Launching coordinate system strapdown inertial navigation track generator

• Main Authors: FANG YAN, CHEN KAI, LI SHUANGJIE, YANG TAO, ZENG CHENGZHI, RAN ZHIQIANG, LI ZHENHAO
• Format: Patent
• Language: Chinese; English
• Published: 21.06.2024
• Subjects: GYROSCOPIC INSTRUMENTS; MEASURING; MEASURING DISTANCES, LEVELS OR BEARINGS; NAVIGATION; PHOTOGRAMMETRY OR VIDEOGRAMMETRY; PHYSICS; SURVEYING; TESTING

The invention relates to a transmitting coordinate system strapdown inertial navigation track generator, and belongs to the field of inertial navigation. Comprising the following steps: solving the attitude, speed and position of the aircraft, the angular velocity output by a gyroscope and the specific force output by an accelerometer according to the initial state and the motion state of the aircraft; according to the invention, navigation parameters such as attitude, speed and position of an aircraft in a launching coordinate system and angular velocity information and specific force information measured by a carrier inertial element can be directly simulated; simulated information can be directly used for calculation of launching system inertial navigation or integrated navigation, a parameter conversion process existing when horizontal system navigation information is used is eliminated, and the efficiency of an algorithm is improved. 本发明涉及一种发射坐标系捷联惯导轨迹发生器，属于惯性导航领域。包括：根据飞行器的初始状态和运动状态求解飞行器的姿态、速度、位置和陀螺仪输出的角