Rapid deduction and determination method for approach landing trajectory of RLV

Abstract

The invention relates to a rapid deduction and determination method for an approach landing trajectory of an RLV. The method comprises the steps that according to a standard design method for a nominal trajectory at a landing section of the RLV, a landing trajectory with a flight state to be deduced and inspected is provided; then, the height is divided at a certain interval, an Euler method and aerodynamic characteristics of the aircraft are utilized to iteratively estimate corresponding trimming attack angles and trimming control surfaces at all height portions in sequence, and therefore thespeed, flight trajectory inclination angle and other flight state parameters corresponding to each height portion can be correspondingly calculated. By means of the method, the influences of real-time deflection of the trimming control surfaces on the trajectory and attitude are considered in the trajectory deduction process, the interpolation principle is introduced in the process of solving thetrimming attack angle of a cross section at each height portion, and the deduction efficiency is greatly improved without any loss of accuracy.

Description

technical field [0001] The invention relates to a method for rapid deduction of landing trajectory and state high-precision estimation of a reusable aircraft (RLV), and belongs to the technical field of aircraft design. Background technique [0002] Reusable launch vehicles (RLV) are a kind of space shuttle vehicle, and will become a highly reliable vehicle for human beings to explore the universe cheaply and a military weapon for competing for space supremacy. Therefore, the major powers in the world continue to invest huge resources in its research and development, and conduct new research and exploration. [0003] The approach and landing section of the RLV must meet the constraints of dynamic pressure, overload, touchdown angle of attack and speed, otherwise it may cause damage to airborne equipment such as sensors or landing gear. When designing approach and landing trajectories, trajectory deduction and flight state estimation methods are important means to evaluate w...

AI Technical Summary

Problems solved by technology

[0003] The approach and landing section of the RLV must meet the constraints of dynamic pressure, overload, touchdown angle of attack and speed, otherwise it may cause damage to airborne equipment such as sensors or landing gear

When designing approach and landing trajectories, trajectory deduction and flight state estimation methods are important means to evaluate whether the designed trajectory can enable the aircraft to meet various constraints. However, the existing deduction and state estimation methods based on the nominal trajectory of the landing segment are generally It is a mathematical model based on three degrees of freedom, and does not consider the influence of the deflection of the rudder surface. In addition, if the estimation speed is increased, the search step size needs to be increased, but this will greatly reduce the estimation accuracy

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