Flight Table Research Articles

OPTIMAL ALLOCATION OF FLEET OF HELICOPTERS AND AIRPORTS TO TRANSPORT PASSENGERS IN OFFSHORE MARITIME UNITS

The choice and distribution of the optimal fleet mix of helicopters to service the offshore air operation is an important logistical problem that has a potential to reduce costs considered in the oil and gas industry. The variability of helicopter models and sizes, as well as the possible operational restrictions of airport bases and airspace, requires that adequate numerical techniques of Operational Research are applied. In this context, this work develops a model to determine the trajectories and distances traveled between airport bases and offshore maritime units and vice-versa, through an airspace modeled by a directed graph. Also develop a helicopter performance model to obtain the estimated payload and flight times for each specified mission and last but not least an integer linear programming model to allocate an optimal fleet and airport mix for passenger transport through the use of different helicopter sizes. The model was applied to offshore units operating in the Santos basin due to their strategic importance in the oil and gas industry. The results obtained included a map of preferred regions for two different helicopter sizes (large and medium), the weekly flight tables showing the allocation of helicopters and airport for different demand scenarios, additionally the impact of fuel prices on different airport bases and the concentration of movements on air routes are also evaluated in order to complement the analysis.

A sustainable method for scheduling maintenance services of an airline with the aims of minimising awaiting times and maximising flights performance

In this research, an efficient multi-objective hybrid method is proposed for scheduling maintenance services of an airline in order to reduce maintenance and repair costs and the work cycle of the aircraft simultaneously. The method is developed based on real conditions in repair shops of international airlines. Schedule aircraft according to their preventive plans and flight tables in order to reduce the awaiting times in the main repair shops of the airline. The method can also rent aircraft from other airlines when necessary and allows alien airplanes to use repair shop services to utilise performance of the repair shop. Several case studies using real number of aircraft in the airlines are solved to evaluate the performance of the proposed method. The results showed the proposed method can schedule maintenance services of large scale airplanes and decrease the multi-objective functions up to 48% in the solved case studies.

A sustainable method for scheduling maintenance services of an airline with the aims of minimising awaiting times and maximising flights performance

In this research, an efficient multi-objective hybrid method is proposed for scheduling maintenance services of an airline in order to reduce maintenance and repair costs and the work cycle of the aircraft simultaneously. The method is developed based on real conditions in repair shops of international airlines. Schedule aircraft according to their preventive plans and flight tables in order to reduce the awaiting times in the main repair shops of the airline. The method can also rent aircraft from other airlines when necessary and allows alien airplanes to use repair shop services to utilise performance of the repair shop. Several case studies using real number of aircraft in the airlines are solved to evaluate the performance of the proposed method. The results showed the proposed method can schedule maintenance services of large scale airplanes and decrease the multi-objective functions up to 48% in the solved case studies.

Airborne Real Time Instrumentation System (ARTISt): Studi Analisis dan Perancangannya

ARTISt is an instrumentation system based on Personal Computer (PC) which is installed on board the prototype aircraft to perform presentation of flight test data in real time. The presentation consists of display the data in table mode, graphic mode, mixed mode (table and graphic), and xplot mode (graphic between 2 parameters), and also print and record the data. The data which has been recorded by ARTISt, can be used by other software through the Disk Management System (DMS). The PC equipped with an interface for Pulse Code Modulation (PCM) decoder called ARTISt Card.In this paper, we are discussing about requirements analysis and design the ARTISt. Keywords: ARTISt, flight test data, real time, table mode, graphic mode, mixed mode, xplot mode, requirements analysis and design

Nominal Model-Based Sliding Mode Control with Backstepping for 3-Axis Flight Table

Based on nominal model, a novel global sliding mode controller (GSMC) with a new control scheme is proposal for a practical uncertain servo system. This control scheme consists of two combined controllers. One is the global sliding mode controller for practical plant, the other is the integral backstepping controller for nominal model. Modeling error between practical plant and nominal model is used to design GSMC. The steady-state control accuracy can be guaranteed by the integral backstepping control law, and the global robustness can be obtained by GSMC. The stability of the proposed controller is proved according to the Lyapunov approach. The simulation results both of sine signal and step signal tracking for 3 axis flight table are investigated to show good position tracking performance and high rcr bustness with respect to large and parameter changes over all the response time.

