Space systems design (spacecraft, satellites, space stations and their equipment)
Vahid Rahimi Ghoradel; Hossein Mahdavy-Moghaddam
Volume 16, Issue 2 , June 2023, , Pages 1-17
Abstract
Each missile has a payload section and an engine section. In the path of the missile, there is a time when the mission of the engine section is over and after that the engine will not play an effective role and will be as extra weight and consequently reduced range or factor for easy detection of the ...
Read More
Each missile has a payload section and an engine section. In the path of the missile, there is a time when the mission of the engine section is over and after that the engine will not play an effective role and will be as extra weight and consequently reduced range or factor for easy detection of the warhead by enemy agents. In such a situation, after completing the engine mission, the mechanism of separating the steps and separating the head from the body is used. One of the separation methods is to use the thrust termination system method. In this paper, with the studies performed on the thrust termination system and the presentation of mathematical relations, the pressure drop and inverse thrust created in the chamber after opening the reverse thrust valves are predicted. Also, cold type separation and thrust termination system were used and the combustion chamber pressure drop is simulated. Then, the effect of important and influential factors on the thrust termination system has been investigated.
Hossein Mahdavy-Moghaddam; mohammad hadi Hamedi
Volume 10, Issue 2 , September 2017, , Pages 23-32
Abstract
Recently, a novel technique using dual throat nozzles is introduced for thrustvectoring applications. The present paper discusses this new technique. All thrustvectoring techniques are evaluated with some common parameters: nozzle dischargecoefficient, system thrust ratio, thrust vector angle and thrust ...
Read More
Recently, a novel technique using dual throat nozzles is introduced for thrustvectoring applications. The present paper discusses this new technique. All thrustvectoring techniques are evaluated with some common parameters: nozzle dischargecoefficient, system thrust ratio, thrust vector angle and thrust vectoring efficiency. For agiven micro turbine nozzle geometry, a double throat nozzle is designed usingdimensional scaling or geometrical analogy. Then, by comparing the results obtainedfrom a designed geometry for discharge coefficient, thrust vector angle and thrust vectorefficiency, the DTN performance is reported. The designed DTN deflected the vectorangle of 18 degrees with the fluidic injection flow rate equal to 10 percent of the primaryflow rate.
