This article summarizes the development process of Beidou1 to Beidou3, the development and changes of Beidou navigation satellite attitude and orbit control technology，as well as the achievements in leading the progress of satellite attitude and orbit control technology and the autonomous controllability of satellite components. At the same time, according to the demonstration demand analysis of the nextgeneration Beidou satellite navigation system, the key technologies that need attention and research on the future navigations satellite attitude and orbit control system are given.

The Tianwen 1 Mars probe, designed to complete orbiting, landing and roving in one mission, is the first planetary exploration mission of China. The Tianwen1 probe is composed of an orbiter，a lander and a rover. The China Academy of Space Technology takes the overall development of the Tianwen 1 probe. This report introduces the mission characteristics and overview, specifically describes the design schemes of key parts and the results of flight, deep space communications, Mars capture, entry descent and landing(EDL), rover unlocking and driving away from the lander and rover exploration phases. This report also summarizes the technical achievements and innovations of the Tianwen 1 probe.

The requirements of the X ray astronomical satellite observation mission are analyzed in this paper. The requirements for observation modes, high precision positioning and alignment of sources, orbit, thermal control, telemetry and telecontrol, data transmission are refined. Observation mode including all sky survey, pointed observation and area observation is designed in this paper, which achieves the goal of all sky survey, galactic plane survey, important inertia area observation, opportunity target observation and gamma ray explosion. This technology has been applied in hard X ray modulation telescope.

This paper introduces the attitude control subsystem of China new generation GEO optical telemetry satellite and lists the technical specification of the key instruments. It describes the control strategy of Geo telemetry satellite focusing on high precision, high stability and smart maneuver, fully automatic sun avoiding in orbit adapting tilted camera baffle, earth velocity compensation and high precision pointing for observing location. The telemetry data verifies the compatibility of design and realization. This satellite’s successful flying makes a good foundation for the recent items.

This paper introduces the all phase autonomous quick rendezvous and docking technology and in orbit verification of Tianzhou 2 cargo spacecraft in China. First, two trends of rendezvous and docking development since the 21st century are introduced: autonomous and quick. Then, the all phase autonomous quick rendezvous and docking scheme of Tianzhou 2 cargo spacecraft and its main technical characteristics are given. Finally, the implementation plan of 5~8 h flight control of Tianzhou 2 cargo spacecraft and the implementation plan of flight control of one day delayed launch are presented, as well as the in orbit verification effect. The autonomous quick rendezvous and docking of Tianzhou 2 cargo spacecraft in orbit is the first fully autonomous quick rendezvous mission in the world, which laid a solid technological foundation for the Chinese space station project.

As a digital image of the real space station，the digital space station integrates multiple professional models such as energy，information，environment and thermal control，dynamics and control，and establishes a multi disciplinary simulation system at the module level and the whole station level to provide technical support for the long term flight control mission of the space station.Based on Modelica and FMI，the integration of digital space station dynamics and control simulation model is completed and successfully applied in space station flight control.

Tianwen 1 successfully achieved China’s first soft landing on the surface of Mars. The entry capsule GNC system is responsible for the attitude and orbit control during the EDL process of the entry capsule to ensure a safe landing on the surface of Mars. The flight phase division, system composition, scheme design and specific design for the EDL process of Tianwen 1 entry capsule GNC system are outlined in this paper. The actual flight results of the entry capsule GNC system during the EDL process are also provided.

With the distance of deep space exploration getting farther and farther, the current planetary rover operating mode using the teleoperation and partial autonomous movement cannot meet the needs of future scientific exploration, as the constraints of teleoperation capability and energy. Moreover, the future of deep space missions puts forward faster, lighter, more intelligent requirements for rover control systems. Firstly, the structure and capability of the autonomous navigation control system of the current lunar and Martian planetary rovers are compared and analyzed in this paper. Secondly, the constraints of the autonomous capability of the current control systems are given, and the architecture and design expectation are put forward for the autonomous navigation control systems of future planetary rovers. Thirdly, the autonomous level of the planetary rovers are divided preliminarily. Finally, the technical support and development planning guidance are provided for the research of autonomous navigation control system of planetary rovers in the future.

The Chang’E 5 (CE 5) guidance, navigation, and control (GNC) system is designed to reacize China’s first lunar sample collection and return mission. Based on the mission requirements and spacecraft characteristics, the GNC system is designed as a combination of three subsystems, which are the orbiter GNC subsystem, the returner GNC subsystem, and the lander and ascender module GNC subsystem. The CE 5 GNC system architecture design, working mode design and onboard flight results are presented. According to the flight results, the GNC system design is correct. Some key actions have been successfully performed, such as powered descent, taking off from lunar surface, rendezvous and docking, and reentry into the earth. Particularly, three missions are first realized, including the taking off from the lunar surface, rendezvous and docking on the lunar orbit, and reentry into the earth with lunar samples. The flight results also show that each system performance index meets the mission requirements.