###### Abstract  
A radar guidance system is a core component of a radar-guided air-to-air missile, and its tracking accuracy of airborne targets determines the operational effectiveness of said missile. To verify the tracking accuracy of the radar guidance system against an airborne target under the real flight conditions of the missile, an experimental verification system was implemented in this study. The mechanical, electrical, and bus interfaces of the verification system were examined. A tracking accuracy evaluation model of the seeker was designed based on the data obtained from the experiments using the proposed test method, and the tracking accuracy of the seeker in the typical state was analyzed.  
wireless measurement analysis; seeker; radar; radio frequency data; test and experiment +
Footnote  
adopted the monopulse semi-active homing guidance mode. When compared to second-generation missiles, its angle measurement accuracy and combat jamming countermeasure capability were significantly improved. Even though an omni-directional attack centered on the target was realized, the operation still relied on continuous illumination of the airborne radar. Additionally, with an obvious defect in the late separation of the carrier aircraft, while the missile is attacking the target, the survivability of the aircraft can be highly threatened [6; 7; 8; 9; 10]. The fourth-generation radar-guided air-to-air missile adopted the compound guidance system of inertial or satellite plus data link plus active radar, which offered a closed system for medium- and long-range attacks and significantly enlarged the combat distance. It is characterized by omni-directional attacks, all-weather day-and-night operations, and multi-target attacks. After adopting the anti-jamming integrated design of active radar guidance and guidance control systems, as well as multiple digital signal processing technologies, it exhibits a stronger anti-jamming capability. Meanwhile, the innovative design in the operational mode post-launch improved the survivability of the carrier aircraft. Additionally, it can receive guidance from another aircraft, which deepens the integration with the platform and combat system and realizes a substantial leap in combat operational mode [11; 12; 13; 14].  
In conclusion, a radar guidance system is a core component of a radar-guided air-to-air missile, which is responsible for the search, interception, and tracking of the target to attack. Meanwhile, it provides the missile guidance system with the necessary information to accomplish its tasks. During the evolvement of missiles, according to the design characteristics, working principle, and operational environment of the guidance system, the tracking accuracy requirements of its radar guidance system also differ. In this study, a \"target situational awareness\" test system was designed for the purposes of evaluating the target interception and tracking performance of the radar seeker during the post-launch flight, thereby verifying the mission reliability in terms of time sequence across the entire workflow, as well as uncovering potential problems to the maximum possible extent such as possible hardware failures and parameter mismatch of the missile in the flight environment. The bus interface, mechanical interface, electrical interface, power supply, data format, working time sequence, and other key technologies required for coordination between the carrier aircraft and pod were implemented. Furthermore, the test data analysis model was examined using the aforementioned technologies. Additionally, the feasibility of the test system was evaluated and the accuracy of airborne target tracking via a typical seeker was analyzed.