KR20070121300A - Method of sound output for simulator - Google Patents

Abstract

A method for outputting flight simulation sound is provided to assign reality and immersion to a pilot performing flight training with a simulator by outputting the flight simulation sound, such noise, signal sounds, and alarm sounds, in connection with action of the pilot and an operation state of an airplane. A database stores the sounds generated from the airplane as a sound file(S102). Sound generation data is received from other systems(S104). A sound realizing program corresponding to the sound generation data is called(S106). A sound outputting control signal is generated according to order of an algorithm included in the sound realizing program(S108). The sound file corresponding to the control signal is called(S110). The sound of the sound file is controlled by a sound pressure level and a pitch band corresponding to the control signal(S112). The sound file stores a predefined sound generation attribute including the sound pressure level and the pitch band to an ADF(Application Definition File).

Description

Flight simulation sound output method

1 is a system configuration applied to implement the present inventors flight simulation sound output method,

2 is a flowchart of an algorithm of a program for outputting engine sound according to the present invention;

3 is a flowchart of an algorithm of a program for outputting a communication sound according to the present invention;

4 is a flowchart of an algorithm of a program for outputting a warning sound according to the present invention;

5 is a flowchart of an algorithm of a program for outputting external sounds according to the present invention;

6 is a flowchart of an algorithm of a program for outputting internal sounds according to the present invention;

7 is a flowchart of an algorithm of a program for outputting subsystem sounds according to the present invention;

8 is a flowchart of an algorithm of a program for outputting environmental sounds according to the present invention;

9 is a flowchart of an algorithm of a program for outputting an ATIS sound according to the present invention;

10 is a flowchart illustrating a flight simulation sound output method according to an embodiment of the present invention.

<Description of Symbols for Main Parts of Drawings>

10: sound processing device 102: DBMS unit

104: API unit 106: application unit

106a: Acoustic Implement Program 106b: Diagnostic / Operation Program

108: acoustic database 20: D / A converter

30: Ethernet 40: other sub-system

The present invention relates to a flight simulation sound output method. More specifically, the present invention relates to a flight simulation sound output method for providing various noises, signals, warning sounds, etc. generated in an aircraft according to the pilot's actions and the operating state of the aircraft.

In general, a flight simulator is a device that trains pilots by allowing pilots to carry out the same hands-on flight on the ground, even if they do not actually fly.

Typically, such a flight simulator is composed of a cockpit system equipped with the same instrument, a control stick and the like as a cockpit of an aircraft, and a control environment, and a flight simulation terminal for performing a simulation using data input from the cockpit system. .

In this case, the flight simulation terminal is configured by installing a flight simulation program capable of driving simulation in a personal terminal capable of interworking through the cockpit system and the communication network.

Therefore, when the pilot manipulates the pilot equipment of the cockpit system, the operation data is input to the flight simulation terminal, and the flight simulation terminal performs a virtual simulation using the input data.

On the other hand, for more effective flight training, it is important to provide pilots in the simulator's cockpit system with the same environment as on board the actual aircraft. The same various noises, beeps and warning sounds as they should be controlled to occur in real time.

However, the sound implementation system applied to the conventional simulator has a problem in that it is difficult to describe the situation in which the sound implementation system is implemented only with specific stored sounds without considering the characteristics of sound source generation, or when the preliminary time is applied in the implementation process. .

In order to solve the above problems, the present invention provides a flight simulation sound output method for providing various noises, signals, and warning sounds generated in an aircraft in accordance with the pilot's actions and the operational state of the aircraft, thereby providing a simulator. The purpose is to give the pilot training to the realism and immersion.

The present invention to achieve this object,

(a) preparing a sound generated from the gas into an acoustic file and storing the sound file in a database;

(b) receiving sound source generation data from another sub-system;

(c) calling a sound implementation program corresponding to the sound source generation data;

(d) generating a sound output control signal according to the order of algorithms included in the sound implementation program;

(e) calling a sound file corresponding to the control signal; And

and (f) adjusting the sound of the sound file with a sound pressure level and a pitch bend corresponding to the control signal.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. First, in adding reference numerals to the components of each drawing, it should be noted that the same reference numerals are used as much as possible even if displayed on different drawings. In addition, in describing the present invention, when it is determined that the detailed description of the related well-known configuration or function may obscure the gist of the present invention, the detailed description thereof will be omitted.

