The invention relates to a de-icing device for an element of a nacelle of a turbojet engine, including at least one heating resistant mat connected to at least one electrical power source (3) and thus defining an assembly (1) of resistant mats, characterized in that the assembly of resistant mats includes one or more subassemblies of resistant mats, each subassembly in turn including one or more resistant mats of the assembly, and each subassembly of resistive mats having a different ohmic value.

The embodiments herein disclose a personal UAV kit for storing, preparing and remote control of micro UAVs (40). The UAV kit includes a base unit (10), a control unit (30) and at least one UAV. The UAVs can typically be a winged aircraft with foldable wings or a helicopter with a two-bladed or foldable rotor. The base unit comprises UAV compartments for housing at least one UAV, bay (14) for storing the control unit, batteries and electronic components for charging, communication, control and processing and storing of data. In addition, the system includes an eye near display device for viewing system information and sensor data, typically live video, transmitted from the UAV.

A method of controlling a group (2) of engines developing a necessary power (Wnec) for driving a rotor (3), said group (2) of engines having at least one electrical member (4), electrical energy storage means (5), and a first number n of engines (6) that is greater than or equal to two. A processor unit (10) executes instructions for evaluating a main condition as to whether the group of engines can develop the necessary power while resting one engine, and if so for resting one engine and accelerating a second number engines not at rest, and for causing the electrical member to operate in motor mode, if necessary, the electrical member operating temporarily in electricity generator mode when the storage means are discharged.

A rotor system is disclosed for a reactive drive rotary wing aircraft. Apparatus and methods are disclosed for maintaining the rigidity of the rotor and eliminating play between flight controls and the rotor by mounting swashplate actuators to a flange rigidly secured to the mast. Methods are disclosed for modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. Structures for reducing pressure losses and drag on components due to air flow through the rotor are also disclosed. A rotor facilitating thermal management by oil and air flow is also disclosed. Surfaces interfacing between the swashplate and the mast and between control rods and the swashplate or pitch horn may bear a solid lubricant layer.

An unmanned, towable aerovehicle is described and includes a container to hold cargo, an autogyro assembly connected to the container and to provide flight characteristics, and a controller to control operation the autogyro assembly for unmanned flight. The container includes a connection to connect to a powered aircraft to provide forward motive force to power the autogyro assembly. In an example, the autogyro assembly includes a mast extending from the container, a rotatable hub on an end of the mast, and a plurality of blades connected to the hub for rotation to provide lift to the vehicle. In an example, an electrical motor rotates the blades prior to lift off to assist in take off. The electrical motor does not have enough power to sustain flight of the vehicle.

A passively torque-balanced device includes (a) a frame; (b) a drivetrain including a drive actuator mounted to the frame and configured for reciprocating displacement, an input platform configured for displacement by the drive actuator, a plurality of rigid links, including a proximate link and remote links, wherein the rigid links are collectively mounted to the frame, and a plurality of joints joining the rigid links and providing a plurality of non-fully actuated degrees of freedom for displacement of the rigid links, the plurality of joints including a fulcrum joint that is joined both to the input platform and to the proximate rigid link; and (c) at least two end effectors respectively coupled with the remote links and configured for displacement without full actuation.

Individually operable ailerons pivotable to extend a forward end below a bottom wing surface and a rearward end above a top wing surface. The extended aileron forward end increases drag and subsumes the rudder function in the turn, while the aileron rear end produces drag and airflow redirection to reduce lift on the wing. The advantage of the safety ailerons is that habitual or instinctive pilot inputs to the yoke will recover from a dropped-wing stall at low speed and altitude, while conventional ailerons require counter-intuitive pilot actions to avoid crashing in such conditions.

An integrated aircraft galley structure includes a service module having a plurality of galley inserts including at least one oven and at least one refrigeration unit. The service module is formed with a plurality of bays sized to receive the plurality of galley inserts, along with a human machine interface for controlling all of the galley inserts. The service module further includes a plurality of galley insert modules for controlling each galley insert, and an insert power and control unit for each galley insert for controlling power to said insert. The entire system is controlled by a galley power and control unit for controlling each of the insert galley power and control units, and an AC distribution unit for distributing power to the insert power and control units.

