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Embodiments relate to a projectile system, method and computer program product for controlling the flight of a projectile to make a course change by approximately 90°, greater than 90° or up to 90°. The projectile system comprises a gun-fired projectile having a body, at least one tail fin, a motor

Embodiments relate to a projectile system, method and computer program product for controlling the flight of a projectile to make a course change by approximately 90°, greater than 90° or up to 90°. The projectile system comprises a gun-fired projectile having a body, at least one tail fin, a motor firing during a first flight phase and during a second flight phase and at least one controllable canard. The projectile system includes one or more processors configured to determine a turn maneuver profile to a target during the first flight phase, produce control signals to destabilize the body, create a pitch attitude change for the turn maneuver profile and effectuate a turn of the projectile in a direction corresponding to the turn maneuver profile during the first flight phase. The processors control the motor to start the second flight phase to the target after the turn.

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1. A projectile system comprising: a gun-fired projectile having a body including an aft section and a forward section, at least one tail fin coupled to the body at the aft section, a motor configured to fire during a first flight phase and fire during a second flight phase and at least one controll

1. A projectile system comprising: a gun-fired projectile having a body including an aft section and a forward section, at least one tail fin coupled to the body at the aft section, a motor configured to fire during a first flight phase and fire during a second flight phase and at least one controllable canard located on the body; andone or more processors configured to determine a turn maneuver profile to a target during the first flight phase, produce control signals to destabilize the body, create a pitch attitude change for the turn maneuver profile and effectuate a turn of the projectile in a direction corresponding to the turn maneuver profile during a turn phase of the first flight phase, and to control the motor to start the second flight phase to the target after the turn. 2. The projectile system of claim 1, wherein the turn maneuver profile includes a turn angle to effectuate the turn, the turn angle is one of: in a range up to 90°, 90°; and in a range greater than 90°. 3. The projectile system of claim 1, wherein the turn maneuver profile includes a turn angle of approximately 90°. 4. The projectile system of claim 1, the one or more processors dynamically determine a turn maneuver profile in response to a turn command received by the projectile in flight. 5. The projectile system of claim 1, wherein the projectile is a 40 mm grenade. 6. The projectile system of claim 1, further comprising: a camera to detect a laser illuminated targets; anda seeker for tracking a target during the first flight phase, the second flight phase or a combination of the first flight phase and the second flight phase. 7. The projectile system of claim 1, further comprising: an onboard inertial sensor configured to sense three-axis linear accelerations and three-axis angular rates wherein the at least one controllable canard is controlled to reduce stability of the projectile to a neutral, or slightly unstable during the turn phase; andan onboard autopilot configured to maintain control of the projectile during the turn phase. 8. The method comprising: providing a gun-fired projectile having a body including an aft section and a forward section, at least one tail fin coupled to the body at the aft section, a motor configured to fire during a first flight phase and fire during a second flight phase and at least one controllable canard located on the body;determining, by one or more processors, a turn maneuver profile to a target during the first flight phase;producing, by the one or more processors, control signals to destabilize the body, create a pitch attitude change for the turn maneuver profile and effectuate a turn of the projectile in a direction corresponding to the turn maneuver profile during a turn phase of the first flight phase; andcontrolling, by one or more processors, the motor to start the second flight phase to the target after the turn. 9. The method of claim 8, wherein the turn maneuver profile includes a turn angle to effectuate the turn, the turn angle is one of: in a range up to 90°, 90°; and in a range greater than 90°. 10. The method of claim 8, wherein the turn maneuver profile includes a turn angle, the turn angle is approximately 90°. 11. The method of claim 8, wherein the determining of the turn maneuver profile includes: determining a lead time-to-distance for the turn;determining a direction of the turn;determining an angle of the turn; anddetermining a side displacement of the body. 12. The method of claim 8, wherein the projectile is a 40 mm grenade. 13. The method of claim 8, further comprising: detecting a laser illuminated target by the projectile; andadjusting a flight path based on a location of the detected laser illuminated target. 14. The method of claim 8, further comprising: tracking, by a seeker, the target during the first flight phase, the second flight phase or a combination of the first flight phase and the second flight phase. 15. The method of claim 8, further comprising: sensing, by an onboard inertial sensor, three-axis linear accelerations and three-axis angular rates;controlling the at least one controllable canard to reduce stability of the projectile to a neutral, or slightly unstable during the turn phase; andmaintaining, by an onboard autopilot, control of the projectile during the turn phase. 16. A computer program product for controlling flight of a projectile to make a course change by approximately 90°, greater than 90° or up to 90°, the computer program product comprising a non-transitory computer-readable medium having instructions embodied thereon, which when executed by a computer cause the computer to implement a method, the method steps comprising: determining a turn maneuver profile to a target during a first flight phase;producing control signals to destabilize the projectile, to create a pitch attitude change for the turn maneuver profile and effectuate a turn of the projectile in a direction corresponding to the turn maneuver profile during a turn phase of the first flight phase; andcontrolling the motor to start the second flight phase to the target after the turn. 17. The computer program product of claim 16, the instruction for determining of the turn maneuver profile includes instructions which when executed by a computer cause the computer to further implement the method steps of: determining a lead time-to-distance for the turn;determining a direction of the turn;determining an angle of the turn; anddetermining a side displacement of the body. 18. The computer program product of claim 17, wherein the angle of the turn is approximately 90°. 19. The computer program product of claim 16, wherein the projectile is a gun-fired 40 mm projectile. 20. The computer program product of claim 16, further comprising instruction which when executed by a computer cause the computer to further implement the method step of: automatically self-arming the projectile as a function of acceleration.