Abstract: A scratch depth measuring instrument (10) for use on opaque matte or specular surfaces (80) includes a light source (16), a body (40) having a knife edge (38). The light source is positioned to project a shadow pattern of the knife edge and to image it on a scratched surface (80) transversely to a scratch (82) for measuring the scratch depth and to project a visible indentation (132, 132A) from the knife edge (38) into the scratch (82). The indentation can be measured in distance from the knife edge image (92, 92A) to determine the depth of the scratch. The knife edge image (92, 92A) is projected to the surface (80) from a first mirror (62) and a mirror system (98, 100) reflects the image (92, 92A) and the measurable indentation (132, 132A).

Abstract: Aircraft passenger seat frames (60, 62, 220, 222 and 224) having legs (54, 56, 210, 212) fixed in place in the aircraft and with the seat frames. Each seat frame has generally horizontal supporting members (66, 68, 74, 76) having their opposite ends secured in seat end webs (70, 72, 78, 80). Tubes (84, 86) are associated with each of the seat end webs of the plurality of seat frames in a supporting relationship, the legs (54, 56) being connected to the tubes to support the seat frames. The tubes have a tube-in-tube slip joint (88, 90) at least at one outside end of the one seat frame on which the seat can be moved toward or away from an adjacent seat frame to change the fare class size of the set frames.

Abstract: A method and tool (12) for use in an automatic machining center for removing drilling coolant from a blind hole (14) and for injecting tapping fluid into the hole (14), the tool having a nozzle (24) for removing the coolant from the hole and for injecting tapping fluid into the hole.

Abstract: An aircraft ejection seat (10, 120) having a combined catapult (46, 122) and rocket motor (88, 90, 130, 132, 142, 144) in which the amount of rocket thrust is selectable. An outer catapult tube (46, 122) forms a seat support structure. In the outer catapult tube there is a plug (66, 66A) at its upper end before ejection and carries a propellant for ejecting the seat from the aircraft when the propellant is discharged. There is a fixed sleeve (84) in the lower end of the outer catapult having an internal circumferential bearing surface with which the inner catapult tube is engaged before and during ejection. The holding sleeve is positioned to engage the plug (66, 66A) when the ejection has become complete. The plug then seals the outer catapult to receive gas from the rocket gas generators to elevate the seat substantially above the aircraft, as necessary under certain conditions.

Abstract: A thrust reverser cascade basket and method including an elongated metal frame having elongated metal strongbacks and metal transverse end portions joining opposite ends of respected strongbacks. Reinforced hard plastic is pressure injection molded on the strongbacks, and transverse vanes formed of the plastic extend between the strongbacks and are integral therewith. The strongbacks have openings having the plastic molded therein, the openings being between the vanes, and substantially all plastic knit lines are formed along strongback surfaces, spaced adjacent mid-span locations between the vanes. The vanes are free of the knit lines.

Abstract: Rocket booster motor vectoring system and method for shortening take-off distance of aircraft, the aircraft being airborne before it is going fast enough for its conventional controls to provide adequate stability and control. A rocket booster motor (52) is coupled to aircraft (50) by means of thrust arm link (56) is pivotal engagement with the aircraft and fixed to the booster, and coupled by rearwardly positioned links (62, 64, 66) having ball and socket joints at both ends, one end being connected to the aircraft through aerodynamic surfaces (68, 70) or through actuators (124, 126), the aerodynamic surfaces being operable by conventional systems within the basic aircraft, and the actuators also being operated by motion sensing systems within the aircraft to vector the thrust of the booster to provide stability augmentation of the aircraft during the boosted launch phase to provide pitch, roll, and yaw control.

Abstract: A combination convergent jet engine aircraft nozzle (86, 142, 146) and a ventilation tube (88, 136, 144) are fixed in place and have no moving parts. Ambient air is entrained through duct inlets (96, 140, 154, 160), through the nozzle walls, through hollow struts (90, 138), the struts supporting and being connected to a hollow central tube (102, 144) or a plurality of tubes (136), to adjacent the downstream end of the nozzle to mix at takeoff with the jet forming gas exhaust. The ducts (102, 136, 144) are positioned with respect to the nozzle exhaust so that entrained ambient air flows into the gas exhaust during takeoff and so that the ambient air flow is substantially restricted or shut off during cruise flight.