QFT Robust Control Design for 3-Axis Flight Table Servo System with Large Friction

The 3-axis flight table is an important device and a typical high performance position and speed servo system used in the hardware in the loop simulation of flight control system. Friction force and uncertainty are the main characteristics in the 3-axis flight table servo system. Based on the description of dynamic and static model of a nonlinear Stribeck friction model, and taking account of the practical uncertainties of 3-axis flight table servo system, the QFT controller is designed. Simulation and real-time results are presented.

Mini-UAV altitude estimation using an inertially stabilized payload

A novel method is introduced for autonomous attitude estimation of a mini unmanned aerial vehicle (UAV) carrying an inertially stabilized payload. The method is based on utilizing the outputs of rate gyros normally used to inertially stabilize the payload, and other data that is normally available from conventional aircraft-mounted sensors. A decentralized estimation algorithm is developed, which uses the aircraft/payload mathematical models to bound the estimation errors. Exploiting modern multiprocessor computer technology, the new estimation algorithm comprises two parallel extended Kalman filters (EKFs) and a data fusion algorithm. Real-time experimental tests, incorporating a payload model with real rate gyros mounted on a three-axis flight table, have validated the feasibility of the concept. The theoretical and experimental investigation demonstrates that the estimation algorithm is capable of estimating the attitude angles with an estimation error not exceeding 1 deg, at output rates of 13 Hz, thus constituting a viable substitute for the conventional vertical gyroscope.

Autonomously aided strapdown attitude reference system

The feasibility of an autonomously aided strapdown attitude reference system, based solely on the measurements of an orthogonal triad of rate gyros and conventional air data, is explored. The aiding is provided by the aerodynamic model of the aircraft and a reduced-order multirate extended Kalman filter (EKF). It is demonstrated that the EKF provides on-line attitude estimates with bounded errors not exceeding 0.5 deg at output rates on the order of 20 Hz. On-line simulation tests, incorporating low-cost rate gyros mounted on a high-precision three-axis flight table, validate the feasibility of the concept.

Three-axis platform simulation: Bond graph and Lagrangian approach

A bond graph model is derived for the geometric constraints of a three-axis flight table. Gimbal dynamics are easily added even in asymmetrical and unbalanced cases. A method is introduced to make the local dependent inertias computable. The bond graph compares favourably to the Lagrangian approach as to modelling effort and accessibility of intermediate variables as well as having computational advantages.

Mini-RPV Lateral Autopilot Design

In this paper the design of a lateral autopilot for a miniature remotely piloted vehicle (RPV) is described. The structure of the autopilot is predetermined , as well as the measured variables. It is shown that, even though aileron alone is used to control the RPV, the system is completely controllable. By use of several indices of performance, the best autopilot gains are determined by minimizing these indices. The minimization is carried out in the complex plane, and comparison is made with state space methods. It is concluded that, when a single error, such as heading error, is considered, the complex plane minimization procedure is superior. It is seen that the RPV poles due to the Dutch-Roll mode stay close to the imaginary axis, although heavy penalty is imposed by the performance index on a persisting error. It is shown that the pole placement is restricted by the fact that the trace of the system matrix is constant. Although no rudder is used, the vehicle executes coordinated turns due to its natural coordination quality. Following the design, an autopilot has been built and tested on a flight table hooked to an analog computer, which simulates the RPV dynamics. The performance of the tested system matched the analog and the digital simulation of the system.

A Three-Axis Flight Table with DC Torque Motors

The use of flight tables and the present state of the art are described and the specifications for the flight table are derived. Major stress is laid on building a relatively cheap model, that will, nevertheless, satisfy the present requirements. A detailed description of the various alternatives that exist when deciding upon the major components is given along with a discussion on the linear design of the servo loops and stability validations for the expected nonlinearities. A grapho-analytical jump prediction is presented and the wiper backlash problem is analyzed.