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Description
The latest , most advanced, longest ranging and perhaps the most persistant in Jihadist family air to air missile .

Under Development in Blender 3D ver 2.49

This missile is designed from the outset to destroy very agile target such as next generation UCAV and UAV that might be capable of puliing over 25G evasive maneuver , as well as next generation fighters equipped with Thrust vector control Stealths and Supercruise capability .

Another design objective is enabling standoff attack against ISR platform using legacy Jihadist delivery platform such as our Deinera Catharina , Shelenia Blanchett, Su-27P , Shelenia Itevira and MiG-29S-3 .

Above stated requirements dictated that the missile would need to be :

-No larger than legacy Jihadist family (Jihadist ERP and Jihadist Agile)
-Persistent Thrust to cope with maneuvering target
-Higher G capability with a design target of 60G in 12.000 meters and over 80G capability in Sea level, approaching that of our Aeris Warfeyr Dogfight missile .
-Better ECM resistance features, including capability to discern true target from Decoy and false target, and may include mainlobe nulling to cancel monopulse self protection jammer .

Earlier Jihadist variants such as Jihadist ERP and Jihadist Agile already have high maneuverability and some features to complicate enemy ECM attempts against them. However these features are considered inadequate to meet above requirements .

Our design team later evaluates possible solutions and design features to met the design objectives and requirements, one solution , by fitting rocket booster to Jihadist was considered, but later dropped due to incompatibility with Deinera Catharina Stealth Fighter's internal weapons bay , another consideration is to mate a modified Aeris Warfeyr dogfight missile with Jihadist's body , in a manner of our recently retired Vympel R-27 Medusa , this solution was also dropped due to same incompatibility reason .

Solid fuel Ramjet and Ducted Rocket in a manner of 9M9 (SA-6 Gainful) and OPFOR's MBDA meteor was also considered and become strong contender , however they were also dropped due to our immature technology in solid fuel thrust modulations

Later , our design team considered employment of Gelled Liquid propellant engine , a recently mature and promising technology, which combine the high impulse specific of liquid propellant and safe handling and high density of solid propellant material .

The Gelled propellant is a liquid propellant that "enriched" with gellant substance, additive materials and sometimes, metal materials such as aluminum or non metalic materials such as carbon, the resulted gel propellant is thixotropic , which would means that the gel will remain semi solid , if there are no pressure applied to the gel. If a pressure applied the gel will liquify , such trait are compatible with our currently available tankage technology . The application of the gelled propellant involve a "doughnut" shaped cylinder tank , the "outer part" of the tank will be used to store the gelled propellant , while the central part will be used as a compressed air bottle , which will provide pressure, necessary to liquify the fuel and "push" it to injector, which shares same actuator as the compressed air bottle's regulating valves , ensures good coordination and thrust throttling capability .

Some other advantages offered by Gel propellant over solid and liquid propellants are related to safety and disposal of damaged or demiliterized propellants, which will be mentioned in following table [1]

[link]

Our design team come up with 2 possible solutions for the employment of propellants , using Bi-propellant, where oxidizer and fuel are separated (Gelled IRFNA and Hydrazine) and a Ducted rocket with solid propellant booster and Gelled fuel gas generator, the Ducted rocket are considered to be simpler thus more cost effective than Bi propellant, which require more complex tankage and valve arrangements . However the Gelled Bi Propellant have its potentials for our future Anti Ballistic and Anti Satellite SAM system , allowing high performance missiles to be carried in our tracked chassis and withstand possible rough handling common in frontline operations .

The Aera Iradia's propulsion , utilizes Carbon loaded MMH Gel gas generator for Ramjet , and Aluminum-Boron Solid Propellant for boost phase . The rocket motor, unlike the OPFOR Meteor utilizes 2 nozzles , one "true" nozzle for Ramjet and "pseudo nozzle" which is a "carbon neck" , which will enhance thrust during boost phase , the neck will erode and burned up during boost phase, as well as the booster propellant, freeing the ramjet nozzle and combustion chamber for the Ramjet to work . The gas generator is restartable and throttleable in flight , allowing high thrust persistence and make maximum use of Thrust vectoring vanes installed in the Ramjet nozzle to enhance maneuverability against receding or evading target , thus solving and met the design requirements for persistence and maneuverability .

For another requirement of enhanced ECM resistance , against large and powerful jammers commonly mounted onboard ISR and Standoff Jammer Platform, our design team decide to employ, Active Phased Array Multi spectal Seeker , a combination between Ku Band Phased Array RADAR Seeker with Radiometric Imaging Seeker , the phased array gave improved missile reliability , high track rate and improved ECCM against jammers , the earlier Jihadist missile's FMCW operating mode is retained as primary operating mode for this new seeker .

The new seeker is powered by same battery as earlier Jihadist variant.

well that's all i could describe for now

REFERENCE
[1]Hodge K. F., Croofot T.A., Nelson S., 1999. Gelled Propellants for -Tactical Missile Application ., TRW Space and Technology Division Redondo Beach., California

Description
The latest , most advanced, longest ranging and perhaps the most persistant in Jihadist family air to air missile .

