Abstract: A control surface restraining system for variably restraining a control surface on a flight vehicle includes a passively triggered and manually movable control surface restraint for keeping the control surface aligned along a longitudinal axis of the flight vehicle, while allowing for temporary control surface rotation during handling and loading. The control surface restraining system allows the control surfaces to be manually rotated out of and back to the “zero position” (i.e., aligned along the longitudinal axis) for loading the flight vehicle with a common load strap, and thereafter maintained in the “zero position” until launch for proper control actuation system initialization. Upon launch, the control surface restraining system is passively actuated for releasing the control surface, requiring no active stimulus from the guidance section, power, or associated wiring, therefore saving critical space and volume within the tactical flight vehicle.

Abstract: A system for restraining one or more control surfaces of a tactical flight vehicle includes a retaining frame secured at an aft end of the tactical flight vehicle and a cover plate releasably coupled to the retaining frame with a resilient lock ring. The resilient lock ring is disposed between the retaining frame and the cover plate and is deformable between a locking configuration and an unlocking configuration. A control surface restraining ring is releasably coupled to the cover plate and has control surface restraints configured to engage respective control surfaces. The resilient lock ring is configured to deform from the locking configuration to the unlocking configuration upon a launch of the tactical flight vehicle such that the cover plate becomes uncoupled from the retaining frame and may be jettisoned from the tactical flight vehicle after the launch.

Abstract: A system for restraining one or more control surfaces of a tactical flight vehicle includes a retaining frame secured at an aft end of the tactical flight vehicle and a cover plate releasably coupled to the retaining frame with a resilient lock ring. The resilient lock ring is disposed between the retaining frame and the cover plate and is deformable between a locking configuration and an unlocking configuration. A control surface restraining ring is releasably coupled to the cover plate and has control surface restraints configured to engage respective control surfaces. The resilient lock ring is configured to deform from the locking configuration to the unlocking configuration upon a launch of the tactical flight vehicle such that the cover plate becomes uncoupled from the retaining frame and may be jettisoned from the tactical flight vehicle after the launch.

Abstract: A control surface restraining system for variably preventing movement of a control surface imparted by a control actuation shaft of a control actuation section of a tactical flight vehicle includes a power take-off shaft operably connected to the control actuation shaft with a power take-off gear train and a control surface restraint. The control surface restraint is configured to variably engage the power take-off shaft, thereby locking the power take-off gear train and preventing the control actuation shaft from imparting the movement of the control surface. The control surface restraint is also configured to variably disengage the power take-off shaft, thereby unlocking power take-off gear train and allowing the control actuation shaft from imparting the movement of the control surface.

Abstract: A control surface restraining system for variably restraining a control surface on a flight vehicle includes a passively triggered and manually movable control surface restraint for keeping the control surface aligned along a longitudinal axis of the flight vehicle, while allowing for temporary control surface rotation during handling and loading. The control surface restraining system allows the control surfaces to be manually rotated out of and back to the “zero position” (i.e., aligned along the longitudinal axis) for loading the flight vehicle with a common load strap, and thereafter maintained in the “zero position” until launch for proper control actuation system initialization. Upon launch, the control surface restraining system is passively actuated for releasing the control surface, requiring no active stimulus from the guidance section, power, or associated wiring, therefore saving critical space and volume within the tactical flight vehicle.

Abstract: A remote actuation system for de-manning a human/machine interface emulates the interface protocol to interact with the interface at a mechanical level. The system may function autonomously or with a remote human operator. At least one imaging module and at least one switch module with the same relative positions as and a complementary relief to the interface's gauge(s) and mechanical switch(es) are mounted on the instrument panel. The modules may be individually mounted or provided on a remote actuation panel that fits over the instrument panel. A data cable connects the imaging and switch modules to a processing module having at least one computer processor configured to execute an image-processing sub-module and a switch sub-module to emulate the protocol to interact with the interface at a mechanical level. The estimate of the measured value may be fed back to generate the switch command to control the remote switch actuator.

Abstract: A remote actuation system for de-manning a human/machine interface emulates the interface protocol to interact with the interface at a mechanical level. The system may function autonomously or with a remote human operator. At least one imaging module and at least one switch module with the same relative positions as and a complementary relief to the interface's gauge(s) and mechanical switch(es) are mounted on the instrument panel. The modules may be individually mounted or provided on a remote actuation panel that fits over the instrument panel. A data cable connects the imaging and switch modules to a processing module having at least one computer processor configured to execute an image-processing sub-module and a switch sub-module to emulate the protocol to interact with the interface at a mechanical level. The estimate of the measured value may be fed back to generate the switch command to control the remote switch actuator.

Abstract: Methods and apparatus for mounting a secondary system on a projectile according to various aspects of the present invention operate in conjunction with a collar. The collar is adapted to at least partially receive a fuze assembly or other projectile structure within the collar. The collar may be adapted to attach to a cover.

Abstract: A system, device and method provide an exhaust assembly adapted for use with a mass ejection drive system to produce rotational torque about the principle axis of the drive system. Representative features generally include a vane suitably configured to at least partially engage a mass ejecta stream to apply a net rotational torque about the principal axis of the drive system, and a tailfin coupled to the at least one vane. The tail fin is configured to selectively deploy from an at least partially stowed position in order to decrease the application of net rotational torque about the principal axis of the drive system.

Abstract: The present invention concerns a method for designing a deployment mechanism for a flight surface on an airborne body, including the steps of determining a stowed position of the flight surface, determining a deployed position of the flight surface, identifying a first rotation axis and respective rotation angle and a second rotation axis and respective rotation angle about and through which the flight surface is rotatable in sequence to move the flight surface from the stowed position to the deployed position, or vice versa, and using the identified first and second rotation axes and rotation angles to determine a single equivalent rotation axis and angle, about and through which the flight surface can be rotated from the stowed position to the deployed position, or vice versa.

Abstract: The present invention concerns a method for designing a deployment mechanism for a flight surface on an airborne body, including the steps of determining a stowed position of the flight surface, determining a deployed position of the flight surface, identifying a first rotation axis and respective rotation angle and a second rotation axis and respective rotation angle about and through which the flight surface is rotatable in sequence to move the flight surface from the stowed position to the deployed position, or vice versa, and using the identified first and second rotation axes and rotation angles to determine a single equivalent rotation axis and angle, about and through which the flight surface can be rotated from the stowed position to the deployed position, or vice versa.