A Compressible Fluid Power Dynamic Model of a Liquid Propellant Powered Rifle

Author(s):  
Mark Adams ◽  
Eric J. Barth

This paper presents a dynamic model of the interior ballistics of an experimental liquid propellant-powered rifle. The liquid propellant-powered rifle described utilizes a misture of Hydroxyl Ammonium Nitrate (HAN) and hydrocarbon fuel to replace gunpowder typically used in such firearms. The motivation for such a development is to discard the need for a shell casing whereby carrying only propellant and bullets will reduce both the mass and volume per shot carried by the soldier. A first-principles dynamic model of the interior ballistics is derived as a compressible fluid power problem with the chemical liberation of heat within the chamber modeled via a condensed-phase reaction rate law. The model is used to predict the overall performance in terms of ballistic kinetic energy as well as draw design insight regarding the role of friction, chamber geometry, and the profile of chamber pressure with respect to time. Simulation results are presented as well as preliminary experimental results from a proof-of concept device.

Author(s):  
Mark Adams ◽  
Eric J. Barth

This paper presents a dynamic model of the interior ballistics of an experimental liquid propellant powered rifle. The liquid propellant powered rifle described utilizes a mixture of hydroxyl ammonium nitrate and hydrocarbon fuel to replace gunpowder typically used in such firearms. The motivation for such a development is to discard the need for a shell casing whereby carrying only propellant and bullets will reduce both the mass and volume per shot carried by the soldier. A first-principles dynamic model of the interior ballistics is derived as a compressible fluid power problem with the chemical liberation of heat within the chamber modeled via a condensed-phase reaction rate law. The model is used to predict the overall performance in terms of ballistic kinetic energy as well as draw design insight regarding the role of friction, chamber geometry, and the profile of chamber pressure with respect to time. Simulation results are presented as well as preliminary experimental results from a proof-of-concept device.


2012 ◽  
Vol 116 (46) ◽  
pp. 24496-24502 ◽  
Author(s):  
Nicholas W. Piekiel ◽  
Garth C. Egan ◽  
Kyle T. Sullivan ◽  
Michael R. Zachariah

2014 ◽  
Vol 25 (11) ◽  
pp. 3109-3121 ◽  
Author(s):  
Morris Brenna ◽  
Federica Foiadelli ◽  
Stefano Riva ◽  
Gianluca Sapienza ◽  
Dario Zaninelli

2015 ◽  
pp. 150127145402000 ◽  
Author(s):  
Garth C. Egan ◽  
Thomas LaGrange ◽  
Michael R. Zachariah

1956 ◽  
Author(s):  
Raymond R. Shaw ◽  
W. Fagan ◽  
P. P. Haag ◽  
A. D. Kafadar ◽  
S. Levin ◽  
...  

1987 ◽  
Author(s):  
Walter F. Morrison ◽  
Paul G. Baer ◽  
Melvin J. Bulman ◽  
John Mandzy

1962 ◽  
Vol 84 (1) ◽  
pp. 19-28 ◽  
Author(s):  
William E. Welsh ◽  
Arvel B. Witte

Experimental data are presented showing heat-flux distributions measured calorimetrically with several liquid-propellant rocket thrust-chamber configurations. Thrust levels of the experimental chambers were from 300 to 5000 lb. Enzian-type and axial-stream showerhead propellant injectors were utilized with hydrazine (N2H4) and nitrogen tetroxide (N2O4) propellants. Nozzle-contraction-area ratios of 8 to 1, 4 to 1, and 1.64 to 1 were tested, each having a 5-in. inlet diameter. Characteristic chamber lengths ranged from 16.95 to 62.8 in. The comparison between the experimental heat flux and the analytical heat flux using the method of Bartz [1] was found to be closest in the nozzle-expansion region. The experimental heat-flux measurements ranged between 80 per cent above and 45 per cent below the analytical estimates at the nozzle throat, however. These differences were dependent upon thrust-chamber configuration, injector type, and chamber pressure, and apparently resulted from nonideal combustion and flow characteristics. It is concluded that a priori determination of heat-flux distribution along the thrust-chamber length was possible only to a first approximation for the conditions of these tests.


Author(s):  
Niels H. Pedersen ◽  
Per Johansen ◽  
Torben O. Andersen

Research within digital fluid power (DFP) transmissions is receiving an increased attention as an alternative to conventional transmission technologies. The use of DFP displacement machines entails a need for applicable control algorithms. However, the design and analysis of controllers for such digital systems are complicated by its non-smooth behavior. In this paper a control design approach for a digital displacement machine® is proposed and a performance analysis of a wind turbine using a DFP transmission is presented. The performance evaluation is based on a dynamic model of the transmission with a DFP motor, which has been combined with the NREL 5-MW reference wind turbine model. A classical variable speed control strategy for wind speeds below rated is proposed for the turbine, where the pump displacement is fixed and the digital motor displacement is varied for pressure control. The digital motor control strategy consists of a full stroke operation strategy, where a Delta-Sigma pulse density modulator is used to determine the chamber activation sequence. In the LQR-control design approach, the discrete behavior of the motor and Delta-Sigma modulator is described by a discrete linear time invariant model. Using full-field flow wind profiles as input, the design approach and control performance is verified by simulation in the dynamic model of the wind turbine featuring the DFP transmission. Additionally, the performance is compared to that of the conventional NREL reference turbine, transmission and controller.


IEEE Access ◽  
2020 ◽  
Vol 8 ◽  
pp. 196940-196950
Author(s):  
Mehran Kiani-Oshtorjani ◽  
Stanislav Ustinov ◽  
Heikki Handroos ◽  
Payman Jalali ◽  
Aki Mikkola

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