51results about How to "Resists deflection" patented technology

The present invention are surgical scissors having first and second pivotably connected elongate blade members wherein the second blade member is associated with a restraining member extending at least partially along said blade member and spaced therefrom to define a slot or channel in which the first blade member is at least partially received during cutting to restrain relative lateral movement of the blade members away from each other during a cutting stroke. Further, the present invention are scissors bearing blade urging means upon a handle portion of the scissors urging handle portions apart during a cutting motion but thereby urging opposing scissor blades, with increasing pressure, together as the cutting motion proceeds.

A bicycle rear sprocket assembly has a sprocket carrier, a first sprocket, a second sprocket and a third sprocket. The first and second sprockets are attached to opposite axial sides of the outer end portion of the attachment member of the sprocket carrier using a common fastener that extends through the first and second attachment portions and the outer end portion of the attachment member. The third sprocket is disposed on adjacent the second sprocket. The second sprocket has a free edge spaced radially inwardly from the common fastener by a distance at least as large as one-half of a maximum transverse dimension of the fastener measured in a direction perpendicular to the rotation axis. At least one space maintaining projection extends axially toward an adjacent one of the second and third sprockets.

An interconnect assembly including a substrate with a plurality of through holes extending from a first surface to a second surface. A plurality of discrete contact member are located in the plurality of through holes. The contact members include proximal ends that are accessible from the second surface, distal ends extending above the first surface, and intermediate portions engaged with an engagement region of the substrate located between the first surface and the recesses. Retention members are coupled with at least a portion of the proximal ends to retain the contact members in the through holes. The retention members can be made from a variety of materials with different levels of conductivity, ranging from highly conductive to non-conductive.

A capacitive ultrasonic transducer is described which include one or more cells including a cavity defined by a membrane electrode supported spaced from a support electrode by insulating walls with a patterned isolation layer having isolation posts or areas located in said cavity to prevent the electrodes for coming into contact during operation of the transducer, and to minimize the accumulation of charge as compared to a non-patterned isolation layer for preventing contact of the electrodes during operation of the transducer.

Apparatus and method are provided for decreasing frictional effects in stacks of Belleville springs and limiting deflection of the springs. In one embodiment, carriers for springs overlap and minimize the effects of lateral forces that are developed as springs in a stack are loaded. Carriers may be used on mandrel guides, in cylindrical guides or without a guide. In other embodiments, maximum load and defection of springs may be provided by the spring carriers.

A momentum management system for attitude control of a spacecraft includes a housing to be fixed to the spacecraft and a momentum wheel rotor in the housing for storing angular momentum. A gimbal assembly mounts the rotor in the housing. The rotor is driven by a drive with its output coupled to the rotor. A torque generation imparts torque to the rotor about axes orthogonal to the drive axis. The gimbal assembly includes a gimbal ring coupling the drive output to the rotor. The gimbal ring in turn includes flexure joints connecting the gimbal ring to the drive and the rotor. The flexure joints are configured to permit the rotor to tilt about two flexure axes orthogonal to the drive axis to incline the rotor axis through a range of angles from about 0 degrees to about 7 degrees with respect to the drive axis under the control of said torque generation device. The preferred flexure joint is formed from two resilient, crossing webs. The webs have ring ends connected to the body of the gimbal ring and mounting ends connected to either the drive or the rotor. The system includes a launch restraint system to limit movement of the rotor along the drive axis, including a stop mounted on the drive output and a cage mounted on the rotor, surrounding the stop. Under high acceleration, the cage engages the stop to support the rotor, relieving excess stress on the flexures of the gimbal suspension. The launch restraint system also includes deflection stops adjacent opposite sides of each web of each flexure for limiting deflection of the webs.

Valve assemblies include a valve body having a fluid passage through the valve body and a valve member disposed in a chamber of the valve body. The valve assembly further includes a first seat and a second seat, where both seats are configured to contact and provide a seal between the valve body and the valve member to at least partially inhibit fluid flow through the fluid passage. Methods of providing a seal in a valve include forcing a primary seat into a seat portion of a valve body to provide a seal between a valve member and the valve body with the primary seat and deflecting at least one arm of a secondary seat to provide another seal between the valve member and the valve body with the secondary seat.

