Abstract: A modification to thermogravimetric analyzers with data acquisition devised to allow concurrent TG (thermogravimetry) and DTA (differential thermal analysis) measurements employs three samples mounted close to each other in a TG furnace. Two of the samples are active ones, i.e. of the material to be analyzed, and the third is a reference sample of an inert material. The first active sample is suspended from the beam of a thermobalance. The change in weight of this sample is recorded and plotted versus the temperature of the second active sample. The sample thermocouple and another identical thermocouple are placed in contact with crucibles containing the second active sample and the reference material, respectively. The differential temperature between the sample and the reference material is taken from the two identical thermocouples. The differential signal is amplified and plotted against the temperature of the second active sample.

Abstract: A device for scaring birds thereby aiding in the prevention of crop destruction due to the birds feeding thereon comprises in combination an actuator, such as an air gun which ejects at increased velocity a gaseous stream in a predetermined path, a frame including a target disposed in an impinging relationship to the gaseous stream path so as to be moved between rest and operative positions responsive to the gaseous stream, and visual scaring member operatively connected to the target for scaring birds, the visual member being reciprocally operable between inactive and active positions in response to the target being moved between the rest and operable position, respectively. According to another embodiment of the present invention, automatic controls are provided for disabling the device during night hours and/or during periods of increased wind velocities which could potentially damage the device.

Abstract: A thermal shock chamber comprising a test area, a high-temperature air conditioning unit having a gas outlet and a gas inlet adjacent to the test area, an outside air supplying unit having an air outlet and an air inlet adjacent to the test area, a low-temperature air conditioning unit having a gas outlet and a gas inlet adjacent to the test area, a first damper assembly for opening the outlet and the inlet of one of the high-temperature air conditioning unit and the outside air supplying unit and closing the outlet and the inlet of the other unit at the same time, and a second damper assembly for opening the outlet and the inlet of one of the low-temperature air conditioning unit and the outside air supplying unit and closing the outlet and the inlet of the other unit at the same time.

Abstract: A fuel gauge includes a stationary capacitor located within a fuel tank in such a manner as to be partially immersed in the fuel so that the capacitance of the capacitor varies with the level of fuel. A measuring device determines the capacitance of the capacitor to measure the level of the fuel or the amount of fuel remaining within the tank.

Abstract: A multicoordinate sensing head is disclosed which includes a sensing pin and a tappet. Both the sensing pin and the tappet define respective 90.degree. conical recesses which serve to capture a ball therebetween. This arrangement converts both axial and radial movement of the pin into axial movement of the tappet at a constant 1:1 ratio. A position measuring system is used to measure the axial position of the tappet. This position measuring system therefore can be used to measure both axial and radial deflection of the sensing pin. The sensing pin is mounted in the sensing head by means of an axial guide and a two-dimensional guide such that the axis of the sensing pin is maintained parallel to the axis of the tappet. This arrangement allows simultaneous radial and axial deflections of the sensing pin.

Abstract: This invention contemplates a rapid method of calibrating probe-pin combinations, such as star probes or rotary-swing probes, which method is applicable when the probe system forms part of or is coupled to the control system of a measuring machine wherein a self-centering probe of workpieces is possible. The calibration procedure employs a calibration standard having a plurality of probe-centering elements distributed over its surface and facing in different directions, the positional geometry of these elements being stored in the computer of the measuring machine. Each of the individual probe balls is successively introduced into a centering element which is accessible. Thereupon, the position of each ball-center point is determined in the computer, from the stored positional data and the pre-established diameter of corresponding probe balls.

Abstract: Liquid hydrogen stored aboard a space vehicle, and constituting a fuel for use in the vehicle's main rocket motor, is introduced, in a gaseous state, into an inflatable aerodynamic braking member, for moving it from a collapsed stored position outwardly into an inflated operational position. Such member provides a large area braking surface which extends generally laterally outwardly from the space vehicle. During reentry the space vehicle is oriented to reenter nozzle end first. Fuel is consumed within the rocket motor to produce gases which are discharged out through the rocket nozzle to provide a cooling layer of gases forwardly of the large area braking surface. A space vehicle equipped with such an aerodynamic braking system is operated to reenter into the atmosphere. The drag produced by the braking member slows the space vehicle down and then the space vehicle is set into a low earth orbit.

Abstract: The player is provided with a pair of spaced apart spine latching members which hook up with an inner record retaining spine as a disc record caddy is inserted into the player so that when the outer sleeve is withdrawn, the record/spine assembly is retained inside the player. A selected one of the spine latching members is equipped with a moveably mounted overtravel member which precludes the selected latching member from capturing the spine until the other latching member is also in position to latch up the spine. A connecting member rigidly intercoupling the latching members precludes the other latching member from capturing the spine until both latching members are ready to latch up the spine to ensure simultaneous latching of the spine.

Abstract: A continuous repeating type simplified sound reproducing device including on its casing, a fixed locking lever having a locking face parallel to the plane of rotation of a record disc and a rotating locking lever on the record disc which rotates together with the record disc and is able to enter under the locking face of the fixed locking lever only when the record disc is placed at its retracted position. At least one of the locking faces of the two locking members are arranged to have a face length corresponding to the angle of rotation sufficient to maintain the record disc at its retracted position until the record disc has completely returned to the starting point of sound reproduction. By virtue of this construction, satisfactory returning motion of this continuous repeating type sound reproduction device can be assured by a comparatively simplified construction.