A space efficient lavatory module for commercial aircraft includes an aft facing concave wall recess that provides a greater distance from an upper, forward facing portion of a cabin structure, such as an aircraft passenger seat to avoid having a passenger's head impact the aft facing lavatory or enclosure wall in a sudden aircraft deceleration. The aft facing concave wall recess also provides space for mounting of a protective cushion, in order to reduce a passenger's risk of head trauma in a sudden deceleration, as well as other items, such as a video monitor, a bassinet or infant bed, without inhibiting passenger movement.

In conventional aircraft cargo compartments panels or similar flat floor elements are fastened to floor beams or similar supporting elements that are installed in the body of the aircraft. Subsequently functional units such as roller elements, latches or PDUs are mounted and connected to one another by way of appropriate control conductors. It is proposed to fasten the floor elements permanently to the supporting beams so as to form prefabricated floor modules and to install these floor modules in the aircraft.

An assembly for shielding an aircraft from electromagnetic energy may include a window mounting configured to be conductively coupled to an aperture in a fuselage of an aircraft. The window mounting may include a window pane having an electromagnetically-reflective coating for reflecting electromagnetic energy. The window pane may remain electrically isolated from the fuselage prior to the electromagnetic energy exceeding a frequency of approximately 1 GHz. The window mounting may further include a capacitive gasket capacitively coupling the window pane to the fuselage after the frequency of the electromagnetic energy reflected by the window pane exceeds approximately 1 GHz.

An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.

A coupling assembly for joining a first component to a second component, the assembly comprising a shaft for connecting to a first component, and a bracket including a mounting plate for connecting to a second component. The bracket has a bracket arm extending from the mounting plate, and a head having a through-bore on the bracket arm. The shaft is received in the through-bore. A setting device acts between the head and the shaft for setting of the position of the shaft with respect to the head in the axial direction of the shaft. The assembly further includes one or more spherical bearing surfaces, which permit self-alignment of the setting device to accommodate tilting of the shaft with respect to the head about a central point in two orthogonal directions. Also, a joint comprising a first component joined to a second component by one or more of the coupling assemblies. Also, a method of forming a joint using one or more of the coupling assemblies.

According to one embodiment, a windshield attachment device for coupling a windshield to a body includes a fastener portion, a bolt, and an elastomeric load isolator. The fastener portion has an opening therethrough. The bolt is configured to extend through the opening of the fastener portion and couple the fastener portion to the body. The elastomeric load isolator surrounds at least a portion of the fastener portion and separating the fastener portion from the windshield.

A method and apparatus comprising a refueling controller. The refueling controller is configured to receive data about a current rate of movement of a refueling boom while the refueling boom is in contact with a receiver aircraft during flight. The refueling controller is further configured to disconnect the refueling boom from the receiver aircraft based on the current rate of movement of the refueling boom and a current position of the refueling boom.

Certain embodiments described herein are directed to devices configured to retain, at least for some period, and provide pre-launch support kites such as stunt kites. In certain instances, the device positions stunt kites of various sizes and design, including, for example, delta wing kits, diamond kits and foil kits, in a reclined position to provide pre-launch stability and wind flow/spill-over across the face of the kite to help prevent unintentional or premature launch. If desired, optional control line upright supports can be present that permit minimum control line pull-back thereby reducing the recline of the kite to bring the face of the kite into the wind and thereby launch the kite. The control line upright supports may also prevent the kite from falling completely face down on the surface, thereby requiring a reset of the kite on the device.

A system has a plurality of spacecraft in orbit around the earth for collecting energy from the Sun in space, using stimulated emission to configure that energy as well defined states of the optical field and delivering that energy efficiently throughout the region of space surrounding Earth.

Methods and apparatus are presented for spacecraft operation using non-Eigen axis attitude transitions via control momentum gyroscopes (CMGs) to avoid or mitigate singularities by providing a time-varying attitude command vector including a plurality of time-varying attitude command signals or values representing a plurality of spacecraft states and control trajectories as a guidance command input to an attitude controller of the spacecraft without modifying the spacecraft feedback control law.

