Abstract: A rotary wing aircraft includes a rotor assembly includes a rotor sensor generating a rotor sensor time domain signal; a rotor transform module converting the rotor sensor time domain signal to a rotor sensor frequency domain signal; and a rotor transceiver for transmitting the rotor sensor frequency domain signal over a transfer medium; an airframe assembly including: an airframe transceiver receiving the rotor sensor frequency domain signal; and an airframe transform module converting the rotor sensor frequency domain signal to the rotor sensor time domain signal. Signals from the airframe assembly may also be converted to the frequency domain prior to transfer over the transfer medium to the rotor assembly.

Abstract: A rotary wing aircraft includes a rotor assembly includes a rotor sensor generating a rotor sensor time domain signal; a rotor transform module converting the rotor sensor time domain signal to a rotor sensor frequency domain signal; and a rotor transceiver for transmitting the rotor sensor frequency domain signal over a transfer medium; an airframe assembly including: an airframe transceiver receiving the rotor sensor frequency domain signal; and an airframe transform module converting the rotor sensor frequency domain signal to the rotor sensor time domain signal. Signals from the airframe assembly may also be converted to the frequency domain prior to transfer over the transfer medium to the rotor assembly.

Abstract: A system and method to facilitate approach of a VTOL aircraft to an offshore facility includes inputting a waypoint for a landing platform of an offshore facility into an aircraft module, inputting an offset distance from the landing platform into the aircraft module, inputting a minimum descent height into an aircraft module, and inputting a final approach inbound course toward the landing platform into the aircraft module.

Abstract: A flight control system and method includes a control loop control law to bias the collective stick toward a trim reference position with a motor and generate a force gradient with a clutch.

Abstract: A flight control system and method includes a control loop control law to bias the collective stick toward a trim reference position with a motor and generate a force gradient with a clutch.

Abstract: A system and method to facilitate approach of a VTOL aircraft to an offshore facility includes inputting a waypoint for a landing platform of an offshore facility into an aircraft module, inputting an offset distance from the landing platform into the aircraft module, inputting a minimum descent height into an aircraft module, and inputting a final approach inbound course toward the landing platform into the aircraft module.

Abstract: An integrated fire and flight control (IFFC) system determines a ballistic firing solution based on the position of targets relative to a helicopter and also based on the type of weapons to be fired. An elevation command is determined based on the required change in helicopter attitude to achieve the ballistic firing solution that, combined with the estimated time required to perform the aim and release of weapons, provides an estimate of deceleration and velocity loss that will occur. A forward acceleration and velocity profile is determined based on the desire to make a symmetrical maneuver sequence involving a nose down acceleration to achieve the acceleration and velocity profile that will be canceled by the subsequent deceleration and velocity loss during the pitch up maneuver to the ballistic firing solution.

Abstract: A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920) the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference.

Abstract: A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920) the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference.

Abstract: During operation of a flight control system in a coordinated area bombing mode, one pair in a group of pairs of fire control azimuth coordinate error signal and elevation coordinate error signals are faded-in as the aircraft yaw attitude reference and pitch attitude reference, respectively. Each pair is respectively indicative of the change in aircraft yaw attitude and pitch attitude for an aircraft reference axis to be aligned with an aiming line of sight. The aiming line of sight corresponds to a target location within a selected target area. A firing signal is provided in response to both the azimuth and elevation coordinate error signals being below respective threshold magnitudes, and the next pair in the group of pairs of azimuth and elevation coordinate error signals provide the aircraft attitude reference. A selected weapon is fired in response to the firing signal.

Abstract: During operation of an integrated fire and flight control (IFFC) system in a coupled aiming mode, the occurrence of a weapon (172), weapon mount (145) or sensor (146) reaching a constraint limit (210) indices a fade-in of a constraint limiting axis command signal (140) for a respective attitude axis as the aircraft attitude reference, replacing the flight control system attitude feedback error signal (111) for the respective attitude axis. The constraint limiting axis command signals provide the aircraft attitude reference only while the pilot manually depresses and holds an enable switch (920). The pilot command stick input (90) remains the primary input to the IFFC system to thereby provide override capability for pilot command maneuvers.

