The invention discloses a
spaceflight propulsion chamber additive manufacturing
combustion channel wall thickness uniformity control method, which comprises the following steps: S1, establishing a three-dimensional geometric model and carrying out layered
slicing to generate an initial
processing control parameter set; s2, constructing a thermal echo spectrum before printing the first layer, and correcting
control parameters of the first layer; s3, generating a wall thickness error graph of the current layer based on the data of the previous layer, and constructing a wall thickness error
potential energy field graph; s4, constructing a target scanning density function, solving a two-dimensional Monge-Amprore equation to generate a path potential function, and generating a quasi potential streamline field; s5, inputting the data of the current layer into the wall thickness prediction neural
network model, and outputting a wall thickness deviation prediction value of the next layer; s6, updating the wall thickness error graph of the next layer according to the wall thickness deviation predicted value, and dynamically adjusting the
control parameters; and S7, circularly executing the steps S3 to S6 until the printing task is completed. According to the method, thermal response modeling and a neural
network model are fused, and dynamic uniformity control over the wall thickness of the
combustion channel is achieved.