RU2249856C1 - Piloted simulator - Google Patents

Abstract

FIELD: aeronautical engineering; training flight personnel in maneuvering, performance of combat mission and higher aerobatics.

SUBSTANCE: proposed piloted simulator includes aircraft cabin equipped with indicators showing parameters of motion and power plant, sensors of control members and visualization system of aircraft spatial motion, computer system with two aircraft spatial motion modules, two modules of power plant dynamics, planning module with initial flight condition and assigned maneuver unit and control lever regulation law unit, assigned flight trajectory visualization module, module for estimation of quality of flight performed by pilot and monitor. Planning of flight is prepared in accordance with instructions for flight operation of aircraft; planning includes flight mission for performing the maneuver. In planning, altitude, speed, heading of flight and time of performing the assigned maneuver are indicated. Piloted simulator makes it possible to create "image" of flight, thus facilitating performance of assigned maneuver by pilot under real conditions.

EFFECT: enhanced accuracy of control and safety of flight.

3 cl, 1 dwg

Description

The invention relates to aircraft and is intended for use in the training in combat units of flight personnel.

A device for monitoring the activities of the operator on an aircraft flight simulator, containing, in particular, a reference characteristics and tolerance setter, the outputs of which are connected to the inputs of the graphic display and the comparison unit, a simulator made in the form of a block of digital inputs, a simulation module of an arms control system and series-connected blocks potentiometers, an analog-to-digital converter, a calibration block, a block for calculating the motion parameters of an aircraft, and a block for forming dependences of the current parameters movement and control, the outputs of the block forming the dependencies of the current parameters of movement and control, the simulation unit of the weapon control system and the block of digital codes are connected to the inputs of the graphic display and the comparison unit, the outputs of which are also connected to the inputs of the graphic display (SU 1831958 A1, G 09 B 9/08, 05/10/1995).

A disadvantage of the known device is associated with obtaining incomplete information about the trajectory of the aircraft, which reduces the reliability of ideas about the spatial position when performing aerobatics.

Closest to the proposed one is an aerobatic flight simulator containing a pilot’s cockpit, including an optical-collimation display device, an acoustic system, a pilot’s seat, a dashboard with flight-navigation instruments and indicators for monitoring aircraft engine operating modes and controls for control surfaces and aircraft engines of a simulated aircraft, a computer system with a personal computer and an information exchange system (RU 94025128 A1, G 09 V 9/08, 09/10/1996).

The disadvantage of this device is determined by the impossibility of creating a “flight image”, which negatively affects the accuracy of control and flight safety.

Known aerobatic stands:

"Pilot Flight Simulator" (publication number 94025128, publication date 1996.09.10).

Description of the invention to the patent "Method for monitoring the activities of the operator on an aircraft flight simulator and device for its implementation." USSR copyright certificate No. 1556393, class G 09 B 9/08, 1989.

RU 2018972 C1 (INSTITUTE OF AVIATION MEDICINE), 08.30.1994.

US 6234799 B1 (AMERICAN GNC CORPORATION), 05.22.2001.

US 4419079 A (AVIONS MARSEL DASSAULT-BREGUET AVIATION), 12/06/1983.

WO 85/00912 A1 (THE COMMONWEALTH OF AUSTRALIA), 02.28.1985.

US 3924342 A (REDIFON LIMITED), 12/9/1975.

DE 3929581 A1 (BODENSEEWEK GERATETECHNIK GMBH), 03/07/1991.

RU 2156501 C1 (PINAEV S.A. et al.), 09/20/2000.

RU 2114460 C1 (Firsov A.V. et al.), 06/27/1998.

The objective of the invention is to increase the effectiveness of training with the facilitation of a given maneuver in real conditions.

