N142-108 TITLE: Electronic Thermally Initiated Venting System (ETIVS) Trigger and Thermal Sensor

TECHNOLOGY AREAS: Air Platform, Ground/Sea Vehicles, Weapons

ACQUISITION PROGRAM: PMA 259

RESTRICTION ON PERFORMANCE BY FOREIGN NATIONALS: This topic is "ITAR Restricted". The information and materials provided pursuant to or resulting from this topic are restricted under the International Traffic in Arms Regulations (ITAR), 22 CFR Parts 120-130, which control the export of defense-related material and services, including the export of sensitive technical data. Foreign nationals may perform work under an award resulting from this topic only if they hold the "Permanent Resident Card", or are designated as "Protected Individuals" as defined by 8 U.S.C. 1324b(a)(3). If a proposal for this topic contains participation by a foreign national who is not in one of the above two categories, the proposal may be rejected.

OBJECTIVE: Design and develop high temperature mixed signal integrated circuit designs suitable for implementing an in-line Electronic Thermally Initiated Venting System (ETIVS) trigger and thermal sensor to replace existing out-of-line devices on current and future weapons systems.

DESCRIPTION: Current Thermally Initiated Venting Systems (TIVS) consist of a thermal sensor, trigger, out-of-line blocking device, initiator, transfer energetic, and a linear shaped charge. A TIVS reduces the reaction violence of munitions exposed to cook-off events by scoring the case of the rocket motor, but not penetrating the case and igniting the propellant. The TIVS trigger is intended to function when the rocket motor is placed in extreme temperature conditions that cause the rocket motor to cook-off, both with slow heating rates (e.g., Slow Cook-off or "SCO") and fast heating rates (e.g., Fast Cook-off or "FCO"). Technologies needed to implement an ETIVS trigger and thermal sensor are desired to increase the flexibility in application, safety and reliability of state-of-the-art TIVS designs. Technology development should be focused on integrating the thermal sensor, trigger and safety features of the TIVS using electronic circuits to form a compact ETIVS device.

The ETIVS device does not currently exist, but is based on existing mechanical TIVS technology and will be a safety-critical device that controls the initiation of energetic materials. This requires implementation of a safety critical design methodology with requirements similar to those laid out in MIL-STD-1901A and MIL-STD-1316E. The safety critical nature of the ETIVS device will necessitate the respondents working closely with technical representatives from the US Navy Safe-Arm Fuzing community during all stages of the development.

Guidelines and Metrics:
� The ETIVS device needs to sit unpowered but support function during cook-off events, i.e., the device must support reliable TIVS operations in fast heating and slow heating (6 to 45�F/hour), as well as non-uniform heating environments.
� The ETIVS device must be tunable for multiple temperatures.
� The ETIVS device needs to integrate onto missile airframes of 5" to 21" diameter with minimum form factor and mass impact. Preference will be given to devices that can easily be integrated into small diameter air-launched platforms.
� The ETIVS device must have no single point of failure and lock out operation after planned ignition event with less than 1 x 10-6 probability of failure in either the TIVS triggering or operational lock-out modes.
� The ETIVS device needs to be capable of surviving tactical missile environments (air and surfaced launched).
� A lock-out during planned flight events, including acceleration of approximately 10g�s, is required. This detector must output a signal that is persistent through the time when the rocket motor burns out. The acceleration detector must function without an external power source or an internal battery. It is preferred, but not required, to implement this acceleration detector using electronic circuit components. Similar logic controls to account for aero-heating environments are desired.
� The ETIVS device will require two independent thermal sensor technologies. Both sensor technologies must measure rocket motor case temperatures up to and including 600�F (316� C). Off the shelf temperature sensing technologies are preferred, but custom solutions are acceptable.
� Multiple temperature sensors may be distributed along the rocket motor case, necessitating small size and low mass thermal sensor technologies to ease integration. Low cost sensor technologies are preferred, but the priority is small size and low mass.
� The ETIVS device will require a variety of mixed-signal electronics. Proposed circuit elements must be operational to 350�F (177� C) with long term storage across the military temperature range of -67�F to 257�F (-55� C to 125� C).
� The ETIVS device will be self-powered using a thermally activated power source. There must be an externally accessible indicator, preferably a visual indicator, which activates when the power source has been activated. Thermal battery technology suitable to implement this power source is currently in development at China Lake. Alternative thermally activated power source technologies may be proposed, but development will not be funded under this solicitation.
� ETIVS solutions must address affordability and producibility using current manufacturing technologies, as well as performance and overall packaging.

PHASE I: Determine technical feasibility of the ETIVS logic circuitry, thermal sensors, self-powering or parasitic power functions and lock-out device under different heating rates and possibly under centrifuge acceleration. These sub-elements may be demonstrated through simulations that demonstrate operation to at least 350�F (177� C).

PHASE II: Continue development of the ETIVS functionality using the circuit elements demonstrated through simulations in Phase I. Demonstrate a prototype integrated package in representative slow and fast heating rates, centrifuge lock-out trials and self-power features. Integrate the ETIVS sensor and trigger with an optional linear shaped charge during these demonstrations. Deliverables for Phase II include a briefing to Fuze and Initiation Safety Technical Review Panel (FISTRP) for technical assistance in approach.

PHASE III: Finalize the prototype design and transition into a Navy system application that meets form factor and environmental conditions. Provide a final design full ETIVS trigger and thermal sensor for motor level Insensitive Munitions (IM) testing to be conducted by the Government at Naval Air Weapons Center Weapons Division China Lake.

PRIVATE SECTOR COMMERCIAL POTENTIAL/DUAL-USE APPLICATIONS: Emerging markets in the commercial sector demand sensor conditioning and other mixed signal application circuitry be placed in extreme temperature environments, such as down oil wells and in hot sections of engines. Technology developed during this effort will be directly transferrable into these emerging markets.

REFERENCES:
1. MIL-STD-1316E - Fuze Design, Safety Criteria For, July 1998.

2. MIL-STD-1901A - Munition Rocket and Missile Motor Ignition System Design, Safety Criteria For, June 2002.

3. MIL-STD-1911A - Hand-Emplaced Ordnance Design, Safety Criteria For, July 1998.

4. STANAG 4170 Rev.3 - Principles and Methodology for the Qualification of Explosive Materials for Military Use, February 2008.

5. MIL-STD-331C - Fuze and Fuze Components, Environmental and Performance Tests For, June 2009.

6. JOTP-52 - Guidelines for the Qualification of Fuzes, Safe and Arm (S&A) Devices, and Ignition Safety Devices (ISD), February 2012.

7. MIL-STD-882E - DoD Standard Practice - System Safety, May 2012.

8. MIL-STD-2105D - Hazard Assessment Tests for Non-Nuclear Munitions, April 2011.

9. AOP-7 Ed. 2 - Manual of Tests for the Qualification of Explosive Materials for Military Use, June 2003.

10. Graham, K. J., January 2010, Mitigation of Fuel Fire Threat to Large Rocket Motors by Venting. AFRL-RZ-ED-TP-2010-368.

KEYWORDS: Fuzes; Insensitive Munitions; Rocket Motors; High-Temperature Electronics; Safety Device; Thermally Initiated Venting System (TIVS)

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