The invention discloses a near-earth satellite redundant flywheel angular momentum autonomous management method, including the steps of S1. dividing given angular momentum increments of a flywheel group into an angular momentum increment of attitude control output by each flywheel in the flywheel group and an angular momentum increment of zero motion; S2. obtaining the central angular momentum of the flywheels; S3. converting a problem of solving flywheel group zero movement into a constrained quadratic form optimization problem, adopting QR decomposition to convert the constrained quadratic form optimization problem into an unconstrained optimization problem, and obtaining a zero movement angular momentum increment of each flywheel, so that the angular momentum of each flywheel approaches the central angular momentum; and S4. according to a relation between flywheel group null space after part of flywheels fail and flywheel group null space when no flywheel fails, completing angular momentum reconstruction of the flywheel group. The advantages of the method are that while the flywheel group generates given moment of force, the rotating speed of each flywheel can approach preset desired rotating speed, thereby preventing frequent zero passage or saturation of the rotating speed of flywheels and realizing on-line reconstruction of a whole system when part of the flywheels fail.