Rocket Motor Separation and Ignition Prevention
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Man-portable rocket armaments pose safety hazards due to the risk of ignition and shrapnel from rocket motors during urban combat, where soldiers must carry and launch explosive payloads, and existing solutions do not adequately address these risks.
Innovation Solution
The rocket armament incorporates a gas dispersion assembly to prevent ignition when not contained and a cutting and separation assembly to disconnect the rocket motor from the payload during flight, ensuring safe launch and reducing the risk of bodily injury and shrapnel.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If the rocket motor is connected to the payload during flight, then the payload can be propelled to destination, but the heavy motor body adds unnecessary weight and could be thrust backwards as dangerous shrapnel
Solution Approach 1:
The rocket motor is separated from the payload during flight through a cutting and separation assembly. The motor body remains in the launcher while the payload continues to flight, eliminating the safety hazard of the heavy motor being thrust backwards as shrapnel.
Solution Approach 2:
The rocket motor is extracted from the payload assembly after launch. The cutting piston severs the connection between the motor and payload, removing the dangerous component from the flight path while maintaining the propelling function during the critical launch phase.
2Ease of operation
If the pyrotechnic assembly is actuated upon piercing, then the rocket motor can be ignited, but inadvertent piercing could cause combustion and ignition endangering the soldier
Solution Approach 1:
A gas dispersion assembly acts as an intermediary between the pyrotechnic assembly and the rocket motor. When inadvertently actuated, this assembly disperses combustion products harmlessly into the environment, preventing ignition of the rocket motor while maintaining the intended ignition capability when properly launched.
Solution Approach 2:
The potential harmful effect of inadvertent pyrotechnic actuation is converted into a safe outcome. The gas dispersion assembly redirects harmful combustion products away from the rocket motor, transforming a potential safety hazard into a benign event that does not endanger the soldier.
3Stability of the object's composition
If the rocket motor body is retained during flight, then the structure remains intact, but it adds unnecessary weight and impairs aerodynamic performance
Solution Approach 1:
The rocket motor structure is segmented from the payload at the appropriate moment during flight. The cutting and separation assembly divides the combined motor-payload structure into separate components, allowing the payload to achieve optimal aerodynamic performance without the heavy motor body while the motor remains secured in the launcher.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This design minimizes safety risks for soldiers by preventing inadvertent ignition and reducing the weight and aerodynamic impact of the rocket motor, enhancing the safety and effectiveness of man-portable rocket launches in urban environments.
Implementation Method 1
a pyrotechnic assembly for ejecting a rocket motor to which the effective payload is connected and distancing them from the launching solider even before the rocket motor is ignited by the pyrotechnic assembly
Implementation Method 2
a gas dispersion assembly, which, when the rocket armament is not contained in the tubular launcher, the ignition of rocket motor is prevented by the gas dispersion assembly
Implementation Method 3
a cutting and separation assembly, which is actuated by gas pressure of the rocket motor in order to mechanically cut the structural connection between the rocket motor and the payload
Data Source
Figure 1
Figure 2~2a
Figure 3
AI summary
Rocket armament launchable from a tubular launcher with an outside launcher non-ignition securing and motor separation during flight and a method to prevent the ignition of the armament's rocket even in the event of actuation of the armament's pyrotechnic assembly, which normally serves to eject the armament from the launcher and to ignite its rocket motor, wherein the armament comprises a gas dispersion assembly, which when the armament is not encased in the tubular launcher, prevents the ignition of the rocket motor even if the armament's pyrotechnic assembly is actuated; and a cutting and separation assembly that is actuated by the pressure of the rocket motor gases for mechanically cutting a structural connection between the rocket motor and the armament's effective payload and separate them during their flight.