KR101501136B1 - Cargo Hook Load manifesting system of Helicopter and Controlling Method for the Same - Google Patents

Abstract

The present invention relates to a cargo hook member having a plurality of load cells for hanging an external cargo on an outer body of a helicopter and detecting a load value of an external cargo on one side of the body and outputting the detected load value; A cargo hook control unit for controlling the function of the cargo hook member and amplifying a load value of the external cargo detected by an analog method from the load cell, correcting the load value, and outputting the corrected load value; A signal converter for converting an analog external load value input from the cargo hook controller into a digital signal and outputting the digital signal; And a mission computer for analyzing the digital external load value output from the signal converting unit and displaying the digital load on the multifunctional viewfinder (MFD) provided on the bulletin board of the helicopter, A hook load presenting system and a control method thereof.
The present invention as described above processes the weight information of the external cargo through the detection means provided in the cargo hook of the helicopter and displays it on the multi-function display device in real time, thereby simplifying the cargo information through the electronic detection system, Since the flight performance data of the helicopter can be displayed on the weather, the weight of the equipment can be easily reduced accordingly.

Description

Technical Field [0001] The present invention relates to a cargo hook load manifesting system for a helicopter,

The present invention relates to a cargo hook load visibility system for a helicopter and a control method thereof. In particular, the weight information of an external cargo is processed through detection means provided on a cargo hook of a helicopter and displayed on a multi- The present invention relates to a cargo hook load visibility system and a control method thereof for a helicopter.

Generally, a helicopter is a helicopter, which means a helicopter is an airplane with lift and propulsive force generated by turning a rotary wing, called a rotor blade, which generates a lift, and is capable of vertical takeoff and landing, To move forward, backward, and horizontally. In addition, the design of the rotor blade provided in the rotor blade aircraft described above can be applied to a variety of designs in which the blade directly influences vibration characteristics, dynamic stability, and handling qualities as well as aerodynamic characteristics such as flight performance, aerodynamic load and noise A comprehensive review of the field is required. In addition, the helicopter is equipped with a fly-by-wire flight control system to improve the ease of flight control. Various specifications of a helicopter equipped with the FBW system as described above are currently being developed. For example, KUH (Korea Utility Helicopter), the first model of the multipurpose helicopter in Korea, has been successfully developed in 2010 through joint research between Korea Aerospace Industries and Eurocopter. Based on the financial support of the Korean government, we have started to develop a helicopter FBW system in order to raise the level of source technology while preparing future helicopter development program. These helicopter FBW systems are fast, reliable, and in building programs that fit the typical helicopter development environment. The KUH helicopter can be used to calculate a control command of a Fly-By-Wire Flight Control System (LAFCS) or a Limited Authority Flight Control System (LAFCS) To improve the maturity of the dynamics model, kinematic modeling of the steering system is needed. At this time, the helicopter is provided with a cargo lifting device capable of mounting an external cargo at the lower end of the body.

Referring to FIG. 1, the conventional cargo handling apparatus of the conventional helicopter includes a cargo hook unit 70 for hanging external cargo on the outer body of the helicopter;

A loadmeter 71 provided in the cargo hook device 70 for detecting and outputting a load value of the external cargo suspended from the cargo hook device 70;

And a load indicator 72 which displays the load value of the external cargo detected by the load meter 71 and is provided separately from the instrument panel on the cockpit instrument panel of the helicopter.

Meanwhile, in the operation of the conventional cargo handling apparatus for a helicopter, the external cargo is hung on the cargo hook device 70, and the helicopter takes off. Then, the load meter 71 provided in the cargo hook device 70 detects the load value of the external cargo suspended from the cargo hook device 70 and transmits the detected load value to the load indicator 72. Therefore, in the helicopter design, the load indicator 72 provided separately from the instrument panel on the cockpit instrument panel of the helicopter in advance processes the load value of the external load inputted from the rodmeter 71 and displays it on the load indicator 72 Tell the pilot of the helicopter the load value of the external cargo that is currently hanging on the helicopter and make sure that it is running properly.