1 is a system configuration applied to implement the present inventors flight simulation sound output method.

The system to which the present invention is applied comprises a database management system unit (DBMS) 102, an application program interface unit (API) 104, an application program unit 106, and an acoustic database unit 108. And a D / A converter 20 for converting a sound source, which is a digital signal output from the sound processing device, into an analog signal, and the sound processing device 10 includes the other sub-system 40 and Ethernet. It is configured to be able to work with the synchronization method through the (30).

That is, the sound processing apparatus 10 to which the present invention is applied is a device that senses sound source generation data of another sub-system 40 (eg, cockpit system) transmitted through Ethernet 30 and processes sound in real time.

The database management system unit (DBMS) 102 recognizes the sound source generation data (for example, operation state information of the aircraft) transmitted from the other sub-system 40, and then applies the application through the application program interface unit (API) 104. The program 106 is approached to execute the sound implementation program 106a corresponding to the sound source generation data information.

In a preferred embodiment, the database management system unit (DBMS) 102 uses an SGI O2 system. Since the O2 system is designed in a multi-threaded structure, the sound processing apparatus 10 supports a function of operating multiple sound sources at the same time. Meanwhile, the digital audio input / output board (PCI) (not shown) may be mounted on the O2 for sound processing.

As a preferred embodiment, the application program interface unit 104 uses Audio Works for IRIX, which is software that has been verified for sound management, stability, and operational problems.

The application program unit 106 includes an acoustic implementation program 106a and a diagnostic / operation program 106b.

The sound implementation program 106a may respectively change the sound pressure level (SPL) and pitch bend (Pitch Bend) values defined in the program code in response to sound source generation data transmitted from the other sub-system 40. This is a program to output the sound according to the situation. However, a more specific program configuration will be described in detail with reference to the sound database unit 108 to be described later for convenience of description.

The diagnostic / operation program 106b is a program configured to generate and transmit a status window to a display unit (not shown) so as to check a state of whether the acoustic implementation program 106a operates normally. According to a preferred embodiment, the diagnostic / operation program checks the operation state of each sound program for each function operated by the sound implementation program, and then checks whether it is normal or abnormal through a display unit (not shown). Configure to display with display items such as

The sound database unit 108 may store each sound property (sound pressure level, pitch bend, etc.) generated in the aircraft in advance and produce the sound file, and then specify the sound file according to the criteria classified for each function. Continue to accumulate and manage sound data.

The sound database unit 108 includes a large engine sound database according to criteria classified for each function; Communication acoustic database; Warning acoustic database; External acoustic database; Internal acoustic database; Subsystem database; Environmental acoustic database; And an ATIS acoustic database, wherein the acoustic file included in each database includes attributes of sound generation such as sound pressure level (SPL) and pitch bend (Application Definition File). Save in advance).

The sound database unit 108 thus constructed is called together with the execution of the sound implementation program 106a to output sound for each situation through the change of the sound pressure level and pitch bend value defined in the program code.

In particular, the sound processing apparatus 10 applied to the present invention generates sound close to the actual sound by simultaneously generating a plurality of sound sources (as well as generating sound with only one sound source) in order to generate sound suitable for each situation. It characterized by outputting. In addition, the sound implementation program 106a to be applied to the present invention is to change the sound by creating a specialized function (Interpolation Function) when it is not possible to obtain the output of the adjacent sound only by simply adjusting the sound pressure level and the pitch bend. This adjusts the sound pressure level and pitch bend.

Hereinafter, a method of constructing the sound database unit 108 and a sound output method using the sound implementation program 106a will be described in detail with reference to Tables 1 to 8 and FIGS. 2 to 9.