Abstract: The invention is an improved flight control system for aircraft. The improved flight control system mixes or blends several flight control movements into a unified operation. The flight control mixing system of this invention combines the functions of standard ailerons (a roll and lateral control device) with standard flaps (a lift control device) on aircraft into a single control device, referred to herein as flaperons. The improved system can also be used on tailess or flying wing type aircraft to combine the functions of standard ailerons with the elevator functions (a nose up or down pitch control device) into a single control device, referred herein as elevons. The improved system is also applicative to V-tail type aircraft for controlling the elevators in a similar single control operation, herein referred to as ruddervators.

Abstract: Apparatus is disclosed for controlling a pair of transverse scanning gauges disposed along the length of a moving sheet of material whereby continuous same-spot measurements of the material may be made irrespective of any variations in the speed of the material even as it traverses the distance between the scanning gauges.

Abstract: A compression-sealed door assembly for use in controlling air flow pressure levels within a supersonic jet nacelle inlet, wherein substantially U-shaped strips of resiliently compressible material is compressed between a door and the nacelle inlet to seal air flow passageways through the inlet when the door assembly is pivoted to its fully closed position.

Abstract: A method for changing the spin rate of a spinning spacecraft having a dynamic balancing mechanism which utilizes the communications channel between the spacecraft and the receiving terminal, the master index pulse generator on the spacecraft, and the spacecraft axial thrusters. To change the spin rate, a dynamic imbalance of a known wobble angle and phase is introduced by the dynamic balancing mechanism. An axial thruster is then fired for a predetermined time interval thereby coupling a portion of the axial thrust force into the rotational energy of the spinning body.

Abstract: A reserve parachute for deployment under low descent speeds includes a rubber ring packed with the canopy and rigging lines and attached to the canopy in the region of the canopy apex and being disposed concentric with respect to a vent hem of the canopy. Upon deployment the ring expands to increase profile drag to ensure the canopy mouth faces substantially downwardly during deployment. The peripheral hem of the canopy at the canopy mouth is stiffened with a tape loop treated with polyurethane so that the peripheral hem springs apart upon deployment. An inhibitor tie is attached to a loop of the folded rigging lines within the pack to permit only a part of the rigging to be released initially; the inhibitor tie breaks at a predetermined tension in the lines to permit the remainder of the rigging lines to be released and to permit fully canopy deployment.

Abstract: An aircraft containing aerodynamic and gyroscopic stability that has a high angle of take-off and landing capabilities, with high speed horizontal powered flight, but is also able to sustain power-off flight with auto-rotation of its multiple extending airfoils. The fuselage has the shape of an inverted saucer with aerodynamic configuration and has an open circular track at its periphery; and riding in this track is a rotary frame and extended airfoil assembly that isin-line with the fuselage. Each extending airfoil contains solid weighted bodies at their tips and this rotary frame and extended airfoil assembly is rotated on the track by an internal power unit. The extending airfoils taper toward their tips and these tips have a knife sharp edge for penetrating the air resistance.

Abstract: This invention relates to an improved satellite servicing system. The improvements include improvements in payload distribution in the cargo bay of the Shuttle Orbiter and improvements in the location of the targets required for positioning end effectors with respect to the component which they are to engage. In the improved satellite servicing system, the remote manipulator system which is normally used for the purpose of capturing and deploying satellites is also used for servicing the satellites when captured and secured for servicing. An improved payload distribution system is provided in the cargo bay which permits optimum utilization of the cargo bay by primary payload units by providing for the location of secondary payload units at any convenient position of opportunity along the length of the cargo bay.

Abstract: A nacelle mounted by a pylon below and forwardly of a wing. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle and pylon have a critical surface region which is an upper side surface portion of the nacelle and the contiguous pylon surface adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface region that is within the critical zone. The critical contour area of the nacelle and pylon are shaped to be in alignment with a plurality of airfoil streamlines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent streamlines and correspond more closely to the engine structure contour.

Abstract: A nacelle mounted by a pylon above and forwardly of a wing. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle and pylon have a critical surface region which is a lower side surface portion of the nacelle and the contiguous pylon surface adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface region that is within the critical zone. The critical contour area of the nacelle and pylon are shaped to be in alignment with a plurality of airfoil stream lines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent stream lines and correspond more closely to the engine structure contour.

Abstract: A nacelle mounted directly to and above a wing so as to extend forwardly therefrom. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle has a critical surface region which is a side surface portion of the nacelle adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface area that is within the critical zone. The critical contour region of the nacelle is shaped to be in alignment with a plurality of airfoil streamlines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent streamlines and correspond more closely to the engine structure contour.

Abstract: A nacelle mounted directly to and below a wing so as to extend forwardly therefrom. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle has a critical surface region which is a side surface portion of the nacelle adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface region that is within the critical zone. The critical contour area of the nacelle is shaped to be in alignment with a plurality of airfoil streamlines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent streamlines and correspond more closely to the engine structure contour.