DESCRIPTION

• Runway penetration bomb is used to neutralize concrete targets like runways, bunkers etc.
• The effect of destruction is obtained by high speed impact, penetration and then upheaval of hard targets by exploding the warhead with no risk to the delivering aircraft.
• The bomb can be released at high speed and low altitude to avoid enemy defenses.
• Upon delivery, the bomb decelerates to a very low speed to obtain the penetration angle and to increase the safety distance between the bomb and the releasing aircraft. Subsequently the firing of the rocket motor accelerates the bomb to a very high speed for penetration into the hard target.
• Release envelope
• 450 < IAS < 600 knots
• Altitude: ≥ 200 feet
• Consists of four main sub-assemblies:-
• The Warhead: located at the front and weight approximately 105 kg
• The Sequence Assembly:located immediately behind the warhead and controls the sequence of operations.
• The Parachute Section: attached to the rear skirt of the booster by a jettisonable clamp ring and contains two drag chutes (deceleration and main).
• The Rocket Motor: double base propellant, burns for 0.45 seconds and provides a Thrust of 10,000 DaN
• Can be carried on NATO standard suspension systems

Stored in a special sealed container, allowing installation on the aircraft directly from the container without any pre-installation assembly or adjustment.

Retarded Phase:

• Ejection of drag chute.
• Deployment of the first drag chute.
• Ejection and deployment of main chute.
• Measurement of the acceleration / time conditions.

Acceleration Phase:

• Ejection of the main chute and ignition of the rocket motor.
• Accelerates to 250 m/s in 0.45 seconds.
• Impact and explosion after penetration.

In case of emergency jettisoning, bomb drops completely inert.

• Overall Length: 2491 mm
• Length excluding the Front Fairing: 2414 mm
• Maximum Body Diameter: 223 mm
• Maximum Span: 430 mm
• Approximate Overall Propelled Weight: 165 kg
• Approximate Launch Weight: 200 kg

• No electrical ignition.
• Drag chutes are not locked during captive flight.
• Rocket motor does not fire if main chute is not deployed for sufficient time.
• The warhead fuze pyrotechnic train stays out of line before Firing of rocket motor.