KR20160043291A - Onboard flight test optimized aircraft character and object of testing flight - Google Patents

Abstract

The present invention relates to an on-board measurement method using an on-board measurement system optimized for properties of an aircraft and a test purpose and, more specifically, to an on-board measurement method using an on-board measurement system optimized for properties of an aircraft and a test purpose characterized by including: a first step (S100) of designing the on-board measurement system in accordance with measurement requirements to design and analyze the aircraft defined by conceptual design and preliminary design of an aircraft development process and to verify functions of each system; a second step (S200) of selecting measurement sensors in accordance with a parameter desired to measure by critical design of the aircraft development process and properties of the parameter, mounting the on-board measurement system designed in the first step (S100), and determining the normal operation of the measurement sensors; and a third step (S300) of acquiring flight data when the normal operation of the measurement sensors are verified through the second step (S200) by performing a test & evaluation of the aircraft manufactured in a trial manufacture step of the aircraft development process by using the on-board measurement system. The purpose of the present invention is to provide the on-board measurement method using the on-board measurement system optimized for the properties of the aircraft and the test purpose capable of conveniently acquiring various information about the aircraft by using the on-board measurement system optimized for the properties of the aircraft and the test purpose.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an onboard flight measurement system,

More particularly, the present invention relates to a flight measurement system that is optimized for aircraft characteristics and flight test purposes, and more particularly, to an aircraft flight measurement system, Aircraft characteristics that can easily acquire various information of aircraft by using onboard measurement system optimized for aircraft characteristics and flight test purpose by classifying development process of onboard measurement system into design, And an onboard measurement method using an onboard measurement system optimized for flight test purposes.

The development of aircraft (rotorcraft and fixed-wing aircraft) is stipulated by the conceptual design process of customers' requirements, technical specifications as specifications, and business requirements as plans.

At this time, since the outer shape and the inner layout are determined in the basic design process, a concrete design shape is determined. After the basic design process, the design drawing and the material requirements are determined in the detailed design process, and then the prototyping process is performed. In this way, a planned development aircraft shape is created. Finally, a test evaluation will be conducted to verify that the aircraft meets specifications.

Technology applied through the design and analysis of the development aircraft can be verified for its operability only after these test evaluation processes.

For this reason, during the aircraft development process, the test evaluation process, including the flight test, accounts for about half of the total development period, accounting for about 25% of the total development cost.

Flight tests require a lot of cost, resources and time in terms of their properties and require special attention to safety. Acquisition of valid flight data and accurate analysis of the acquired flight data will determine the safety and success of the flight test.

In other words, a reliable and efficient flight measurement system is the driving force behind flying tests.

This flight measurement system is a system for acquiring, storing, transmitting, processing and analyzing flight data by accurately measuring the flight status of the flight test aircraft. It is equipped with an onboard measurement system that measures flight data on a test aircraft, And a ground measurement system that receives and processes the flight data.

The onboard measurement method using the onboard measurement system optimized for the characteristics of the aircraft of the present invention and the flight test purpose is to measure the flight of various aircraft such as KT-IT, KC-100, T / FA-50, KUH and police helicopter Based on our system development experience,

Based on the characteristics of the aircraft and the flight development schedule information according to the purpose of the flight test, the development process of the onboard measurement system among the flight measurement systems of the aircraft is classified into design, production and operation, and by linking with and applying each process of the aircraft development schedule, And an on-board measurement method using an on-board measurement system optimized for the purpose of flight test, which is capable of easily acquiring various flight data of an aircraft using an on-board measurement system optimized for flight test purposes.

Korean Patent No. 10-1056263 ("Aircraft Embedded System for Flight Simulation and Testing ", hereinafter referred to as Prior Art 1) provides database access software (S / W) for managing ICD data in STEM for operating AHB , Flight simulations that can quickly insert, update, modify, and delete simulation / monitoring signals through database access software even if the Signal Interlock Specification (ICD) changes occur when the STE is developing or updating the project An aircraft embedded system for testing, a database access method thereof, and a recording medium storing a program by the method.

