Hypersonic aircraft trajectory online prediction method based on parameter extrapolation
A hypersonic and prediction method technology, applied in prediction, neural learning methods, instruments, etc., can solve problems such as difficult to accurately characterize nonlinear laws, prediction model interference, and affect prediction performance, so as to improve prediction accuracy and good prediction performance , the effect of improving accuracy
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Embodiment 1
[0054] figure 1 A preferred embodiment of the present application is shown ( figure 1 A schematic flowchart of a method for online prediction of a hypersonic aircraft trajectory based on parameter extrapolation provided by the first embodiment of the present application) is shown. For the convenience of description, only the parts relevant to this embodiment are shown, and the details are as follows:
[0055] Step 1: Select hypersonic vehicle trajectory prediction parameters;
[0056] Step 2: estimating the trajectory prediction parameters of the hypersonic vehicle based on the dynamic tracking model;
[0057] Step 3: denoising the hypersonic vehicle trajectory prediction parameters based on the set empirical mode decomposition, constructing a data set, and training a pre-built attention time series neural network model according to the data of the data set;
[0058] Step 4: Input the data set into the trained attention time series neural network model to obtain the predicte...
Embodiment 2
[0125] In this embodiment, the above method is verified in combination with a specific calculation example, and the process is as follows:
[0126] The present invention designs the following simulation experiment scenario: a hypersonic aircraft is boosted to a height of 50km by launching a rocket, then continues to rise to the highest point by inertia, and then re-enters the atmosphere, enters the jumping and gliding stage, and maneuvers according to a preset mode. Assume that the geographic coordinates of the radar site are [12°, 0.5°, 1km], the sampling interval is 0.5s, the azimuth and pitch errors are 0.15°, and the distance error is 200m. The tilt angle of the hypersonic vehicle is always 5°, and the angle of attack is set as a continuous function related to the speed according to formula (20), such as image 3 shown. Unscented Kalman (UKF) is used for filtering in the tracking process. Target maneuver trajectories, observation trajectories such as Figure 4 shown. I...
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