The problem is solved in that in the flight bench of the ground-based complex for planning and preparing the pilot to fly on a fighter plane containing the cockpit of the aircraft with indicator devices for motion parameters and the power plant, sensors of control elements and a visualization system for the spatial movement of the aircraft, as well as a computer system, including the first module of the spatial motion of the aircraft, the first module of the dynamics of the power plant and a monitor, while the input of the first module of the dynamics of forces of the new installation and the first input of the first module of the spatial movement of the aircraft are connected with the sensors of the controls, the output of the first module of the spatial movement of the aircraft is connected with indicator devices of the motion parameters and the visualization system of the spatial movement of the aircraft, and the output of the first module of the dynamics of the power plant is connected with the second input of the first module of the spatial movement aircraft and with indicator devices of the power plant parameters, - a flight planning module with a block n the initial flight conditions and the given maneuver and the block of laws for regulating the control levers, the second module of the spatial movement of the aircraft, the second module of the dynamics of the power plant, the module for visualizing the given flight path and the module for assessing the quality of the pilot's flight, the input of the second module of the dynamics of the power plant and the first input of the second the spatial motion module of the aircraft is associated with a block of initial flight conditions and a given maneuver and a block of laws for regulating control levers, the output of the second module spatial motion of the aircraft - with indicator devices of motion parameters and a system for visualizing spatial motion of the aircraft, and the output of the second module of the dynamics of the power plant - with the second input of the second module of spatial motion of the aircraft and indicator instruments of the parameters of the power plant, the outputs of both modules of spatial motion of the aircraft and both modules the dynamics of the power plant are connected to the corresponding inputs of the visualization module of a given flight path, the outputs of both modules a spatial movement of the aircraft are connected to respective inputs of evaluation of quality of performance of pilot flight module and imaging module outputs a predetermined flight path and perform quality assessment module pilot flight connected to a monitor.

Partial essential features of the invention contribute to the solution of the problem.

Each of the modules of the spatial movement of the aircraft includes a bank of aerodynamic coefficients, a block of a system of differential equations, a block of algorithms for automated control and a block of drives of controls, while the outputs of a bank of aerodynamic coefficients and a block of drives of controls are connected respectively to the first and second inputs of a block of a system of differential equations , the output of the block of the system of differential equations is connected to the input of the block of algorithms of automated control, and in the course of the block of automated control algorithms is connected to the first input of the block of drives of the controls, the combined input of the bank of aerodynamic coefficients and the second input of the block of drives of the controls are the first input of the module of the spatial motion of the aircraft, and the third input and output of the block of the system of differential equations, respectively, the second input and output of this module.

The constituent blocks of the flight planning module and the cockpit are connected with the spatial motion modules of the aircraft and the power unit dynamics modules through the interface node.

The drawing shows a functional diagram of the proposed aerobatic stand.

The flight bench contains an airplane cockpit 1 with indicator devices 2 motion parameters, indicator devices 3 power plant parameters, control sensors 4.1-4.n and the aircraft spatial motion visualization system 5, as well as a computer system including a first module 6 and a second module 7 spatial motion of the aircraft, the first module 8 and the second module 9 of the dynamics of the power plant, module 10 flight planning with block 11 of the initial flight conditions and the specified maneuver and block 12 of laws is regulated ia control levers, module 13 visualization of a given flight path, module 14 assess the quality of the pilot's flight performance and monitor 15.

The input of the first module 8 of the dynamics of the power plant and the first input of the first module 6 of the spatial motion of the aircraft are connected with the sensors 4.1-4.n of the controls, the output of the first module 6 of the spatial motion of the airplane is connected with indicator devices 2 of the motion parameters and the system 5 for visualizing the spatial motion of the airplane, the output of the first module 8 of the dynamics of the power plant - with the second input of the first module 6 of the spatial movement of the aircraft and with indicator devices 3 parameters of the power plant. The input of the second module 9 of the dynamics of the power plant and the first input of the second module 7 of the spatial movement of the aircraft are connected to the block 11 of the initial flight conditions and the specified maneuver and the block 12 of the laws of regulation of the control levers, the output of the second module 7 of the spatial movement of the aircraft - with indicator devices 2 movement parameters and the system 5 visualization of the spatial movement of the aircraft, and the output of the second module 9 of the dynamics of the power plant with the second input of the second module 7 of the spatial movement of the aircraft and with indicator bubbled devices 3 parameters powerplant. The outputs of the modules 6 and 7 of the spatial movement of the aircraft and the modules 8 and 9 of the dynamics of the power plant are connected to the corresponding inputs of the module 13 of the visualization of the given flight path, the outputs of the modules 6 and 7 of the spatial movement of the aircraft are connected to the corresponding inputs of the module 14 for assessing the quality of the pilot's flight performance, and the outputs of the module 13 visualization of a given flight path and module 14 evaluating the quality of the pilot's flight are connected to the monitor 15.