Under Development in Blender 3D ver 2.49

This missile is designed from the outset to destroy very agile target such as next generation UCAV and UAV that might be capable of puliing over 25G evasive maneuver , as well as next generation fighters equipped with Thrust vector control Stealths and Supercruise capability .

Another design objective is enabling standoff attack against ISR platform using legacy Jihadist delivery platform such as our Deinera Catharina , Shelenia Blanchett, Su-27P , Shelenia Itevira and MiG-29S-3 .

Above stated requirements dictated that the missile would need to be :

-No larger than legacy Jihadist family (Jihadist ERP and Jihadist Agile)
-Persistent Thrust to cope with maneuvering target
-Higher G capability with a design target of 60G in 12.000 meters and over 80G capability in Sea level, approaching that of our Aeris Warfeyr Dogfight missile .
-Better ECM resistance features, including capability to discern true target from Decoy and false target, and may include mainlobe nulling to cancel monopulse self protection jammer .

Earlier Jihadist variants such as Jihadist ERP and Jihadist Agile already have high maneuverability and some features to complicate enemy ECM attempts against them. However these features are considered inadequate to meet above requirements .

Our design team later evaluates possible solutions and design features to met the design objectives and requirements, one solution , by fitting rocket booster to Jihadist was considered, but later dropped due to incompatibility with Deinera Catharina Stealth Fighter's internal weapons bay , another consideration is to mate a modified Aeris Warfeyr dogfight missile with Jihadist's body , in a manner of our recently retired Vympel R-27 Medusa , this solution was also dropped due to same incompatibility reason .

Solid fuel Ramjet and Ducted Rocket in a manner of 9M9 (SA-6 Gainful) and OPFOR's MBDA meteor was also considered and become strong contender , however they were also dropped due to our immature technology in solid fuel thrust modulations

Later , our design team considered employment of Gelled Liquid propellant engine , a recently mature and promising technology, which combine the high impulse specific of liquid propellant and safe handling and high density of solid propellant material .

The Gelled propellant is a liquid propellant that "enriched" with gellant substance, additive materials and sometimes, metal materials such as aluminum or non metalic materials such as carbon, the resulted gel propellant is thixotropic , which would means that the gel will remain semi solid , if there are no pressure applied to the gel. If a pressure applied the gel will liquify , such trait are compatible with our currently available tankage technology . The application of the gelled propellant involve a "doughnut" shaped cylinder tank , the "outer part" of the tank will be used to store the gelled propellant , while the central part will be used as a compressed air bottle , which will provide pressure, necessary to liquify the fuel and "push" it to injector, which shares same actuator as the compressed air bottle's regulating valves , ensures good coordination and thrust throttling capability .

Some other advantages offered by Gel propellant over solid and liquid propellants are related to safety and disposal of damaged or demiliterized propellants, which will be mentioned in following table [1]

[link]

Our design team come up with 2 possible solutions for the employment of propellants , using Bi-propellant, where oxidizer and fuel are separated (Gelled IRFNA and Hydrazine) and a Ducted rocket with solid propellant booster and Gelled fuel gas generator, the Ducted rocket are considered to be simpler thus more cost effective than Bi propellant, which require more complex tankage and valve arrangements . However the Gelled Bi Propellant have its potentials for our future Anti Ballistic and Anti Satellite SAM system , allowing high performance missiles to be carried in our tracked chassis and withstand possible rough handling common in frontline operations .

The Aera Iradia's propulsion , utilizes Carbon loaded MMH Gel gas generator for Ramjet , and Aluminum-Boron Solid Propellant for boost phase . The rocket motor, unlike the OPFOR Meteor utilizes 2 nozzles , one "true" nozzle for Ramjet and "pseudo nozzle" which is a "carbon neck" , which will enhance thrust during boost phase , the neck will erode and burned up during boost phase, as well as the booster propellant, freeing the ramjet nozzle and combustion chamber for the Ramjet to work . The gas generator is restartable and throttleable in flight , allowing high thrust persistence and make maximum use of Thrust vectoring vanes installed in the Ramjet nozzle to enhance maneuverability against receding or evading target , thus solving and met the design requirements for persistence and maneuverability .

For another requirement of enhanced ECM resistance , against large and powerful jammers commonly mounted onboard ISR and Standoff Jammer Platform, our design team decide to employ, Active Phased Array Multi spectal Seeker , a combination between Ku Band Phased Array RADAR Seeker with Radiometric Imaging Seeker , the phased array gave improved missile reliability , high track rate and improved ECCM against jammers , the earlier Jihadist missile's FMCW operating mode is retained as primary operating mode for this new seeker .

The new seeker is powered by same battery as earlier Jihadist variant.

well that's all i could describe for now

REFERENCE
[1]Hodge K. F., Croofot T.A., Nelson S., 1999. Gelled Propellants for -Tactical Missile Application ., TRW Space and Technology Division Redondo Beach., California