A post-combustion lance for directing a gas at least partially therethrough. The post-combustion lance includes a body having a primary tip from which a first part of the gas exits, upper and lower portions, and a post-combustion distributor mounted between the upper and lower portions and upstream from the primary tip. The distributor includes a number of ports through which a second part of the gas exits the lance. The lance also includes an upper inner tube positioned at least partially upstream from the distributor and an internal support assembly for supporting the body. The internal support assembly includes an internal tube positioned inside the body and coaxial with the body.

An apparatus is provided for attenuating shock and vibration energy levels within a spacecraft interface isolation system. The apparatus includes one or more spring plate assemblies fitted with mechanical stops and damping devices. The isolation system is typically incorporated into an interface unit, which is connected between the launch vehicle and the payload, in order to reduce the shock and vibration load energy imposed on the payload during the fairing separation processes. The mechanical stops maintain a desired level of stiffness for the payload supporting structure during lift-off and Max q, and the damping devices reduce the spring plate oscillation tendency during fairing separation. The combination of spring plate, stop, and damping device provides a significant reduction in shock and vibration energy levels in the approximate frequency range of 100 to 300 Hz.

A hydromount (2) includes: a housing (4) and a compensating diaphragm (6), which enclose a hydraulic volume (8), a partition wall (12), which partitions the hydraulic volume (8) into a working chamber (14) and into a compensating chamber (16). The partition wall (12) contains a transfer channel (18), via which the two chambers (14, 16) are connected to one another, and wherein the partition wall (12) has an opening, in which there is a diaphragm (20) of flexible, elastomeric material clamped between two components (22, 24), wherein the diaphragm (20) is clamped between the two components (22, 24) in such a way that, as a result of the clamping, a radial pretension is produced in the diaphragm (20).

A bat for striking a ball comprises an axis, a handle, and a barrel. The handle includes a knob end, an attachment end, and a length separating the knob end from the attachment end. The barrel includes an end cap end, a barrel portion, a barrel length, and a transition section. The transition section is operatively attached to the attachment end of the handle. The bat can include a joint connecting the transition section to the attachment end while separating the barrel from the handle. Further, the bat can include an internal tubular member operatively attached to the end cap end and positioned within the barrel. A knob can be attached to the knob end of the handle while an end cap can be attached to the end cap end of the barrel. A grip can be attached to the handle adjacent the knob.

A connector is provided that may include first and second housings. The first housing may include a first body and a lock arm. The first body may include a first receptacle. The lock arm may be pivotably coupled to the first body. The second housing may include a second body having a second receptacle and a support member. The first and second housings may be engageable with each other in a first position and a second position and movable relative to each other from the first position to the second position. The lock arm may be deflectable relative to the support member when the first and second housings are in the first position. The support member may restrict deflection of the lock arm when the first and second housings are in the second position.

The invention relates to an actuation device for a motor vehicle door lock (1), comprising a handle (7), and a locking lever (10) which renders the handle (7) inactive when accelerating forces of a predetermined magnitude occur, for example, in the event of an accident. In the normal operation, the locking lever (10) is displaced when impinged upon by the handle (7) and the handle (7) is simply rendered inactive in the locked operation.

The invention provides an aircraft comprising an aircraft wing. The aircraft wing comprises a fixed wing and a wing tip device at the tip thereof, wherein the wing tip device is configurable between: (i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced. The aircraft wing further comprises a locking mechanism for locking the folding wing tip device in the flight configuration. The locking mechanism comprises a locking hook associated with one of the folding wing tip device and the fixed wing, and a locking pin associated with the other of the folding wing tip device and the fixed wing, and a biasing device, wherein in the locked configuration the locking pin is engaged with the locking hook and the biasing device acts to preload the locking mechanism.

A moving plate (13) is inserted into a receptacle (11) of a connector body (12) and movable between a partial locking position and a connection position and includes partial locking portions (91) and resilient locking pieces (46). The partial locking portions (91) restrict movement of the moving plate (13) to the connection position. The resilient locking pieces (46) lock to receiving portions (75) of a mating connector (60) and allow movement from the connection position to the partial locking position by being kept locked to the receiving portions (75) while separating the mating connector from the receptacle (11). The connector body (12) has restricting surfaces (28) to restrict deflection of the resilient locking pieces (46) until a riding amount of the partial locking portions (91) on second interfering portions (36) is a maximum when the moving plate (13) returns from the connection position to the partial locking position.