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Missles flight control systems

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Thank you for all video clips.
https://www.youtube.com/watch?v=HWZXinRwCaE (icbm)
https://www.youtube.com/watch?v=mE-q1IaPIUk (how missiles launch)
https://www.youtube.com/watch?v=SOXmVi3A_PI (satan R36)
https://www.youtube.com/watch?v=LvHlW1h_0XQ (LRASM)

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Missles flight control systems

  1. 1. Intercontinental ballistic missile
  2. 2.  Early development  The first developed by Nazi Germany in World War II  The V-1 flying bomb and V-2 rocket, both of which used a simple mechanical autopilot to keep the missile flying along a pre-chosen route.
  3. 3.  Missile is a self-propelled precision-guided munition system,
  4. 4.  Conventional guided missiles Air-to-air missile Air-to-surface missile Anti-ballistic missile Anti-tank guided missile Surface-to-air missile Surface-to-surface missile  Cruise missiles
  5. 5.  Ballistic missiles - Short Range Ballistic Missile Range < 1000 Km - Medium Range Ballistic Missile Range 1000 – 3000 Km - Intermediate Range Ballistic Missile Range 3000 – 5500 Km - Intercontinental Ballistic Missile Range > 5500 Km
  6. 6. - Guided Weapon - Unguided - Higher atmosphere
  7. 7. 4 system components: Missile guidance Flight system Engine Warhead.
  8. 8.  Around the base of the RV are pressurized spheres containing propellant for the attitude control and spin-up rocket engines.  The light-colored object in front of the primary is the adaption kit containing the warhead's safing, arming and fusing circuits.  The red object in the RV's nose is the inertial measurement and guidance unit which continuously calculates the position and motion of the RV in space in order to trigger warhead detonation at the optimum point above the ground over its target.
  9. 9.  Gyroscopes required to keep track of pitch, roll, and yaw. Then get the rate called rate gyros are normally installed in a missile to measure the accelerations about the three mutually perpendicular missile axes
  10. 10.  Types of Sensors in Missiles Aneroid barometer which detects atmospheric pressure. they detect energy in the form of electromagnetic waves or heat sensor and they can guided to the radio wave of the radar.
  11. 11. Input Systems Outpu t
  12. 12.  Missile guidance refers to a variety of methods of guiding a missile or a guided bomb to its intended target. The missile's target accuracy is a critical factor for its effectiveness. On the battlefield of today, guided missiles are guided to or acquire their targets by using: Radar signal Wires Lasers Most recently GPS
  13. 13.  Self-contained  Command  Beam-rider  Homing
  14. 14.  R-36 (SS-18 Satan)  The SS-18 Satan is a very capable missile, mainly because of its high speed and extremely high throw weight. It can carry up to 10 Multiple independently targetable reentry vehicle  up to 40 penetration aids.  with a blast yield of 0.75-1 MT. This missile has a range of 11,000 km.
  15. 15.  LRASM technology will reduce network links, and GPS navigation in aggressive electronic warfare environments.  The routing and guidance capabilities of LRASM allows it to safely navigate to the enemy area, where the weapon can use gross target cueing data to find and destroy its pre-determined target in denied environments.
  16. 16.  https://sketchfab.com/models/  http://www.brahmos.com/content.php?id=10&sid=9  http://missilethreat.com/physics-of-ballistic-missiles/  https://www.facebook.com/gtabrasil.fanpage/videos/434937136696055/  http://defencyclopedia.com/2014/08/01/explained-how-cruise-missiles-work/  Video from youtube.com
  17. 17.  Boonyisa Sanaethammasiri 5710545031  Kamonwan Ketdam 5710545058
  18. 18.  Acceleration commands,  Attitude commands, etc. depends on the specific application  For instance, a typical rule of thumb for intercepting a target that has constant acceleration perpendicular to the LOS is for the missile to have a 3:1 acceleration advantage over the target.
  19. 19.  The dynamics of the airframe are governed by fundamental equations of motion, with their specific characteristics determined by the missile aerodynamic response, propulsion, and mass properties.
  20. 20.  Actuator converts the desired control command developed by the autopilot into physical motion, such as rotation of a tail fin, that will effect the desired missile motion.  Most actuators are electromechanical, with hydraulic actuators being an option in certain applications.
  21. 21.  The IMU measures the missile dynamics for feedback to the autopilot.  the IMU is composed of accelerometers and gyroscopes to measure three components of the missile translational acceleration and three components of missile angular velocity.
  22. 22.  Set of equations that takes as inputs the guidance commands and the feedback measurements from the IMU and computes the control command as the output.
  23. 23.  Acceleration Control System is designed to track commanded acceleration perpendicular to the missile longitudinal axis. The control deflection produces a small aerodynamic force on the tail fin. The induced moment rotates the missile to produce the AOA, which in turn produces aerodynamic lift to accelerate the airframe.
  24. 24.  Attitude Control System can be used to control the attitude of the missile. In this case, the control effector is the thrust-deflection angle that is actuated by either a nozzle or jet tabs. The feedback loops have a structure similar to that used in the acceleration control system The integration of pitch rate measured by the IMU to pitch attitude would typically be done via discrete integration in the missile navigation processing in the flight computer.
  25. 25.  Flight-Path Angle Control System can be used to track flight-path angle commands using thrust- vector control. This type of system assumes that aerodynamic forces are small and hence applies for exoatmospheric flight or for endoatmospheric flight when the missile speed is low. The pitch rate is measured by the IMU. The other feedback quantities are estimated in the missile navigation processing in the flight computer.
  26. 26.  Preset  Terrestrial  Inertial  Celestial Navigation
  27. 27. Target location and the trajectory of the missile must follow are calculated and set into the missile before it is launched.
  28. 28.  Terrestrial reference navigation relies on comparisons of photos or maps carried in the missile with an image of the terrain over which the missile is flying at that time.
  29. 29.  Similar to preset  The method of controlling the flight path is based on the use of accelerometers which are mounted on a gyro-stabilized platform.
  30. 30. Navigation by the stars The navigator measures the angular elevation of two or more known stars or planets, using a sextant.
  31. 31.  Missile Remote Control by Radar  Missiles tracking radar tracks the missile by track beam and command link that receive from computer.
  32. 32. A device in the missile keeps it centered in the beam. After the missile is captured (by the capture beam), it rides the capture beam for a few seconds. During this time it gets closer to the scan axis of the radar beam. Then, capture- guidance change over takes place.
  33. 33. Target illumination is supplied by a component carried in the missile, such as a radar transmitter. The radar signals transmitted from the missile are reflected off the target back to the receiver in the missile.
  34. 34. In the passive homing system, the directing intelligence is received from the target. Examples of passive homing include homing on a source of infrared rays (such as the hot exhaust of jet aircraft) or radar signal
  35. 35. In the semi active homing system, the missile gets its target illumination from an external source, such as a transmitter carried in the launching aircraft.

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