Indian Missile News And Discussion

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(50% reduction in payload doubles the range)





How so Bharat?



Any data that you can corroborate on this ¿¿¿¿



If I remember well, when they shaved the payload of Ghauri missile from 1000KG to 700KG they increased the range from 950 to 1120.....



And look @ the following from david right:

David Wright at the Union of Concerned Scientists has done an excellent analysis of the Taepodong-2 based on the CSS/Nodong configuration. He calculates that the Taepodong-2, used as a ballistic missile, could deliver a one ton payload to a range of 6,000 kilometers, which would allow it to reach Anchorage, Alaska, and, with a 500 kg payload, the missile would have a range of 9,000 kilometers, putting San Francisco within range and all U.S. cities along the Pacific coast north of there.

The efficiency of a rocket engine is measured by its specific impulse. Specific impulse is defined as the thrust divided by the mass of propellant consumed per second. The result is expressed in seconds. The specific impulse can be thought of as the number of seconds that one pound of propellant will produce one pound of thrust. If thrust is expressed in pounds, a specific impulse of 300 seconds is considered good. Higher values are better. Although specific impulse is a characteristic of the propellant system, its exact value will vary to some extent with the operating conditions and design of the rocket engine. It is for this reason that different numbers are often quoted for a given propellant or combination of propellants.

Do we know what prepellants Brahmos is using and thereby its specific impulse? and the quantity/mass of it? Since impulse is the product of a thrust, and its bounce to the ounce theory in rocketery science, we would know nothing on yr above question under the absence of above material facts.



For example:

A shoulder fired rocket such as the LAW has an average thrust of 600 lbs and a firing duration of 0.2 seconds for an impulse of 120 lb sec. The Saturn V rocket, used during the Apollo program, not only generated much more thrust but also for a much longer time. It had an impulse of 1.15 billion lb sec

A rocket's mass ratio is defined as the total mass at lift off divided by the mass remaining after all the propellant has been consumed. A high mass ratio means that more propellant is pushing less missile and payload mass, resulting in higher velocity. A high mass ratio is necessary to achieve the high velocities needed for long-range missiles.