Dynamic skip reentry vehicle aiming point adjustment method

Abstract

The invention discloses a dynamic skip reentry vehicle aiming point adjustment method. The method includes: calculating dimensionless forward speed U1 according to secondary reentry point speed and path angle obtained by forecast calculation; calculating maximum range R1 according to aircraft lift-drag ratio and minimum heeling angle data; calculating minimum range R2 according to overload design parameters in the secondary reentry phase; calculating secondary reentry range capacity level R according to corridor design parameters; calculating dynamic adjustment amount deltaR according to distance to go RTG from the secondary reentry point to the parachute-opening point and the secondary reentry range capacity level R. The secondary reentry range capacity is quickly predicated by means of analysis, linking of the primary reentry phase and the secondary reentry phase is realized, calculated amount for numerical prediction is reduced, and parachute-opening point control accuracy is improved. The method can be conveniently applied to guidance of reentry flight of the aircrafts with low lift-drag ratio at the second cosmic velocity.

Description

technical field [0001] The invention relates to a method for dynamically adjusting the aiming point of a jumping aircraft, especially a calculation method for adjusting the guidance law to the expected range before the aircraft jumps out of the atmosphere during the initial re-entry stage, which can be directly applied to use after re-entry at a speed higher than the local circular orbit. The lift adjustment realizes the reentry guidance of the aircraft with jumping trajectory. Background technique [0002] The speed of the lunar exploration and return vehicle is extremely high. When it reaches the vicinity of the earth (below 120km, after entering the dense earth's atmosphere), its ground speed will be much greater than the local circular orbit speed. For this type of aircraft, even if its own lift and drag are relatively small, it can still achieve a large flight range through a jumping trajectory, thereby ensuring the geometric constraint relationship between the re-entry...

AI Technical Summary

Problems solved by technology

However, numerical prediction will bring a large computational burden to the on-board computer, especially in the initial reentry stage. If the numerical prediction method is used to calculate the final landing point, the calculation cost will more than double according to conservative estimates.

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