Projectile Trajectory Shaping via Spin-Activated Thrusters
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Solution Overview
Problem
Existing vertical launching systems lack the capability to efficiently deflect projectiles during launch in desired directions, particularly for applications like Multiple Launch Rocket Systems, where quick targeting is critical, and they often require significant time to reorient the launcher.
Innovation Solution
A launching system comprising a control circuitry, a booster engine, and thrusters connected to the projectile, which are spun during launch to achieve deflection by executing a sequential burning phase of the booster engine, allowing for precise control of the projectile's trajectory through activation timing and thruster profiles.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the launcher reorients itself to engage a target, then the projectile can be directed toward the target, but it requires significant time to turn the launcher
Solution Approach 1:
The system pre-positions the projectile in a vertical launch cell and pre-configures thrusters to be activated at specific times during the burn phase. By preparing the launch system in advance and using pre-programmed thruster activation sequences, the system eliminates the need for time-consuming mechanical reorientation of the entire launcher, enabling rapid engagement of time-critical targets.
Solution Approach 2:
The system dynamically controls the projectile's trajectory by activating one or more thrusters during the booster engine's burn phase. The thrusters can be activated at different times (e.g., mid-burn) and at different orientations (e.g., 90 degrees from the longitudinal axis) to create dynamic trajectory changes. This dynamic control allows the projectile to be deflected in any desired direction without requiring the physical reorientation of the launch platform.
2Ease of operation
If thrusters are activated during the second burning phase with lower thrust, then the projectile can turn at a certain rate and azimuth, but the overall acceleration is reduced
Solution Approach 1:
The booster engine's burn phase is segmented into three distinct phases: first burning phase (high thrust, vertical ejection), second burning phase (lower thrust, trajectory shaping with thruster activation), and third burning phase (high thrust, final acceleration). By segmenting the burn process, the system can optimize each phase for its specific function - using high thrust for acceleration and lower thrust for precise trajectory control, thereby achieving both speed and control precision.
Solution Approach 2:
The system uses periodic thruster activation during the second burning phase, where thrusters are activated in specific cycles at predetermined times. This periodic activation pattern allows for controlled trajectory shaping while the lower thrust of the second phase prevents excessive acceleration, enabling precise directional control without sacrificing overall speed.
3Device complexity
If the projectile is ejected vertically from the cell, then the launch structure is simplified, but the ability to engage targets in any direction is limited
Solution Approach 1:
The system extracts the trajectory shaping function from the launch structure itself and places it in the projectile's propulsion system. Instead of requiring a complex mechanically adjustable launch structure, the patent uses thrusters mounted on the projectile to provide directional control. This extraction simplifies the launch structure (vertical cell ejection only) while maintaining full directional capability through the projectile's own propulsion system.
Solution Approach 2:
The thrusters act as an intermediary between the simple vertical launch and the desired complex trajectory. The vertical ejection provides the initial velocity, and the thrusters serve as an intermediary propulsion system that can be activated at any time during flight to deflect the projectile in any direction. This intermediary approach allows the simple launch structure to achieve complex engagement capabilities.
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
Enables rapid and accurate deflection of projectiles in any desired direction, reducing the time needed to engage targets by shaping the projectile's trajectory post-launch, thus enhancing the effectiveness of launch systems in time-critical scenarios.
Implementation Method 1
ignition of propellant stowed in a combustion chamber of the booster engine
Implementation Method 2
the booster engine is configured to launch the projectile
Implementation Method 3
one or more thrusters adapted to be connected to the projectile and capable of being spun during launch around a longitudinal axis of the projectile
Implementation Method 4
the one or more thrusters are spun during launch around a longitudinal axis of the projectile
Implementation Method 5
ignition of the propellant initiates a sequential execution of a first burning phase, a second burning phase, and a third burning phase; wherein the thrust generated during the second burning phase is lower than the thrust generated during the first and the third burning phases
Data Source
AI summary
The presently disclosed subject matter includes a system and a method for launching a projectile towards a target, wherein the system comprises a control circuitry, a booster engine, and one or more thrusters adapted to be connected to the projectile and capable of being spun during launch around a longitudinal axis of the projectile, the control circuitry being operatively connected to the one or more thrusters; wherein responsive to ignition of propellant stowed in a combustion chamber of the booster engine, the booster engine causes the projectile to launch from its cell; following launch of the projectile, cause the projectile to turn at a certain rate and a certain azimuth.