空间光学导航敏感器技术综述(特 邀)

Significance With the rapid advancement of deep space exploration, on-orbit servicing, and constellation networking missions, the demand for high-precision and highly autonomous navigation capabilities of space vehicles is continuously increasing. Optical navigation technology, owing to its advantages of high accuracy, complete autonomy, rich information acquisition, and strong environmental adaptability, has become a critical means for achieving autonomous spacecraft operations. This paper reviews the core component of such systems-spaceborne optical navigation sensors. The classification methods, development status, key technical characteristics, and typical applications of these sensors are systematically summarized. Furthermore, the current challenges and future development trends are analyzed, providing a valuable reference for related research and engineering applications. Progress Star trackers achieve autonomous, high-precision, three-axis attitude determination for spacecraft through the imaging, detection, and identification of celestial stars. As the most accurate attitude measurement instrument currently available, the star tracker is the primary determinant of a spacecraft’s on-orbit orientation precision. Since the turn of the 21st century, rapid advancements in detector technology, optical design, manufacturing processes, and information processing have led to a transformative leap in overall performance. Global developments in star tracker technology have yielded significant improvements in accuracy, dynamic performance, updating rates, and structural miniaturization, resulting in a diverse and robust product ecosystem. Currently, star trackers can be generally categorized by their specific application scenarios into three primary classes: high-accuracy, high-dynamic, and ultra-lightweight star trackers. Based on the performance metrics of various models in recent years, it is evident that domestic star tracker technology in China has undergone intensive development. Across key performance indicators, these systems have achieved state-of-the-art performance levels on par with global leaders. Sun sensor provides precise measurements of Sun’s orientation to facilitate stable attitude control. Based on signal output characteristics, Sun sensors can be generally categorized into three primary architectures: 0-1 Sun sensors, analog Sun sensors, and digital Sun sensors. While the global development of Sun sensor technology began in the early stages of space exploration, domestic advancements in China have accelerated significantly in recent years. Numerous research institutions and industrial entities have successfully developed a wide array of sun sensors tailored for diverse mission profiles. Current performance metrics demonstrate that domestic capabilities have reached parity with established international benchmarks. Near-field celestial body sensors are a class of navigation instruments designed to observe planets, satellites, asteroids, and other near-field celestial objects. By processing geometric center or limb information, these sensors determine the position vector of the target body relative to the spacecraft. As the earliest iteration of celestial body sensors, Earth sensors were primarily developed for Earth-observation missions, measuring Earth vector by detecting optical radiation from the planet and its atmosphere. With the expansion of deep-space exploration, the target objects for these sensors have diversified to include Moon, Mars, Jupiter, and various planetary satellites, as well as asteroids and comets. In the context of deep-space missions, celestial body sensors are predominantly utilized during the transfer and capture phases. Optical navigation was first implemented for lunar exploration during the American Apollo 8 mission in 1968. In China, lunar exploration is conducted through the Chang’e lunar exploration program, which has successfully executed six missions to date. During lunar orbit operations, Chang’e-1 utilized an ultraviolet lunar sensor to determine the lunar vector, enabling attitude and position estimation while providing a reference for inertial measurement units. Extensive international missions have been conducted targeting Mercury, Mars, Jupiter, Saturn, and various small solar system bodies. An analysis and categorization of the sensor parameters employed in these missions are summarized in Table 5. The data indicates that performance specifications for celestial body sensors vary significantly depending on the specific mission requirements, operational phases, and target characteristics. Looking forward, the primary developmental trajectory for these sensors focuses on achieving higher navigation precision for specialized deep-space missions. Concurrently, the research and development of more generalized celestial body sensors-capable of adaptation across diverse deep-space exploration scenarios-represents a critical future objective. Landmark sensors are a class of navigation instruments that facilitate localization by detecting surface features of celestial bodies. The fundamental operational principle is terrain-relative navigation (TRN), which determines the relative position and attitude of a spacecraft by correlating detected landmark data with pre-stored onboard landmark databases. The TRN techniques employed by landmark sensors are generally categorized into two methodologies. One is non-specific terrestrial feature image matching, which utilizes general surface imagery to provide relative pose information. The other is crater matching, which utilizes identified impact craters to provide absolute pose information. The performances of the United States’ Perseverance rover and Japan’s SLIM probe are analyzed. Although pulsar navigation technology has not yet been widely deployed in operational space missions, significant progress has been achieved through both theoretical research and experimental validation. Scientists from nations including China and the United States have successfully conducted in-orbit pulsar navigation experiments on platforms such as the international space station, China’s Tiangong-2 space laboratory, and the hard X-ray modulation telescope satellite. These experiments have verified the fundamental feasibility of pulsar navigation technology and established a framework for future practical implementation. Conclusions nd Prospects From an application standpoint, diverse optical sensors fulfill distinct roles: star trackers excel in precision attitude determination; Sun and Earth sensors remain indispensable for LEO and planetary missions; celestial body and landmark sensors offer unique advantages for small-body exploration and landing; and pulsar sensors provide high potential for long-duration autonomous deep-space navigation. Together, they form a comprehensive optical navigation ecosystem. Technologically, these sensors are evolving toward higher precision, enhanced intelligence, and broader applicability. Driven by breakthroughs in image processing, deep learning, and advanced hardware, significant gains have been made in measurement accuracy, environmental adaptability, system integration, and reliability. Future development trends are primarily focused on three areas: multi-source information fusion, mission generalization, and miniaturization with low power consumption.