Hovering Dual-Spin Vehicle Groundwork for Bias Momentum Sizing Validation Experiment

摘要

Angular bias momentum offers significant stability augmentation for hovering flight ve-hicles. The reliance of the vehicle on thrust vectoring for agility and disturbance rejection is greatly reduced with significant levels of stored angular momentum in the system. A me-thodical procedure for bias momentum sizing has been developed in previous studies. This current study provides groundwork for experimental validation of that method using an experimental vehicle called the Dual-Spin Test Device, a thrust-levitated platform. Using measured data the vehicle's thrust vectoring units are modeled and a gust environment is designed and characterized. Control design is discussed. Preliminary experimental results of the vehicle constrained to three rotational degrees of freedom are compared to simula-tion for a case containing no bias momentum to validate the simulation. A simulation of a bias momentum dominant case is presented.