Abstract: During operation of a flight control system in a coupled aiming mode, wherein a fire control system (55) azimuth command and elevation command provide an aircraft attitude reference, a bank angle calculation function (1077) provides a bank angle signal to place the aircraft in a roll angle which results in a substantially coordinated turn. The bank angle signal is determined primarily as a function of an aiming line of sight heading rate for small azimuth commands, and is determined primarily as a function of aircraft heading rate for large azimuth commands. Additionally, the bank angle initially comprises a component as a function of aircraft lateral acceleration for driving aircraft lateral acceleration to zero, and after the aircraft assumes a roll attitude for turn coordination, the bank angle comprises a component as a function of aircraft side slip for driving aircraft side slip to zero.

Abstract: A safety cage including two end plates connected by straps extending therebetween is adapted to be placed over an assembled quick connect-disconnect coupling, and the end plates engage behind abutment surfaces on the coupling to prevent accidental separation of the coupling elements. The cage also carries a pair of spaced vertical bars that engage a shoulder on the operating sleeve of the coupling, and lock it against any axial movement. The coupling includes an abutment ring that prevents any forward shifting of the sleeve because of component wear, further eliminating the possibility of accidental separation.

Abstract: The loading station of the invention includes an intake fitting, a pair of pressure operated motorized flow control valves, and a pair of loading boom assemblies that are all mounted on a movable equipment skid. The intake fitting is connectable with a source of high pressure natural gas, and the boom assemblies are universally adjustable and include coupler portions that are connectable with matching coupler portions carried on pressure vessels. Natural gas is loaded into the pressure vessels through the boom assemblies, and the loading station further includes a pressure control system that operates the motorized valves and which prevents natural gas from flowing into the boom assemblies when a pressure vessel is not connected thereto.

Abstract: Natural gas wells in a tight formation area are drilled and completed with piping, the piping being capped with a Christmas tree. The piping is then utilized as a reservoir to collect natural gas from the tight formation over a prolonged time period. Mobile pressure vessel units are employed periodically to recover the collected natural gas, on a schedule designed for maximum economic efficiency. In the preferred embodiment, the reservoir is formed between the inner production tubing and the outer casing tubing, and conduits are connected to direct the natural gas from the production tubing into the reservoir. Liquid/gas separators and dehydrator units are employed on wells as necessary, so that the natural gas stored in the reservoir is ready for transport.

Abstract: A bias voltage, which can be added to force commands applied to a helicopter control stick actuator, to compensate for static null offset errors, is generated as the average of the summation or integral of actuator pressure, or pressure differential, sensed while the force is moved from a first position which is halfway aft through null to a second position which is halfway forward and back through null to the first position, the pressure readings which are averaged being taken only through the central portion of the motion, the motion being controlled to be extremely slow compared to normal permissible stick motion.

Abstract: A user terminal is provided with two off-loading stations, and at least two separate pressure vessel means are employed to supply natural gas to the user terminal. At least one of the separate pressure vessels is movable to a supply terminal. The off-loading stations are preferably provided with an automatic switchover arrangement to change from one pressure vessel means to another, and the resulting method and system for distributing natural gas assures a continuous supply of natural gas at varying demand rates to the user terminal.

Abstract: The foldable rotor blades (12) of a helicopter are automatically adjusted to pitch angles where they can be locked as a prerequisite to folding, by commands generated (98, 112) to cause trim actuators (39-41) to drive swash plate servos (17-19) to the correct positions, initially (98) in response to stored trim references (120) and eventually (112) in response to the difference (109) between stored swash plate servo positions (120) and current servo positions (20-22). A claimed embodiment uses values of servo positions (20-22), just before unlocking the blades upon re-spreading them, to store, in nonvolatile memory (138), deviations (131) from nominal positions stored in read only memory, and generates (159) trim references in a subsequent folding operation in response to integrated values (166) to reduce actual position errors (162) toward zero from desired positions indicated by the stored deviations (148).