Download or read book Advanced Flight Control Actuation System AFCAS E P Fabrication and Design Verification Testing of a Dual Mode Electro Pneumatic Actuator for the T 2C Aircraft written by Wallace Kineyko and published by . This book was released on 1982 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt: Report of the fabrication and design verification testing of a Dual Mode Electro/Pneumatic Actuator. Pneumatic model open loop operation and control verified. Torque/Speed performance less than design goal due to excessive gear separation force. (Author).

Download or read book Flight Verification of the Advanced Flight Control Actuation System AFCAS in the T 2C Aircraft written by Joseph N. Demarchi and published by . This book was released on 1978 with total page 149 pages. Available in PDF, EPUB and Kindle. Book excerpt: The feasibility of the Advanced Flight Control Actuation System (AFCAS) concept was demonstrated in a T-2C aircraft. The test installation contained a localized 8000 psi (55 MPa) hydraulic power supply, control-by-wire direct-drive modular design rudder actuator, electronic drive unit, and force transducer. The system performed exceptionally well during 10.2 hours of flight evaluation. Successful completion of this project confirmed prior analyses and laboratory testing. (Author).

Download or read book Advanced Flight Control Actuation System AFCAS E P Feasibility Investigation of an Electro Pneumatic Dual Power Driven Concept written by Robert E. Feucht and published by . This book was released on 1978 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is a report of design study on Dual-Mode Dynavector Actuator for use as control-surface actuator on aircraft. Actuator operates on pneumatic power and /or electric power. Operation within specifications continues despite loss of either electric or pneumatic power, providing survivability feature for aircraft. (Author).

Download or read book Flight Verification of Direct Digital Drive for an Advanced Flight Control Actuation System AFCAS in the T 2C Aircraft written by Lloyd K. Kohnhorst and published by . This book was released on 1979 with total page 149 pages. Available in PDF, EPUB and Kindle. Book excerpt: The feasibility of Direct Digital Drive for an Advanced Flight Control Actuation System (AFCAS) was successfully demonstrated in a T-2C aircraft. The test installation contained a digitally-controlled direct-drive rudder actuator, microcomputer, electronic drive unit, force transducers, and a localized 8000 PSI (55 MPa) hydraulic power supply. The system met all laboratory and flight test objectives and demonstrated direct microcomputer control of primary flight control surfaces. This program has demonstrated an approach that will improve performance and reliability of fly-by-wire control systems by reducing the system complexity. (Author).

Download or read book Fabrication And Design Integration of an Electronic Control Unit for a Dual Mode Electro Pneumatic Actuator for the T 2C Aircraft written by and published by . This book was released on 1981 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Report of the design, fabrication and test of Electronic Control Unit (ECU) for Dual Mode Electro/Pneumatic Actuator. Integration tests establish control capability of ECU in both pneumatic and electric modes. Closed-loop operation fully implemented in design. Evaluation restricted to open-loop due to limited actuator performance.

Download or read book Advanced Electromechanical Actuation System EMAS Development and Flight Test C 141 Aircraft Demonstration written by T. Mark Bailey and published by . This book was released on 1988 with total page 336 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Design and Test of a Hydra Optic Flight Control Actuation System HOFCAS Concept written by Lloyd L. Kohnhorst and published by . This book was released on 1980 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the development, testing and demonstration of a Hydra-Optic Flight Control Actuation System (HOFCAS) suitable for the actuation tasks of a Digital Fly-By-Wire flight control system. HOFCAS offers a realistic, cost effective approach to reducing the susceptibility of aircraft fly-by-wire systems to EMP, EMI, RFI, lightning, etc. By removing the conventional wiring to the actuation areas of an aircraft, the concept eliminates the opportunity for electromagnetic hazards to enter the system. The HOFCAS concept provides a direct drive, hydraulically powered surface actuation system that provides immunity to electromagnetic radiation. The direct drive actuator, developed in a previous multiphase Navy Advanced Flight Control Actuation System (AFCAS) program, uses an electrical torque motor to power a single stage hydraulic valve for control of the actuator. A hydraulically powered alternator supplies the electrical power needed to operate the torque motor. The actuator command signal is supplied by a fiber optic link. The HOFCAS was configured to operate the directional control system in a T-2C aircraft. The AFCAS program demonstrated direct digital control of a surface actuator, and the HOFCAS extends this technology to demonstrate that conventional interconnecting electrical wiring to the surface actuators can be eliminated.

