Method of determining boundary of drag acceleration corridor of glide vehicle

Abstract

The invention discloses a method of determining a boundary of a drag acceleration corridor of a glide vehicle. The method comprises the following steps: expressing a second derivative S'' (x) of a cubic spline interpolation function S (x) as a linear function on each interpolation interval, and performing quadratic integral on the second derivative S'' (x) to obtain an expression of the cubic spline interpolation function S (x); taking the derivative of the cubic spline interpolation function S (x), and establishing a relation of a second derivative at the adjacent nodes according to the characteristic that a first derivative is continuous at an interpolation node; respectively deriving endpoint equations according to three different boundary conditions, so as to establish a system of linear equations for the cubic spline interpolation function S (x) at each node second derivative value Mj (j=0,1, to n), solving the system of linear equations to obtain the expression of the cubic spline interpolation function S (x) as the interpolation result.

Description

technical field [0001] The invention relates to the technical field of data processing, in particular to a method for determining the boundary of a drag acceleration corridor of a gliding aircraft. Background technique [0002] The re-entry corridor of the gliding flight of a hypersonic vehicle refers to the area determined by two Kepler orbits at different altitudes that the spacecraft returning to the earth must pass through when re-entering the atmosphere. For re-entry corridors with unlimited landing zones, the velocity of the spacecraft when it enters the atmosphere can be converted into the perigee altitude of the Kepler orbit. A Kepler orbit with a higher perigee is the upper boundary of the re-entry corridor, a Kepler orbit with a lower perigee is the lower boundary of the re-entry corridor, and the difference between the heights of the two perigees is the width of the re-entry corridor. [0003] In the prior art, the reentry corridor of the gliding flight of a hype...

AI Technical Summary

Problems solved by technology

However, since the drag acceleration corridor cannot be expressed analytically, it can only be calculated point by point by numerical calculation

There is a lack of good methods in the prior art to approximate the drag-acceleration corridor as a function of energy

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