A space debris remover aiming to remove a space debris object in earth orbits. Angular thrust calculation unit calculates angular thrust. Radial thrust calculation unit calculates radial thrust based on the angular thrust, estimated angular momentum and estimated space debris mass. A foam bonding mechanism connects the space debris remover and the space debris object. A space debris removal controller calculates firing time, and sends a space debris removal control signal comprising the radial thrust, the angular thrust and the firing time. A plurality of first stage thrusters generate the radial thrust and the angular thrust after the firing time. After the stage separator separates a first stage and a second stage of the space debris remover, a plurality of second stage thrusters generate the radial thrust and the angular thrust, and propel the space debris object towards the sun.

A device for thermal monitoring a piece of equipment, which is integrated on a craft placed in a forced vacuum environment, an outside part of the equipment projecting outside of a wall of the craft and being subjected to a solar radiation flux, includes an absorbent screen that is suitable for being placed between the outside part of the equipment and the wall of the craft, whereby this absorbent screen has—on at least one portion of its front face, designed to be placed on the side removed from the wall of the craft—an absorptivity αSOLAR that is the largest possible in the field of solar radiation, coupled to a low emissivity εIR in the infrared spectrum. The absorbent screen is made of a very heat-conductive material and has—on at least a portion of its rear face, suitable for being oriented toward the wall of the craft—a high emissivity εIR in the infrared spectrum, typically greater than or equal to 0.7.

A method for simulating the movement behavior of a fluid in a closed moving container is provided. The simulation is based on the determination of the potential movement path of the center of gravity of the volume of the fluid as an elliptical trajectory situated in a disturbance plane having certain semi-axes.

A system and method for mitigating an aircraft incident is provided. The invention includes an aircraft panic component coupled to a terminal component. The aircraft panic component facilitates identification of a panic situation and communicates information associated with the panic situation to the terminal component. The aircraft panic component is further operative to at least partially disable a navigation system and/or operational system of an aircraft. The aircraft can then be sent to a safe zone, navigated remotely and/or a course of action for the aircraft can be determined. A safe zone component is adapted to facilitate identification of a course of action for the aircraft based at least in part upon aircraft positional information, aircraft condition information and/or aircraft resource(s). Further, aircraft navigational information and/or aircraft operational information can be sent via an aircraft communication component to a remote system having a remote communication component and a remote analyzing component facilitating transfer of information related to navigational and/or operational system(s) of the aircraft.

The spiroid wing tip according to embodiments of the invention including a continuous segmental assembly having a closed loop frontal profile comprising a lower near vertical segment, a horizontal segment, a vertical segment, a second horizontal upper segment, and a near vertical segment. Accordingly to some embodiments of the invention, the spiroid profile is lowered with respect to the wing chord plane, such that a portion of the spiroid wing tip extends below the wing chord plane.

A variable length light shield is disclosed for an electro-optical sensor within a nose cone. The light shield includes a base, a telescopic shade supported by the base, and a ring rotatably supported about the base. The light shield also includes a guide tube disposed proximate the ring with an end extending away from the ring about a side of the telescopic shade. The light shield further includes an extension spring supported by the guide tube with an end coupled to the telescopic shade. Additionally, the light shield includes a cable extending through the guide tube and the extension spring, with one end of the cable coupled to the ring and another end of the cable coupled to the telescopic shade. The extension spring is configured to exert a force on the telescopic shade to extend the telescopic shade. Rotation of the ring causes retraction of the telescopic shade.

A harness is provided comprising a body having a series of electrical conductors embedded therein and substantially running along the length thereof. The body may be part of a structural component such as stringer.

The invention is a projectile, device and system having a roll control device which may be fixed or deployable, for providing torque counter to the spin of the projectile and providing drag on the projectile. The roll control device includes a guidance collar rotatably attached to the projectile located near a front end of the projectile wherein the guidance collar includes one or more guidance collar aero-surfaces shaped to provide torque counter to the spin on the projectile. The guidance collar aero-surfaces may be controlled by a brake and guidance electronics on the projectile. The invention also includes a body collar fixedly attached to the projectile aft of the guidance collar, wherein the body collar includes one or more body collar aero-surfaces and fixed or deployable drag devices. Another embodiment use only a guidance collar aero-surfaces to orient a fixed drag device relative to an Earth inertial reference frame to create asymmetrical drag on the projectile and thereby altering its trajectory.

