The invention discloses a
momentum wheel mounting structure optimization and
verification method suitable for in-
orbit vibration source frequency avoidance, and the method comprises the steps: determining whether the
momentum wheel generates
resonance at a normal working rotating speed or not through the response measurement of the speed increasing process of the
momentum wheel under the condition of a free boundary of a whole
satellite, and further generating disturbance vibration to other sensors; establishing a
system-level whole
satellite model containing an
assembly or a local
simulation model capable of reflecting installation local rigidity, and carrying out
modal analysis; the method comprises the following steps: under limited space constraints, carrying out operation
efficacy and reinforcement state
simulation iteration without disassembling a product, determining a reinforcement mode direction according to a formation, determining specific parameters according to frequency, and carrying out convergence to obtain a lightest, most efficient and operable integrated lightweight reinforcement structure under different momentum wheel mounting positions; and performing reinforcement design to the whole
satellite, performing momentum wheel acceleration process response measurement under the condition of the free boundary of the whole satellite, determining the
local structure frequency of the reinforced momentum wheel according to the
formant occurrence frequency, and determining whether the in-
orbit frequency avoidance reinforcement design meets the requirement or not.