A torsional thrust stand, calibrated for impulse bits in the range of $0.1–0.5\mathrm{mN}\cdot \mathrm{s}$, was used to measure impulse bits from a metal plasma thruster. Impulse data were obtained on roughly 1400 shots, with metal plasma thruster targets of molybdenum, niobium, palladium, aluminum, and carbon. Model predictions (based on a simple circuit model and published plasma parameters) were validated by data from the calibrated torsional thrust stand. Over a typical 50-shot firing sequence, the impulse bits measured showed a coefficient of variation of approximately 5%. This implies that individual impulse bits of about $0.4\mathrm{mN}\cdot \mathrm{s}$ can be imparted to a satellite with $\pm 5\%$ variation about the mean in a total impulse burst of $20\mathrm{mN}\cdot \mathrm{s}$. For a 20 kg satellite, this would result in a velocity increment $\mathrm{\Delta }V$ of just $1\mathrm{mm}/\mathrm{s}$, enabling very precise attitude control and fine positioning control of nano- and microsatellites. The metal plasma thruster uses solid metal propellant and hence requires no liquids, gases, flow valves, or flow controls and has no moving parts. Total impulse approximately $5000(\mathrm{N}\cdot \mathrm{s})/\mathrm{liter}$ provides orbit raising and drag compensation capability.

扭转推力架，已针对以下范围内的脉冲钻头进行了校准： $0.1–0.5\mathrm{牛顿}\cdot \mathrm{s}$用来测量来自金属等离子推进器的脉冲钻头。脉冲数据是在大约1400次枪击中获得的，其金属等离子推进器目标为钼，铌，钯，铝和碳。模型预测（基于简单的电路模型和公开的等离子体参数）已通过来自校准的扭转推力机架的数据进行了验证。在典型的50发射击序列中，测得的脉冲位显示出约5％的变化系数。这意味着单个脉冲位约为$0.4\mathrm{牛顿}\cdot \mathrm{s}$ 可以用 $\pm 5％$ 总脉冲爆发中均值的方差 $20\mathrm{牛顿}\cdot \mathrm{s}$。对于20公斤的卫星，这将导致速度增加$\mathrm{\Delta }V$ 只是 $\mathrm{1个}\mathrm{毫米}/\mathrm{s}$，可以对纳米和微卫星进行非常精确的姿态控制和精细定位控制。金属等离子推进器使用固体金属推进剂，因此不需要液体，气体，流量阀或流量控制装置，并且没有活动部件。总冲量约$5000（\mathrm{ñ}\cdot \mathrm{s}）/升$ 提供升轨和阻力补偿功能。