KR20130012727A - Helicopter performance planning card real-time automatic calculation system and computer-readable recording medium saving helicopter performance calculation simulation program based on pc - Google Patents

Abstract

PURPOSE: A real time automatic generation system for a helicopter performance schedule table and a computer readable recording medium storing a PC based helicopter performance calculation simulation program are provided to receive only minimum necessary inputs from a pilot, thereby reducing a work load of the pilot and a required time. CONSTITUTION: An input unit(100) receives a parameter necessary for calculating a helicopter performance schedule table. A processing unit(200) generates a performance schedule table in real time by using the parameter. An output unit(300) outputs the performance schedule table. The parameter is classified into a common input parameter and an individual input parameter. The common input parameter includes basic operating weight, FUEL/Position and external salvage freight weight. The individual input parameter is inputted from a helicopter pilot. [Reference numerals] (100) Input unit; (200) Processing unit; (300) Output unit

Description

HELICOPTER PERFORMANCE PLANNING CARD REAL-TIME AUTOMATIC CALCULATION SYSTEM AND COMPUTER-READABLE RECORDING MEDIUM SAVING HELICOPTER PERFORMANCE CALCULATION SIMULATION PROGRAM BASED ON PC}

The present invention relates to a system for calculating the flight capability, cruise flight capability, weight and balance that can provide the helicopter performance information in real time based on the helicopter sensor and mission plan input information, and more specifically, the flight capability calculation The system uses the current available power, required power, and IGE / OGE (abbreviation for In Ground Effect, if no ground effect is available) where the helicopter needs to refer to its flight in the air. Provides weight and GO-NO / GO torque, and the cruising capability calculation system provides the maximum overspeed, maximum flight / speed, maximum flight time / speed, and horizontal flight maximum that must be provided for the helicopter's cruise. Provides minimum speed and ascent rate information, and the weight and parallel calculation system provides the helicopter's total weight and center of gravity information.

Conventionally, before the mission, the pilot calculates the performance information according to the shape information of the helicopter with reference to a total of 36 performance charts (about 140 pages) as shown in Fig. 1 (a performance table at the start, a performance table at the cruise, Prepare the performance plan card (PPC) of the performance table, the high drag performance table, the weight and the equilibrium performance table on arrival, and refer to the performance plan table created during the mission to fly within the performance range of the helicopter. Was performed.

At this time, an error due to the helicopter state information predicted when preparing the performance plan table using the conventional manual, an error due to margin application, and an error due to readability when acquiring data from the performance chart occurred.

In addition, when an emergency mission or an in-flight mission change, the performance plan is rewritten with reference to the in-flight performance chart, thereby increasing the burden on the pilot in flight.

Accordingly, the technical problem to be achieved by the present invention is to calculate the performance of a helicopter, which is conventionally made by manual, based on sensor information mounted on a helicopter and information input by an operator or a data loading device, thereby automating the calculation of each performance information under a current operating condition. The pilot's performance information that the helicopter can provide is the pilot's multi-function display (MFD: Abbreviation for Multi Function Display) and equipment that displays various information of the aircraft and control display (CDU: Control & Display Unit. It is to provide a system that can be referred to in real time through the equipment to input and display ().

Another technical problem to be achieved by the present invention is to minimize the work load of the pilot by the task computer automatically performs the performance calculation, and to provide accurate helicopter performance information in the current operating conditions using the real-time sensor information It is to provide a system that can maximize the mission capability by making the most of the calculated helicopter operating range.

As a means of the present invention for achieving the above object, an input unit for receiving a parameter required for calculating the helicopter performance schedule; A processor configured to generate a performance plan table in real time using parameter values received through the input unit; And an output unit for outputting the performance plan table generated through the processing unit. Helicopter performance planner comprising a real-time automated generation system comprising a.

In addition, the parameter received through the input unit provides a helicopter performance plan real-time automated generation system, characterized in that divided into common input parameters and individual input parameters.

In addition, the common input parameters, the OPR GWT (basic operating weight), FUEL / Position (total fuel amount and fuel amount per fuel tank) and EXT LOAD (external salvage cargo weight), characterized in that the real-time automated generation system To provide.

