Discrete simulation method for large rocket take-off drift

Abstract

The invention provides a discrete simulation method for a large rocket take-off drift. The method comprises the steps of (1) building a three-dimensional model of a rocket, a mobile launch platform and a ground facility on the mobile launch platform, and carrying out assembly location according to an actual launch state; (2) carrying out simulation on a time period from rocket take-off to attention, obtaining a rocket take-off altitude, maximum drift amount and roll attitude data within the time period; and (3) carrying out discrete simulation on the time period of attention and carrying out the following processing on every moment after discretization: (3.1) searching the rocket take-off altitude, the maximum drift amount and the roll attitude data corresponding to the moment from the result in the step (2), (3.2) fabricating a circumference path along a lunching axis by employing the rocket launching axis as the circle center and the maximum drift amount as the radius and combining the roll attitude data of the rocket at the moment according to the maximum drift amount data at the moment and (3.3) calculating and recording the minimum distance between the tail part of the rocket and all attention objects according to the obtained circumference path.

Description

technical field [0001] The invention relates to digital prototype design, assembly and interference analysis technology of aerospace products, and belongs to the field of digital design and system simulation of aerospace products. Background technique [0002] The launch test of the large launch vehicle CZ-5 was carried out at the Hainan launch site, using ground equipment such as movable launch platforms and tail end service towers. Due to the influence of shallow winds in Hainan, the rocket deflects and drifts to a certain extent when it takes off and leaves the tower. It is necessary to simulate and predict the drift of the rocket's take-off time in advance to find out the dangerous distance and the risk position where interference may occur. The design takes into account the rocket's take-off safety. [0003] In analyzing the possible collision of the rocket with ground equipment such as the active launch platform and the tail service tower due to drift at the moment of...

AI Technical Summary

Problems solved by technology

The disadvantages of this planar analysis method are: 1) The rocket is surrounded by ground equipment. This method can only analyze a single direction at a time, and cannot perform a 360-degree comprehensive analysis. It is very likely to miss the danger of certain directions. The distance and analysis cost increase with the increase of the analysis direction, which consumes time and manpower; 2) Manual observation of dangerous distances in two-dimensional drawings will bring in subjective factors, and there are risks of missing items and misreading; 3) Traditional analysis When dealing with the drift direction, the most likely wind direction is often selected according to the data statistics, and the drift direction calculated based on this is used for subsequent distance inspection and verification. Since the wind direction is difficult to predict, the drift direction of the rocket is often compared to the drift amount. The size of is more unpredictable, and traditional analysis methods cannot meet the requirements for simulation verification of arbitrary drift directions

Due to the impact of the shallow wind on takeoff, the large rocket will be subject to wind force or error offset in an uncertain constraint direction. Considering that the traditional continuous simulation method based on attitude control data interpolation cannot predict the deviation in each direction, the attitude control data must be completed. Frame discretization as the basis for simulation

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