Thrust Efficiency on an Idealized Deformable Sail

2014 ◽  
pp. 457-467
Author(s):  
Alexandra B. Artusio-Glimpse ◽  
Grover A. Swartzlander
Keyword(s):  
Thrust Efficiency

Power management of vessel propulsion system for thrust efficiency and emissions mitigation

2016 ◽  
Vol 161 ◽  
pp. 124-132 ◽  
Author(s):  
Feiyang Zhao ◽  
Wenming Yang ◽  
Woei Wan Tan ◽  
Wenbin Yu ◽  
Jiasheng Yang ◽  
...  
Keyword(s):  
Power Management ◽  
Propulsion System ◽  
Emissions Mitigation ◽  
Thrust Efficiency

scholarly journals Numerical Optimization of Thrust Efficiency of Propulsion in Fluid using a Fin with Variable Stiffness

2016 ◽  
Vol 5 (1) ◽  
pp. 1-9 ◽  
Author(s):  
Masataka Nakabayshi ◽  
Yusuke Yamaguchi ◽  
Wataru Yamazaki
Keyword(s):  
Numerical Optimization ◽  
Variable Stiffness ◽  
Thrust Efficiency

scholarly journals Improvement of thrust efficiency of laser fusion rocket with shaped target

2008 ◽  
Vol 112 (4) ◽  
pp. 042079
Author(s):  
N Matsuda ◽  
R Kawabuchi ◽  
Y Kajimura ◽  
H Nakashima ◽  
Y P Zakaharov
Keyword(s):  
Laser Fusion ◽  
Thrust Efficiency

Thrust Efficiency of Powered Lift Systems

1987 ◽  
Author(s):  
John L. Loth ◽  
Mathew Funk
Keyword(s):  
Thrust Efficiency

scholarly journals Microplasma thruster for ultra-small satellites: Plasma chemical and aerodynamical aspects

2008 ◽  
Vol 80 (9) ◽  
pp. 2013-2023 ◽  
Author(s):  
Yoshinori Takao ◽  
Takeshi Takahashi ◽  
Koji Eriguchi ◽  
Kouichi Ono
Keyword(s):  
Microwave Power ◽  
Attitude Control ◽  
Specific Impulse ◽  
Experimental Results ◽  
Station Keeping ◽  
Plasma Chemical ◽  
Small Satellites ◽  
Thrust Efficiency

A microplasma thruster has been developed of electrothermal type using azimuthally symmetric microwave-excited microplasmas. The microplasma source was ~2 mm in diameter and ~10 mm long, being operated at around atmospheric pressures; the micronozzle was a converging-diverging type, having a throat ~0.2 mm in diameter and ~1 mm long. Numerical and experimental results with Ar as a working gas demonstrated that this miniature electrothermal thruster gives a thrust of >1 mN, a specific impulse of ~100 s, and a thrust efficiency of ~10 % at a microwave power of <10 W, making it applicable to attitude-control and station-keeping maneuver for a microspacecraft of <10 kg.

scholarly journals A Stiffness-Adjusting Method to Improve Thrust Efficiency of a Two-Joint Robotic Fish

2014 ◽  
Vol 6 ◽  
pp. 537905 ◽  
Author(s):  
Dong Xu ◽  
Shaoguang Zhang ◽  
Li Wen
Keyword(s):  
Dynamic Model ◽  
Control Strategy ◽  
Cfd Simulation ◽  
Control Method ◽  
Wake Flow ◽  
Negative Power ◽  
Stiffness Control ◽  
Thrust Efficiency ◽  
Cfd Analyses ◽  
Two Degree Of Freedom

Fish are very efficient swimmers. In this paper, we studied a two degree-of-freedom (DOF) propeller that mimic fish caudal fin like locomotion. Kinematics modelling and hydrodynamic CFD analyses of the two DOF propellers were conducted. According to the CFD simulation, we show that negative power was generated within the flapping cycle, and wake flow at different instant was demonstrated. Based on the dynamic model, we compared the thrust efficiency under different stiffness control method. The results show that the thrust efficiency was enhanced under moderate stiffness control strategy.

scholarly journals Design fabrication and performance analysis of length morphing rotor blade

2018 ◽  
Vol 7 (3.3) ◽  
pp. 139
Author(s):  
G Saravanan ◽  
Vinoth Kumar Annamalai ◽  
N Bharath ◽  
Antonio Kevin ◽  
G Rahul Teja ◽  
...  
Keyword(s):  
Rotor Blade ◽  
Operating Conditions ◽  
Rotor Blades ◽  
Blade Element Theory ◽  
Weight Variation ◽  
Design Variables ◽  
Thrust Efficiency ◽  
Length Variable ◽  
And Performance ◽  
Maximum Thrust

The present work deals with helicopter theory involving the study, design and fabrication of the helicopter rotor blades with the length-morphing mechanism. The research of the rotor blades has enabled in a proper understanding of the aerodynamics and design of the same. The thrust produced by a blade is proportional to its area, and for every motor RPM, maximum thrust efficiency is achieved for a discrete length of the rotor blade. Facing this complexity, designers compute an optimal length for the average motor RPM while designing the heli-copter blades. Acknowledging the challenges, Length-Morphing rotor blades targeting maximum thrust efficiency for each motor RPM was developed with the aid of knowledge in Blade Element Theory. The rotor blade was designed and fabricated to be driven by the centrifugal force from the motor. The rotor blade was divided into fixed inboard section and sliding outboard part in a span-wise direction. The analy-sis was carried out to study and comprehend the operating conditions of the length-variable rotor during revolutions and to derive the design variables of extension-spring and rotor weight. Variation of thrust concerning the length of the rotor blade was studied, and the setup was fabricated. The project aims to enable maximum rotor blade thrust efficiency for each RPM of the motor by varying the length of the rotor blade and computing the performance characteristics of the same.  

Sign in / Sign up

Export Citation Format

Share Document