A projectile control system includes a plurality of fins, a drive mechanism coupled to each of the plurality of fins to enable the plurality of fins to be independently retracted or deployed, and a control mechanism in communication with the drive mechanisms to independently control the deployment or retraction of the plurality of fins. A projectile having the projectile control system and a method of operating a projectile are also described herein.

The present invention relates to landing gear (5) having at least one undercarriage (10) comprising a landing gear leg (11) carrying at least one wheel (12). The undercarriage (10) includes a retraction actuator (20) having an electric motor (23), blocking means (30) for blocking the actuator in the retraction position and for enabling the retraction actuator to be positioned in the “landing gear extended” position by gravity, first monitoring means (35) for monitoring the operation of the retraction actuator (20), first control means (65) for controlling the refraction actuator (20), and second control means (75) for controlling the blocking means (30).

A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.

An actuation system and method includes a tubular defining a passage, and an assembly disposed with the tubular. The assembly includes a restriction operatively arranged to receive a restrictor for enabling actuation of the assembly. The restriction includes a degradable material with a protective layer thereon, the degradable material degrading upon exposure to a fluid in the passage and the protective layer isolating the degradable material from the fluid.

Systems and methods for activating a down hole tool in a wellbore. A piston is moveable from a first position to a second position for activating the down hole tool. The piston includes a first side exposed to a first chamber, and a second side exposed to a second chamber. A rupture member has a first side exposed to the first chamber and a second side exposed to a third chamber. The rupture member is configured to rupture when a pressure differential between the first chamber and the third chamber reaches a predetermined threshold value, at which point the rupture member allows fluid communication between the first chamber and the third chamber. When the rupture member is intact, the piston is in the first position, and when the rupture member ruptures, the piston moves to the second position and activates the down hole tool.

A system for securing a first tubular to a second tubular including a housing having at least one group of at least one window therein. A gripping assembly is disposed in the housing and has at least one member operatively arranged for selectably extending through the at least one window for internally gripping the first tubular. A coupling unit is included having a first clamping mechanism and a second clamping mechanism. The first clamping mechanism is operatively arranged for externally clamping the housing, and the second clamping mechanism is operatively arranged for externally clamping the second tubular component. A method of securing together two tubular components is also included.

A stator for a progressive cavity pump comprises a stator housing having a central axis, a first end, and a second end opposite the first end. In addition, the stator comprises a stator liner disposed within the stator housing. The stator liner has a first end and a second end opposite the first end. The first end of the stator liner is axially spaced from the first end of the stator housing. Further, the stator comprises a tag insert positioned in the stator housing between the first end of the stator housing and the first end of the stator liner. The tag insert has a through passage defining a radially inner surface that includes a tag shoulder.

A casing window assembly for completion of a lateral wellbore. The casing window assembly includes a tubular casing sleeve with a casing window and an inner sleeve releasably secured within the casing sleeve at a pre-released position adjacent the casing window.

A tubular anchoring system includes a frustoconical member and a sleeve with at least one first surface that is radially alterable in response to longitudinal movement of the frustoconical member relative to the sleeve. The at least one first surface is engagable with a wall of a structure positioned radially thereof to maintain position of at least the sleeve relative to the structure when engaged therewith. A seal with at least one second surface is radially alterable in response to longitudinal movement of the frustoconical member relative to the seal, and a seat is in operable communication with the frustoconical member having a land which is sealingly engagable with a removable plug runnable thereagainst. The land is longitudinally displaced relative to the sleeve in an upstream direction defined by direction of flow that urges the plug thereagainst.

The well pump flow sleeve assembly provides a method of quickly fitting a flow sleeve to a well pump. The sleeve is made by cutting a pipe normal to the pipe centerline of the pipe surfaces, to a length appropriate for the well pump length. A pump centering bottom cap is inserted into the pipe lower opening and the well pump assembly is then inserted into the pipe upper opening and mates with the bottom cap to align the pump in the sleeve. The pump is now completely within the sleeve with the pump discharge and electrical connection extending through the pipe upper opening. Two flow sleeve cap halves are then fitted around the pump discharge and electrical connection/safety rope to form an upper cap which is inserted into the pipe upper opening. The submersible pump is then ready for service.

