Trajectory shaping
AssigneeIsrael Aerospace Industries Ltd.
InventorJacob Rovinsky
Life of this patent
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Abstract
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.
Claims26
A system for launching a projectile towards a target, the system comprising:
- 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 the booster engine is configured such that ignition of propellant stowed in a combustion chamber of the booster engine, initiates a sequential execution of a first burning phase, a second burning phase and a third burning phase of the propellant;
- wherein during the first burning phase the projectile is ejected from a cell and wherein thrust generated by burning of the propellant during the second burning phase is lower than the thrust generated during the first and the third burning phases;
- wherein the control circuitry is configured to activate during the second burning phase the one or more thrusters;
- wherein upon the activation, the projectile begins to turn in a certain deflection azimuth that is dependent on activation timing.
A method of launching a projectile towards a target, the method comprising:
- in response to a command to launch the projectile towards the target:
- igniting propellant stowed in a combustion chamber of the projectile;
- wherein ignition of the propellant initiates a sequential execution of a first burning phase, a second burning phase and a third burning phase of the propellant;
- wherein during the first burning phase the projectile is ejected from a cell and wherein thrust generated by burning of the propellant during the second burning phase is lower than the thrust generated during the first burning phase and the third burning phases;
- ejecting, during the first burning phase, the projectile out of a cell in a manner that causes one or more thrusters fixed to the projectile, to spin around a longitudinal axis of the projectile;
- activating, during the second burning phase, the one or more thrusters;
- wherein the one or more thrusters are fixed to the projectile, such that upon an activation of the one or more thrusters, the projectile begins to turn in a certain deflection azimuth according to activation timing.
A projectile, comprising:
- 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 the booster engine is configured such that ignition of propellant stowed in a combustion chamber of the booster engine, initiates a sequential execution of a first burning phase, a second burning phase and a third burning phase of the propellant;
- wherein during the first burning phase the projectile is ejected from a cell and wherein thrust generated by burning of the propellant during the second burning phase is lower than the thrust generated during the first and the third burning phases;
- wherein the control circuitry is configured to activate during the second burning phase the one or more thrusters;
- wherein upon the activation the projectile begins to turn in a certain deflection azimuth that is dependent on a timing of activation.
Dependencies are inferred from the claim text.