Abstract: In order to secure a copper spacer element between two wires while brazing the wires to the spacer, a brazing clip is provided with retaining members to aid in maintaining the brazing clip and the copper spacer between the wires during the brazing operation. Retention of the copper spacer element between the two wires is additionally facilitated by configuring the clip to retain the spacer element by means of spring forces.

Abstract: By utilizing a radio altimeter in conjunction with a measure of the aircraft speed, landing gear position and flap position, an aircraft terrain warning system is made possible which provides a voice warning indicating that the aircraft is too low with respect to the terrain when the aircraft is above a predetermined speed. For aircraft speeds below the predetermined speed, a voice warning is provided when the aircraft is below a predetermined altitude with the landing gear up indicating that the aircraft is too low with the gear up and when the gear is down and the flaps are not in a landing position and the aircraft descends below a second predetermined altitude a voice warning is generated indicating that the aircraft is too low with flaps up.

Abstract: In a vehicle wherein power is applied to each track or wheel through a hydrostatic transmission and control system including: a displacement control unit for regulating each transmission; a steering control valve associated with each displacement control unit for modifying the operation of the displacement control unit; and a speed and direction control unit for applying hydraulic pressure to each of the displacement control units for controlling the basic direction and speed of the vehicle; wherein the maintenance of the desired direction of operation of the vehicle is enhanced by an electronic tracking control circuit that includes: means for measuring the actual speed of each track; a phase comparator for providing a signal indicating the difference in track speeds; an integrator for providing a signal proportional to the difference in speed as measured over time; and comparator circuits responsive to the integrator for triggering a solenoid control valve connected between the appropriate steering control

Abstract: A fuel burner pumping system includes a pump having an inlet communicating with a fuel source and an outlet which communicates with a control valve assembly for regulating the pressure of the fuel supplied to the fuel burner nozzle or nozzles through a nozzle passage leading from an outlet port of a main chamber in the control valve assembly. High pressure fuel is pumped into the main chamber through a first outlet passage leading from the pump. A second outlet passage leading from the pump to the nozzle passage by-passes the control valve assembly so that air may be purged from the system when the pump initially is started. An air purging valve within the second outlet passage is movable between closed and open positions for blocking fuel flow through such passage during normal operation of the pump and for opening the second passage when the pump initially is started.

Abstract: In order to remove heat from integrated circuit modules a layered aluminum heat transfer structure is secured to the upper portion of a circuit board. The heat transfer structure includes a number of heat pipes for transferring heat to a condenser region. Each heat pipe is composed of a central vapor channel with a number of parallel capillary channels, each of which is open on one side to the vapor channel thereby serving as the wick of the heat pipe, running the length of the circuit board to a condenser region. There is one heat pipe for each row of integrated circuit modules wherein the modules are placed on the upper portion of the heat transfer structure and secured by means of terminal pins that run through the structure to the circuit board. The heat from the circuit modules vaporizes a working fluid in the capillaries and the vapor, in turn, travels in the vapor channel to a condenser region to be cooled and condensed by a cooling medium over this region.

Abstract: To enhance the cooling of an alternator stator, each end of the stator including the end turns of the stator wires is enclosed in a fluid tight assembly containing a matrix of ceramic balls. Since the stator wires are contained in slots in the stator laminations, cooling of the stator wires is facilitated by the cooling fluid flowing parallel to the stator wires in the stator slots from one end assembly to the other end assembly with the ceramic balls assuring uniform coolant flow through the stator slots. An external fluid passage contains a pressure drop orifice resulting in a pressure differential between the end assemblies so that a certain proportion of the cooling fluid will flow through the stator slots.

Abstract: In an aircraft terrain warning system utilizing a radar altimeter wherein the rate of closure to the terrain is compared with the aircraft's altitude above the terrain to generate a warning signal when the closure rate is excessive for a particular altitude, the closure rate signal is limited and biased depending upon the aircraft's closure rate and configuration in order to significantly increase the time response of the system while at the same time reducing nuisance warnings. The amplitude limit on the closure rate signal is varied, above a predefined altitude, as a function of the closure rate signal in order to provide increased warning times at greater closure rates. Circuitry, responsive to the aircraft's flap positions, is also provided to alter the characteristics of rate limiter so as to provide warning parameters that more accurately reflect operating conditions at lower aircraft speeds.

