TECHNOLOGY AREA(S): Weapons OBJECTIVE: Demonstrate control mechanism technology for munitions to improve performance along the axes of maneuverability, gun launch survivability loading scales, and/or size-weight-power of components. DESCRIPTION: Gun-launched guided munitions are of tremendous interest to the U.S. Army. These technologies offer more accuracy, extended range through glide, more favorable terminal approach for lethality, and the ability to engage advanced threats like partially hidden (defilade) and moving ground and air targets. The M982 (Excalibur), fielded in the mid-2000s, is a guided artillery projectile which delivers the warhead to within about 10m of the target compared with traditional unguided artillery which have a delivery accuracy of about 200m. The M1156 (Precision Guidance Kit) was introduced in the mid-2010s and is a low cost fuze-replacement guidance kit for stock-piled artillery munitions which delivers the warhead approximately 50m from the target. Research conducted 10+ years ago was pivotal in providing these capabilities to the U.S. Army. As an example, the concept of the spin-stabilized artillery fuze kit that M1156 performance relies on was initially published in the Journal of Spacecraft and Rockets in 19751. Current gun-launched guided munition technologies are limited to indirect fire against stationary targets on the ground. Enhanced control mechanism technologies (e.g., actuator speed, torque) could increase the maneuverability of aerodynamically controlled vehicles and ultimately result in advanced weapons system capabilities such as: extreme range extension, enhanced maneuver authority which enables intercepting moving ground and air targets, and increased trajectory shaping that could be used to change the mid-course path of the projectile or control the terminal approach angle to maximize lethality. Several operational constraints have limited the effectiveness of actuation technology that is conventionally used in guided missiles to their gun-launched counterparts. The gun launch event imposes severely high structural loadings as the projectile is accelerated from stationary to muzzle velocities exceeding 4 times the speed of sound. On-board components such as actuators must survive these loads during launch. There are some actuation technologies which have been demonstrated to survive the indirect fire launch environment (peak loads ~20,000 Gs) but very little research conducted to meet requirements for any other launch environments (e.g., direct fire) where loads can exceed 60,000 Gs. Additionally, actuation technologies have primarily been form factored into large caliber munitions but a much wider range of applications (e.g., small-medium caliber direct fire, grenades, shoulder-launched munitions, small mortars) could be guided if small, robust actuation technologies existed. Finally, achieving sufficient torque and speed with conventional motors has typically been achieved with complex and precise custom gearing which increases the cost of the system. Thus, advancements of actuation technologies in speed, torque, size, and survivability with reduced cost would benefit the guided weapons community. Small business specializing in areas such as precision motion solutions may offer unique actuation technologies which could provide enhanced characteristics to enable these future gun-launched guided munitions capabilities. Innovative solutions in electro-mechanical design, power conditioning, feedback sensing, embedded processing, and control algorithms are encouraged, for example, to enhance the actuator speed (>1200deg/s), torque (>1N-m aerodynamic loads), backlash (<1% nonlinearity), size (<20cm3) and power (<100mA-hr at 12V) specifications over existing motor and servomechanism technologies for short duration (<5min) operation in this environment subject to extreme structural loadings (>40,000 Gs) at launch. Commercialization of this technology will result in licensing and sales to the military for guided weapons programs. Other applications that may benefit from commercialization of small, fast, high torque, linear, low cost flight actuators include the drone community. PHASE I: Conceptualize control actuation technologies for enhancing maneuverability of high-G survivable, small munitions. Apply physics-based modeling of the dynamics to design and characterize the performance of the software (e.g., control algorithm) and hardware component technologies. Ensure that extreme environment constraints (e.g., loading at gun launch) are considered appropriately. Perform simulations and provide models and results to assess technical feasibility along performance metrics of speed, torque, backlash, power budget, and survivability. Conduct limited experiments (e.g., breadboard components in lab, component response on shock table) to validate some aspects of modeling and simulation. PHASE II: Employ advanced laboratory experimental characterization to perform system identification and develop a full-spectrum performance model of the technology (for example to use in modeling and simulation). Conduct dynamic wind tunnel experiments to assess performance in a well-controlled, realistic environment. Air-gun, and gun-launched firings of the technology to determine the survivability of actuation components as well as open- and closed-loop controlled (i.e., maneuvering) flights for demonstration in a ballistic environment. These activities validate the estimates of speed, torque, backlash, power budget, and survivability to confirm that the technology meets the performance requirements. Provide results to the technical and user (in this case the Fires and Maneuver Centers of Excellence would be the most relevant organizations) communities for consideration in generating requirements for future gun-launched guided munitions. PHASE III: Improve market competition and act as a component technology provider to industry weapons systems integrators (e.g., Raytheon Missile Systems, Lockheed-Martin Missiles and Fire Control, Orbital ATK) for these novel control mechanism technologies in future weapons systems (e.g., High Explosive Guided Mortar). REFERENCES: 1: Regan, F.J. and Smith. J., "Aeroballistics of a Terminally Corrected Spinning Projectile" Journal of Spacecraft and Rockets, Vol. 12, No. 12 (1975), pp. 733-738.KEYWORDS: Guided Weapons, Maneuver Technologies, Control Actuation, Gun Launched Munitions CONTACT(S): Frank Fresconi (410) 306-0794 frank.e.fresconi.civ@mail.mil
