Maneuverable reentry vehicle
A maneuverable reentry vehicle (abbr .: MARV or Marw) or maneuverable re-entry is a steerable warhead .
Functionality
MARVs are a further development of the MIRVs ( multiple independently targetable reentry vehicles ) and share with them the goal of increasing the survivability of the warheads compared to strategic or ballistic missile defense ( SDI , NMD ). As with the Pershing II , the maneuverability can also serve to increase the accuracy of hits on the final approach.
While conventional warheads always describe a predictable ballistic trajectory, MARV can carry out rapid and unpredictable flight movements in the end phase of the flight. This makes it much more difficult for a defense missile to destroy the entry body with the required hit-to-kill hit.
Systems
Weapon systems equipped with MARV technology were or are:
- Minuteman I with Advanced Maneuverable Reentry Vehicle (AMaRV) from McDonnell Douglas (prototype only, test flights: 1979–1981)
- the American MGM-31C Pershing II medium-range missile with active radar guidance on final approach ( decommissioned under the INF contract );
- the mobile Russian Topol-M intercontinental ballistic missile ;
Tax principles
In principle, the flight phase of the warheads can be divided into an exo- and an endo-atmospheric section. Maneuvers are possible in both, although different control principles may be used.
Exo-atmospheric section
This section is located between the exposure of the warheads after burnout of the last stage rocket and the start of the atmospheric reentry. For maneuvering, attitude control engines can be used, which are also used in a similar form in an interceptor missile ( NMD ).
It is possible that a MARV itself is equipped with sensors to detect approaching interceptor missiles and to carry out evasive maneuvers in direct response. It is more likely, however, that random evasive maneuvers will be carried out instead.
Endo-atmospheric section
This section lies between re-entry into the atmosphere and the impact or ignition at the target point. Interception is also possible in this phase, especially in the higher atmospheric layers. In order to prevent this, on the one hand, impulses can be transmitted to the missile by means of control engines, which influence its descent path. On the other hand, an aerodynamic control is also conceivable. Since the MARV moves at hypersonic speed , it can be shaped as a support hull or as a wave rider . This results in an asymmetrical outer shape. The air flowing around is diverted on one side of the MARV. The resulting shock waves slow down the air on this side and pressure builds up. Since this only happens on one side of the MARV, a force acts on it that can be used for control. The direction of the force can be tilted by suddenly rolling around the longitudinal axis. This makes it possible to "hit the hook" by suddenly rolling the MARV. This makes defense measures much more difficult. Continuous scrolling would create a descent path similar to a corkscrew. This trajectory also makes a defense more difficult, but provides overall better controllable control maneuvers and reduces the aerodynamic mechanical loads. The rolling maneuvers could be controlled via aerodynamic control surfaces or by means of rolling engines. The advantage of such a configuration lies in a fundamentally simpler structure of the MARV compared to a design with several position control engines. On the other hand, aerodynamic stabilization can be problematic in all flight phases. With this system, maneuvering is only possible within the atmosphere; interception in the much longer exospheric section is not hindered.
Individual evidence
- ^ Frank J. Regan, Satya M. Anandakrishnan: Dynamics of Atmospheric Re-Entry. AIAA Education Series, American Institute of Aeronautics and Astronautics, Inc., New York 1993, ISBN 1-56347-048-9 .