Each of the modules 6 and 7 of the spatial movement of the aircraft includes a bank of 16 aerodynamic coefficients, a block 17 of a system of differential equations, a block of 18 algorithms for automated control and a block of 19 drives of the controls. The outputs of the bank 16 aerodynamic coefficients and the block 19 of the actuator controls are connected respectively to the first and second inputs of the block 17 of the system of differential equations. The output of block 17 of the system of differential equations is connected to the input of block 18 of automated control algorithms. The output of block 18 of automated control algorithms is connected to the first input of block 19 of the actuator controls. The combined bank input 16 of the aerodynamic coefficients and the second input of the control unit drive unit 19 are the first input of the aircraft spatial motion modules 6 and 7, and the third input and output of the differential equation system unit 17 are the second input and output of the modules 6 and 7.

The constituent blocks of the flight planning module 10 and the cockpit 1 are connected with the modules 6 and 7 of the spatial movement of the aircraft and modules 8 and 9 of the dynamics of the power plant through the interface node 20.

Work on the flight bench is as follows.

Flight planning is compiled in accordance with the instructions for the flight operation of the aircraft and includes a flight mission to perform maneuver. This complex is intended for training pilots in combat units to perform maneuvers in solving combat missions and aerobatics. When planning a flight, all necessary conditions are indicated: time dependences for flight altitude H, flight speed V (number M), flight course ψ and time dependences for angular coordinates and overloads.

Consider the types of maneuvers that are performed on the flight bench and are included in the program of flight planning module 10.

1. A bend (at steady or unsteady speeds) with a given roll angle γ.

Design tasks for the parameters of a given maneuver are determined by the formulas:

- bend radius

where: n _y - overload in the longitudinal channel,

g = 9.8 m / s ²

V _sup - [m / s];

- bend speed

where V _GP - the speed of horizontal flight at a given height;

- engine thrust on a bend

P _sup = P _gp n _y ,

where R _GP - thrust of the engine in horizontal flight at V _GP at a given flight altitude.

- power consumption to perform a turn

N _in = N _gp n _y ,

where N _gp - is the power required for horizontal flight at V _in = const at a given height.

- turn time during a turn at the angle of the course Δ ψ

where: t _sup [sec], Δ ψ - [rad]

2. Dive - the flight of a plane along a steep downward trajectory and exit from the dive.

Basic calculations of the value for this maneuver:

- radius of curvature of the trajectory at the entrance to the dive

where: θ is the angle of inclination of the trajectory when diving,

θ = ϑ -α,

ϑ - pitch angle

α is the angle of attack;

- radius of curvature when exiting a dive

where: V is the average value of the speed of flight,

n _usr - the average value of the overload,

θ ₀ - steady-state angle of inclination of the trajectory during a dive;

- loss of height

Δ HR _cp (1-cosθ _cp ),

where R _cp is the average radius of curvature of the trajectory.

3. Slide - unsteady curvilinear movement of the aircraft in a vertical plane for quick climb. The slide is the main type of maneuver in a vertical plane for a fighter aircraft.

The calculation of the main parameters of this maneuver is similar to the calculation when performing a dive maneuver.

4. Loop Nesterova (PN) - unsteady movement of the aircraft in a vertical plane. PN is carried out under the condition that the flight speed is more than 1.6-2.2 times the minimum speed of the aircraft during operation of the power plant and not less than 3 times more when the power plant is off. When performing this maneuver, attention is paid to changing the flight speed, because as you climb while performing the maneuver, the speed drops, at the top of the loop it is minimal, and then begins to increase. The main parameters of the maneuver are determined by calculating the curvature at different points of the loop:

- start of loop

- loop entry

- radius of curvature at an angle of inclination of the trajectory θ = 90 °

where V ₀ is the speed at θ = 90 °;

- radius of curvature at the top of the loop

where V _Вepx is the speed at the top of the loop.

