A sub-micronewton level thrust stand is used to evaluate the performance of five different microthrusters. Using a torsional balance design, the JPL microthrust stand (μTS) is capable of measuring steady-state thrust as low as 1 μN with sub-micronewton resolution and an impulse as low as 1 μNs with sub-micronewton-second resolution. The μTS can support a test object with a mass as large as 10 k...

Laser ablation of a Near Earth Object (NEO) on a collision course with Earth produces a cloud of ejecta which exerts a thrust on the NEO, deflecting it from its original trajectory. The DE-STAR system provides thrust by illuminating an Earth-targeting asteroid or comet from afar with a stand-off system consisting of a large phased-array laser in Earth orbit. A much smaller version of the same s...

The success of the LISA project depends on the ability of the disturbance reduction system to shield the proof masses from all external forces and maintain tight pointing requirements relative to the other two spacecrafts. μN-thrusters are required to compensate for the solar radiation pressure acting on the spacecraft. The force noise from these thrusters must be low enough to not disturb the ...

The feasibility of using a stand alone Fluidic Thrust-Vectoring (FTV) system for the purpose of longitudinal trim of an unmanned aerial vehicle is the focus of the research presented in this paper. Since the fluidic thrust vectoring requires high pressure secondary air to deflect the engine exhaust gases, this research also provides an analytical toolset for preliminary sizing of a suitable sec...

Due to their size, small rotorcraft are vulnerable to external flow disturbances that are challenging to flight stability and control. This paper describes preliminary results from using onboard flow measurements to augment inertial sensors for attitude control. We derive a dynamic model that captures the aerodynamic effects of wind on a single degree-of-freedom tandem-rotor test stand. A pair ...

A variation of a hanging pendulum thrust stand capable of measuring the performance of an electric thruster operating in the vertical orientation is presented. The vertical orientation of the thruster dictates that the thruster must be horizontally offset from the pendulum pivot arm, necessitating the use of a counterweight system to provide a neutrally stable system. Motion of the pendulum arm...

Drag-free technology functions as the keystone for space-based gravitational wave detection satellites moving along a geodesic path, like Laser Interferometer Space Antenna (LISA) Pathfinder, to achieve ultra-high microgravity level. Several prerequisites micro-thrusters operated under drag-free technique include constantly adjustable thrust, high resolution, low noise and fast response time. A...

There is interest in using a helicon plasma source in propulsive applications as both an ion source and as a thruster. Developing a helicon thruster requires a performance baseline as a basis for future optimization and expansion. The thrust of a helicon is measured using an null-type inverted pendulum thrust stand at a pressure of 2x10 -5 Torr through the operating range of 215-840 W RF power,...