Download or read book Feasibility Study of Advanced Flight Control Actuation System AFCAS written by ROCKWELL INTERNATIONAL CORP COLUMBUS OHIO COLUMBUS AIRCRAFT DIV. and published by . This book was released on 1972 with total page 264 pages. Available in PDF, EPUB and Kindle. Book excerpt: The study is directed toward establishing the feasibility of a new and innovative flight control actuation system. Analytical and some experimental data are presented such as interface considerations, trade off justifications, failure-survivability-maintainability and reliability analysis, operational and performance characteristics, weight and space considerations. In addition, a specific concept is recommended for future hardware fabrication. This concept is based on the utilization of a directly controlled surface actuator and standardized modules which can be assembled using the 'building block' approach to provide the actuator configuration and power classes. The overall actuation concept consists of three basic disciplines and they are as follows: actuator building block, power distribution, and control. (Modified author abstract).

Download or read book Advanced Electromechanical Actuation System EMAS Flight Test written by and published by . This book was released on 1986 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt: The EMAS flight test project successfully demonstrated, for the first time, the electrical actuation of a primary flight control surface in flight. This test was a major step toward the realization of the All-Electric Airplane (AEA) concept. An electric actuator was installed in a modified C-141A aircraft to power the left aileron. Testing included ground and flight trials to ensure unchanged control system damping. Aircraft roll performance tests included maximum effort rolls, degraded system rolls, and autopilot rolls. Sideslip and trim test points were also performed. It was verified that EMAS performance was similar to the normal hydraulic actuator. Results include lessons on aircraft modification, general system characteristics, maintenance factors, and compatibility with other aircraft systems that may influence future installations. Keywords: Electromechanical actuation system; Ailerons; Flight controls; Damping.

Download or read book Laboratory Test Set up to Evaluate Electromechanical Actuation System for Aircraft Flight Control written by Street A. Barnett and published by . This book was released on 2015 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt: A laboratory apparatus and data acquisition system were constructed for evaluating aircraft flight control actuators under simulated mission profiles. A MTS hydraulic load frame was used to simulate a control surface's aero load. A NI based DAQ system was used to record the motor controller's DC bus voltage at a high rate, actuator's position, load, and temperatures. The DC bus rms voltage, current, and power, and regenerative power were recorded by a Newton's 4th power analyzer. Key performance characteristics tests such as frequency response, step response, reversal, backlash, and holding with a Danahar EC5 actuator were carried out to verify this laboratory setup.The continuous frequency sweeping test revealed that the EMA reached the speed limit first, then the current limit, and finally the temperature limit. When the actuator's electronics reached the thermal limit, the actuator controller drastically reduced its power. This caused drastic magnitude attenuation and phase lagging. Continuous frequency sweeping proved to be a useful test to evaluate the EMA's characteristics. The lab tests showed that holding presents the most significant challenge to the thermal management of an EMA system. To reduce the thermal gradient within the motor, a half rotation back forth at 0.01 Hz sinusoidal disturbance was imposed during holding to evenly engage the motor's three phases. This resulted in an 81% temperature variation reduction among the three windings. Although this small motion disturbance is effective in reducing the motor and motor drive's thermal gradient, it is not known if such a disturbance is feasible in practice.The step response and reversal test showed that when an EMA reverses direction or suddenly decelerates, a significant spike of regenerative power occurred. This regenerative power could present itself as a thermal challenge to an aircraft flight control EMA system.Using the MTS hydraulic load frame to simulate a dynamic aero load of a flight control surface in synchronization with position movement of an actuator proved to be a challenge. A double loop control scheme has been derived which compensates the time delay difference between the load frame and the actuator. It is our hope that this control strategy, once fully implemented, will enable more accurate dynamic load control in simulating an EMA's mission profile for performance evaluation.