In addition, in the common input parameter, the OPR GWT (Basic Operating Weight) value is read from a value stored in advance in the mission computer, and the FUEL / Position (total fuel amount and fuel amount for each fuel tank) and EXT Load (external lifting) Cargo weight) values are received from sensors installed in the helicopter.

In addition, the individual input parameters are INT LOAD (internal cargo load), PSGR (passenger weight) and DRAG FACTOR (descent coefficient) when the flight conditions are in-flight and cruise flight, and the flight conditions are gravity and equilibrium, Helicopter performance planner real-time automated generation system, including INT LOAD / Position (internal cargo weight and loading position) and PSGR / Position (rider weight and boarding position).

In addition, the individual input parameter provides a helicopter performance plan real-time automated generation system, characterized in that the input from the helicopter pilot.

The output unit provides a helicopter performance planner real-time automated generation system, characterized in that to provide the performance information of the helicopter through the helicopter control and display device.

In addition, the performance information of the helicopter output through the multi-function display device, PR (required power) and GO-NO / GO power for each of the PA (available power) and IGE / OGE when the flight conditions are in flight, If flight conditions are cruising, include VNE (Super Stop Speed), RNG (Maximum Flight Distance) and END (Maximum Flight Time), and CG (Weight Center) if flight conditions are in equilibrium with weight. Helicopter performance plan provides a real-time automated generation system.

Provided is a computer-readable recording medium storing a PC-based helicopter performance calculation simulation program including respective components of the helicopter performance scheduler real-time automated generation system according to any one of claims 1 to 8.

In addition, the parameter value input to the program provides a computer-readable recording medium storing a PC-based helicopter performance calculation simulation program, characterized in that consisting of a spreadsheet file.

According to the present invention, by receiving only the minimum necessary information from the aircraft pilot when preparing the performance plan, it is possible to reduce the burden on the pilot work, it is possible to reduce the time required in the process of preparing the performance plan.

In addition, according to the present invention, by automating the method of manually preparing the existing performance schedule, it is possible to reduce the workload of the pilot, and to reduce the calculation error generated when the performance schedule.

In addition, according to the present invention, by receiving and calculating the sensor information necessary for the preparation of the performance plan in real time, it is possible to increase the accuracy and reliability of the performance information of the performance plan.

1 is a view briefly showing a performance planner drawing process of a conventional helicopter,
2 is a view schematically showing a conceptual diagram of a helicopter performance planner real-time automated generation system according to an embodiment of the present invention,
3 is a diagram illustrating an example of defining an input / output parameter according to a flight condition of a helicopter according to an embodiment of the present invention.
4 is a diagram illustrating a result of classifying and integrating all parameters corresponding to three flight conditions according to an embodiment of the present invention.
5 is a view showing an interface relationship with other equipment of the helicopter performance schedule real-time automated generation system according to an embodiment of the present invention,
6 is a functional sharing design diagram for the input / output of the helicopter performance schedule real-time automated generation system according to an embodiment of the present invention,
7 is a view showing a CDU among the output of the helicopter performance planner real-time automated generation system according to an embodiment of the present invention,
8 is a view showing a multi-function display (MFD) of the output of the helicopter performance planner real-time automated generation system according to an embodiment of the present invention,
FIG. 9 is a diagram illustrating a helicopter performance simulation simulation program operating based on a personal computer (PC) developed to verify a performance calculation algorithm and a performance database according to an embodiment of the present invention.

The following detailed description of the invention refers to the accompanying drawings, which illustrate, by way of illustration, specific embodiments in which the invention may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the invention. It should be understood that the various embodiments of the present invention are different, but need not be mutually exclusive. For example, certain shapes, structures, and characteristics described herein may be embodied in other embodiments without departing from the spirit and scope of the invention in connection with one embodiment. In addition, it is to be understood that the location or arrangement of individual components within each disclosed embodiment may be changed without departing from the spirit and scope of the invention. The following detailed description is, therefore, not to be taken in a limiting sense, and is defined only by the appended claims, along with the full scope of the present invention, and all equivalents to which the claims are entitled. In the drawings, like reference numerals refer to the same or similar functions throughout the several views.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings so that those skilled in the art can easily implement the present invention.

2 is a diagram schematically illustrating a conceptual diagram of a helicopter performance planner real-time automated generation system according to an exemplary embodiment of the present invention.

