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...
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Format | Patent |
Language | Chinese English |
Published |
21.06.2024
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Abstract | 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 |
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AbstractList | 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 |
Author | RAN ZHIQIANG FANG YAN CHEN KAI ZENG CHENGZHI LI ZHENHAO LI SHUANGJIE YANG TAO |
Author_xml | – fullname: FANG YAN – fullname: CHEN KAI – fullname: LI SHUANGJIE – fullname: YANG TAO – fullname: ZENG CHENGZHI – fullname: RAN ZHIQIANG – fullname: LI ZHENHAO |
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DocumentTitleAlternate | 一种发射坐标系捷联惯导轨迹发生器 |
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Snippet | The invention relates to a transmitting coordinate system strapdown inertial navigation track generator, and belongs to the field of inertial navigation.... |
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SubjectTerms | GYROSCOPIC INSTRUMENTS MEASURING MEASURING DISTANCES, LEVELS OR BEARINGS NAVIGATION PHOTOGRAMMETRY OR VIDEOGRAMMETRY PHYSICS SURVEYING TESTING |
Title | Launching coordinate system strapdown inertial navigation track generator |
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