Metrics include a 50-100% improvement in overall minefield performance; a 2-3-km minimum range acoustic detection; a 7+ target tracking; and a robustness criteria for ACTD residuals. Technical barriers include target association and classification, target location accuracy, and real-time target information processing.

Aspects of the technology demonstration phase of the Future Missile Technology Integration (FMTI) Program include captive flight testing of missile components (including seeker, RF datalink, autotracker, and automatic target recognition); and static firings of gel rocket motor, hardware-in-the-loop, digital simulation of all missile components, and development of a distributed interactive simulation of a virtual prototype of FMTI missile capability on the future battlefield. In addition, the FMTI technical demonstration phase will demonstrate in FY98, through three live missile firings, lock-on-before-launch fire-and-forget guidance against an armored vehicle at ranges up to 5 km. Milestones include, by the end of FY97, demonstration of all missile flight components to include an imaging infrared seeker and a gel bipropellant rocket motor.

Technical barriers include the ability to lock onto ground vehicles in clutter at long range (up to 5 km), efficient packaging of all missile components in a TOW-size missile volume, and developing the capability to control gel motor delivered thrust during long-range flyout.

Primary metrics for this demonstration will be atmospheric compensation performance, residual satellite tracking error, and laser beam pointing accuracy for aimpoint stabilization. Specific performance goals are classified, but they generally involve an improvement by factors of two to four over currently demonstrated capabilities at the subsystem level, as well as the simultaneous demonstration of improved performance for all subsystems in integrated testing. A series of increasingly complex integrated beam control field tests will culminate in the final ATD demonstration in FY01. Intermediate ATD results include initial active tracking of LEO satellites (FY97), installing full-scale adaptive optics on 3.5-m telescope (FY98), and integrated beam control tests against lower (400 km) LEO satellites in nighttime testing (FY99). The final ATD demonstration in FY01 will be conducted against higher (up to 1,200 km) LEO satellites during night and day. Low-power integrated beam control results will be extrapolated to high power through detailed simulation and performance analysis.

The objective of this effort is to provide the best AJ capability for the lowest possible increment (less than $3,000) to the Joint Direct Attack Munition (JDAM) unit production cost (based on a 72,000-unit buy in FY92 dollars). Success will be measured by maintaining JDAM-required GPS navigation accuracy at the target (13-m CEP) while in a jammed environment. Additionally, the program will develop a cost/performance modeling tool that will enable a user to determine the cost per jam resistance needed for his particular application.

During Phase I, the AJ concept was tested at the subsystem level against scenarios containing multiple jammers to demonstrate AJ performance capability. Phase I subsystem tests were conducted in anechoic-chamber (Naval Research and Development, Warminster, PA) and bench-test (Antenna Wavefront Simulator, Wright Laboratory Avionics Directorate) environments. Phase II of the program (Jan 96-Feb 97) integrates the AJ concept into a suitable carrier vehicle (a JDAM Tail Kit Assembly) for ground and flight tests in a jamming environment. Phase III (Mar 97-Aug 97) involves ground tests of the fully integrated Tail Kit Assembly in a static and semi-dynamic environment. The Tail Kit Assembly will be evaluated in the anechoic chamber at Eglin AFB to obtain antenna performance data of the actual flight hardware, which will be used to update the cost/performance model. The second ground test will use the Wright Laboratory Armament Directorate's Mobile Test Vehicle to introduce the AJ-equipped JDAM navigation system to a low dynamic jammed environment for risk reduction prior to flight testing. Phase IV (Sep 97-Feb 98) is the flight test portion of the program. The test will use a GPS-equipped F-16 to release the AJ-equipped munition in two jamming environments of increasing difficulty.

Specific technology advancements are expected in the areas of RF transmitters, antennas, long standoff shaped-charge warheads, advanced materials for missile armor, and impact sensors for characterizing high-velocity impact phenomena.

