Launching coordinate system strapdown inertial navigation track generator
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 speci...
Saved in:
Main Authors | , , , , , , |
---|---|
Format | Patent |
Language | Chinese English |
Published |
21.06.2024
|
Subjects | |
Online Access | Get full text |
Cover
Loading…
Summary: | 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 |
---|---|
Bibliography: | Application Number: CN202410308523 |