TABLE 1

[Table 1] is a table showing sound file characteristics of the engine sound database included in the sound database unit 108, and FIG. 2 is a diagram showing an algorithm of the program 106a for outputting engine sound.

The engine sound database includes sounds related to the engine as sound files, which predefine characteristics of each sound (eg, sample width, sample rate, number of channels, and looping).

Sound files of sounds related to these engines include sounds of engines, turbines, propellers, propeller washes, and engine igniter sounds.

For reference, when explaining the sound source characteristics of the sound associated with the engine, all sound sources except the igniter are always generated at the same time, these (engine, turbine, propeller, propeller wash) are each engine revolution (rpm: revolution per minute) The sound pressure level and pitch bend change according to). Basically, the sound pressure level and pitch bend increase as the ALMP increases, and the degree of increase is determined by the output value in which the ALPM is input to a specific function value.

On the other hand, the igniter is a device for starting the airplane, the sound of the igniter is repeatedly generated while operating the igniter.

Referring to FIG. 2, when an algorithm for outputting engine sounds is described, the sound implementation program 106a for outputting engine sounds may have a prepared looping sound file if a corresponding flag is turned on in the case of an igniter. Print out (eng.ignitor.aifc). However, the sound related to other engines should output various sound changes by using the change of the loudness and pitch bend according to the AlPM and the altitude change.

Therefore, the received ALMP value is transferred to the interpolation function to change to the appropriate pitch bend and sound pressure level values, and then the various sound values are output for each situation using the changed values.

Here, the interpolation functions are all linear functions according to ALPM, and this function is an experience-based function by comparing sounds. In addition, the interpolation function pre-determines the sound pressure level and pitch bend function for each engine, turbine, propeller, and propeller wash, and outputs the result of the function when the ALMP value, which is the main variable of the engine sound, is input. To produce

In addition, the change in the sound according to the change of altitude is applied to the pitch bend and the sound pressure level is configured to output the final sound. As the altitude increases, the volume decreases and the pitch bend increases. In other words, the sound of an engine including a propeller, a turbine, etc. changes the value once changed by the interpolation function by the altitude and outputs the value similar to the actual sound.

TABLE 2

[Table 2] is a table showing sound file characteristics of the communication sound database included in the sound database unit 108, and FIG. 3 is a diagram showing an algorithm of the program 106a for outputting the communication sound.

The communication sound database includes all sounds related to communication except ATIS as sound files. The sound files pre-store and store the characteristics (eg, sample width, sample rate, number of channels, and loops) of each sound.

Sound files of sounds related to such communication include sounds generated from Very High Frequency (VHF), Ultra High Frequency (UHF), and TACtical Air Navigation System (TACAN), and VHF and UHF are the noises generated by the change of frequency. Noise and Tone.

Here, VHF / UHF noise is a noise generated during communication. When the frequencies for communication do not coincide with each other, the sound is loud and when the frequencies coincide, the sound is greatly reduced. On the other hand, VHF / UHF noise does not occur when the mute switch is on.

In addition, the VHF / UHF tone is a sound generated when the frequency is tuned, and is generated only when the tone switch is turned on. It does not occur when the mute switch is turned on.

On the other hand, the TACAN tone is a Morse signal that transmits information about where the airport is at the airport to the pilot. When the name of the airport is selected, the TACAN tone is changed to a Morse signal corresponding to the airport, and the dot and dash ( The two notes of dash) are printed in order.

Referring to FIG. 3, when an algorithm for outputting communication sounds is described, the sound implementation program 106a for outputting communication sounds is configured to simultaneously or alternately output the sounds of VHF, UHF, and TACAN.

In more detail, the VHF / UHF sound is a noise generated during communication as described above, and is composed of noise and tone sounds, and the VHF / UHF sound is generated only when the volume of the communication volume is greater than 0. It only consists of calling the function if the size is greater than zero.

At this time, the noise is composed of a change in the loudness in response to the change in the volume. In addition, the noise and tone sounds are configured such that sound is generated only when the mute switch is not turned on and the tone switch is turned on.

