AbstractAccording to the features of container–type missile launch technology for multi-barrel rocket, combined with non-lethal weapons in the field of application, a new concept about the launching unit for anti-riot rockets, which was the integration of storing and launching non-lethal rockets, was proposed. The load bearing on the launcher was analyzed and engineering plastics were selected as launch tube materials. Combined the computer aided design software Pro/Engineer with the finite analysis software ANSYS, the numerical simulation of the launch tube was created. To ensure the launch tube design according with the theoretical design requirements, the stress and displacement of the launch tube under the maximum load were analyzed in ...
The transition from inner to outer ballistics is a crucial part of the launch of a projectile from a...
AbstractIn order to adjust the transmitted energy and control the end effect, and adapt the needs of...
Feasibility of explosive lining in launch tube for hypervelocity projectile acceleratio
AbstractAccording to the features of container–type missile launch technology for multi-barrel rocke...
Pyrotechnic devices have been employed in satellite launch vehicle missions, generally for the separ...
Structural analysis is a critical aspect in the successful design of tube launched projectiles, such...
The blast tube flowfield of a solid rocket motor is explored numerically by solving 3-D RANS equatio...
The rocket nozzle is one of the core components to ensure the safe flight of rockets. To overcome th...
The paper provides an overview of research (analytical, numerical and experimental methods) related ...
This paper describes the design of a portable rocket rack and static stress analysis using numerical...
ABSTRACTThis paper presents the structural design, fabrication and testing of a rocketmotor nozzle c...
Propellant loading from the Storage Tank to the External Tank is one of the very important and time ...
This article aims to study the effect of pressure on rocket motor case by Finite Element Method simu...
The objective of the Suborbital Technology Experimental Vehicle for Exploration research project is ...
Several design modifications to commercial off-the-shelf solid rocket motors have been evaluated in ...
The transition from inner to outer ballistics is a crucial part of the launch of a projectile from a...
AbstractIn order to adjust the transmitted energy and control the end effect, and adapt the needs of...
Feasibility of explosive lining in launch tube for hypervelocity projectile acceleratio
AbstractAccording to the features of container–type missile launch technology for multi-barrel rocke...
Pyrotechnic devices have been employed in satellite launch vehicle missions, generally for the separ...
Structural analysis is a critical aspect in the successful design of tube launched projectiles, such...
The blast tube flowfield of a solid rocket motor is explored numerically by solving 3-D RANS equatio...
The rocket nozzle is one of the core components to ensure the safe flight of rockets. To overcome th...
The paper provides an overview of research (analytical, numerical and experimental methods) related ...
This paper describes the design of a portable rocket rack and static stress analysis using numerical...
ABSTRACTThis paper presents the structural design, fabrication and testing of a rocketmotor nozzle c...
Propellant loading from the Storage Tank to the External Tank is one of the very important and time ...
This article aims to study the effect of pressure on rocket motor case by Finite Element Method simu...
The objective of the Suborbital Technology Experimental Vehicle for Exploration research project is ...
Several design modifications to commercial off-the-shelf solid rocket motors have been evaluated in ...
The transition from inner to outer ballistics is a crucial part of the launch of a projectile from a...
AbstractIn order to adjust the transmitted energy and control the end effect, and adapt the needs of...
Feasibility of explosive lining in launch tube for hypervelocity projectile acceleratio