Variable Stability In-Flight Simulation System Based on Existing Autopilot Hardware

Scholten, Pepijn A.; Paassen, M.M. van; Chu, Q.P.; Mulder, Max

doi:10.2514/1.g005066

Cited by 7 publications

(8 citation statements)

References 23 publications

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“…The ground closed-loop system collects signals from airborne equipment, including pilot controls sensors, cockpit control panels, rudder surface sensors, throttle stick positions, and flight control system bus signals, and converts the signals into flight status parameter signal [10][11][12]. This includes various signal types such as analog, discrete and bus signals, and the signal simulation method is complex.…”

Section: Signal Acquisition and Simulation Of Airborne Equipmentmentioning

confidence: 99%

Design of Improved Ground Closed-loop Test System Based on Variable-stability Flight Control Computer

Yahui,

Wei,

Ertai

2024

J. Phys.: Conf. Ser.

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With the development of civil aviation, ground simulation test has gradually become a key link in the transformation of basic theory to engineering application. By forming a closed-loop link between the variable stability aircraft (VSA) dynamics model and the aircraft rudder surface, sensors, etc., the variable-stability ground closed-loop test system can simulate the aircraft flight state and response characteristics in the ground environment. However, the current ground test system suffers from a wide range of signals, complex signal simulation methods, and low system integration. In this study, an improved modular ground closed-loop test system for VSA is designed from three aspects: signal acquisition and simulation of airborne equipment, parameter monitoring and data processing, and fault simulation subsystem, which improves its compatibility and integrates with the software hardware of the variable-stability flight control computer and other air-borne equipment. After the system interconnection test, the generalized ground closed-loop test system designed in this study can replace the original system more efficiently, and its signal connection has inheritability, and provides a design method reference for other related researches of the variable-stability flight control computer.

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Section: Signal Acquisition and Simulation Of Airborne Equipmentmentioning

confidence: 99%

Design of Improved Ground Closed-loop Test System Based on Variable-stability Flight Control Computer

Yahui,

Wei,

Ertai

2024

J. Phys.: Conf. Ser.

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“…The experimental system runs on a dedicated computer, equipped with an Intel® Core™ i5-3550S quad-core processor, and running Ubuntu 20.04 LTS with real-time kernel (PREEMPT_RT). More details are given in [25,26].…”

Section: Hardwarementioning

confidence: 99%

Flight Testing Reinforcement Learning based Online Adaptive Flight Control Laws on CS-25 Class Aircraft

Konatala,

Van Kampen,

Looye

et al. 2024

AIAA SCITECH 2024 Forum

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“…In [9], a stability control system was designed for a medium-range jet using nonlinear dynamic inversion. The aircraft's control system is based on the existing autopilot, inheriting limited performance and safety protection.…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

“…In (9), the movement of DOF6 along pitch and yaw are connected linearly. This makes it possible to calculate the coordinates of the centers of rotation of the hinges of the upper jacks according to the formulas:…”

Section: Determination Of Permissible Movements Of Dof6mentioning

confidence: 99%

Optimizing the utilization of structural resources of flight simulator motion systems

Kabanyachyi

Hrytsan

2023

EEJET

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The object of the study is a six degrees-of-freedom motion system of the synergistic type of a flight simulator. The latter is the main technical means for training pilots and means of research and development of aircraft. The task of optimal utilization of its structural resources was solved, which provides an opportunity to improve the quality of motion cueing. The result is the developed method, which ensures optimal use of structural resources of motion systems of flight simulators. This is explained, first of all, by the use of the developed simplified operator for converting the movements of jacks into the movement of a motion system along individual degrees of freedom on the basis of quadratic approximation. Given this, it became possible to describe the coordinates of the centers of the axes of rotation of the motion system by cubic spline functions. Secondly, the solution of the task of estimating the structural resources of the motion system along linear degrees of freedom on the basis of the developed criterion was carried out by an effective modified method of the deformed polyhedron. This method combines the random search method in the first steps of the search and the gradient method in determining the global extremum. Thirdly, the problem of determining the dependence of the coordinates of the pitch and yaw axes along the pitch angle was stated and solved. Owing to the optimal utilization of the structural resources of motion systems, the coordinates of the axis of their rotation along pitch are as close as possible to the coordinate of the axis of the aircraft. Thus, the quality of motion cueing on the flight simulator is significantly increased and it is possible to use motion systems with shorter lengths of jacks, and therefore, to reduce the cost of their manufacture and operation

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Variable Stability In-Flight Simulation System Based on Existing Autopilot Hardware

Cited by 7 publications

References 23 publications

Design of Improved Ground Closed-loop Test System Based on Variable-stability Flight Control Computer

Design of Improved Ground Closed-loop Test System Based on Variable-stability Flight Control Computer

Flight Testing Reinforcement Learning based Online Adaptive Flight Control Laws on CS-25 Class Aircraft

Optimizing the utilization of structural resources of flight simulator motion systems

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