Download or read book Fiber Optic Control System Integration for Advanced Aircraft Electro optic and Sensor Fabrication Integration and Environmental Testing for Flight Control Systems written by and published by . This book was released on 1994 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Fiber Optic Control System Integration for Advanced Aircraft Electro optic and Sensor Fabrication Integration and Environmental Testing for Flight Control Systems Laboratory Test Results written by and published by . This book was released on 1994 with total page 396 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Integrated Avionics Instruments and Flight Control Systems Specialist F 16 AFSC 32657C written by Dennis M. Holliday and published by . This book was released on 1985 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Design and Fabrication of an 8000 PSI Control by Wire Actuator for Flight Testing in a T 2C Airplane written by Joseph N. Demarchi and published by . This book was released on 1976 with total page 45 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the design and fabrication of an 8000 psi control-by-wire hydraulic rudder actuator for future flight testing in a T-2C airplane. Actuator output is commanded by a single stage spool/sleeve valve driven directly by a permanent magnet force motor. Actuator design criteria were based on T-2C aerodynamic considerations and envelope constraints. A system analysis was conducted to determine heat dissipation and hydraulic line sizes and routing. Modifications required on the T-2C airplane to accommodate the test system installation were outlined. (Author).

Download or read book Test and Development of Flight Control Actuation System Components for Military Aircraft written by Gavin D. Jenney and published by . This book was released on 1971 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt: Contents: NAK Integrated Package Laboratory Tests; B-47 FBW Pumping Module Evaluation; Actuator Gunfire Vulnerability Evaluation; Flow Difference Sensor Continued Evaluation Life Testing; flow Difference Sensor Continued Evaluation Gunfire Testing; Flow Difference Sensor Continued Evaluation Contamination Sensitivity; Flow Difference Sensor Continued Evaluation Detection Level Improvement; Active Load System Actuator Test Rig; Evaluation of Simplex Integrated Actuator Package; duplex Package Evaluation; Hydraulic Fluid Contamination Research; Input-Output Redundancy Investigation.

Download or read book Control By Wire Modular Actuator Tests AFCAS written by Joseph N. Demarchi and published by . This book was released on 1975 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of tests conducted on an engineering model of a primary flight control hydraulic surface actuator that is controlled directly by electrical inputs. The actuator is modular configured and utilizes an operating pressure of 8000 psi. Electrical inputs are applied to force motor, direct-driven, single stage flow control valves. A laboratory type electronic interface unit containing redundancy features powered the force motors. Static and dynamic tests were conducted on the force motors, motor/valve sub-assemblies electronic interface unit, and actuator assemblies including dual system tandem, dual system parallel, and single system configurations. The dual tandem actuator was tested under load.

Download or read book Advanced Actuation Systems Development written by Gavin D. Jenney and published by . This book was released on 1989 with total page 365 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes six different research and development activities in flight control actuation. The activities are: (1) the development and test of a unique linear actuator sealing system for high pressure systems, (2) the development and test of a digital servovalve using piezo-controlled high speed solenoid valves, (3) the performance evaluation of an F-15 rudder actuator under applied loads, (4) the performance evaluation of a Mission Adaptive Wing section under different load conditions, (5) the evaluation of output impedance modification of an electrohydraulic actuator for flutter suppression, and (6) the development and test of a direct drive valve and electronics (analog and digital) for an F-16 Horizontal Tail/Flaperon actuator. Volume I of the report presents activities 1, 2, and 3. Volume II present activities 4, 5, and 6.