Use of two different methods, either each by itself or in combination, to enhance the stiffness, strength, maximum possible use temperature, and environmental resistance of thermoset polymer particles is disclosed. One method is the application of post-polymerization process steps (and especially heat treatment) to advance the curing reaction and to thus obtain a more densely crosslinked polymer network. The other method is the incorporation of nanofillers, resulting in a heterogeneous “nanocomposite” morphology. Nanofiller incorporation and post-polymerization heat treatment can also be combined to obtain the benefits of both methods simultaneously. The present invention relates to the development of thermoset nanocomposite particles. Optional further improvement of the heat resistance and environmental resistance of said particles via post-polymerization heat treatment; processes for the manufacture of said particles; and use of said particles in the construction, drilling, completion and/or fracture stimulation of oil and natural gas wells are described.

Fluid treatment systems and compositions are provided including (a) at least one material including (1) at least one carboxylic acid functional group and (2) at least one sulfur-containing group selected from the group consisting of sulfonyl functional groups, sulfonate functional groups and mixtures thereof; and (b) at least one friction reducing agent selected from the group consisting of guar gums, polyacrylamides, hydratable cellulosic materials, viscoelastic surfactants, and mixtures thereof. The fluid treatment systems and compositions can be used to treat aqueous systems, for example as fracturing fluids for use in fracturing subterranean formations. Methods for inhibiting formation and/or precipitation of metal oxides in an aqueous composition using the fluid treatment systems or compositions also are provided.

Fluid treatment systems and compositions are provided including (a) at least one material including (1) at least one carboxylic acid functional group and (2) at least one sulfur-containing group selected from the group consisting of sulfonyl functional groups, sulfonate functional groups and mixtures thereof; and (b) at least one scale control agent. The fluid treatment systems and compositions can be used to treat aqueous systems, for example as fracturing fluids for treating aqueous compositions found in subterranean formations. Methods for inhibiting formation and/or precipitation of calcium salts in an aqueous composition using the fluid treatment systems or compositions also are provided.

A geological perforating tool (gun) shape charges disposed at an angle that provides an improvement over other known embodiments by accurately securing the charges in the tool to facilitate reliable, reproducible focus of the shaped charges. Charges are disposed on metal strips fitted into slots that are precision cut at predetermined angles in a tool barrel circumference.

A wellbore tubular lift safety system and tubular lifting apparatus for removing tubulars can include a lower section with a lower base plate hole, sliding rods, and a lower gripping member. An upper section can have an upper base plate hole, a saw mounting plate hole, an upper gripping member, and cylinder barrels. The sliding rods can be engaged within the cylinder barrels, and can be moved therein for extending and retracting the upper section. The apparatus can be positioned over the wellbore in a retracted position to align with the tubular. The tubular can be lifted out of the wellbore by gripping the tubular using the gripping members, and extending and retracting the upper section. The apparatus can form lifting holes in the tubular, install lifting members in the lifting holes, saw the tubular, and allow the cut tubular to be lifted via a hoist.

A shaped charge casing cutter is constructed with the cutter explosive formed into radial section modules aligned in a toroidal cavity between a pair of housing plates. The center sections of the plates are contiguously aligned with opposite parallel surfaces of a center disc. The plate rims are offset from respective center disc planes in opposite directions from each other to form a toroidal cavity. The toroidal cavity is enclosed by a circumferential belt secured to said plate rims. V-grooved shaped charge explosive in the form of multiple pi sections is distributed about the cavity to intimately contact a pair of frusto-conical liners.

A dump bailer for downhole placement of flowable materials in a wellbore. The dump bailer has an elongated housing with a cavity for placement of the flowable materials. The housing has an open bottom. An expendable cap or plug, of a magnetic material, is held within the open bottom by a shear pin, sufficient to hold the plug in place with the material within the cavity. An electric solenoid surrounds the plug. Energizing the solenoid coil by electric current creates a magnetic field which overcomes the shear pin and forces the plug out of the open bottom. The material may then flow out of the cavity. Alternatively, a sliding sleeve may be disposed in the open bottom, which moves from a first closed position to a second open position, in response to the magnetic field.

