Computing Delta-V requiredfor Ballistic Missiles(Created October 2009)(Last Updated July 2016)

References:
Space Vehicle Design by Griffin, referencing Fundamentals of Astrodynamics by Bate, Mueller and White

Pre-Calculated Delta V requirements for Ballistic Missiles on Earth

Notes: These were calculated with the equations below.

Missile

Range /Apogee (km)

Delta-V required

Atlas F ICBM
(range/apogee from Standard Missile Characteristics)

12,570 km range
1,413 km apogee

5,680 m/sec

Thor IRBM
(public sources)

2,400 km range
450 km apogee

4,257 m/sec

Iraqi Al Hussein
(public sources)

644 km range
151 km apogee

2,420 m/sec

Equation to Compute Delta-V for a Given Range

Equation Explained

• BurnoutVelocity = Final Velocity (Delta-vee) required by the missile to achieve it's range in km/sec.

• GRad: Solved independently below to simplify equation.

• RangeAngle: Solved independently below to simplify equation.

GravityParameter: Gravitational Parameter of planet in km3/s2.

 Gravitational Parameters ofPopular Objects (km3/s2) Earth 398,600.4418 Moon 4,902.7779 Mars 42,828 Titan 8,978.2 Pluto 871 Ceres Asteroid 63.1