to-drag ratio, high maneuverability, and good controllability are the basic performance for flight vehicles. Studying the rolling stability problems of a high lift-to-drag ratio aircraft is of great significance to the safety and control in maneuvering flight. The research on the static stability in the rolling direction of a HTV-2 like shape under a typical Mach number and attack angle was carried out. Similarly, by using Euler, laminar, turbulence and transition models, investigations of the dynamic stability in a single degree of freedom rolling motion of the same shape structure were executed. The numerical results show that the dynamic derivative of Euler is the largest, and the dynamic derivatives resulting from laminar, turbulence, and transition models are not much different.

It is an important scientific research activity in China to carry out near-space exploration and scientific experiments via aerospace carriers. Early near-space exploration projects mainly used aircraft, balloons, sounding rockets and Earth satellites to carry out space environment exploration. With the development of China’s space science and technology, microgravity science has become a frontier science that has developed rapidly in the past 20 years. With the continuous progress of national space science and technology, the demand for near-space exploration and scientific experiments is increasing year by year. In the next 2 to 3 years, many advanced science activities and the associated technologies need to conduct corresponding experimental research work. This paper mainly analyzes the significance
of scientific research and the ways to realize near-space exploration at home and abroad, and analyzes the directions and innovations that can be carried out in the future.

In the past two decades, the world’s unmanned aerial vehicle (UAV) industry has developed rapidly.Various kinds of UAVs have been used in military and civilian fields. Based on the characteristics of UAVs and the development of aerodynamics, this article analyzes the development of aerodynamic optimization design and dynamic numerical simulation technology, then lists engineering applications. Both erodynamic optimization design and dynamic numerical simulation have greatly shortened the UAV design period and reduced the research and design cost. These two methods gradually replace traditional methods such as wind tunnel test.

This article reviews Mars sampling and return technology, by retrieving and analyzing the patents of domestic and foreign sampling equipment and mechanism technology, Mars surface removal technology and ultra-high-speed light and small sample return technology. It conducts patent analysis from the macro-technical view down to the
micro-specific content view using statistical, quantitative and qualitative analysis methods. In the process of macro-analysis, it analyzes patent data from multiple perspectives such as time, region, technical composition, and applicants, and establishes the development trends for Mars sampling and return technology at home and abroad. In the process of micro-analysis, through the analysis and interpretation of key patents, we can learn the development priorities and development direction of foreign Mars sampling and return technology. This paper also proposes China’s Mars sampling and return technology development suggestions.