Methods are provided for identifying the location and height of induced subterranean formation fractures and the presence of any associated frac-pack or gravel pack material in the vicinity of the borehole using pulsed neutron capture (PNC) logging tools. The proppant/sand used in the fracturing and packing processes is tagged with a thermal neutron absorbing material. When proppant is present, increases in detected PNC formation and/or borehole component cross-sections, combined with decreases in measured count rates, are used to determine the location of the formation fractures and the presence and percent fill of pack material in the borehole region. Changes in measured formation cross-sections relative to changes in other PNC parameters provide a relative indication of the proppant in fractures compared to that in the borehole region.

Methods of treating a wellbore in a subterranean formation including providing an oil-external treatment fluid, wherein the oil-external treatment fluid is a 3D-network comprising a chemical interaction between a hydrocarbon fluid, an aqueous fluid, and a surface modification agent; providing proppant particulates; suspending the proppant particulates in the oil-external treatment fluid; and introducing the oil-external treatment fluid comprising the proppant particulates into the wellbore in the subterranean formation.

A method may include determining a first particle size distribution for particulate additives in a first wellbore fluid circulated through a wellbore through an earthen formation, and determining a second particle size distribution for drilled cuttings resulting from drilling of the wellbore. The first and second particle size distributions may then be compared to determine a third particle size distribution for the combined particulate additives and the drilled cuttings. A lost circulation material having a fourth particle size distribution may then be selected based on the third particle size distribution and the selected lost circulation material may be pumped into the wellbore.

A pourable aqueous cement composition is disclosed. The cement composition comprises a hydraulic cement, water and a selectively removable material comprising a plurality of selectively corrodible metal powder particles dispersed within the cement or a nanomatrix powder compact, or a combination thereof. An article, including a downhole article, and more particularly a reconfigurable downhole article is disclosed. The article includes a hydraulic cement, wherein the hydraulic cement has at least partially set into a permanent form. The article also includes a selectively removable material dispersed within the cement, the selectively removable material comprising a plurality of selectively corrodible metal powder particles dispersed within the cement or a nanomatrix powder compact, or a combination thereof, wherein the selectively removable material is configured for removal in response to a predetermined wellbore condition.

An apparatus for use in stage-cementing an oil well in the region of a lost-circulation zone that is proximate an annular space defined by the lower end of an outer casing surrounding an inner casing include a load-bearing annular steel plate of substantial thickness that is positioned on, and maintained stationary relative to the inner casing by supporting and retaining means secured to the inner casing, the outer diameter of the plate being less than the inside diameter of the outer casing so that the plate can be lowered with the inner casing string to the desired location inside of the outer casing and, with a layer of gravel, to provide a seal and support the cement poured into the annulus between the inner and outer casings.

In an embodiment, the cement compositions comprise: (i) hydraulic cement, wherein the hydraulic cement has a ratio of CaO to SiO2 in the range of 2.0 to 4.0; and (ii) a water-soluble metaphosphate in a concentration of at least 2.5% bwoc. In another embodiment, the cement compositions comprise: (i) hydraulic cement, wherein the hydraulic cement has a ratio of CaO to SiO2 of less than 2.0; and (ii) a water-soluble metaphosphate; wherein any alkali nitrate is in a concentration of less than 2% bwoc; and wherein any alkali hydroxide, alkali carbonate, or alkali citrate is in a concentration of less than 0.2% bwoc. Methods of cementing in a well comprising forming either of such cement compositions and introducing it into the well are provided.

A cutting tool for cutting pipe or the like from the inside out includes a housing assembly. A first blade actuating wedge assembly is inside the housing assembly and is movable along a longitudinal axis. The first blade actuating wedge assembly has multiple first tapered blade actuating wedges. Each cutting blade is supported in a manner such that a position of the cutting blade relative to the housing assembly along the longitudinal axis is substantially fixed. Each cutting blade is coupled to a respective one of the first tapered blade actuating wedges such that movement of the first tapered blade actuating wedge assembly along the longitudinal axis causes each cutting blade in the first plurality of cutting blades to move perpendicular to the longitudinal axis.