Abstract: An automatic countersink depth control tool and a combination of the same with an installer for fasteners having countersink heads. The tool has a nonrotatable stop (76) for limiting the depth of a countersink drilled in a fastener hole. The stop (76) is adjustably movable toward or away from a workpiece in which the countersink is to be drilled, the movement of the stop being relative to the depth of the countersink. There is a rotatable screw gear (50) having an external ring gear (54) for moving the stop in accordance with the depth of the countersink and in accordance with the height of the head of the countersink head of the fastener to be installed in the hole. There is a motor (90) having a spur gear (94) engaged with the ring gear (54) to rotate it a predetermined amount by a threaded engagement of the screw gear (50) and the stop (76). Because the stop is nonrotatable, the rotation of the threads moves the stop the desired amount.

Abstract: The invention is a single jaw (52) seven point (70, 72, 74, 76, 78, 80 and 82) open-ended wrench (50) having a double square socket (64) attached to one opposite ends (60) spaced by an opening (62) from the other opposite end (58). The jaw (52) is dynamically stiffened and has a substantial jaw support (66). Where the arc of the jaw ends, there are flat surfaces (96, 102 and 98, 104) to receive opposite flat sides (108, 110) of a six point nut (112) or the nut may be received by moving the wrench in the direction of the axis of the nut to thereby engage it. The drive socket (64) is positioned at 90.degree. from the jaw opening (62).

Abstract: Apparatus for adjustably mounting an ejection seat (16) in an aircraft in which outer catapult cylinders (58, 60) support inner catapult cylinders (62, 64) and supply force to the inner cylinders to eject the inner cylinders and the seat from the aircraft, the inner cylinders being connected to an upper rear end of the seat (66, 68). The seat (16) is supported in the aircraft by the inner and outer catapult cylinders (62, 64, 58, 60), by adjusting actuators (40) to raise and lower and to tilt the seat forwardly and rearwardly, by lower anchor links (30) pivotally connected to the aircraft and to lower end (26, 28) of the outer catapult cylinders and to the actuators (40), and by upper links (50). The seat is connected to the catapult cylinders (58, 60) by slipper blocks 82. The slipper blocks (82) are pivotally connected to the seat by pins (84) and are slidably engaged with the outer catapult cylinders.

Abstract: An ejection seat (10) having roll thrusters (38, 40, 112, 114) and propellant chambers in the inner catapult tubes (44, 46, 124, 126). The roll thrusters (38, 40, 112, 114) are adapted to roll the seat (10), when ejected from an inverted or unsatisfactory attitude to an upright proper attitude. Solid propellants (44, 46, 128, 130) within the inner catapult tubes are to be ignited after the seat is being ejected. There is a roll thruster valve housing (36, 110) connected to both roll thruster nozzles (38, 40, 112, 114) and to both inner catapult tubes (24, 26, 124, 126) so that propellant gas may flow from both catapult tubes to both nozzles. The check valve (52) in each inner catapult is operable to open during ejection by ejection gas and is operable to close by the roll thruster gas when the roll thruster propellants are ignited. The check valve system modulates the catapult gas pressure during ejection, prior to roll thruster propellant ignition.

Abstract: A minimum weight horizontal and vertical stabilizer (188) which a primary torque box is formed within the skins (202, 204) and extends transversely from the most forwardly spars (190, 212) to the most rearwardly spar (196) to occupy spaces between all of the spars (190, 212, 192, 194, 196).

Abstract: An airfoil (10) having improved life capability and having airfoil curves including a camber divided into three regions I, II and III. Region I has a starting point aft and adjacent a leading edge (12) and encompasses the airfoil stagnation point. Region I has a high curvature around the leading edge and decreases aft along the chord to a first local minimum value of less than 3 for K times C, where C is the length of the chord and K is the reciprocal of the local radius of curvature. The curvature region II starts at the after end of region I within 10% of the chord length and the curvature in region II first increases from the first local minimum at the aft end of region I and then decreases to a second local minimum within 40% of the chord length.