As shown in FIG. 2, the helicopter performance schedule real-time automated generation system includes an input unit 100 that receives parameters required to generate a performance schedule table, and a processing unit that generates a performance schedule table using parameter values received through the input unit ( 200) and an output unit 300 for outputting the performance plan table generated by the processing unit.

The data input from the input unit 100 is read from values stored in advance in a mission computer, or it can be read at various positions of the helicopter (GPS / INS (Global Positioning System / Intertia Navigation System)). Device that receives information about the device, FADEC (abbreviation for Full Authority Digital Electronics Control) and a function that can be adjusted to include aircraft engine performance data), and ADC (abbreviation for Air Data Computer). Receiving device), FQMS (abbreviation for Fuel Quantity Measurement System), or a sensor attached to the device, or a pilot of an aircraft.

Using the parameter value received from the input unit 100, the processing unit 200 generates a performance plan table, and outputs a combination of the parameters received from the input unit 100 by databaseting helicopter performance information for generating the performance plan table. The performance plan table is output through the unit 300.

The output unit 300 provides the performance plan table generated from the processing unit through a multi function display (MFD) or a control display unit (CDU).

3 is a diagram illustrating an example of defining input / output parameters according to a flight condition of a helicopter according to an embodiment of the present invention.

In the present invention, in order to minimize and classify and integrate the number of parameters received through the input unit 100, five types of existing helicopter performance calculation information are known, that is, a departure performance table and a cruise performance. The performance plan of the table, Arrival performance table, High Drag performance table, and Weight & Balance performance table is functionally developed to include three flight conditions: in-flight, cruise and weight and balance. Classified as

As shown in FIG. 3, the cruise flight of the three flight conditions is taken as an example, and the input / output parameters corresponding to the cruise flight conditions are defined and listed.

In other words, the input parameters defined for cruise flight conditions are ALT (abbreviation of Altitude) and OAT (Outside Air Temperature) received from ADC (the abbreviation of Air Data Computer). It includes the abbreviated external temperature data, the preset OPR GWT (Operational Weight) and the fuel quantity received from the FUEL (Fuel Quantity Measurement System) sensor, and EXT LOAD (abbreviation for Internal Load). External salvage weight received from the meter, INT LOAD (abbreviation of Internal Load, the weight of internal cargo input by aircraft pilots as a flight plan), PSGR (abbreviation of Passenger, weight of internal passengers) and DRAG It includes gross weight including the FACTOR (the drag coefficient generated by the equipment and cargo maneuver mounted outside the helicopter).

Output parameters also include VNE (Velocity Never Exceed), MAX SPD (Max Level Speed), MIN SPD (Minimum Speed). Abbreviation for Max Endurance Speed), END (short for Max Endurance Time), VRNG (short for Max Range Speed) and RNG (abbreviation for Max Range). Maximum flight distance).

The input parameters defined in this way together with the parameters corresponding to the other flight conditions, that is, the input parameters corresponding to the three flight conditions are classified and integrated to minimize the input parameters.

4 is a diagram illustrating a result of classifying and integrating all parameters corresponding to three flight conditions according to an exemplary embodiment of the present invention.

As shown in FIG. 4, when divided into three flight conditions, that is, in-flight flight, cruise flight, and weight and equilibrium, and classifying and integrating required inputs for each flight condition, the input unit 100 receives input through the input unit 100. The parameters are classified into common input parameters and individual input parameters, where the common input parameters include OPR GWT (Basic Operating Weight), FUEL (Total Fuel Quantity), and EXT LOAD (External Salvage Weight). INT LOAD (internal cargo weight), PSGR (passenger weight) and DRAG FACTOR for in-flight flight conditions; INT LOAD / Position and PSGR for gravity and equilibrium flight conditions. / Position (passenger weight and boarding position).

Such classification of parameters is achieved by classifying input and output information by flight conditions, defining parameters to be mutually exclusive and totaling elements, classifying defined parameters by flight conditions, and integrating duplicated parameters. You lose.

Therefore, the helicopter performance plan real-time automated generation system does not need to receive or input all the parameters corresponding to each flight condition for each flight condition. Breaking away from the planning table, you can create a performance plan by entering only the individual input parameters OPR GWT (basic operating weight), FUEL / Position (total fuel volume and fuel for each fuel tank) and EXT LOAD (external salvage weight). It became possible.

