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Loitering munition high-precision combination navigation method

An integrated navigation and high-precision technology, which is applied in the field of high-precision integrated navigation of loitering missiles, can solve problems such as difficult to meet continuous, reliable and high-precision navigation requirements, cumbersome fixed ambiguity, and low navigation and positioning accuracy, and achieve reduction System computing complexity, avoiding solution ambiguity, and achieving real-time effects

Active Publication Date: 2016-01-13
JINLING INST OF TECH
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Problems solved by technology

The Tightly-coupled navigation method based on pseudo-range is affected by observation noise, and the accuracy of navigation and positioning is relatively low; the Tightly-coupled navigation method based on carrier phase has high positioning accuracy, but the ambiguity is fixed and cumbersome, and the real-time performance is poor. It is difficult to meet the requirements of continuous, reliable and high-precision navigation; at present, the ultra-tightly-coupled navigation method is still limited to theoretical technical research, and there are still a series of problems to be solved urgently in the application of distance engineering

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  • Loitering munition high-precision combination navigation method

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Embodiment

[0047] The embodiment proposes an application method of time-inter-satellite differential carrier phase in GPS / SINS tight integrated navigation. Firstly, the detailed dynamic model of 15-state GPS / SINS tight integrated navigation is given, and then the observation mathematical model based on carrier phase time-inter-satellite double difference observation is derived, and the Kalman filter is used for data fusion. The effectiveness of the new algorithm is verified by simulation and airborne measured data. The results show that: compared with the traditional pseudo-range tight integrated navigation algorithm, the time-inter-satellite differential carrier phase method can provide a meter-level positioning accuracy and a mm / s-level velocity accuracy for the cruise missile navigation system with short and medium endurance .

[0048] A high-precision integrated navigation method for loitering missiles, such as figure 1 , including the following steps:

[0049] S1. Use the informa...

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Abstract

The invention provides a loitering munition high-precision combination navigation method. The method comprises the following steps: calculating the strapdown inertial navigation position increment through using information resolved by using strapdown inertial navigation, and projecting the obtained position increment in the visual line direction of a satellite to obtain a predicted carrier wave phase temporal difference observed quantity; resolving through using a navigation satellite system GNSS receiver to obtain a carrier wave phase time-difference between satellites, and carrying out data fusion on the carrier wave phase time-difference between satellites and an strapdown inertial navigation SINS predicated carrier wave phase temporal difference through a Kalman filter to obtain an error obtained after combination navigation estimation; and carrying out error correction on the strapdown inertial navigation SINS combination navigation solution and an inertia sensor by using the error obtained after combination navigation estimation to obtain a next epoch of combination navigation solution. The method can provide a meter level positioning precision and a millimeter / second level speed precision for a loitering munition in a short time. The method has the advantages of simple calculation, avoiding of the resolving fuzziness, realization of the real time property of a navigation system, and strong practicality.

Description

technical field [0001] The invention relates to a high-precision integrated navigation method for a loitering missile. Background technique [0002] Loitering ammunition is the product of the combination of ammunition technology and UAV technology. It can patrol and fly above the target area and perform various combat missions. It is a development direction of precision-guided weapons in the future. As the combat distance and number of loitering missiles increase, higher requirements are placed on the accuracy and cost of the guidance system. The combination of micro-electromechanical systems (MEMS) with the advantages of low cost, small size, and high overload and global navigation satellite system (GNSS) forms a navigation system with complementary advantages, which can obtain high navigation accuracy at a relatively low cost and realize conventional Ammunition guidance. [0003] Most of the existing research on weapon systems uses high-precision navigation equipment, an...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/16G01C21/20
CPCG01C21/165G01C21/20
Inventor 吴有龙杨忠于继明徐楠杨荣根
Owner JINLING INST OF TECH
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