Near-space hypersonic target trajectory prediction method

A technology of hypersonic speed and target trajectory, applied in geometric CAD, sustainable transportation, special data processing applications, etc., can solve the problems of difficult online estimation, large error, complex and changeable hypersonic target guidance law, etc.

Active Publication Date: 2020-11-13
BEIJING INST OF ELECTRONICS SYST ENG +1
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0005] In order to solve the problems in the prior art by means of online identification of guidance laws, fitting extrapolation or template matching and other methods to realize trajectory prediction, in the process of defense against hypersonic targets , the

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  • Near-space hypersonic target trajectory prediction method
  • Near-space hypersonic target trajectory prediction method
  • Near-space hypersonic target trajectory prediction method

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specific Embodiment approach 1

[0118] Specific Embodiment 1: This embodiment provides a hypersonic target trajectory prediction method in adjacent space, and the steps are realized through the following steps:

[0119] Step 1: decompose the obtained historical ballistic data into ballistic trend signal and ballistic cycle jump signal;

[0120] Step 2: Model the trend signal;

[0121] Step 3: Model the cycle-hopping signal;

[0122] Step 4: Superpose the trend signal model established in step 2 and the period jump signal model established in step 3 to obtain a complete parametric model of the ballistic trajectory, and then realize trajectory prediction based on the complete model extrapolation.

[0123] In this embodiment, in step 1, the obtained historical ballistic data is decomposed into a ballistic trend signal and a ballistic period jump signal by using an integrated empirical mode decomposition method. Hypersonic target ballistic data is a nonlinear, non-stationary signal, with obvious trends and per...

specific Embodiment approach 2

[0127] Specific embodiment two: this embodiment is to further limit the step one described in the specific embodiment one. In this embodiment, the specific content of the step one is: adopt the integrated empirical mode decomposition method to decompose the gained historical ballistic data into Ballistic trend signal and ballistic period jump signal, where the integrated empirical mode decomposition method is as follows:

[0128] Step 11: Add K groups of Gaussian white noise sequences G to the ballistic sequence X(n) k , get the noise-added signal X k (n), namely:

[0129] x k (n)=X(n)+G k (1)

[0130] In the formula, k=1,...,K

[0131] Step 1 and 2: Add noise signal X to each group k (n) Carry out EMD decomposition, obtain I intrinsic mode function IMF component and residual term:

[0132]

[0133] Step 13: Take the mean value of the output of K times EMD decomposition as the decomposition result of the integrated empirical mode decomposition:

[0134]

[0135]...

specific Embodiment approach 3

[0140] Specific embodiment three: This embodiment is to further limit the step two described in the specific embodiment one. In this embodiment, the specific content of the step two is: using the autoregressive (AR) modeling method to analyze the trend signal For modeling, the model order and model coefficients determine the modeling accuracy, and the autoregressive (AR) modeling method is as follows:

[0141] Step 21: Autoregressive model coefficient estimation;

[0142] Step 22: Autoregressive model order selection.

[0143] Other compositions and connection methods are the same as those in the second embodiment.

[0144] In this embodiment, the trend signal R D (n) is a linear, slow-varying, low-frequency signal, a stationary signal whose period and amplitude vary with time, so the autoregressive (AR) modeling method is sufficient to accurately ensure the stability and accuracy of the modeling.

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Abstract

The invention discloses a near-space hypersonic target trajectory prediction method. The method belongs to the field of near-space hypersonic target trajectory prediction. In order to solve the problems that in the prior art, trajectory prediction is achieved through methods such as guidance law online identification, fitting extrapolation or template matching, in the defense process of an approaching hypersonic speed target, a dynamic model of the target is unknown, and the hypersonic speed target guidance law is complex and changeable, and online estimation is difficult and an error is large, the obtained historical ballistic data is decomposed into the ballistic trend signal and the ballistic cycle jump signal; modeling is carried out on the trend signals respectively; modeling is carried out on the periodic jump signal; and finally, superposing the trend signal model established in the step 2 and the periodic jump signal model established in the step 3 to obtain a trajectory complete parameterized model, and realizing trajectory prediction based on complete model extrapolation. The method is mainly suitable for the aspects of hypersonic target transverse maneuvering trajectoryprediction, target speed prediction and the like.

Description

technical field [0001] The invention belongs to the field of trajectory prediction of a hypersonic target in a near space, and in particular relates to a method for predicting a trajectory of a hypersonic target in a near space. Background technique [0002] Near-space hypersonic aircraft refers to aircraft that fly in the airspace at an altitude of 20-100 km, have a flight Mach number greater than 5, and have the ability to perform rapid strike missions. Compared with traditional ballistic missile targets, this type of aircraft has the characteristics of fast speed, long range, strong maneuverability, and high strike accuracy. With the help of superior aerodynamic performance, this type of aircraft has powerful lateral maneuvering and vertical jumping maneuverability, posing a huge threat to modern defense systems. Accurate trajectory prediction is the basis for effective interception of hypersonic targets in near space. Therefore, research on trajectory prediction method...

Claims

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Application Information

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IPC IPC(8): G06F30/15
CPCG06F30/15Y02T90/00
Inventor 李君龙荆武兴胡玉东陈晓波陈赜霍明英
Owner BEIJING INST OF ELECTRONICS SYST ENG
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