On the other hand, since the TACAN sound is composed of a combination of two dots and dashes, when information on which airport is located where the pilot is located is selected, first, the TMOS signal is changed to a Morse signal corresponding to the airport, and the changed dot and dash combination is performed. Is configured to repeatedly output the dashed sound in the order of outputting the dashed sound in the order of outputting the dot sound in order.

For example, in a cockpit system, if a virtual plane is simulated to pass over a virtual space, Sichuan Airport, and the TACAN switch is turned on, then the acoustic implementation program 106a will first determine that the current airport is Sichuan Airport. It consists of checking and repeatedly outputting "S (...)", "A (.-)", and "C (-.-.)" Corresponding to "SAC", which is the Morse signal tone corresponding to Sichuan Airport. .

TABLE 3

[Table 3] is a table showing sound file characteristics of the warning sound database included in the sound database unit 108, and FIG. 4 is a diagram showing an algorithm of the program 106a for outputting the warning sound.

The alert sound database contains six sound alerts: Fire, Overheat, Stall, Stall2, Overspeed, and Landing Gear. The sound file stores and stores the characteristics of each sound (eg, sample width, sample rate, number of channels, and loops) in advance.

The warning sound is generated when there is an abnormal condition of the airplane. It consists of two types, a tone sound and a voice sound.

Here, the tone tone is a sound generated by a constant tone noise every two seconds, and the voice tone is a sound that is repeatedly generated a specific voice for warning. When the CWS button is turned on, the voice tone is generated according to a predefined priority (for example, Fire, Overheat, Stall, Overspeed, and landing gear). Configure.

Referring to FIG. 4, when the algorithm for outputting the warning sound is described, the sound implementation program 106a for outputting the warning sound may specify the priority among the warning sounds in advance, and then correspond to the condition data for recognizing a specific situation. It is configured to output specific beep repeatedly according to priority.

Here, the specific warning sound means two sound components, a voice sound and a tone sound, as described above. Here, the voice tone is to output a word meaning a warning state as a human voice, and the tone tone is a unique sound is output for 2 seconds for each warning situation.

In addition, these two beeps (voice tone and tone tone) are configured to be repeated and output repeatedly. That is, if there is only one specific situation in which the warning sound is to be generated, the warning sound is repeatedly outputted, and when there are two or more specific situations in which the warning sound is to be generated, the warning sound is repeatedly output according to a predetermined priority. For example, if there is a warning of Fire, Overheat, and Stall, the warning sound will continue in the order of high priority, such as "Fire Overheat Stall Fire Overflow Stall", until the warning ends. Output

In addition, if a new warning situation is added during this repetition cycle, the newly added warning sound is outputted first, and then the new priority ring is added to form a new circular ring from the highest priority warning sound. For example, if a warning state of "over-speed" is newly added in a situation in which "fire-over stall" is repeatedly output, the sound of "over-speed" is output first, and as in "fire-over stall over-speed," Again configure the Fire to create a new cycle.

TABLE 4

[Table 4] is a table showing sound file characteristics of the external sound database included in the sound database unit 108, and FIG. 5 is a diagram showing an algorithm of the program 106a for outputting external sound.

The external acoustic database contains runway rumble, touch down, touch bump, air friction sound, which are generated outside the aircraft by the movement of the aircraft (independent of the pilot's instrument operation). A GPU (Groud Power Unit) and a Puffet sound are included as a sound file, and the sound file defines and stores the characteristics (eg, sample width, sample rate, number of channels, and looping) of each sound in advance.

When explaining the sound source characteristics of the external sound, the runway rumble occurs while the landing gear (all three) contact the runway with the sound of the wheels of the landing gear rolling the runway while the plane moves on the runway.

