For decades the space domain has been used for military purposes. When enemy forces establish counter-space capabilities, this could become a weakness. Responsive Space is a concept that focuses on replenishing lost capabilities and/or granting additional capabilities from space assets quickly. The continuous miniaturization of technologies has enabled small satellites to fulfill many desired functions. To launch such satellites, it might be possible to modify a missile into a small launch vehicle that can be launched from a naval ship using a shipborne missile canister launching system, the Mark 41 Vertical Launching System, thereby giving the military autonomous and quick-response space launch capability. Modifying a missile that has already been integrated in the VLS instead of developing a fully new launch vehicle could have the benefit that integration cost could be lower. Also, a fully new vehicle would require more development, which can be costly and time consuming. It is investigated what the maximum payload is of a launch vehicle developed from an already integrated missile that is launched from the Mark 41 Vertical Launching System and whether it is capable of launching microsatellites. The Block IIA version of the Standard Missile-3 anti-ballistic missile is determined to be the most capable missile to modify. A multidisciplinary design optimization tool has been created that maximizes the payload mass and the perigee altitude of the orbit of the new launch vehicle. The results show that it is possible to launch a microsatellite to various Low-Earth orbits from different launch locations. For example, for an equatorial orbit, it is possible to launch a payload mass of up to 17.8 kg to a near-circular orbit with a perigee altitude of 200 km.