In otherwords, it assumes an all-boost motor not a boost sustain motor.įor example, let'a take a look at the AIM-120A AMRAAM which we have some decent info on. None is used to provide just enough thrust to sustain a given velocity. This assumes that all the fuel is used to get the missile as fast as possible and It goes like this:-Ĭhange in Velocity (Delta V) = 10 x Specific Impulse x LN (initial weight / final weight) m/s I want to take this opportunity to introduce everyone to a very simple formula thatĬan be used for estimating the performance of a missile. Some of which are well backed by facts, some are so far out there it is like claiming that There has been a lot of arguments over the performance of A2A missiles here. 15th February 2010 at 14:58 - Edited 1st January 1970 at 01:00Ĭola had a good briefing how it works, here. then we have optimal conditions, and this is what PR guys quote when they sell their missiles.Ī missile has ~7 sec worth of fuel to burn If on the other hand the launching aircraft was closing in at M1.5 at missile launch, and the target was also closing in at supersonic, while also having a lower altitude then launch a/c, and flying a straight line so that the missile does not have to waste energy on anything,
then there is no hope of the missile ever gets close to the target. Speed of launching aircraft at missile launch in the direction towards the target is also a very important parameter, lets say it was flying away from the target at launch, and the target was also flying away, Then we have sea level, pretty good maneuverbility but only WVR. Next comes high altitude in atmosphere, still long range but real poor maneuverbility. In space, the range of an AMRAAM is 500 light-year, but the probability of a hit is zero, cause the fins has no authority to change the missiles direction.
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