In addition, the OPR GWT (Basic Operating Weight), FUEL / Position (total fuel volume and fuel volume for each fuel tank) and EXT LOAD (External salvage weight) parameters entered by the pilots of the aircraft are required. Weight), PSGR (passenger weight), DRAG FACTOR, INT LOAD / Position (internal cargo weight and loading position), and PSGR / Position (passenger weight and boarding position) are either already set or mission storage devices within the helicopter ( As it is received in real time from the DTS (Data Transfer Systyem), the performance plan table output through the output unit 300 is a value calculated in real time, thereby increasing the accuracy and reliability of the performance information of the helicopter.

5 is a diagram illustrating an interface relationship with other equipment of a helicopter performance planner real-time automated generation system according to an exemplary embodiment of the present invention.

As shown in FIG. 5, the input through the input unit 100 is an input of INT LOAD (internal load weight), PSGR (passenger weight) and DRAG FACTOR (descent coefficient) from the helicopter pilot through the control display device, or is controlled. It is possible to input the preset OPR GWT (Basic Operating Weight) through the display device, to receive EXT LOAD (External salvage weight) from various equipment (shown as Miscellaneous) sensor, or to calculate the total fuel quantity and each from FQMS (Fuel Quantity Measuring Device). Receives the amount of fuel for each tank, or is input from the air data computer (ADC) through altitude and outside air temperature (OAT).

In addition, the output through the output unit 300 outputs a performance plan table processing the data input through the input unit 100 through the control and multi-function display.

In this case, an example of the output through the control display device is shown in FIG. 7, and an example of the output through the multi-function display device is shown in FIG. 8.

6 is a functional sharing design diagram for the input / output of the helicopter performance schedule real-time automated generation system according to an embodiment of the present invention.

As shown in FIG. 6, the preset OPR GWT (Basic Operating Weight), the helicopter pilot inputted by the control display device, the PSGR (Passenger Weight), INT LOAD (Internal Cargo Weight), DRAG FACTOR (Deflection Coefficient) and the helicopter The EXT LOAD received from the device sensor will be used to output a performance plan based on the current helicopter flight conditions.

7 is a view showing a control and display device among the input and output unit of the helicopter performance schedule real-time automation generation system according to an embodiment of the present invention, Figure 8 is a helicopter performance schedule real-time automation generation system according to an embodiment of the present invention Is a diagram showing a multi-function display unit among the output units of the?

As shown in FIG. 8, the performance plan table output to the multi-function display is a CONFIGURATION (helicopter shape) part indicating an input value through the input unit, and a performance plan table indicating a flight condition when the flight condition is in place. A performance plan that shows when the condition is cruising. The CRUISE section, the MAX GWT section that shows the maximum usable weight of the aircraft, and the S-ENG (Single Engine) showing the performance of the aircraft when a single engine is operated. ) And the Center of Gravity (CG), which represents the aircraft's equilibrium.

In detail, the main output information output to the multi-function display device, the output information when the flight conditions are in place flight is the current power availability (PA :) in the HOVER (flying in place), the ground effect ( Includes information about IGE: In Ground Effect and Out of Ground Effect (OGE), and includes Power Required (PR) and GO-NO / GO Power for each. .

In addition, the output information when the flight condition is a cruise flight is the Velocity Never Exceed (VNE), Maximum Range and Speed (Maximum Range Speed), maximum flight in the CRUISE (cruising flight) part. It includes time (Maxumum Enurance) and speed (Maximum Endurance Speed).

In addition, the output information indicated when the flight condition is in balance with the weight includes the center of gravity information.

In addition, the performance information output when the flight conditions are in-flight and cruising flight includes both information for the case of a single engine (OEI: One Engine Operative) and the case of a dual engine (AEO: All Engine Operative) do.

Embodiments according to the present invention described above may be implemented in the form of program instructions that may be executed by various computer components, and may be recorded in a computer-readable recording medium. The computer-readable recording medium may include program commands, data files, data structures, and the like, alone or in combination.

