Aircraft rapid trajectory optimization method meeting strict time and position constraints

Abstract

The invention discloses an aircraft rapid trajectory optimization method meeting strict time and position constraints. The aircraft rapid trajectory optimization method comprises the steps of: step 1,setting parameters, wherein the parameters in a quasi-state comprise that the load is injected into a track at time t1, and a standard injection point is r1; supposing that through track online replanning and self-adaptive guidance, the load is injected into the track at time t2, and an actual injection point is r2; step 2, defining a point coordinate system, wherein an origin OP of the coordinate system is the geocenter, and an xp axis is on a connecting line of the geocenter and a target track perigee and points to the perigee; step 3, based on the parameters and the point coordinate systems in the step 1 and the step 2, calculating time delta t of an aircraft flying from r1 to r2 by utilizing the concept of an approximate point angle phi; and step 4, correcting the orbit injection timedeviation of a satellite by using the steps 1-3 and a core secondary secondary startup time iterative correction method. The problems that the thrust of a high-thrust liquid rocket engine applied toa carrier rocket cannot be adjusted, the orbit injection point cannot be accurately controlled, and in other words, the orbit injection position cannot be restrained are solved.

Description

technical field [0001] The invention belongs to the field of aircraft trajectory optimization and guidance; in particular, it relates to an aircraft fast trajectory optimization method satisfying strict time and position constraints. Background technique [0002] Since the Soviet Union launched the first artificial earth satellite in human history in the 1950s, the space for human activities has expanded from the atmosphere to outer space, and the development of space has also begun to expand rapidly. basis for proceeding. In order to accurately send the payload into the target orbit, the high-precision guidance technology of the launch vehicle has been widely concerned by scholars at home and abroad. Over the years, guidance methods such as perturbation guidance, closed-circuit guidance, and iterative guidance have been proposed and developed rapidly. At the same time, online trajectory planning algorithms represented by convex optimization have also been widely studied an...

AI Technical Summary

Problems solved by technology

[0003] The present invention provides a fast trajectory optimization method for aircraft satisfying strict time and position constraints, which is used to solve the problem of high-thrust liquid rocket engines used in launch vehicles. Constraint problem

For the orbit-entry mission where the payload is a geosynchronous orbit satellite, we cannot simply consider sending it into the target orbit, but must strictly restrict the geosynchronous satellite from entering the sky above the predetermined point, otherwise it is easy to cause signal interference with other geosynchronous orbit satellites

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