Korean Registered Patent No. 10-1056263 (registered on August 4, 2011)

SUMMARY OF THE INVENTION The present invention has been made in order to solve the problems of the conventional art as described above, and it is an object of the present invention to provide a flight measurement system of an aircraft based on aircraft characteristics and flight development schedule information By classifying the process as design, production and operation and linking it with the development schedule of the aircraft, the characteristics of the aircraft and the characteristics of the flight that can easily acquire various information of the aircraft by using the onboard measurement system optimized for the purpose of the flight test And to provide a mounting measurement method using the on-board measurement system optimized for the on-board measurement system.

The onboard measurement method using the onboard measurement system optimized for the characteristics of the aircraft and the flight test according to the embodiment of the present invention can be applied to the development aircraft defined by the conceptual design and the preliminary design of the aircraft development process (S100) of performing onboard measurement system design according to the designing and analyzing of the functions of each system and the measurement need for verifying the functions of the respective systems, the parameters and parameters to be measured by the detailed design of the aircraft development process A second step S200 of determining whether the measurement sensors are normally operated or not by mounting the mounting measurement system designed in the first step S100 and the second step S200 , When the normal operation status of the measurement sensors is confirmed, it is possible to use the built-in measurement system to check the state of the development aircraft manufactured in the manufacture of the aircraft development process And a third step (S300) of performing flight evaluation by performing a test & evaluation (Test & Evaluation).

In this case, the first step S100 may include a first step (S101) of selecting a corresponding flight test item among the predetermined flight test review fields according to the measurement request of the development aircraft, (Step S102) for selecting a development flight for each flight test item selected in step S101), a 1-3 step (step S103) for setting a measurement requirement for each flight test item selected in the step 1-1, (Step S104) to generate measurement parameters for each development aircraft selected in step 1-2 (S102), measurement sensors and measurement instruments for the measurement parameters generated in step 1-4 (step S104) (Step S106) of setting the mounting positions of the measuring sensor and the measuring instrument set in the first to fifth steps (S105) and (1-5) And the on-board measurement system is designed using steps (S101) to (1-6) (S106).

In the second step S200, the on-board measurement system designed in the first step S100 is installed on the development aircraft, and whether or not the measurement sensor and the measurement equipment mounted on the development aircraft through the on- , The validity of the flight data from the measurement sensor and the measurement instrument, and whether or not the flight data is communicated with the ground measurement system, and finalize the measurement system installed on the development aircraft.

In addition, the third step (S300) performs a test evaluation of the development aircraft through the onboard measurement system mounted on the development aircraft, performs the validity check by measuring the flight test data, defines the failure investigation and measurement shape, And the system is operated.

According to another embodiment of the present invention, there is provided a computer-readable recording medium storing a program for implementing an on-board measurement method using an on-board measurement system optimized for aircraft characteristics and flight test purposes .

According to another embodiment of the present invention, there is provided a computer program produced by a command for implementing an on-board measurement method using an on-board measurement system optimized for an aircraft characteristic and a flight test purpose.

The aircraft characteristics according to the present invention and the on-board measurement method using the on-board measurement system optimized for the purpose of the flight test according to the present invention, based on the characteristics of the aircraft and the flight development schedule information according to the purpose of the flight test, By classifying the measurement system development process as design, production, and operation and linking it with the flight development schedule process, it is possible to acquire various information of the aircraft easily by using the onboard measurement system optimized for the characteristics of the aircraft and the flight test purpose .

That is, since the conventional on-board measurement system is reviewed and applied at the final stage of the development of the aircraft, there is a disadvantage that additional schedule and cost are required for building the on-board measurement system,

The onboard measurement method using the onboard measurement system optimized for the characteristics of the aircraft of the present invention and the purpose of the flight test classifies the onboard measurement system development process itself into the design, production and operation, and performs the step schedule and application technology in connection with the aircraft development process It is possible to provide an on-board measurement system optimized for the characteristics of the aircraft and the purpose of the flight test, and at the same time, it is possible to effectively shorten the development schedule and development cost of the aircraft.