FIG. 9 is a diagram illustrating a helicopter performance simulation simulation program operating based on a personal computer (PC) developed to verify a performance calculation algorithm and a performance database according to an embodiment of the present invention.

As shown in FIG. 9, the performance calculation simulation program operated on a personal computer (PC) is configured by using a keyboard or a mouse, such as engine shape, temperature, altitude, speed, fuel weight, total fuel amount and fuel tank position, external salvage weight and It includes simulation functions for HOVER information, CRUISE information, weight and equilibrium information, and drag coefficient information by inputting shape, internal cargo loading and loading location, passenger weight and boarding position.

In addition, the PC-based helicopter performance calculation simulation program is implemented to upload the helicopter performance database in the form of a spreadsheet program (for example, an Excel program developed by Microsoft), so that when the performance database is updated, It is a PC-based performance calculation simulator program that includes the ability to upload spreadsheet files by modifying only spreadsheet files without modifying the simulator program.

The program instructions recorded on the computer-readable recording medium may be those specially designed and configured for the present invention or may be those known and used by those skilled in the computer software arts. Examples of computer readable recording media include magnetic media such as hard disks, floppy disks, and magnetic tape, optical recording media such as CD-ROMs, DVDs, and magneto-optical media such as floptical disks. optical media) and hardware devices specifically configured to store and execute program instructions, such as ROM, RAM, flash memory, and the like. Examples of program instructions include not only machine code generated by a compiler, but also high-level language code that can be executed by a computer using an interpreter or the like. The hardware device may be configured to operate as one or more software modules to perform the process according to the invention, and vice versa.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, Those skilled in the art will appreciate that various modifications and changes may be made thereto without departing from the scope of the present invention.

Therefore, the matters of the present invention should not be limited to the embodiments described above, and all of the equivalents or equivalents of the claims, as well as the claims described below, fall within the scope of the spirit of the present invention. I will say.

100 input unit 200 processing unit
300: output unit

Claims (10)

An input unit for receiving a parameter for calculating a helicopter performance plan table;
A processor configured to generate a performance plan table in real time using parameter values received through the input unit; And
An output unit for outputting the performance plan table generated by the processing unit;
Helicopter performance schedule real-time automated generation system comprising a.
The method of claim 1,
Helicopter performance plan real-time automated generation system, characterized in that the parameters received through the input unit is classified into common input parameters and individual input parameters.
The method of claim 2,
Wherein said common input parameters include OPR GWT (Basic Operating Weight), FUEL / Position (Total Fuel Amount and Fuel Amount per Fuel Tank) and EXT LOAD (External Salvage Weight).
The method of claim 3, wherein
In the common input parameter, the OPR GWT (Basic Operating Weight) value is read from a preset value stored in the mission computer, the FUEL / Position value and the EXT Load value Helicopter performance plan real-time automated generation system, characterized in that the value is received from the sensor installed in the helicopter.
The method of claim 2,
The individual input parameters are INT LOAD (internal cargo load), PSGR (passenger weight) and DRAG FACTOR (descent coefficient) for flight conditions in-flight and cruise, and INT LOAD if flight conditions are gravity and equilibrium. Helicopter performance schedule real-time automated generation system, including / Position (internal cargo weight and loading position) and PSGR / Position (rider weight and boarding position).
The method of claim 5, wherein
Helicopter performance plan real-time automated generation system, characterized in that the individual input parameters are input from the helicopter pilot.
The method of claim 1,
The output unit provides a helicopter performance plan, real-time automated generation system, characterized in that to provide the performance information of the helicopter through the helicopter control and display device.
The method of claim 7, wherein
Performance information of the helicopter output through the multi-function display,
Includes PR (required power) and GO-NO / GO power for PA (available power) and IGE / OGE, respectively, if the flight condition is in-flight; Helicopter Performance Plan real-time automated generation system, including (maximum flight distance) and END (maximum flight time), including CG (Weight Center) when the flight conditions are in equilibrium with weight.
A computer-readable recording medium storing a PC-based helicopter performance calculation simulation program including respective components of the helicopter performance schedule according to any one of claims 1 to 8.
The method of claim 9,
The parameter value input to the program is a computer-readable recording medium storing a PC-based helicopter performance calculation simulation program, characterized in that consisting of a spreadsheet file.

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