Abstract: By using air speed as an input to a ground proximity warning system that includes: a signal representative of the time rate of change of the aircraft altitude with respect to ground; circuitry for limiting the amplitude of this signal; a signal that represents a time rate of change of the aircraft's barometric altitude; and circuitry for combining the amplitude limited signal, representing the time rate of change of the aircraft with respect to ground, with a signal that represents the aircraft's altitude over ground; the effective warning time is extended by increasing the allowable amplitude, of the signal representing rate of change of the aircraft with respect to the ground, in response to the speed of the aircraft.

Abstract: In a system that compares the rate of descent of an aircraft with its altitude above ground and generates a warning signal when the sink rate exceeds a predetermined limit for a particular altitude, the maximum warning time is limited to a specified value in order to minimize nuisance warnings at higher altitudes. At a descent rate above a certain value, the excessive sink rate warning signal is inhibited for combinations of descent rates and aircraft altitudes which would provide a warning greater than a selected time to impact, such as 30 seconds.

Abstract: An interrupted ignition system for a burner control circuit having a primary side which has as its primary function the application of a line voltage to a burner motor and a fuel igniter and a secondary side, which is responsive to a thermostat, and includes a light sensitive element for detecting a flame at the burner plus a current responsive element which in combination with a circuit breaking switch in the primary functions as a circuit breaker for disconnecting the igniter and motor from the line voltage under certain conditions. The igniter is controlled by a triac switch in the primary side which in turn is responsive to an optical coupler connected to the secondary side of the burner control circuit. When the thermostat contacts are closed, thereby indicating a call for heat, the optical coupler will cause the triac to switch on resulting in current flow through the igniter.

Abstract: The warning system includes a function generator for generating a signal representative of a minimum altitude over terrain as a function of the aircraft's speed. This signal is combined with a signal representing the aircraft's actual altitude over the terrain and if the aircraft is below this minimum altitude a warning signal is generated. A circuit is included to inhibit the warning signal, and thereby nuisance warnings, when the aircraft overflys another aircraft. In addition, electronic circuitry is disclosed for implementing the invention that is compatible with at least two separate types of air data computers.

Abstract: The primary side of the burner control circuit, which has as its primary function the application of a line voltage to the burner motor and igniter, includes: a triac switch for applying the line voltage to the burner motor and igniter; in response to a first optical coupler; a circuit breaker switch for disconnecting the primary from the line voltage; and a light source for a second optical coupler. The secondary side of the burner control circuit, which is responsive to a thermostat, includes: a light sensitive element for detecting a flame at the burner; a light source for the first optical coupler; and a current responsive element which in combination with the circuit breaking switch in the primary functions as a circuit breaker.

Abstract: An improved character reading system that utilizes two separate read devices: a first read device and a second read device in combination with a random access memory for storing each character read by the first read device, a memory control circuit for writing each character into the random access memory, and a comparison logic circuit for comparing each character as read by the second read device with the corresponding character stored in the random access memory. The system also includes a time-out counter for indicating when the last character has been read and a comparison logic timing circuit for controlling the comparison logic and triggering the random access memory read control circuit so as to provide the corresponding character to the comparison logic.

Abstract: In an aircraft terrain warning system utilizing a radar altimeter wherein the rate of closure to the terrain is compared with the aircraft's altitude above the terrain to generate a warning signal when the closure rate is excessive for a particular altitude, the closure rate signal is limited and biased depending upon the aircraft's closure rate and configuration in order to significantly increase the time response of the system while at the same time reducing nuisance warnings. The amplitude limit on the closure rate signal, is varied, above a predefined altitude, as a function of the closure rate signal in oreder to provide increased warning times at greater closure rates. Circuitry, responsive to the aircraft's flap positions, is also provided to alter the characteristics of rate limiter so as to provide warning parameters that more accurately reflect operating conditions at lower aircraft speeds.

Abstract: In a terrain warning system wherein the rate of the aircraft's closure to the terrain is compared to the aircraft's altitude above the terrain in order to generate a warning signal for excessive closure rates, a circuit is provided to inhibit the warning signal when the aircraft begins to climb in response to the warning signal and to measure the altitude gained by the aircraft resulting in the reactivation of the warning signal if the aircraft has leveled off before gaining a predetermined amount of altitude. The circuit includes: a memory element to indicate that a warning signal has been generated; a circuit to generate a climb signal in response to a barometric rate of change signal indicating the aircraft is climbing; and an integrating circuit responsive to the barometric rate signal to determine the amount of altitude the aircraft has gained while climbing.