5. Combat reversal - an upward spatial maneuver in which the angle of rotation in the horizontal plane is approximately 180 °, the angle of inclination of the trajectory is approximately equal to zero. A combat U-turn can be performed with various roll angle changes. When calculating this maneuver determine:

- angular velocity in the horizontal plane

- angular velocity in the vertical plane

- radius of curvature of the trajectory in the vertical plane

- vertical speed

V _y = Vsinθ;

- horizontal speed

V _x = Vcosθ.

6. Maneuver in an inclined plane that makes up the dihedral angle ψ _v with the horizontal plane (flight without slip, slip angle β = 0).

Basic calculation formulas:

- longitudinal acceleration

j _np = g (n _x -sinψ _v sinμ),

where: μ is the angle of rotation in the plane of maneuver,

n _x - overload in a high-speed coordinate system;

- angular velocity of turning the trajectory in the maneuver plane (rad / s)

- vertical speed

V _y = Vsinψ sinμ;

- roll angle at various points on the path

движением самолета и закона управления ручкой тяги двигателя Х_руд.The basic calculation formulas given are given for the steady-state maneuver and are the initial data for calculating the time control law of the control levers

the movement of the aircraft and the control law of the engine thrust handle X _ores .

In the flight planning module, depending on the given flight maneuver, the control laws are introduced on the basis of the calculations made:

X _p ϑ (t), X _p γ (t), X _n (t) and X _ores (t).

These laws are introduced taking into account the existing restrictions for the aircraft overload, the maximum angle of attack, the maximum and minimum flight speeds, the restriction on the number M and the minimum flight height when performing the maneuver.

These dependencies are introduced to perform the maneuver as if by an “ideal pilot”, i.e. the maneuver is carried out without the participation of the pilot, who is preparing for the flight.

To perform the “ideal pilot” maneuver, the output of the planning module 10 (outputs of blocks 11 and 12) is connected to the input of the second module 7 of the aircraft spatial movement and to the input of the second module 9 of the power plant dynamics.

From the output of the second module 7 of the spatial movement of the aircraft, the signals are fed to the input of the module 13 for visualizing the specified path of the aircraft, which forms the silhouette of the aircraft and its spatial path on the screen - monitor, and also displays on the screen of the monitor 15 the current coordinates of the aircraft either in the form of graphs, or in digital form.

At the same time, the signals from the output of the second module of the spatial movement 7 are received through the interface unit 20 to the indicator devices 2 movement parameters in the cockpit 1 of the pilot.

The signal of the flight planning module 10 is also input to the second module 7 of the dynamics of the power plant, in which the engine thrust signal is generated depending on the given position. The engine thrust is given taking into account the dynamics of the power plant depending on the operating mode (throttle response, throttle, low gas, maximum, small boost, afterburner, afterburner and full flight and altitude and speed flight conditions).

In general, engine thrust is defined as

P = f (X _pyg , H, V); W (p)

where W (P) - takes into account the dynamics of the power plant and is presented in the form:

where: T ₁ , T ₂ , ξ ₂ - depend on the flight conditions for H and V and the operating mode of the power plant,

τ - when the afterburner mode is on, in other modes τ = 0.

The signal from the output of the second module 9 of the dynamics of the power plant is fed to the input of the second module 7 of the spatial movement of the aircraft (block 17 of the differential equation system) to solve the differential equation for V. Simultaneously, from the output of the second module 9 of the dynamics of the power plant, the signals through the interface node 20 are sent to the indicator devices 3 display parameters of the power plant.

All parameters of the movement of the aircraft and the power plant in the module 13 visualization of a given flight path are remembered, while it is possible at each time section to change the image scale and shift the picture in time in any direction.

A pilot who is undergoing training can observe the actions of the “ideal pilot” (actions under the program of flight planning module 10) and the corresponding flight path, as well as the movement of the aircraft relative to its center of gravity.

After the pilot decided to control the aircraft himself, he turns on the system and flies with the execution of a given maneuver. In this case, the signals from the sensors 4.1-4.n of the controls in the cockpit 1 of the pilot are fed through the interface unit 20 to the first modules 6 and 8 of the spatial movement of the aircraft and the dynamics of the power plant, the output signals of which are stored in the module 13 visualization of a given flight path similar to working with "perfect pilot." In addition, the spatial motion parameters (flight and navigation parameters) of the aircraft piloted by the pilot are supplied to the corresponding indicator devices 2, and the power unit parameters to the corresponding indicator devices 3.

