Lift Engine Bleed Flow Management for a V/STOL Fighter Reaction Control System

1973 ◽  
Author(s):  
C. N. Webster
Keyword(s):  
Control System ◽  
Performance Characteristics ◽  
Flow Management ◽  
Yaw Control ◽  
Control Power ◽  
Aerodynamic Control ◽  
Management Concept ◽  
Control Surfaces ◽  
Selection Of ◽  
Reaction Control System

In a lift-plus-lift/cruise V/STOL fighter, reaction control may be used to provide pitch, roll and yaw control power during hover and low speed flight when aerodynamic control surfaces are ineffective. This power is provided by reaction jets in the pitch, roll and yaw axes. Reaction thrust is derived from lift engine bleed air. This paper discusses the trade studies leading to the selection of a reaction control system arrangement and a bleed air management concept. The selected system, its performance characteristics, and flow management are discussed.

Robust adaptive sliding sector control and control allocation of a missile with aerodynamic control surfaces and reaction jets

2016 ◽  
Vol 231 (3) ◽  
pp. 397-406 ◽  
Author(s):  
Biao Xu ◽  
Di Zhou ◽  
Zhuo Liang ◽  
Guofeng Zhou
Keyword(s):  
Optimal Control ◽  
Control System ◽  
Control Law ◽  
Control Allocation ◽  
Parameter Uncertainties ◽  
Control Effort ◽  
Virtual Control ◽  
Aerodynamic Control ◽  
Robust Adaptive ◽  
Control Surfaces

Based on L2 optimal control allocation, an autopilot design approach is proposed for the missile with aerodynamic control surfaces and reaction jets. The control system involves a control allocator and a virtual control law. A robust sliding sector with a parameter update law is proposed to deal with unmatched parameter uncertainties and unknown disturbances in the system. Then a control law is designed to produce virtual control effort signals by using the robust adaptive sliding sector. In order to distribute the virtual signals to the aerodynamic control surfaces and reaction jets on the missile, a control allocator is designed by L2 optimal control allocation strategy. Simulation results show that the missile control system tracks the acceleration command fast and smoothly. In the tracking process, aerodynamic control surfaces cooperate with reaction jets, verifying the effectiveness of the proposed approach.

On the maximisation of control power in low-speed flight

2019 ◽  
Vol 123 (1266) ◽  
pp. 1099-1121
Author(s):  
L. M. B. C. Campos ◽  
J. M. G. Marques
Keyword(s):  
Control Surface ◽  
Pitching Moment ◽  
Multiple Control ◽  
Rolling Moment ◽  
Yaw Control ◽  
Control Power ◽  
Moment Coefficient ◽  
Engine Failure ◽  
Surface Deflections ◽  
Control Surfaces

ABSTRACTThe maximisation of control power is considered for an aircraft with multiple control surfaces, with the force and moment coefficients specified by polynomials of the control surface deflections of degree two. The optimal deflections, which maximise and minimise any force or moment coefficient, are determined subject to constraints on the range of deflection of each control surface. The results are applied to a flying wing configuration to determine: (i/ii) the pitch trim, at the lowest drag for the fastest climb, and at the highest drag for the steepest descent; (iii) the maximum and minimum pitching moment; (iv) the maximum and minimum yaw control power and the fraction needed to compensate an outboard engine failure for several propulsion configurations; (v) the maximum and minimum rolling moment. The optimal use of all control surfaces has significant advantages over using just one, e.g. the range of drag modulation with pitch trim is much wider and the maximum and minimum available control moments larger.