In the case of a touchdown sound, the landing gear rubs against the runway at the moment the plane lands, producing a large friction sound, which varies according to the z-force transmitted to each gear, so the z-force value for each gear To adjust the volume of the sound. In addition, the touch bump sound, which is a sound source generated when the wheels of the landing gear rolls on the runway immediately after contacting the runway, has a characteristic that the faster the ground speed of the plane's fuselage is, the louder the sound is generated.

Air friction sounds only when the true airspeed is above Mach 2. In addition, in the case of the air friction sound, the larger the difference between the dynamic pressure and the static pressure, the larger the width of the pitch bend change correspondingly.

On the other hand, the GPU sound refers to the sound of the ground-assisted power unit, the buffet sound is a kind of vibration caused when the aircraft rides a certain air flow in the air.

Referring to FIG. 5, when an algorithm for outputting external sounds is described, the sound implementation program 106a for outputting external sounds classifies each target into a sound source for generating static sound and a sound source for generating dynamic sound. In the case of sound, the sound pressure level and the pitch bend are adjusted and output according to the conditions of each situation.

For example, the runway rumble, the GPU, and the buffet sound are all sound sources for generating static sound. When the corresponding flag is turned on, the sound file is called to generate sound.

However, since the touchdown, touch bump, and air friction sound are not only one sound but a so-called dynamic sound that changes according to each condition, the touch-down applies a z-force transmitted to each landing gear. Adjust the volume of the sound, in the case of the touch bump is configured to adjust the volume of the sound according to the ground speed in the fuselage direction, the greater the difference between the external air pressure and the internal air pressure of the air, the larger the pitch bend value In addition, as the speed of the gas increases, the volume of the sound of the air friction sound is also increased correspondingly.

TABLE 5

[Table 5] is a table showing sound file characteristics of the internal sound database included in the sound database unit 108, and FIG. 6 is a diagram showing an algorithm of the program 106a for outputting the internal sound.

The internal acoustic database contains as sound files the sound generated when operating the ESC (Environment Control System), which functions as a type of air conditioner inside the aircraft, which contains the characteristics of the sound (e.g. sample width, sample rate, channel). Number and loop) are stored in advance.

In the case of ESC, the operation phase is divided into two stages, and the output is made larger when the button which designates the second stage is pressed than when the button which designates the first stage is pressed. Therefore, the sound output program should be configured to generate a different volume of sound by three steps, 0, 1, and 2, rather than two types of flags.

TABLE 6

[Table 6] is a table showing sound file characteristics of the subsystem sound database included in the sound database unit 108, and FIG. 7 is a diagram showing an algorithm of the program 106a for outputting the subsystem sound.

The subsystem sound database contains landing sound, gear lock, flap, and speed brake sounds as sound files, which are sounds generated by the pilot's operation. The characteristics of the sound (eg, sample width, sample rate, number of channels, looping) are predefined and stored.

Referring to the sound source characteristics of the subsystem sound, the landing gear movement sound is a sound generated when the pilot manipulates the landing gear to move up or down.

The gear lock sound is configured to output the locking sound when the flag is turned on because the sound of raising and locking the gear is different from the sound of lowering and locking the gear.

In addition, in the case of flap sounds, when the flap device is operated, nitrogen is released to generate a 'flap extension sound', which is a sound flowing into the flap hydraulic system. Here, the flap device is a device operated by a pilot for vertical movement of the plane.

Meanwhile, the flap movement sound is generated while the flap is moving, and the flap movement sound is continuously generated when the flap movement sounds like the movement sound of the landing gear.

The speed brake sound varies in volume depending on the operating angle of the blade. The greater the angle, the louder the friction sound is. The speed brake here is a device for slowing down the speed of the aircraft and is usually operated on the runway after landing.

On the other hand, the program for outputting the above-described subsystem sound is a static sound in the case of the gear lock sound is configured to be simply controlled by the flag (flag) on / off. However, since the landing gear movement sound and the flap sound are generated while the angle changes, respectively, the sound must be continuously output while the angle is changed while comparing the angle between the initial angle and the operation.

Finally, the speed brake sound is configured to output a louder sound because the greater the angle, the wider the surface that resists air, according to the blade angle of the speed brake.