FIG. 1 is a flowchart illustrating an on-board measurement method using an on-board measurement system optimized for flight characteristics and aircraft characteristics according to an exemplary embodiment of the present invention.
FIG. 2 is a flowchart illustrating a first step (S100) of an on-board measurement method using an on-board measurement system optimized for flight characteristics and aircraft characteristics according to an exemplary embodiment of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described in detail with reference to the accompanying drawings. The following drawings are provided by way of example so that those skilled in the art can fully understand the spirit of the present invention. Therefore, the present invention is not limited to the following drawings, but may be embodied in other forms. In addition, like reference numerals designate like elements throughout the specification.

In this case, unless otherwise defined, technical terms and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. In the following description and the accompanying drawings, A description of known functions and configurations that may unnecessarily obscure the description of the present invention will be omitted.

In addition, a system refers to a collection of components, including devices, mechanisms, and means that are organized and regularly interact to perform the required function.

The onboard measurement method using the onboard measurement system optimized for the characteristics of the aircraft of the present invention and the purpose of the flight test is designed to develop the onboard measurement system among the flight measurement systems of the aircraft based on the aircraft characteristics and the flight development schedule information according to the purpose of flight test , Production and operation, and linking with the aircraft development schedule process, various information of the aircraft can be easily acquired by using the onboard measurement system optimized for the characteristics of the aircraft and the flight test purpose.

That is, the aircraft characteristics of the present invention and the on-board measurement method using the on-board measurement system optimized for the purpose of the flight test are optimized based on the development schedule of the aircraft by dividing the development process of the onboard measurement system into the design, To effectively shorten aircraft development schedules and development costs.

FIG. 1 is a flowchart showing a loading measurement method using an on-board measurement system optimized for flight characteristics and aircraft characteristics of the present invention. Referring to FIG. 1, a detailed description will be made of a method of mounting measurement using an on-board measurement system optimized for flight characteristics and flight characteristics of the present invention.

The onboard measurement method using the onboard measurement system optimized for the characteristics of the airplane of the present invention and the purpose of the flight test is about the development process of the onboard measurement system applied to the development aircraft (on the flywheel and fixed wing aircraft) It is possible to provide an on-board measurement system that is optimized.

As shown in FIG. 1, the first step S100 of designing the on-board measurement system, the second step S200 of mounting the on-board measurement system, and the third step S300 of onboard measurement system operation.

To learn more about each step,

The first step S100 is a step of designing and analyzing the development aircraft defined by the conceptual design and the preliminary design of the aircraft development process, Perform the design of the measurement system.

2, the first step S100 includes a first step S110 for selecting a flight test item, a first step S22 for selecting an aircraft for each flight test item, (Step S103), which is the measurement requirement setting for each flight test item, Step 1-4 (S104), which is the measurement parameter setting for each flight test aircraft, Step 1-5, which is the measurement parameter measurement sensor, (S105), and the 1-6 step (S106) of setting the mounting position of the measuring sensor and the measuring instrument.

The first step S100 is carried out at the conceptual design stage of the aircraft development process in which the shape of the aircraft is determined and the structure of the airframe and the sub-system are determined.

The measurement requirements are almost the same for fixed and rotating wings as flight test data acquisition and storage, real-time data monitoring, time synchronization, video and audio data storage and transmission, atmospheric information measurement (altitude and speed) Do.

The first-step (S101) selects the corresponding flight test item among the preset flight test review fields according to the measurement request of the development aircraft.

Flight test review areas include structure, flight technology, propulsion, flight detail, cockpit and escape systems, diagnostic systems, avionics, power systems, electromagnetic environment effects, production quality, flight tests, and system safety.

The step 1-2 (S102) selects a development aircraft for each flight test item selected in the step 1-1 (S101), and the step 1-3 (S103) The measurement requirements for each selected flight test item are set.

In step 1-4, the measurement parameter for each development aircraft selected in step 1-2 is generated, and the step 1-5 (S105) is performed in step 1-4 (step S104) The measurement sensor of the measurement parameter and the measurement equipment are set.

The step 1-6 (S106) sets the mounting position of the measuring sensor and the measuring instrument set in the step 1-5 (S105).

