Impact of opening time of the take-off pneumatic launcher main valve on take-off pressure losses

• Autorzy: Jastrzębski G.

Identyfikatory

DOI

10.5604/12314005.1217204

• Języki publikacji: EN

Abstrakty

EN

This publication presents UAV rope and pneumatic launchers constructed and operated in the Air Force Institute of Technology. The construction and operating principle were presented, and functional properties of the UAV take-off pneumatic launcher were characterised. Furthermore, a detailed diagram of the take-off pneumatic launcher was shown, and an operating principle of the launcher take-off system and pneumatic control of the take-off procedure were discussed. The operation parameters of the most important operational elements (main ball valve, semi-rotary actuator, pneumatic valves controlling the flow) from the launcher pneumatic system were specified. On the basis of data sheets of pneumatic elements, a calculation model of the mass flow (volumetric flow rate) of compressed air flowing through the main valve (ball valve in the take-off cylinder supply line) of the take-off pneumatic launcher was designed. The possible cracks, through which compressed air leaks and the take-off cylinder dead sections during the main valve opening and shot, were characterised and discussed. The calculation model designed for individual leaks and total compressed air leaks in the take-off line of the pneumatic launcher was presented. Based on the mass flow model (volumetric flow rate) of compressed air flowing through the main valve, and total compressed air leaks, the relationship of compressed air energy losses depending on opening time of the main valve of the take-off pneumatic launcher was determined. In the paper, the results of simulation studies for the times shorter than data sheets of the main valve opening were presented. In addition, the change of the compressed air disposable energy losses was defined. Based on the results of simulation studies, the opening time of the take-off launcher main valve for the acceptable disposable energy loss level of the take-off pneumatic launcher was specified.

Słowa kluczowe

EN

take-off launcher; pneumatic take-off systems; pressure losses

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2016
• Tom: Vol. 23, No. 4
• Strony: 175--182
• Opis fizyczny: Bibliogr. 8 poz., rys.

Twórcy

autor

Jastrzębski G.

• Air Force Institute of Technology Ksiecia Boleslawa Street 6, 01-494 Warszawa, Poland tel.: [phone]

Bibliografia

• [1] Dindorf, R., Woś, P., Determination of time and filling and emptying pressure of the pneumatic tank, Hydraulics and Pneumatics, 3, pp. 5-8, 2014.
• [2] Iwaszko, J., Resistance of air flow through pneumatic elements, Scientific Works of the Warsaw University of Technology, Is. 177, Mechanics 1999.
• [3] Jastrzębski, G., Determination of functional properties of WPA – 1 pneumatic launcher with an electropneumatic take-off system, ML–XV, PTMTS, Warsaw 2012.
• [4] Jastrzębski, G., Ułanowicz, L., Methods for determining the UAV take-off launcher carriage speed, ML-XVI, PTMTS, pp. 171-181, Warsaw 2014.
• [5] Kamiński, Z., Methods for determining the flow properties of pneumatic elements, Hydraulics and Pneumatics, 5, 2007.
• [6] Kroczek, R., Domin, J., Project of the pneumatic drive module as an initial speed transmitter in the hybrid electromagnetic launcher, Electrical Machines – Problem Issues, No. 4, (108), 2015.
• [7] Potrykus, J., Mechanic’s guide, ISBN-978-83-7993-018-0.
• [8] Zbrowski, A., Pneumatic gun for collision tests, Problems of Operation, 3, pp.133-143, 2012.

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę.