III.N.11—Guided Multiple Launch Rocket (MLRS) System ATD.  By the end of FY98, demonstrate a low cost G&C package for the MLRS rocket. At extended ranges, large quantities of baseline rockets are required to defeat the target. With the addition of a guidance system, an improved delivery accuracy will be achieved. The number of rockets required to defeat the target will be reduced to one–sixth the current quantity at maximum ranges. The goal of the program is to conduct test flights in FY97–FY98. Technologies that will be integrated include a low cost inertial measurement unit, GPS receivers and antennas, and a canard or ring thruster control package, all of which must be housed in the forward section of the MLRS rocket.

Supports: MLRS Family of Munitions and RFPI ACTD, technology options for Joint Directed Attack Munition, Precision Strike—Korea.

III.N.15—Multimode Airframe Technology (MAT):LONGFOG.  By the end of FY97, demonstrate through sled testing a functioning multimode airframe that includes an integrated turbine engine, GPS/INS, ground station computer, and fiber optic datalink. By the end of FY98, demonstrate technologies through modeling, simulation, and flight testing, that will provide a 40 km day/night, multiple and high value time sensitive point target strike capability while inflicting minimum collateral damage. The technologies will provide a flexible airframe and subsystems to support missile systems that can select priority targets after launch, conduct limited man–in–the–loop BDA, and provide target area reconnaissance in addition to target attack by means of variable cruise velocity over areas of interest. These capabilities will be achieved by means of integrated GPS and inertial navigation, variable throttle air–breathing propulsion, composite material airframe providing low IR signature and low RCS, variable geometry wings for multiple speed regimes, imaging IR seeker, and other appropriate technologies.

Supports: RFPI, JPSD Precision/Rapid Counter MRL ACTDs.

III.N.17—Ducted Rocket Engine.   By FY98, develop and demonstrate a ducted rocket engine for a medium surface–to–air missile to significantly increase the intercept envelope against aircraft, cruise missiles, and tactical ballistic missiles when compared to surface–to–air missiles using current solid rocket propulsion technology. Component technology development will focus on the design and testing of a minimum signature, insensitive munitions, compatible booster, supersonic air inlets, and solid fuel gas generator that provides for high impulse, minimum signature ramburner operation. In FY96, complete heavyweight integration and initiate flightweight propulsion system development. In FY97, complete flightweight development and conduct ground testing. In FY98, complete ground testing and data reduction.

Supports: Battle Command, Depth and Simultaneous Attack, and Early Entry Lethality, and Survivability Battle Labs.

III.N.18—Auto–Registration System.  By FY98, this STO will demonstrate an 155mm Auto–Registration System (ARS) Projectile with a 140 CEP accuracy goal at 35 km. In FY97, fabrication and testing of subsystems for a P/Y Code GPS ARS. In FY98, conduct system demonstration including Standard Fuze GPS Translators and a Real Time Ground Receiver integrated with the ARL automated fire control system for towed howitzers. The demonstration will take place at YPG and Ft. Sill where a comparison between predicted fire accuracy and auto–registration correction accuracy will be shown. Auto–registration will utilize technology leverage from the Navy competent munitions program. Also, in FY98 complete engineering study to adapt a low cost GPS/INS guidance package (currently being developed by Navy with $26M leverage) for PGMM application.

Supports: PGMM ATD, Indirect Precision Fire Warfighting Experiment; Cost effective, enhanced accuracy for the entire stockpile of artillery ammunition, ORD currently in draft, Depth & Simultaneous Attack Battle Lab.

III.N.19—Advanced SADARM Sensor.  By FY01, this STO will demonstrate the application of a common aperature LADAR/IR transducer to enhance the current smart submunition (SADARM) sensor suite for use in gun launch environments. The sensor suite will improve CM performance and provide target classification capability with specific performance goals to include probability of detection (Pd) >.90, probability of classification (Pc) >.75, and 20 times increase in footprint compared to basic SADARM. The enhanced sensor suite performance will greatly reduce cost per kill for basic SADARM. In FY98, conduct analysis of SADARM BLOCK II sensor requirements in extended range 155mm and MSTAR, and fabricate LADAR/IR prototype hardware for preliminary sensor suite evaluation. In FY99, fabricate test hardware for sensor CFT data gathering and for G–hardening experiments; perform CFT data gathering. In FY00, conduct system tradeoff studies on alternate Block II sensor designs, perform sensor suite packaging analyses, finalize sensor detailed design, and begin fabication of sensor hardware. In FY01, conduct tactical sensor CFT, conduct sensor components G–hardening testing.

Supports: SADARM Munitions, MSTAR, Sensor Fuze Munitions.

III.N.21—Future Direct Support Weapon. The objective of this STO is to demonstrate the viability of a 5,000 pound towed howitzer. The first phase of the program will involve a demonstration of a 6,750 pound towed howitzer. The second phase will involve a demonstration of a 5,700 pound towed howitzer, with a decision to go forward with the program to develop a 5,000 pound towed howitzer to begin in FY02. This effort will leverage the technology from current congressionally funded Electro–Rheological (ER) fluid research, which includes fluid characterization, software control methodology, materials and structures modeling, power supply design, 155mm soft recoil test bed fabrication, subscale laboratory test apparatus, and accuracy and effectiveness studies of 155mm vs. 105mm. In FY98, perform direct support (DS) weapon interior ballistics modeling, initiate virtual prototype and modeling of soft recoil testbed (6,750 pound), perform materials investigations, and develop an Army–wide database of ER fluids. In FY99, conduct a live fire of an existing (hard stand) soft recoil mechanism, design/fabricate a DS weapon cannon, modify a 155mm soft recoil testbed for DS, and develop concepts for a 5,700 pound ER fluid controlled soft recoil weapon. In FY00, initiate firing program for 6,750 pound testbed, verify modeling and simulation of 6,750 pound testbed, and initiate virtual prototype and modeling of 5,700 pound testbed. In FY01, execute limited user evaluation of 6,750 pound testbed, fabricate 5,700 pound testbed, and execute live fire evaluation; and validate virtual simulations.

Supports: 155mm towed howitzer for the light forces.

III.N.22—Multiple Launch Rocket System (MLRS) Smart Tactical Rocket (MSTAR).  MLRS Smart Tactical Rocket (MSTAR) will demonstrate the feasibility of deploying smart submunitions from one MLRS rocket. This technology will provide the ability to deliver smart submunitions to the target area while being a transparent MLRS Family of Munitions (MFOM) user. Logistic support, resupply, maintenance, required number of firing platforms (launchers), and other support equipment will be reduced by the relationship of the number of submunitions expected to be housed and dispensed by the rocket. Stowed kills will be increased due to the ability of the submunitions to attack multiple targets. Proof of an integrated design concept will be demonstrated through subsystem engineering hardware testing and verified by system level simulations. Results must ensure a relatively benign dispensing environment with a high probability of placing the submunitions in a posture to counter the posed threat and account for the required search characteristics of the various smart submunition candidates. Studies will be accomplished utilizing 6–degrees of freedom (DOF) simulations to evaluate aerodynamic characteristics, dispersion patterns, and dispersion accuracy, and to provide inputs into the submunition flight and terminal phase simulations

Supports: Multiple Launch Rocket System (MLRS).