CAPS mid-term RF countermeasures will be demonstrated in a breadboard form by FY98, and in flight prototype (FY99 and FY00). Far-term RF countermeasures will be breadboarded by FY99 and demonstrated in flight prototype by FY01 and FY02. A near-term RF countermeasure is currently being transitioned to a flight demonstration sponsored by a missile system project manager. Long standoff warheads will be demonstrated statically in FY98 and dynamically in FY99. A long standoff warhead integrated with munition survivability technology will be demonstrated in a dynamic sled test in FY99 and in an integrated flight demonstration against an APS target in FY01.

The payoff for successful development and demonstration of CAPS technologies will be to limit the reduction of ATGW lethality to less than 10% against modern tanks using APS.

Producibility enhancements under consideration have the potential to reduce seeker costs from $150,000 to less than $30,000 per unit, significantly improving weapon affordability. This effort will provide a revolutionary new air-to-surface precision guidance capability for operations in adverse weather.

FY96 goals include component development, with FY97 demonstration of 120mm KE precursor penetrator to defeat the 2005 ERA projected threat with a 50% increase in lethality over the M829A2. In FY98, the goal is to statically demonstrate a 120mm STAFF dual-liner explosively formed penetrator (EFP) warhead function to form an ultra long EFP and conduct a hardstand dynamic demonstration of an Electric Direct (gearless) Turret Azimuth Drive technology. In FY99, a Smart Barrel Actuator active damping control of a M256 120mm gun tube will be demonstrated in a nonfiring, dynamic test resulting in FY00-01 demonstrations of same. The ATD exit criteria in FY00 require an integrated 120mm KE Cartridge to defeat the 2005 ERA protected threat, with a 30% increase in system accuracy under stationary conditions over the M829A2/M1A2, and the demonstration of a 33% or more increase in armor defeat with a 120mm dual-liner STAFF warhead. In FY01, demonstrate a 300% increase (at 3 km) in probability of hit over the M1A2 under dynamic scenarios using Smart Barrel Actuators, fully integrated gearless turret/gun direct drives, and modern digital servo control. (Note: The Advanced KE Cartridge Fast Track Acquisition Program is a joint effort with PM-TMAS. The PM will provide $4.6 million in FY98 and $6.8 million in FY99, pending an M829E3 technology decision in FY97.)

An alternate approach for a miniaturized IMU being pursued by the Navy, the Precision Strike Navigator, will be demonstrated by FY98. Using advanced polymer-on-silicon technology, a low cost ($2,000/axis), 1-nmi/hr (inertial grade), hybrid fiber optic gyro (FOG)-based inertial measurement unit (IMU) chip, containing the accelerometer, FOG optics, and all of the IMU electronics, will be demonstrated. The fiber coil is external to the chip. It provides a potential low-cost miniature inertial grade IMU whose projected cost is $6,000 (based on 100,000-unit production volume) for a complete three-axis IMU. This IMU could then be integrated with a miniaturized GPS receiver.

Milestones include, by FY97, integrating and testing the flight computer/autopilot software, integrating and testing flight hardware, and performing a full-up missile sled test; and, by FY98, 40-km flight tests. Technology barriers include 40-km fiber payout in missile-sized canister; low-cost turbojet technology for both boost and sustain; and reconfigurable airframe for slow and fast flight.

The goal is to demonstrate bandwidth five times that of existing torpedo sonars. Broadband sensors and signal processing technologies will be developed in the 6.2 program and demonstrated in water in an ATD planned for FY99. The ATD will integrate broadband sensors and signal processing techniques into a test vehicle and demonstrate improved performance in shallow-water environments against both artificial and real targets. The demonstrations will show detection ranges increased by a factor of two and false alarm probabilities reduced by a factor of two, relative to existing narrow-band systems. These demonstrations will be concluded in FY01. The sensors and signal processing demonstrated will be capable of being inserted with minimal impact into existing operational torpedo inventories and into any new torpedo developments, and will provide significant, cost-effective enhancements to warfighting capabilities.