However, in the conventional cargo handling apparatus for a helicopter, when a helicopter is designed, a load simulator for displaying the load value of the external cargo transferred from the cargo hook device having the load metering function is installed on the cockpit dashboard of the helicopter separately from the instrument panel The weight of the equipment is considerably increased, and the space design of the cockpit is considerably deteriorated.

SUMMARY OF THE INVENTION Accordingly, the present invention has been made in order to solve the above-mentioned problems of the prior art, and it is an object of the present invention to provide a helicopter capable of easily handling cargo information through an electronic detection system, And it is an object of the present invention to provide a cargo hook load visibility system and a control method thereof for a helicopter which significantly reduces the weight of the cargo.

In order to detect the weight information of the external cargo, the present invention as described above requires that the external load value detected by the cargo hook is not required to be separately installed inside the helicopter, The present invention provides a cargo hook load visibility system and a control method thereof for a helicopter that maximizes the convenience of helicopter design.

According to an aspect of the present invention, there is provided a helicopter comprising: a cargo hook member having a load cell for hanging an external cargo on an external body of a helicopter and detecting a load value of an external cargo on one side of the body;

A cargo hook control unit for controlling the function of the cargo hook member and amplifying a load value of the external cargo detected by an analog method from the load cell, correcting the load value, and outputting the corrected load value;

A signal converter for converting an analog external load value input from the cargo hook controller into a digital signal and outputting the digital signal;

And a mission computer for analyzing the digital external load value output from the signal converting unit and displaying the digital load on the multifunctional viewfinder (MFD) provided on the bulletin board of the helicopter, Provides a hook load visibility system.

According to still another aspect of the present invention, there is provided a method of detecting a load value of an external cargo suspended from an external body of a helicopter through a plurality of load cells,

After the first step, the cargo hook control unit amplifies the load value of the external load detected in an analog manner from the load cell, corrects the load value, and outputs the corrected load value to the signal converting unit;

A third step of, after the second step, converting the analog external load value inputted from the cargo hook control unit into a digital signal and outputting the digital load signal to the mission computer;

After the third step, the mission computer analyzes the digital external load value output from the signal converting unit, and then displays it on the control unit (CDU) and the MFD provided on the board of the helicopter The present invention provides a control method of a cargo hook load visibility system of a helicopter including four steps.

According to the present invention, the weight information of the external cargo is processed through the detection means provided in the cargo hook of the helicopter and displayed on the multi-function display device in real time, so that the cargo information can be easily processed through the electronic detection system, It is possible to display the flight performance data of the helicopter on the multifunction visibility gauge so that the weight of the equipment can be easily reduced.

In order to detect the weight information of the external cargo, the present invention as described above requires that the external load value detected by the cargo hook is not required to be separately installed inside the helicopter, It is possible to significantly increase the utilization of the space generated due to the absence of a separate vision device in the helicopter cockpit, thereby maximizing the convenience of helicopter design.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is an explanatory view for explaining a conventional cargo handling apparatus for a helicopter. FIG.
2 is an explanatory view for explaining an example of a cargo hook load sighting system of a helicopter according to the present invention;
3 is an explanatory view for more specifically explaining the cargo hook control unit of the present invention.
4 is a flowchart of the present invention.

DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, preferred embodiments of a cargo hook load visibility system for a helicopter according to the present invention will be described with reference to the accompanying drawings.

However, the present invention is not limited to the embodiments of the cargo hook load sight system of the helicopter according to the present invention described here, but may be embodied in other forms. Rather, the embodiments disclosed herein are provided so that the disclosure can be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Like reference numerals designate like elements throughout the specification. It is to be understood that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. In the present specification, the singular form includes plural forms unless otherwise specified in the specification. The term " comprises " And / or "comprising" does not exclude the presence or addition of one or more other elements, steps, operations, and / or elements.

Example

FIG. 2 is an explanatory view schematically illustrating an embodiment of a cargo hook load visibility system of a helicopter according to the present invention, FIG. 3 is an explanatory diagram illustrating a cargo hook control unit of the present invention in more detail, 1 is a flowchart of the present invention.

