Design, calibration and error analysis of a piezoelectric thrust dynamometer for small thrust liquid pulsed rocket engines

TL;DR: In this paper, a dynamic calibration method of frequency response characteristics of high-pressure sensor is presented, where the pressure sensor was under high hydrostatic pressure in advance, then use the bullet impacted Hopkinson bar and generated quasi-δ function signal with small amplitude, which excited the sensor being calibrated.

TL;DR: In this article, a new approach to thrust measurement for pulse detonation engines was developed to account for the effects of system dynamics, which was applied to a pulse-detonation engine operating at 10 and 20 Hz.

TL;DR: This short paper describes some of these activities and appears as results start to come in from the Curiosity rover, which landed on Mars on the 6th of August, 2012, with over 20 piezoelectric and mechanically-resonant components on board.

TL;DR: In this article, the authors describe the design, development, and testing of a torsional-type thrust stand to evaluate the performance of a Torsional Type Thrust Stand.

TL;DR: In this article, an optical interferometric proximeter system (IPS) for measuring thrust and impulse bit of pulsed electric thrusters was developed, which can yield electromagnetic interference-free, high accuracy (<2% error) thrust measurements within a very wide range of impulses (100 μN to above 10 N) covering the impulse range of all known pulsed plasma thrusters.

TL;DR: A pendulum type balance has been designed and fabricated to characterize solid propellant micro-thrusters as discussed by the authors, where the thrust measurement system mainly consists of a rigid arm rotating freely around a pivot and a feedback control loop, and the deflection of the arm produced by the applied thrust is detected using a high frequency transmitter and antenna.

TL;DR: In this paper, a thrust stand was developed for performance measurements on pulsed plasma thrusters in the l-100 joule energy range, and used to determine the single-pulse impulse bit and efftciency of a coaxial PPT.

TL;DR: In this article, a 10 kW Hall thruster was characterized over a range of discharge voltages from 300-500 V and discharge currents from 15-23 A. This corresponds to power levels from a low of 4.6 kW to a high of 10.7 kW.