Specific demonstrated capabilities of ETC include, by FY99, 17-MJ muzzle energy from an 120mm XM291 cannon. Specific demonstrated capabilities in EM and ETC include, by FY99, pulsed power systems compact enough for armored vehicles, specifically compensated pulsed alternators capable of 3.0 J/g. Specific demonstrated capabilities in EM include, by FY99, hypervelocity launchers with a 100-round tube life and integrated launch packages with less than 50% parasitic mass launched at 2.5 km/s having a muzzle energy of 7 MJ. For all classes of electric armaments, systems analysis and critical tests show improved battlefield effectiveness and no fatal flaws.

Milestones for ETC include, in FY97, two possible propulsion candidates which can be fired from a 120mm cannon and, in FY98, demonstration of 14-MJ muzzle energy fired from an 120mm M256 cannon. Milestones for CPA include, in FY97, 1.5 J/g specific energy in a pulsed power system. Milestones for EM include, in FY97, a demonstration of a wear-resistant rail material; by FY98, that there are no EM specific accuracy barriers; and, by FY97, that parasitic mass in subscale projectiles is reduced.

Technical barriers for ETC include high-energy, high-density propellant formulations and geometries; design of plasma capillaries for effective coupling of electrical energy into propellants; and control of propellant temperature gradient effects. Those for EM are high-strength, thick-section composites; high-current capacity, fast-actuating and -recovering solid-state switches; high-efficiency launchers; thermal management; and reduced mass armatures.

Specific capabilities to be demonstrated include a weapon system with component weight goals as follows: weapon less than 38 lb, a ground mount less than 12 lb, ammunition less than 0.35 lb, and a fire control less than 7 lb. The system will have the capability to defeat defilade targets and 51mm rolled homogeneous armor.

Technical challenges for the OCSW include efficient fragmentation, electronics miniaturization (fire control and fuze), systems integration, and overall system weight.

The Air Superiority Missile Technology (ASMT) concept consists of a reduced drag, wingless AMRAAM airframe modified with main propulsion chamber-bleed reaction jet controls positioned aft of the reduced span tail fins. The ASMT concept allows stable flight at angles of attack up to 90 deg, using robust reaction jets to rotate the missile to the rear hemisphere slightly over 2 seconds after launch; the reaction jet assembly also provides critically needed missile roll control. The reaction jets are only used when necessary for high off-boresight maneuvers and have no impact on beyond-visual-range flight performance. The current box size for the ASMT concept is 9.5", as compared to the 12.5" box size of the clipped-fin AIM-120C. Production cost estimates for a conceptual tactical weapon employing ASMT technologies indicate a cost impact relative to nominal AMRAAM of less than 4% of the total missile cost.

By FY02, the program will demonstrate increased f-pole, decreased inner boundary, increased average velocity, increased maneuverability, increased high-altitude controllability, decreased box size, and increased maximum flyout range over both AIM-9X and AIM-120C. Program milestones include: by FY98, developing an agile-AMRAAM missile design that uses reaction jet/tail fin control, and conducting manned air combat evaluations; by FY01, fabricating sufficient test articles through ground tests in preparation for unguided flight demonstrations; and by FY02, conducting unguided flight demonstrations of the advanced airframe concept, and developing seeker integration designs for an electronically steered conformal array seeker under parallel development. Technical barriers include reaction jet control implementation onto inventory AMRAAM rocket motors, reaction jet response time less than 10 milliseconds, stable flight of modified AMRAAM at a 90-deg angle of attack, compact packaging of all new technologies within the length/weight constraints of F-22 weapons bay, and development of over-the-shoulder guidance methodologies.

The expected products for transition of this advanced technology demonstration include a new autopilot design through the use of robust optimization techniques; a new guidance filter and guidance law design integrated with the autopilot to substantially reduce the overall guidance time constant; and an increase in maneuverability through the accommodation of cross-coupling effects at high angles of attack and structural strength of critical missile components. Additional benefits include improved performance against targets, jammers, and decoys, and application to hit-to-kill interceptors.

Key demonstrations include projected missile capability and technical objectives, time response improvements, guidance filter performance, and 6-DOF simulation (FY96); subsystem test results, flight software performance, and hardware-in-the-loop and 6-DOF simulations (FY97); and flight tests and results, guidance performance, and EMD readiness (FY98).

