A solid rocket engine erosion combustion rapid parameter identification method
A technology for parameter identification and solid rockets, which is applied to rocket motor devices, machines/engines, mechanical equipment, etc., can solve problems such as the lack of low-cost parameter identification methods, and achieve the effects of wide applicability, simple and easy-to-understand methods, and cost reduction.
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[0045] This embodiment is a fast parameter identification method for erosive combustion of a solid rocket motor.
[0046] The rapid parameter identification method for erosion and combustion of solid rocket motors in this embodiment is to obtain test pressure data with erosion pressure peaks by manufacturing and designing a standard erosion test engine and a standard erosion propellant grain, and conducting a ground ignition test with the two. Finally, the parameter identification is carried out on the pressure data, and the unknown parameters in the propellant velocity erosion formula are obtained.
[0047] 1) Manufacture of standard propellant grains
[0048] The standard propellant grain designed for the erosion test is a cylindrical tubular charge with small meat thickness and full-surface burning or a cylindrical tubular charge with both ends coated on the inner and outer surfaces. Before the test starts, ensure that the basic burning rate given by the propellant manufac...
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