A Lorentz force magnetic levitation universal stability platform was proposed in response to the pressing need for universal agility and ultra-precise pointing performance of spacecraft payload in complex space missions. The design and analysis of double-magnetic circuit rotating Lorentz force magnetic bearings were conducted, and the moving coil rotor scheme was chosen. The four-hanging lug-shaped coils of the rotor assembly were wound in pairs and glued into the grooves on both sides of the skeleton axial direction. The stator components are arranged in pairs in parallel with a common rotating shaft and a double annular axial magnetized magnetizer to create a uniform and stable magnetic density, and provide a circumferential dual-channel symmetrical working air gap for the agile maneuver of the load compartment. Based on the equivalent magnetic circuit method, the magnetic density model of the air gap was established, and the linearity of the magnetic density was defined from the two aspects of the uniformity and fluctuation rate of the magnetic density of the air gap, and then the rotor rotation dynamics was modeled and the rotational moment model was constructed. Utilize Maxwell's finite element method to establish a finite element model for rotary magnetic bearings and conduct the simulation, the results demonstrate that the magnetic density at the center position of the air gap rotation envelope of the rotating magnetic bearing scheme can reach 685.624 mT, and the circumferential magnetic density uniformity is 99.72%. This significantly improves the uniformity of air gap magnetic density, avoids the limitations of radial magnetization schemes such as air gap magnetic density attenuation and longitudinal magnetic field diffusion, and effectively enhances the stability and pointing accuracy of the payload bay under rotating conditions.

To improve the angular momentum envelope analysis efficiency of typical gimbal-type momentum exchange devices such as single-gimbal control moment gyroscope (SGCMG), double-gimbal momentum wheel (DGMW), and magnetically suspended control and sensing gyroscope (MSCSG), a gimbal equivalent-based angular momentum envelope analysis method of gimbal-type momentum wheel was proposed. The similarities and differences of angular momentum exchange principles between SGCMG and DGMW based on a mechanical solid gimbal and MSCSG based on a magnetic levitation micro-gimbal. The equivalent coefficients between radial/axial angular momentum components of SGCMG and MSCSG were studied and designed. The biorthogonal solid gimbal of SGCMG was used to construct the equivalent model of the MSCSG micro-gimbal. The angular momentum expressions of ergodic methods for MSCSG and DGMW were compared, and the applicability of the gimbal equivalent method in the angular momentum analysis of DGMW was analyzed. The error of the gimbal equivalent method was quantified to prove that the absolute error and the direction error of angular momentum calculated by the gimbal equivalent method are both less than one thousandth compared with the traditional ergodic method. The parameter dimensions of the two methods were analyzed to prove the rapidity of the gimbal equivalent method. The angular momentum envelopes of MSCSG and DGMW were simulated and compared based on the traditional ergodic method and the gimbal equivalent method, respectively, which proved the effectiveness of the method. This method has a wider application in angular momentum envelope analysis of MSCSG groups.