Referring to FIG. 2, a cargo hook load visibility system for a helicopter according to an exemplary embodiment of the present invention includes a load cell (not shown) for hanging an external cargo on an external body of a helicopter and detecting a load value of external cargo on one side of the body 1; Fig.

A cargo hook control unit 3 for controlling the function of the cargo hook member 2 and amplifying the load value of the external cargo detected in analog fashion from the load cell 1 to correct the load value and outputting the corrected value;

A signal conversion unit 4 for converting the analog external load value inputted from the cargo hook control unit 3 into a digital signal and outputting the digital signal;

And a task for analyzing the digital external load value output from the signal converting unit 4 and then displaying the digital value on the control unit (CDU: 5) and the multifunctional display unit (MFD: 6) provided on the board of the helicopter And a computer (7).

The cargo hook member 2 is, for example, provided with an average load cell (strain gage) signal output of 0.25 to 0.275 mV / V at FS 8000 lbs. When the load signal (mV) of the cargo hook is input, the cargo hook control unit 3 can amplify the input load signal to a range (1V to 9V) that can be input to the signal conversion unit 4. [ Furthermore, since the load cell (strain gage) mounted on the cargo hook member 2 has different signal characteristics (output), it is necessary to carry out a calibration operation (by using a communication cable to connect the J3 connector (MV) of the standard load becomes the corresponding output after connecting the mission computer.

The signal converting unit 4 converts the 1V to 9V input from the cargo hook control unit 3 into digital signals of 0 lbs to 9000 lbs and transmits the converted digital signals to the mission computer MC. The mission computer 7 may display the data input from the signal conversion unit 4 in a CDU and a MFD and may have a read range of 0 to 50 lbs The software is applied to prevent sudden changes of the output signal and to be red when the operating load is over 6000 lbs. To be applied.

3, the cargo hook control unit 3 includes an amplifier 8 for amplifying a detection signal of the load cell 1 to a predetermined level, and an amplifier 8 for amplifying the signal output from the amplifier 8, An A / D converter 10 for converting a signal output from the low-pass filter unit 9 into a digital signal and outputting the digital signal; (Not shown) via a communication port 11 (for example, an RS-232 port), and outputting the signal after outputting the signal; And a D / A converter 14 for converting the digital signal output from the MPU 12 into an analog signal and transmitting the digital signal to the signal converting unit 4 through the output port 13.

In another embodiment of the present invention, the mission computer 7 is provided at one side of the body and converts the load value of the external cargo into a wireless Internet signal, and transmits the wireless Internet signal to the smartphone 16, And a wireless Internet implementation unit (17) for displaying the wireless Internet in real time.

Next, a control method of the system of the present invention having the above-described configuration will be described.

The method includes a first step (S2) of detecting a load value of an external cargo suspended from an external body of a helicopter through a plurality of load cells in an initial state (S1) as shown in FIG. 4;

A second step S3 of amplifying the load value of the external load detected by the cargo hook control unit in an analog manner from the load cell after the first step S2 and correcting the load value and outputting the corrected load value to the signal converting unit;

A third step S4 of converting the analog external load value inputted from the cargo hook control unit into a digital signal and outputting the analog external load value to the mission computer after the second step S3;

After the third step S4, the mission computer analyzes the digital external load value output from the signal converting unit, and then analyzes the digital load value of the digital output from the signal conversion unit on the control unit CDU and the MFD provided on the board of the helicopter And a fourth step (S5) for displaying the image.

In the fourth step S5, the mission computer converts the load value of the external cargo into the wireless Internet signal through the wireless Internet implementing unit, and transmits the wireless Internet signal to the designated smart phone through the wireless Internet network on the ground. .

