Accession Number : ADP011110


Title :   Integrated Thrust Vectored Engine Control


Corporate Author : MOTOREN- UND TURBINEN-UNION G M B H MUNICH (GERMANY F R)


Personal Author(s) : Christian, Rausch


Full Text : http://www.dtic.mil/get-tr-doc/pdf?AD=ADP011110


Report Date : JUN 2001


Pagination or Media Count : 10


Abstract : Thrust vectoring is a key technology for future combat aircraft. Together with an advanced thrust vectored engine control system, the ITP thrust vectoring nozzle concept with a common actuation system for all nozzle functions (throat area, exit area and all axis vectoring) is an appropriate solution to meet the stringent requirements concerning performance, reliability and safety resulting from the intended use of thrust vectoring for flight control. An enhanced link between the flight control system and the engine control system will be necessary and the combined engine and nozzle control will have to meet new functional requirements. These requirements are on one hand related to the nozzle itself and on the other hand to the interactions between the nozzle and the engine.


Descriptors :   *MILITARY AIRCRAFT , *THRUST VECTOR CONTROL SYSTEMS , *THRUST AUGMENTOR NOZZLES , KINEMATICS , FUNCTIONS , STEADY STATE , CONTROL SYSTEMS , COMPUTATIONS , JET ENGINES , LIMITATIONS , VECTOR ANALYSIS , GERMANY , ENGINES , GEOMETRY , ACTUATORS , COMBAT FORCES , GERMAN LANGUAGE , MINIATURIZATION , GAS FLOW.


Subject Categories : AIRCRAFT
      ROCKET ENGINES


Distribution Statement : APPROVED FOR PUBLIC RELEASE