More specifically, the on-board measurement system to meet measurement needs consists of equipment that generally acquires, stores, and transmits all data related to the flight test.

The main factors that determine the design of such on-board measuring systems should be the parameter quantity, sample rate, precision, sign and method, time link system, transmission method and frequency, storage medium, storage capacity and storage format, .

In the first step S100, various parameters required for the flight test are classified according to test items and development aircraft, and a hardware design for parameter measurement is performed.

Because the onboard measurement system is required to acquire all required data, it should be designed to meet the requirements of performance, cost, weight, etc., and should not change the basic aircraft shape unless it is inevitable for flight test measurement purposes, As much as possible, the flight system should be equipped with the full utilization of the free space without changing the aircraft structure and system, and the corresponding electrical design should be installed.

When designing measurement sensors and measurement equipment of the onboard measurement system, consideration should be given to the operating conditions (vibration, temperature, humidity, etc.) of the measurement equipment, the mounting space environment (temperature and vibration conditions according to altitude and speed) It is preferable to mount it.

For example, in a fixed-wing aircraft, there is no space for mounting the on-board measurement system when the on-board measurement system and the electrical design are mounted, so that the measurement sensor , Measurement equipment, and electrical design installation space should be reviewed and secured,

In the case of a rotary wing aircraft, it is possible to mount a test engineer on the aircraft due to the sufficient free space and flight characteristics, so that the test engineer can attach the data processing and analysis system so that the test engineer can check the main data directly. It is desirable to perform an electrical design.

In addition, for flight testing of a development aircraft, in addition to the basic form of the aircraft, additional equipment required for flight safety or data acquisition is installed on the development aircraft, Because the characteristics of the aircraft can vary according to the characteristics, the external shape must be determined through aerodynamic influence analysis in advance. In addition, it is preferable that the structural analysis be preceded by ensuring sufficient structural strength at the time of installation so that damage to the developed aircraft due to detachment of the auxiliary equipment does not occur.

In particular, in the case of a rotorcraft aircraft, it is desirable that sufficient reinforcement design be made considering the effects of vibration and rotor.

In the second step S200, a measurement sensor is selected according to parameters and parameter characteristics to be measured by a detailed design of an aircraft development process, and the mounting measurement system designed in the first step S100 is mounted And it is possible to determine whether the measurement sensors are operating normally.

In more detail, the second step S200 is to mount the mounting measurement system designed in the first step S100 to the development aircraft, to measure the measurement sensor mounted on the development aircraft through the mounting measurement system, And whether the validity of the flight data from the measurement sensor and the measurement instrument and the normal communication with the ground measurement system are determined and finally the onboard measurement system is finally constructed.

To be more specific, if the measurement sensor is determined in step S100, parameters are determined according to the characteristics of the parameter.

The most common sensors used in flight tests are vibration / acceleration, temperature, pressure, and load sensors. The measurement sensors for flight tests include physical quantities to be measured, measurement range, accuracy, mounting method, And the aircraft operating conditions (environmental conditions such as temperature / vibration) are basically considered.

Specifically, the vibration / acceleration sensor measures the frequency to be measured,

The pressure sensor is used to measure the absolute pressure / relative sum / differential pressure,

The temperature sensor measures the response and the medium to be measured,

The load sensor should be selected considering the size of the resistance (generally 350 Ω applied to the aircraft), durability and the medium to be measured.

Most of the types of sensors used in these flight tests are universally used for one year, but sensors that are not accessible after installation can be difficult to calibrate.

Mounting of the onboard measurement system is generally performed at the final stage of the development aircraft, and the load / temperature / pressure sensor mounted on the aircraft structure and part is mounted on the sensor at the same time as the aircraft part is manufactured.

In addition, most of the sensors directly mounted on the aircraft structure can not be reworked or modified.

For example, when a fixed-wing aircraft is equipped with a measuring sensor and a measuring instrument, it is constructed as a compact, decentralized system,

In the case of a rotary wing aircraft, it is effective to construct an integrated type considering the convenience of vibration and maintenance.

