A hardware-in-the-loop simulation system of a separation guiding mechanism

Abstract

A hardware-in-the-loop simulation system of a separation guide mechanism comprises a tooling bench, an engine simulation boundary of an upper stage, a shell section of a lower stage, a separation motion loading system, a load loading system, a separation motion control system and a separation motion data acquisition system. The engine simulation boundary of an upper stage is fixed on the tooling bench, and the shell section of a lower stage is sleeved with the upper engine simulation boundary through the separating motion guide mechanism. The separation motion loading system controls the separation of the lower stage housing section from the upper stage engine simulation boundary. The load loading system provides severe additional loads for the next shell segment. The split motion controlsystem provides a split signal to the split motion loading system and a load loading signal to the load loading system. The separation motion data acquisition system collects and analyzes the data inthe process of separation motion, and analyzes and evaluates the separation motion characteristics of the separation guide mechanism. The invention improves the development efficiency, shortens the development period and reduces the test cost.

Description

technical field [0001] The invention relates to a semi-physical simulation system of a separation and guidance mechanism, which belongs to the technical field of test simulation verification of aerospace separation and guidance mechanisms. Background technique [0002] At present, the flight mission of aerospace payloads is usually achieved through the launch of multi-stage launch vehicles. The connection and separation between the upper-stage engine and the lower-stage shell of a multi-stage launch vehicle is an important structural and functional element. The upper-stage engine and the lower-stage shell section are generally connected in the form of axial butt joint, and the larger-sized nozzle of the upper-stage engine is wrapped inside the lower-stage shell section. When the next sub-stage flight task is completed, the upper-stage engine is separated from the next-stage shell section. During the separation process, multiple sets of separation rockets inside the lower-st...

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Problems solved by technology

[0003] Traditionally, to solve the above requirements, the separation power is generally provided in the form of "real product + simultaneous ignition of multiple groups of separation rockets" in the open and safe outdoors for test verification. There are large site area occupied, long preparation period, high test cost, and verification schemes. Once unsuccessful, problems such as design repetition and test repetition will seriously affect the development progress and design efficiency

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