A Fast Trajectory Optimization Method for Aircraft Satisfied with Strict Time and Position Constraints

Abstract

The invention discloses a fast trajectory optimization method for an aircraft satisfying strict time and position constraints. Step 1: Setting parameters; the parameters in the quasi-state include the load at t 1 Time to orbit, the standard orbit point is r 1 ;Assume that through trajectory online replanning and adaptive guidance, the load is at t 2 Time to orbit, the actual orbit point is r 2 ;Step 2: define point coordinate system; coordinate system origin O P is the center of the earth, x p The axis is on the line connecting the center of the earth and the perigee of the target orbit, pointing to the perigee; Step 3: Based on the parameters and the point coordinate system in Step 1 and Step 2, and then using the concept of the eccentric point angle φ to calculate the aircraft from r 1 fly to r 2 time Δt; Step 4: Use step 1-3 and the iterative correction method of the second-stage power-on time of the core to correct the deviation of the satellite orbit entry time. It is used to solve the problem that the thrust of the high-thrust liquid rocket engine used in the launch vehicle cannot be adjusted, and the orbital point cannot be accurately controlled, that is, the orbital position cannot be constrained.

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...

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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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