Minimum energy trajectory strict construction method considering influence of earth rotation

A construction method and technology of the earth's rotation, applied in the field of ballistic construction, can solve the problems of ballistic parameters other than energy, the increase and increase of the center distance between the launch point and the target point, etc.

Active Publication Date: 2020-07-31
ZIJINSHAN ASTRONOMICAL OBSERVATORY CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The idea of ​​iterative solution in Algorithm 1 is a reasonable idea to solve the dynamic change of the target point position, but the minimum energy ballistic construction formula in each iteration process does not take into account the two independent processes of dynamic motion law and earth rotation, so Algorithm 1 Only an approximate solution can be obtained, but a strict solution cannot be obtained. This has been verified by the calculation of the trajectory construction traversing the launch elevation angle mentioned in the invention of the patent No. 201910941400.5 "A Free Ballistic Construction Method with a Specified Launch Elevation Angle". Therefore , the ballistic parameters output by Algorithm 1 are not optimal in energy
In addition, the ballistic construction formula of Algorithm 1 takes the earth as a homogeneous regular sphere, and assumes that both the launch point and the target point are located on the surface of the regular sphere. The deviation of the ballistic structure caused by the two aspects of physics, the deviation increases with the increase of the range, and also increases with the increase of the distance between the launch point and the target point.
To sum up, Algorithm 1 is neither a strict construction method of the minimum energy trajectory, nor is it universal. It is not suitable for the situation where the distance between the launch point and the target point is not equal, and the algorithm fails when the launch point is located at the poles or above.

Method used

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  • Minimum energy trajectory strict construction method considering influence of earth rotation
  • Minimum energy trajectory strict construction method considering influence of earth rotation
  • Minimum energy trajectory strict construction method considering influence of earth rotation

Examples

Experimental program
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Effect test

Embodiment 1

[0152] Example 1: Launch time t of any given missile 0 , the geodetic coordinates of launch point A and target point B (see Table 2 for the specific parameters), construct the minimum energy free trajectory under the two-body motion model, and compare it with the trajectory construction method of ergodic launch elevation angle and the trajectory construction results of Algorithm 1.

[0153] Table 2. Example 1 (launch time: 18:45:20 on May 25, 2013, Beijing time)

[0154]

[0155]

[0156] Note: The convergence condition of iteration δ ν and δ T Take 1E-8 and 10μs respectively. In order to apply Algorithm 1, this example specially sets the geocentric distances of points A and B to be equal, but this setting is not a requirement of the patented algorithm.

Embodiment 2

[0157] Example 2: Launch time t of any given missile 0 and the geodetic coordinates of the target point B, the launch point A is located at the North Pole (see Table 3 for specific parameters), and the minimum energy free trajectory is constructed under the two-body motion model, and compared with the results of the ergodic launch elevation trajectory construction method.

[0158] Table 3. Embodiment 2 (launch time: 18:45:20 on May 25, 2013, Beijing time)

[0159]

[0160] Note: The convergence condition of iteration δ ν and δ T Take 1E-8 and 10μs respectively. In this example, the earth center distances of points A and B are also specially set to be equal.

[0161] Except above-mentioned known condition, the present invention has also used following geophysical constant:

[0162] Equatorial radius a of the reference ellipsoid e =6378136m.

[0163] Gravity constant μ=0.39860043770442×10 15 m 3 / s 2 .

[0164] The flatness of the earth f=1 / 298.25781.

[0165]The e...

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Abstract

The invention discloses a minimum energy trajectory strict construction method considering influence of earth rotation, which adopts an accurate geophysical model (considering earth oblateness and rotation) and can accurately construct a minimum energy trajectory between two three-dimensional geodetic points under a two-body motion model. Besides, the influence of earth rotation on the trajectorystructure is deeply excavated; the strict analytical solution of the minimum energy trajectory is found theoretically, and two small quantities of the difference value epsilon between the ratio of thegeocentric distance of the target point to the geocentric distance of the launching point and 1 and the perigee amplitude angle offset delta omega of the elliptical orbit are introduced, so that themethod has universality and a simple formula, and is a minimum energy free trajectory strict construction method suitable for any two space points.

Description

technical field [0001] The invention relates to the technical field of solving the ballistic structure of ballistic missiles under the framework of celestial mechanics, and in particular relates to a strict construction method of minimum energy ballistics considering the influence of the earth's rotation. Background technique [0002] The range of a missile refers to the distance measured along the great circle of the earth between the launch point and the impact point. It is the key factor for effectively attacking the target and the most important tactical indicator. For a certain type of missile, the maximum range depends on various factors such as engine performance, fuel performance, aerodynamic characteristics, ballistic characteristics, etc. It needs to master some difficult-to-know technical parameters and physical conditions, which cannot meet general ballistic research. and application requirements; when the position of the shutdown point is determined, the range o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/13G06F17/16
CPCG06F17/13G06F17/16
Inventor 徐劲杜建丽杨冬曹志斌马剑波
Owner ZIJINSHAN ASTRONOMICAL OBSERVATORY CHINESE ACAD OF SCI
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