Future Trends in Flight Control Systems

1975 ◽  
Vol 28 (3) ◽  
pp. 286-299
Author(s):  
G. H. Hunt
Keyword(s):  
Control System ◽  
Control Systems ◽  
Flight Control ◽  
Pressure Sensors ◽  
System Structure ◽  
Total System ◽  
Central Processor ◽  
Flight Control System ◽  
Control Surfaces ◽  
Selection Of

This paper was presented at a joint meeting of the Institute with the Institution of Electronic and Radio Engineers in London on 15 January 1975. The theme of the meeting at which six papers were discussed (a selection of which will be published in the Journal) was Advances in Airborne Equipment for Navigation and Freight Control.Modern data processors because of their increasing power and flexibility are increasingly used for a variety of functions in modern aircraft, both civil and military. It might seem that a flight control system could be designed of the form shown in Fig. 1, with a powerful central processor taking in signals from all the relevant sensors, gyros, pressure sensors, radar, &c., and operating the control surfaces so as to drive the aircraft along any desired course. But such a system would be quite inadequate in two vitally important aspects: there is no facility for inputs from the aircrew and no account has been taken of failure cases. These and other factors drive the control system designer inexorably towards a total system structure very similar to the type currently used in operational aircraft. There are of course a wide variety of such systems, but most of them are characterized by a number of common features.

DESIGN, SIMULATION AND IMPLEMENTATION MONITORING SYSTEM FOR SYSTEM CONTROL C4 FEEDING PUMP FOR FEED VAPORIZATION IN THE BUTADIENE PLANT

2020 ◽  
Vol 1 (1) ◽  
pp. 31-35
Author(s):  
Fahmi Yunistyawan ◽  
Yunistyawan J Berchmans ◽  
Gembong Baskoro
Keyword(s):  
Motor Control ◽  
Control System ◽  
Field Operator ◽  
System Control ◽  
Variable Speed ◽  
Variable Speed Drive ◽  
Software And Hardware ◽  
Discharge Pressure ◽  
Selection Of

This study implements the auto start control system on an electric motor 3 phase C4Feeding pump when the discharge pressure is low-low (4.3 kg /cm²). The C4 feeding pumpmotor was initially manually operated from the local control station, this was very ineffectiveand inefficient because it still relied on the field operator to operate the pump motor and whenthe plant was in normal operating it is very risk if the field operator late to operate motor then itwill impact to quality of the product, and if the delay time to operate motor is too long then planthave to shut down, therefore improvement is needed in the C4 feeding pump motor controlsystem. In this paper, various types of 3-phase motor control are explained which allow it to beapplied to the C4 feeding pump motor that are on-off, inverter, and variable speed drive andefficient selection of the three systems control of the motor. Software and hardware used in thisthesis work are DCS CENTUM VP Yokogawa.

Determination of YAV-8B Reaction Control System bleed flow usage

1992 ◽  
Author(s):  
PAUL BORCHERS ◽  
ERNESTO MORALEZ, III ◽  
VERNON MERRICK ◽  
MICHAEL STORTZ ◽  
DAVID EAMES
Keyword(s):  
Control System ◽  
Reaction Control System

scholarly journals Collective Losses of Low Power Cage Induction Motors—A New Approach

Energies ◽  
2021 ◽  
Vol 14 (6) ◽  
pp. 1749
Author(s):  
Elzbieta Szychta ◽  
Leszek Szychta
Keyword(s):  
Control System ◽  
Experimental Studies ◽  
Complex Problem ◽  
Accurate Estimation ◽  
New Approach ◽  
Water Pumping ◽  
Efficiency Control ◽  
Interacting Systems ◽  
Cage Induction Motor ◽  
Selection Of

Energy efficiency of systems of water pumping is a complex problem since efficiency of two distinct interacting systems needs to be combined: water and power supply. This paper introduces a non-intrusive method of calculating the so-called “collective losses” of a cage induction motor. The term “collective losses”, which the authors define, allows for accurate estimation of motor efficiency. Control system of a pump determines operating point of a pumping station, and thus its efficiency. General estimated performance characteristics of a motor, components of a control system, are assumed to serve selection of a range of pumping speed variations. Rotational speed has a direct effect on motor load torque, pump power and head, and thus on motor performance. Hellwig’s statistical method was used to specify characteristics of estimated collective losses on the basis of experimental studies of 21 motors rated at up to 2.2 kW. The results of simulations and experiments are used to verify validity and efficiency of the suggested method. The method is non-intrusive, simple to use, and requires minimum data.

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