The parametric analysis of the centrifugal insurance mechanism in MEMS safety and arming device
In this paper, a MEMS S&A device has been proposed. The size of the device is φ 12×0.3mm. The role of the centrifugal insurance mechanism is to ensure the safety in handling transportation and storage, and reliable firing with the launch overload. Through establishing the three-dimensional model of the centrifugal insurance mechanism, establishing the force and the parameters of the centrifugal insurance mechanism, deriving the mathematical model according to the rigid dynamic mechanics theory and establishing the finite element model by using ANSYS/LS-DYNA, appropriate centrifugal insurance mechanism is designed to meet two items, one item is deformation of elastic beam can reliably release slider when the speed is more than 30000r/min and the centrifugal insurance mechanism can restrict the slider again when the speed is reduced; the other item is the centrifugal insurance mechanism can effectively restrict the slider to ensure the safety of the device when primary insurance accident arming in handling transportation.
DEVELOPMENT OF INEXPENSIVE, ULTRA-MINIATURE MEMS-BASED SAFETY AND ARMING (S&A) DEVICE FOR SMALL-CALIBER MUNITION FUZES
The development and demonstration of an inertially-operated micro-electro-mechanical systems (MEMS) mechanical safety and arming (S&A) device for artillery and small caliber fuzing has proceeded through concept, analysis, design, initial prototyping, and ballistic demonstration phases. This paper summarizes the implementation of “microscale inertial mechanical logic” for mechanical safety and arming functions in the form of sliders, rotors, latches, springs, and locks that interact on a planar substrate in response to inertially-induced forces, and the technical/fabrication issues encountered in the process. The program is sponsored by the U.S. Army TACOM ARDEC Joint Services Small Arms Program (JSSAP) Office, under the Objective Individual Combat Weapon (OICW) Systems Enhancements Science and Technology Objective (STO). The goal is to rapidly develop, demonstrate and transition lethality-enhancing and weight/cost-reducing technologies into the OICW system to ensure Objective Force Battlefield superiority.
MEMS-Based Solid Propellant Rocket Array Thruster
The prototype of a solid propellant rocket array thruster for simple attitude control of a 10 kg class micro-spacecraft was completed and tested. The prototype has 10×10 φ0.8 mm solid propellant micro-rockets arrayed at a pitch of 1.2 mm on a 20×22 mm substrate. To realize such a dense array of micro-rockets, each ignition heater is powered from the backside of the thruster through an electrical feedthrough which passes along a propellant cylinder wall. Boron/potassium nitrate propellant (NAB) is used with/without lead rhodanide/potassium chlorate/nitrocellulose ignition aid (RK). Impulse thrust was measured by a pendulum method in air. Ignition required electric power of at least 3–4 W with RK and 4–6 W without RK. Measured impulse thrusts were from 2×10−5 Ns to 3×10−4 Ns after the calculation of compensation for air dumping.