TABLE 7

[Table 7] is a table showing sound file characteristics of the environmental sound database included in the acoustic database unit 108, and FIG. 8 is a diagram showing an algorithm of the program 106a for outputting the environmental sound.

The environmental acoustic database includes thunder sound as a sound file, and the sound file defines and stores the characteristics (eg, sample width, sample rate, number of channels, and looping) of each sound in advance.

In describing the sound source characteristics of the thunder sound, it is necessary to consider the delay time for the pilot to hear the thunder sound after the thunder sound is flagged on. Therefore, the sound implementation program 106a should be configured in consideration of the delay time. That is, the thunder sound is a static sound generated when the corresponding flag is on, but the sound is not output immediately after the flag is turned on, but the thunder sound is output after the delay time is applied by applying a predetermined delay time. Configure.

Table 8-1

Table 8-2

Table 8-3

Table 8-4

[Table 8-1, 2, 3, 4] is a table showing sound file characteristics of the ATIS sound database included in the sound database unit 108, and FIG. 9 shows an algorithm of the program 106a for outputting ATIS sound. Drawing.

The Automatic Terminal Information Services (ATIS) acoustic database contains voice sounds of weather, wind direction, wind speed, etc. around the airport, which are transmitted unilaterally from the airport by the ATIS station, and the acoustic file includes the characteristics of each sound (e.g., a sample). Width, sample rate, number of channels, and looping) are pre-defined and stored.

Referring to FIG. 9, the algorithm for outputting the ATIS sound will be described. The sound implementation program 106a for outputting the ATIS sound is configured in consideration of the number of all cases in accordance with the output standard of the ATIS. To this end, the sound implementation program 106a is divided into a "static" array for outputting only sound determined according to the ATIS output standard and a "dynamic" array for outputting the condition according to changing conditions. Also, the sound implementation program 106a outputs the sound and releases the index set in its turn when the order is returned based on the index indicating the order of the array divided into static and dynamic. It is configured to set the index to be printed next. On the other hand, all voice notes included in static will be output as soon as their order is returned. In the case of dynamic, however, if a numerical value is to be outputted, the delivered numerical value should be outputted, and if it is necessary to output a specific voice sound related to the weather, select a specific voice sound such as "clear" or "smoke" to match the condition. Should print

In addition, if dynamic is a number, it divides the transmitted value by the number of digits and outputs the corresponding voice sound in the form of "one" or "two" for each digit. Similarly, if dynamic is a code word, the output is in the form "alpha" or "bravo".

On the other hand, in order to output these variable values as voice tones, each conditional statement is made and when the condition is satisfied, a switch-case statement for outputting the corresponding voice tone is used.

In addition, when outputting numerical values as voice notes, only one function that outputs numerical values is called, but the flag for this is considered considering whether to output a "zero" sound before the numerical value or not. Should be configured separately.

10 is a flowchart illustrating a flight simulation sound output method according to a preferred embodiment of the present invention.

First, each sound attribute generated in the gas is stored in advance to produce a sound file, and then classified into respective functions to construct a sound database 108 (S102).

Next, in order to output the sound file stored in the sound database to a sound pressure level and pitch bend similar to the actual sound, a sound implementation program 106a is constructed in consideration of the characteristics of the generation of each sound.

The sound processing apparatus 10 to which the sound implementation program 106a is applied performs the synchronization of the other sub-system 40 and the synchronous method through the Ethernet 30.

Therefore, when receiving data for generating a sound source from another sub-system (for example, the cockpit system) (S104), the sound processing apparatus 10 calls the sound implementation program 106a corresponding to the data (S106). Generates a control signal to process the sound in the order of (S108).

Accordingly, the sound implementation program 106a performs an operation of calling the sound file corresponding to the data from the database 108 (S110).

In addition, the sound implementation program 106a performs an operation of adjusting the sound pressure level and the pitch bend of the sound file in the order of the algorithm (S112).