Abstract: A substantially one piece molded shell ejection seat (10) having a rocket motor propulsion system (74), the propulsion system (74) being adapted to be integrated into the molded seat (10) during the molding process. The seat body (12) has upper and lower side walls (14, 16, 20, 22), front wall (60) between the lower side walls (20, 22) and back wall portions (30, 32, 34, 36, 38, 40, 42, 44). A molded backrest panel (50) is removably secured to the body (12) to extend generally between the upper side walls (14, 16). The rocket motor propulsion system (74) is incorporated within the body (12) below the upper side walls (14, 16), within the lower side walls (20, 22), generally rearwardly of and below the backrest panel (50), and generally rearwardly of the occupant sitting area (66). A rocket nozzle (78) is connected to the motor (86) by a manifold (82) and is fitted generally within the lower back seat periphery and seat envelope.

Abstract: A positive displacement pump (10) for precisely dispensing liquids through a dispensing tube (126) in which there is a pump body (12) having a shaft (18) fitted for reciprocating therein. Incremental adjusting nuts (24, 26) on an outer end (22) of the shaft limit the movement thereof in a pumping direction. There is a first friction clamp (46) pivotally mounted adjacent one of its ends on the other end (48) of the shaft and a second friction clamp (82) is pivotally mounted adjacent one of its ends on a member (80) fixed to the body (12) adjacent the other end (48) of the shaft (18). The other ends of the clamps (46, 82) have cylindrical openings (66, 92) in substantial alignment to receive a hardened, smoothly finished pump rod (102). The pump rod is precisely aligned in bushings (98, 100) secured to the pump body. There are springs (70) and (90) biasing the clamps between the pivotal mountings and the cylindrical openings against the direction of pumping.

Abstract: A fire extinguishing system including a first rapid discharging Halon bottle (I) and a second metered discharging Halon bottle (II), and the method for providing a violent boil-off when the Halon is discharged from liquid nozzles (60) connected to the second bottle (II) to provide for a thorough and rapid mix of the gas within the compartment.

Abstract: A motor driven rotary scraper assembly (10) for use on concrete floors for removing adhering residues includes a plate (12, 180) for rotary driving attachment to a motor rotatable device. There are a plurality of annularly spaced scraper units (50, 112, 182) secured to the plate. Each scraper unit (50, 112, 180) has floating blades (52, 116, 190). The scraper units (50, 112) include a support member (80, 160) having limit or pivot means (92, 130, 270) to limit upward movement of the blade (52, 116, 190).

Abstract: A power torque servo system (100) for roller swaging (122), including a servomotor (132) having a gear box (134) with a drive shaft (138). The motor is supported on two members (150, 152) on opposite sides of the drive shaft (138) and a third member (146) on which the motor may pivot. Strain gages (154, 156, 158, 160) are mounted on the members (150, 152) to measure servodrive reaction torque in the shaft when the shaft is rotated by the motor to function as a swage drive or in another torquing operation. There are switches (236) to set a final torque value to be obtained in the servo system and an electrical servo system for receiving the strain gage measurement signals to provide a smooth low speed approach to a final torque value (182) in the shaft (138) and to eliminate any dynamic torque overshoot in the shaft.

Abstract: Apparatus and method for repositioning an aircraft ejection seat (10) during an ejection sequence from a semi-reclined position (FIG. 1) to a more upright position (FIG. 2) for safer ejection. The seat (10) is supported in the aircraft by inner catapult cylinders (18, 20) slidably engaged in outer catapult cylinders (14, 16), collapsible truss links (54, 56), connected to the seat at one end and having their other ends connected to slipper blocks (68) slidably engaged on the outer catapults (14, 16). The collapsible truss links hold the seat away from the lower ends of the catapults and firmly in a semi-reclined position during normal operation. There are triangular trusses comprised of seat structure (10), the catapults (14, 16, 18, 20), stops (70) on lower ends of the outer catapult cylinders (14, 16) and the compression links (56). The slipper block (68) are restrained by the down stops (70) and the compression links (56).

Abstract: A waterproof floor panel (10) fastening system, accessible from above in which floor panels (10) have spaced upper and lower plates (12, 14), the panels being waterproof and being secured on support structure (74) thereunder. There are fastening assemblies securing the panels to the support structure and extending into openings through the upper and lower plates (12, 14) and supporting honeycomb (16) therebetween. Each assembly has an upwardly opening first cup (48), having a central hole (52) in its bottom and having a fastening bolt (60) extending therethrough. An upper second cup (100) is fitted in the opening of the first cup, the second cup or cap having a central portion forming a transverse wall or web (98), spaced above the bolt head. A hardened seal (96) extends across and above the transverse wall or web of the upper cup and forms a seal across the opening of the upwardly open first cup (48).