The characteristics of the modules 6 and 7 of the spatial movement of the aircraft and the modules 8 and 9 of the dynamics of the power are similar. The presence of two identical modules is explained by the fact that sometimes it is advisable to combine the work of real and "ideal" pilots.

After completing the planned flight mission, the pilot has the opportunity to combine on the monitor screen the trajectory of the “ideal pilot” and the path of his flight, as well as display on the monitor screen 15 the output signals of module 14 for assessing the quality of the pilot's flight performance.

By analyzing the motion paths, the pilot has the opportunity to evaluate his actions, while his analysis is supported by a quantitative assessment of module 14 for assessing the quality of the pilot's flight performance, as the quantitative value of the error and the value of the error tolerance are given over the entire portion of the path.

Particular attention is paid to changing flight course and altitude. If, according to the assessment of the quality of control, the control is unsatisfactory, then the pilot repeats flights and again evaluates the quality of the maneuver.

According to the reviews of the pilots, this flight bench of the ground-based planning complex allows you to create an “image” of the flight, which makes it much easier for the pilot to carry out a given maneuver in real conditions, to improve control accuracy, and also to ensure flight safety when performing complex maneuvers at low altitudes.

Claims (3)

1. The pilot stand of the ground-based complex for planning and preparing the pilot for flight in a fighter aircraft, comprising a cockpit with indicator indicators of motion parameters and a power plant, sensors of controls and a system for visualizing the spatial motion of the aircraft, as well as a computer system including the first module spatial movement of the aircraft, the first module of the dynamics of the power plant and a monitor, while the input of the first module of the dynamics of the power plant and the first input of the first mo the muzzle of the spatial motion of the aircraft is connected with the sensors of the controls, the output of the first module of the spatial motion of the aircraft - with indicator instruments of the motion parameters and the visualization system of the spatial motion of the airplane, and the output of the first module of the dynamics of the power plant - with the second input of the first module of the spatial motion of the airplane and the indicator instruments of parameters power plant, characterized in that a flight planning module with a block of initial conditions p flight and a given maneuver and a block of laws governing control levers, the second module of the spatial movement of the aircraft, the second module of the dynamics of the power plant, the module for visualizing the given flight path and the module for assessing the quality of the pilot's flight performance, while the input of the second module of the dynamics of the power plant and the first input of the second module of the spatial the movements of the aircraft are associated with a block of initial flight conditions and a given maneuver and a block of laws for regulating control levers, the output of the second space module the motion of the aircraft - with indicator devices of the motion parameters and the spatial motion visualization system of the aircraft, and the output of the second module of the dynamics of the power plant - with the second input of the second module of the spatial motion of the aircraft and with indicator instruments of the power plant, the outputs of both modules of the spatial motion of the aircraft and both dynamics modules the power plant is connected to the corresponding inputs of the visualization module of a given flight path, the outputs of both spatial modules about the movement of the aircraft are connected to the corresponding inputs of the module for assessing the quality of the pilot's flight performance, and the outputs of the module for visualizing the specified flight path and the module for assessing the quality of the pilot's flight are connected to the monitor. 2. An aerobatic bench according to claim 1, characterized in that each of the spatial motion modules of the aircraft includes a bank of aerodynamic coefficients, a block of a system of differential equations, a block of algorithms for automated control and a block of drives of the controls, while the outputs of the bank of aerodynamic coefficients and a block of drives controls are connected respectively to the first and second inputs of the block of the system of differential equations, the output of the block of the system of differential equations is connected to the input of the block a algorithms of automated control, and the output of the block of algorithms of automated control is connected to the first input of the block of drives of the controls, the combined input of the bank of aerodynamic coefficients and the second input of the block of drives of the controls are the first input of the module of the spatial movement of the aircraft, and the third input and output of the block of the system of differential equations, respectively second input and output of this module. 3. An aerobatic bench according to claim 1 or 2, characterized in that the constituent blocks of the flight planning module and the cockpit are connected with the spatial motion modules of the aircraft and the power unit dynamics modules through the interface unit.