By the operation of the sound implementation program 106a, the sound file is controlled as a sound in a situation closest to the data transmitted from the other sub-system 40, and is output as an audible sound through an external device such as a speaker or a headset.

The above description is merely illustrative of the technical idea of the present invention, and those skilled in the art to which the present invention pertains may make various modifications and changes without departing from the essential characteristics of the present invention. Therefore, the embodiments disclosed in the present invention are not intended to limit the technical idea of the present invention but to describe the present invention, and the scope of the technical idea of the present invention is not limited by these embodiments. The protection scope of the present invention should be interpreted by the following claims, and all technical ideas within the equivalent scope should be interpreted as being included in the scope of the present invention.

As described above, according to the present invention, the pilot using the simulator equipment provides a more realistic sound effect, thereby improving the performance of flight training.

Claims (8)

(a) preparing a sound generated from the gas into an acoustic file and storing the sound file in a database; (b) receiving sound source generation data from another sub-system; (c) calling a sound implementation program corresponding to the sound source generation data; (d) generating a sound output control signal according to the order of algorithms included in the sound implementation program; (e) calling a sound file corresponding to the control signal; And (f) adjusting the sound of the sound file with a sound pressure level and a pitch bend corresponding to the control signal; Flight simulation sound output method characterized in that it comprises a. The method of claim 1, The sound file is a flight simulation sound output method, characterized in that for storing the properties of the sound generation, including sound pressure level and pitch bend in advance in the Application Definition File (ADF). The method of claim 1, The database in the step (a), An engine acoustic database for storing including one or more sounds of an engine, a turbine, a propeller, a propeller wash or an ignitor; A communication sound database including one or more sounds from among VHF, UHF, and TACAN sounds; An alarm sound database including one or more sounds of Fire, Overheat, Stall, Stall2, and Overspeed beeps; An external acoustic database including one or more of a runway rumble, a touch down, a touch bump, an air friction sound, a GPU power unit, and a puffet sound; An internal acoustic database for storing and containing an Environment Control System (ECS) sound; A subsystem database for storing one or more sounds of a landing gear movement sound, a gear lock sound, a flap sound, and a speed brake sound; An environmental sound database for storing thunder sounds; And An ATIS acoustic database for storing the sound transmitted from the airport with respect to weather, wind direction and wind speed information around the airport; Flight simulation sound output method characterized in that it comprises a. The method of claim 1, When the sound source generation data in the step (b) is the data for generating the sound source of the engine, turbine, propeller, propeller wash, The algorithm in the step (d), by transmitting the transmitted rpm value to the interpollation function to adjust the pitch bend and sound pressure level corresponding to the data, characterized in that the flight simulation sound output method. The method of claim 1, When the sound source generation data in the step (b) is data for generating a touch down, touch bump, air friction sound source, respectively, The algorithm in the step (d), the step of adjusting the sound pressure level by applying a z-force transmitted to each landing gear in the touch down, the sound pressure by applying the ground velocity of the body in the touch bump Adjusting a level of the pitch bend in response to an air pressure difference inside / outside the gas in the air friction sound and adjusting a magnitude of the sound pressure level in response to the speed of the gas; Flight simulation sound output method. The method of claim 1, When the sound source generation data in step (b) is data for generating a speed brake sound source, The algorithm in the step (d), the flight simulation sound output method comprising the step of adjusting the sound pressure level corresponding to the blade (blade) angle of the speed brake. The method of claim 1, When the sound source generation data in the step (b) is data for generating a thunder sound (Thunder) sound source, The algorithm in the step (d), the thunder sound is output after a predetermined delay time after a predetermined flag after the flag (on) to confirm whether the data corresponding to the thunder sound Flight simulation sound output method comprising a. The method of claim 1, When the sound source generation data in step (b) is data for generating an ATIS (Automatic Terminal Information Service) sound source, The algorithm in the step (d) is divided into a "static" array for outputting only sound determined according to the ATIS output standard and a "dynamic" array for outputting a sound corresponding to the condition according to the changing condition. Flight simulation sound output method.

Images