Abstract: A wing deployment initiator initiates penetration of frangible cover seals by missile guidance wings during wing deployment. The initiator includes a central, rotatable hub extending above a baseplate. Lobes extending from the hub prevent rotation of associated flippers by torsion springs. Locking and deployment tabs extend from the flippers into corresponding notches in proximal ends of the wings. The locking tabs prevent deployment of the wings until the central hub is rotated, whereupon the flippers are released, causing the deployment tabs to transfer deployment energy from the torsion springs to the wings. The hub can be rotated by an electrical actuator such as a solenoid or motor, or the lobes can be rotationally offset so that feedback pressure from the flippers applies a torque to the hub, and missile electronics can cause a wing control surface to inhibit and then enable hub rotation via a rocker link.

Abstract: A wing deployment initiator initiates penetration of frangible cover seals by missile guidance wings during wing deployment. The initiator includes a central, rotatable hub extending above a baseplate. Lobes extending from the hub prevent rotation of associated flippers by torsion springs. Locking and deployment tabs extend from the flippers into corresponding notches in proximal ends of the wings. The locking tabs prevent deployment of the wings until the central hub is rotated, whereupon the flippers are released, causing the deployment tabs to transfer deployment energy from the torsion springs to the wings. The hub can be rotated by an electrical actuator such as a solenoid or motor, or the lobes can be rotationally offset so that feedback pressure from the flippers applies a torque to the hub, and missile electronics can cause a wing control surface to inhibit and then enable hub rotation via a rocker link.

Abstract: A pressure relief valve having two rigid sealing surfaces lapped to a smoothness Ra of 8 micro-inches or less, and flatness within 80 micro-inches, forms a reliable seal by direct contact therebetween without an elastomer. The sealing surfaces and surrounding structures can be made of one or more metals, such as alloys of stainless steel, and can be CTE-matched, so that the valve is not impeded by environmental temperature changes. In a disclosed embodiment, a “poppet” is axially pressed against a seal plate by a spring. The poppet can be axially stabilized by sliding within a surrounding cylinder or spacer, and can contact the surrounding surface with a plurality of “arms” that reduce friction and enable gas flow therebetween. The poppet can be made from anti-galling Nitronic 60 alloy, and the surrounding structures can be stainless steel. Embodiments are suitable for low-pressure gas applications in extreme environments.

Abstract: A pressure relief valve having two rigid sealing surfaces lapped to a smoothness Ra of 8 micro-inches or less, and flatness within 80 micro-inches, forms a reliable seal by direct contact therebetween without an elastomer. The sealing surfaces and surrounding structures can be made of one or more metals, such as alloys of stainless steel, and can be CTE-matched, so that the valve is not impeded by environmental temperature changes. In a disclosed embodiment, a “poppet” is axially pressed against a seal plate by a spring. The poppet can be axially stabilized by sliding within a surrounding cylinder or spacer, and can contact the surrounding surface with a plurality of “arms” that reduce friction and enable gas flow therebetween. The poppet can be made from anti-galling Nitronic 60 alloy, and the surrounding structures can be stainless steel. Embodiments are suitable for low-pressure gas applications in extreme environments.

Abstract: A battery door assembly for a battery compartment is disclosed. The battery door assembly includes a battery cover, glide track, a spring-loaded button, a locking tab and a plurality of hinges. The plurality of hinges is pivotally connected to a chassis of a scope. The locking tab keeps the battery cover from opening. The battery cover can be unlocked by first applying pressure on the spring-loaded button, and then sliding the spring-loaded button and the locking tab from one end of the glide track to another end of the glide track while maintaining the applied pressure on the spring-loaded button.

Abstract: A battery door assembly for a battery compartment is disclosed. The battery door assembly includes a battery cover, glide track, a spring-loaded button, a locking tab and a set of hinges. The set of hinges is pivotally connected to a chassis of a scope. The locking tab keeps the battery cover from opening. The battery cover can be unlocked by first applying pressure on the spring-loaded button, and then sliding the spring-loaded button and the locking tab from one end of the glide track to another end of the glide track while maintaining the applied pressure on the spring-loaded button.

Abstract: Non-linear forces are simulated by a dual-rate spring apparatus, which may also be used to impose nonlinear forces. The apparatus includes a carriage and at least two springs arranged sequentially in series with one another. The spring constant is changed by initially allowing both of the springs to compress to a point and, thereafter, after one spring is generally completely compressed, allowing only the other spring to compress further.

Abstract: Non-linear forces are simulated by a dual-rate spring apparatus, which may also be used to impose nonlinear forces. The apparatus includes a carriage and at least two springs arranged sequentially in series with one another. The spring constant is changed by initially allowing both of the springs to compress to a point and, thereafter, after one spring is generally completely compressed, allowing only the other spring to compress further.

Abstract: An apparatus for deploying stowed control surfaces of a projectile is disclosed. The apparatus for deploying stowed control surfaces of a projectile includes a first and second hot gas generators, a first and second gas chambers, a piston wedge, a piston and a barrel. Initially, the first hot gas generator discharges a surge of hot gas into the first gas chamber. In response to the surge of hot gas being discharged into the first gas generator, the piston wedge displaces at least one of the control surfaces to break an environmental seal covering the projectile. After a predetermined amount of time has lapsed, the second hot gas generator discharges a surge of hot gas into the second gas chamber. The surge of hot gas displaces the piston and barrel for deploying the control surfaces completely.

Abstract: An apparatus for deploying stowed control surfaces of a projectile is disclosed. The apparatus for deploying stowed control surfaces of a projectile includes a first and second hot gas generators, a first and second gas chambers, a piston wedge, a piston and a barrel. Initially, the first hot gas generator discharges a surge of hot gas into the first gas chamber. In response to the surge of hot gas being discharged into the first gas generator, the piston wedge displaces at least one of the control surfaces to break an environmental seal covering the projectile. After a predetermined amount of time has lapsed, the second hot gas generator discharges a surge of hot gas into the second gas chamber. The surge of hot gas displaces the piston and barrel for deploying the control surfaces completely.

Abstract: A low cost, lightweight frangible wing slot seal can be applied to a guidance wing slot of a folding fin aerial rocket or missile, providing a barrier against exposure of internal missile components to external contaminants, while allowing unhindered deployment of missile guidance wings simply by bursting through the seals. The simple design is nearly foolproof, and has no impact the likelihood of weapon failure. The seal is a flexible sheet which is sufficiently thin so as not to exceed the required volume envelope of the missile. The sheet includes a burst seam, which is breached when impacted by the leading edge of a deploying wing. No additional wing deployment force is required, and after deployment the seal has minimal impact on the aerodynamic performance of the wing.

Abstract: A low cost, lightweight frangible wing slot seal can be applied to a guidance wing slot of a folding fin aerial rocket or missile, providing a barrier against exposure of internal missile components to external contaminants, while allowing unhindered deployment of missile guidance wings simply by bursting through the seals. The simple design is nearly foolproof, and has no impact the likelihood of weapon. failure. The seal is a flexible sheet which is sufficiently thin so as not to exceed the required volume envelope of the missile. The sheet includes a burst seam, which is breached when impacted by the leading edge of a deploying wing. No additional wing deployment force is required, and after deployment the seal has minimal impact on the aerodynamic performance of the wing.