Experimental study of a low-thrust measurement system for thruster ground tests

Abstract The results of experimental study of pressure variations inside core box during resin bonded sand filling process are reported. The test core specimens were produced using Laempe® Test Specimen Curing Machine L 1. A special pressure measurement system was designed and built with safety and portability requirements of the foundry environment. Special experiments were conducted to establish the effect of sand deposition on vent permeability.

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Development of Direct Thrust Measurement System for the Completely Electrodeless Helicon Plasma Thruster

Plasma and Fusion Research ◽

10.1585/pfr.9.3406025 ◽

2014 ◽

Vol 9 (0) ◽

pp. 3406025-3406025 ◽

Cited By ~ 12

Author(s):

Daisuke KUWAHARA ◽

Yushi KOYAMA ◽

Shuhei OTSUKA ◽

Takamichi ISHII ◽

Hiroki ISHII ◽

...

Keyword(s):

Measurement System ◽

Helicon Plasma ◽

Plasma Thruster ◽

Thrust Measurement

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Development and Validation of an On-Wing Engine Thrust Measurement System

Volume 1: Aircraft Engine; Fans and Blowers; Marine; Honors and Awards ◽

10.1115/gt2017-63277 ◽

2017 ◽

Cited By ~ 4

Author(s):

Marc Bauer ◽

Jens Friedrichs ◽

Detlev Wulff ◽

Christian Werner-Spatz

Keyword(s):

Measurement System ◽

Standard Procedure ◽

Flight Test ◽

Engine Thrust ◽

Thrust Measurement ◽

Ground Test ◽

Engine Maintenance ◽

The Cost ◽

Development And Validation ◽

Engine Condition

Maintenance on aircraft engines is usually performed on an on-condition basis. Monitoring the engine condition during operation is an important prerequisite to provide efficient maintenance. Engine Condition Monitoring (ECM) has thus become a standard procedure during operation. One of the most important parameters, the engine thrust, is not directly measured, however, and can therefore not be monitored, which makes it difficult to distinguish whether deteriorating trends e.g. in fuel comsumption must be attributed to the engine (e.g. due to thermodynamic wear) or to the aircraft (e.g. due to increased drag). Being able to make this distinction would improve troubleshooting and maintenance planning and thus help to reduce the cost of ownership of an aircraft. As part of the research project APOSEM (Advanced Prediction of Severity effects on Engine Maintenance), Lufthansa Technik (LHT) and the Institute of Jet Propulsion and Turbomachinery of Technische Universität Braunschweig develop a method for direct measurement of engine thrust during the operation. In this paper, the design process of the On-Wing (OW) Measurement System is presented, including the validation in labratory tests, the mechanical and thermal calibration as well as the final ground test during an engine test run at LHT test cell and the work on the flight test certification.

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The thrust measurement system research for combined nozzle in small space

Transactions of the Institute of Measurement and Control ◽

10.1177/0142331218793485 ◽

2018 ◽

Vol 41 (4) ◽

pp. 1149-1159

Author(s):

Yonghua Lu ◽

Jing Li ◽

Xiang Zhang ◽

Yang Li

Keyword(s):

Measurement System ◽

Force Sensor ◽

Test Method ◽

Small Space ◽

System A ◽

Calibration Experiment ◽

Different Types ◽

Thrust Measurement ◽

Nozzle Thrust ◽

Thrust Forces

For measuring the thrust of combined nozzles in satellite thruster with a small space, the test method that the nozzle directly sprays on the load baffle is employed in this paper. The key problem is how to design the positions of 10 load baffles and how to construct the measurement system. A set of complete and automatic nozzle thrust measurement system is designed and built, and the influence of the load baffle applied on the flow field of nozzles is analyzed using the software FLUENT. Furthermore, the load surface locations of the sensors for the different types of nozzles are analyzed. We draw the conclusion that the load baffle position should range from 4–8 mm for the I-type nozzle and range in 6–12 mm for II-type and III-type nozzle. The correction coefficients of the thrust forces for all channels of the measurement system are determined in the calibration experiment. The uncertainty of measurement system is estimated and the error source of the measurement system is traced. We found that the systematic uncertainty is mainly contributed by the A-type uncertainty which is related with the nozzle dimension and its inner structure. The B-type uncertainty of system is contributed by the force sensor.

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