In other words, in order to use the helicopter cargo hook load visibility system 18 of the present invention, the external cargo to be transferred to the cargo hook member 2 located at the lower end of the outer body of the helicopter is firmly held and the helicopter is taken off. Then, a plurality of load cells 1 provided on the cargo hook member 2 detect the load value of the external cargo suspended in the cargo hook member 2 as an analog value, and input the detected load value to the cargo hook control unit 3. The cargo hook control unit 3 amplifies the load value of the external load inputted in analog form from the load cell 1, corrects the load value, and outputs the corrected load value to the signal conversion unit 4. The signal conversion unit 4 converts the analog external load value inputted from the cargo hook control unit 3 into a digital signal and outputs the digital signal to the mission computer 7. Then, the mission computer 7 analyzes the digital external load value output from the signal converting unit 4, analyzes the digital load value of the digital output from the signal converting unit 4, The external load value detected by the cargo hook is detected by the mission computer using the flight performance calculation data as described above without the need to separately mount the viewfinder inside the helicopter in order to detect the weight information of the external cargo. It is manifested in the weather of the vision. Therefore, according to the present invention as described above, it is possible to significantly increase the utilization of the space generated due to the absence of a separate visualizer in the helicopter cockpit, thereby maximizing the convenience of helicopter design. In addition, the present invention as described above processes the weight information of the external cargo through the detection means provided on the cargo hook of the helicopter and displays the weight information in real time on the multi-function display device, thereby easily processing the cargo information through the electronic detection system The multifunctional vision system can display the flight performance data of the helicopter on the meteorological instrument, thereby easily reducing the weight of the apparatus.

According to another embodiment of the present invention, the mission computer 7 converts a load value of an external cargo into a wireless Internet signal through the wireless Internet implementing unit 17, And transmitted to the designated smartphone 16 in real time.

1: load cell 2: cargo hook member
3: cargo hook control unit 4: signal conversion unit
5: Controlled vision device 6: Multifunctional vision device
7: Mission Computer 8: Amplifier
9: Low-pass filter unit 10: A / D converter
11: Communication port 12: MPU
13: Output port 14: D / A converter
15: wireless Internet network 16: smart phone
17: Wireless Internet Implementation Part 18: Cargo Hook Load Imaging System

Claims (5)

A cargo hook member having a load cell capable of hanging an external cargo on the outer body of the helicopter and detecting a load value of the external cargo on one side of the body and outputting the detected load value;
A cargo hook control unit for controlling the function of the cargo hook member and amplifying a load value of the external cargo detected by an analog method from the load cell, correcting the load value, and outputting the corrected load value;
A signal converter for converting an analog external load value input from the cargo hook controller into a digital signal and outputting the digital signal;
And a task computer for analyzing the digital external load value output from the signal converting unit and displaying the digital load on the multi-function monitor (MFD) and the CDU provided on the board of the helicopter;
Wherein the cargo hook member carries out a calibration operation in order to approximate and output a true value because the signal characteristics (outputs) of the load cell (strain gauge) are different from each other. delete The method according to claim 1,
In order to improve the readability of the output signal, the mission computer displays 0 to 50 lbs of the input data in the signal conversion unit on the CDU and the MFD, lbs, and a filter is applied to prevent a sudden change of an output signal, and a red color is displayed when an operation load (6000 lbs) is exceeded. A first step of detecting a load value of the external cargo suspended from the outer body of the helicopter by the cargo hook member through a plurality of load cells;
After the first step, the cargo hook control unit amplifies the load value of the external load detected in an analog manner from the load cell, corrects the load value, and outputs the corrected load value to the signal converting unit;
A third step of, after the second step, converting the analog external load value inputted from the cargo hook control unit into a digital signal and outputting the digital load signal to the mission computer;
After the third step, the mission computer analyzes the digital external load value output from the signal converting unit, and then displays it on the control unit (CDU) and the MFD provided on the board of the helicopter 4 steps;
In the fourth step, the mission computer further includes a wireless Internet view conversion step of converting the load value of the external cargo into a wireless Internet signal through the wireless Internet implementation unit, and transmitting the wireless Internet signal to the designated smart phone through the wireless Internet network Wherein the helicopter is mounted on a vehicle. delete

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