The program also will develop, by FY01, Fotofighter laser technology by combining technology development for semiconductor laser diodes, coherent laser diode array architectures, and electronic beam steering into a demonstration of moderate- to high-power laser systems which can be constructed as conformal arrays of phased, electronically steerable diode lasers in the skin of an advanced aircraft. This demonstration will establish the technology for low-drag, compact, high-efficiency laser weapons for use in both offensive and defensive roles. Fotofighter provides an all-aspect capability for air-to-air and air-to-surface engagements. Technology advances needed include wide-angle beam steering, high-power thermal control of laser arrays, and wavelength versatile semiconductor laser materials. The criterion for success is demonstration of a building-block, kilowatt-class, phased-array-laser module for scaling to multikilowatt applications. The program will demonstrate, by FY05, kilowatt-level, short-wavelength, phased-laser arrays and by FY06, 100-W IR phased laser arrays.

This program will develop and demonstrate a three-band, packaged mid-infrared semiconductor laser system. The focus of the Multiband IRCM Laser Source Solution (MISS) effort will be fixed-wing and rotary-wing IRCM programs. The principal technology issues are development of high-brightness, high-operating-temperature Band IV laser diodes, and development of novel resonator configurations for current-generation Band I and II laser diodes. The metrics for this program will be far-field brightness in the mid-IR bands of interest and weight/volume and electrical power requirements of the IRCM system. Specific performance goals are a factor of three improvement in the brightness over current generation Band IV semiconductor lasers and a 50 K increase in the operating temperature for Band IV laser output. This program will be a coordinated Army/Navy/Air Force effort to develop and demonstrate semiconductor laser technology for advanced IR missile threats.

Milestones include, in FY97, demonstrate detection, classification, and localization of quiet submarines and surface ships at medium water depths (150-600 ft); in FY98, demonstrate shallow- and intermediate-water-depth, low-data-rate communications between mines/relay nodes, and use of low-cost acoustic transmitters/receivers to ranges of up to 10 nmi; by FY99, demonstrate the ability to accurately classify targets detected by a suite of acoustic and nonacoustic sensors integrated into sensor nodes in a sensor field; by FY00, demonstrate multiple concepts for RECO connectivity from manned air, surface, and subsurface command platforms to shallow-water planted mines; by FY01, demonstrate in a virtual laboratory environment, using actual autonomous node hardware embedded in a virtual simulation environment, an armed autonomous network capability; and by FY03, demonstrate the feasibility of a minefield with the effectiveness, flexibility, and RECO capability provided by an intelligent, intercommunicating sea minefield/distributed surveillance network concept.

Technical barriers include underwater detection of quiet targets; automated classification of targets; multisensor node coordination and real-time target decision algorithms; very shallow water underwater communications at tactically significant ranges; autonomous network control/coordination protocols; safe, reliable, low-volume/-weight, high-energy, long-life batteries; and data management.

Specific demonstrated capabilities are to deliver M829A2-equivalent KE at 175 m and maintain as a minimum that level of energy to beyond 5 km with the advanced KE penetrator delivered by a lightweight (35-40 kg) miniature hypervelocity KE missile. The program will demonstrate the missile, which accelerates to a peak velocity of 2,200 m/s and delivers in excess of 30 MJ to the target at a range of less than 500 m out to a range of 4 km, and 25 MJ at 5 km. The propulsion system will meet joint service insensitive munitions requirements.

Milestones include demonstrating motor and propulsion concepts by FY98; novel penetrators integrated with the airframe by FY00; and a miniaturized, hardened inertial guidance system by FY01. Flight tests will be conducted in FY03.

Technical barriers include: development and integration of miniaturized guidance and continuous control actuation technology, application of advanced composite technologies in high-performance propulsion systems, fire control, propulsion technologies, and enhanced lethality effects from advanced KE penetrator designs.

Technical barriers include achieving effective engagement range capability against the full target set, developing and packaging the complete seeker including electronics in a 2.75" missile-compatible size, demonstrating advanced IR CCM capability against known projected countermeasures, and achieving operational and computability with a rolling airframe missile.