However, in case of direct mounting on the rotary part of a rotorcraft aircraft, it should be checked whether the available electric wiring or radio communication is available to prevent the loss of equipment operation and flight data. In order to minimize the influence of rotation, It is desirable to consider weight and balance when wiring.

When the installation of the measuring sensor and the measuring instrument constituting the measuring instrument and the electric wiring work are completed, a data verification operation for judging whether the mounted measuring sensor and the measuring instrument are in normal operation or not is performed.

The inspection of the data by the measurement sensor is firstly checked on the development aircraft in the same manner as the inspection of the integrated system of the Lab installed in the aircraft, and the verification is performed according to the sensor type.

Most of the sensors are checked at the time of sensor glazing, but in case of displacement sensors, calibration is necessarily required on the aircraft.

In the second step S200, the validity of the measured data and the operation status of the measurement sensor and the measurement equipment constituting the on-board measurement system must be checked. In addition, the integration check with the ground measurement system .

In the third step S300, when the operation state of the measurement sensor and the measurement equipment is confirmed to be in a normal operation state by the second step S200, a manufacturer of the aircraft development process using the on- And the flight data can be obtained by performing the test & evaluation of the developed aircraft manufactured by the user.

In detail, the third step (S300) performs a test evaluation of the development aircraft through the on-board measurement system mounted on the development aircraft, performs the validity check by measuring the flight test data, So that the onboard measurement system can be operated.

More specifically, the validity of the flight test data is to verify that the instrumentation data obtained from the onboard measurement system of the development aircraft is valid for analysis and should be checked from the system build.

After the on-board measurement system is built, the operation characteristics of the whole system are checked. This is called on-board checkout. Data validation to check the validity of the measurement data acquired by the on-board measurement system is called data validation. The validity of the measurement data is checked by comparing the measurement data input through the input unit and the data output from the final ground measurement system.

For example, flight test of fixed-wing aircraft has many limitations on utilization of internal space of development aircraft because there are many constraints on facilities and external environment.

Due to this flight condition, flight test of fixed-wing aircraft must be carried out before and after the flight to the detailed measurement system for each aircraft in order to ensure safety of the aircraft. The ground measurement system must also check the validity of measurement data .

Flight test of a rotorcraft aircraft has many advantages for flight test as compared to flying test of a fixed-wing aircraft. Due to its wide internal space, test engineers can fly directly on the flight test.

Failure of the on-board measurement system occurring during the flight test is important to solve the problem quickly and accurately within a given time. In general, the failure investigation is based on the use period of the onboard measurement system, the change after normal operation, And to perform quick and accurate fixed inquiry.

The number of fixed explorations was higher in the fixed flight aircraft at the beginning of the flight test, then decreased gradually,

It is common for the rotor blades to have the same frequency of failure detection from early to late.

In order to obtain valid flight data in flight tests, one of the most important parts is metrological configuration management. The on-board measurement system can define measurement form for each flight, acquire valid data, process analysis, and manage the measurement form and share information about it.

In other words, since the conventional on-board measurement system is reviewed and applied at the final stage of the development of the aircraft, there is a disadvantage that additional schedule and cost are required for building the on-board measurement system,

According to the embodiment of the present invention, the on-board measurement method using the on-board measurement system optimized for flight characteristics and flight characteristics can be classified into designing, manufacturing and operation itself, It is possible to provide an on-board measurement system optimized for the characteristics of the aircraft and the purpose of the flight test, and at the same time, it is possible to effectively shorten the development schedule and development cost of the aircraft.

Although the description has been made of the onboard measurement method using the onboard measurement system optimized for the characteristics of the aircraft and the flight test according to the embodiment of the present invention, the onboard measurement using the onboard measurement system optimized for the characteristics of the aircraft and the flight test described above It will be readily understood by those skilled in the art that the method may be provided in a recording medium which can be read by a computer by tangibly embodying a program of instructions for implementing it or may be provided by a computer program written in computer instructions . In other words, it may be implemented in the form of a program command that can be executed through various computer means, recorded in a computer-readable recording medium, or may be a computer program written in an instruction word. The computer readable recording medium or the computer program may include program instructions, data files, data structures, and the like, alone or in combination. The program instructions recorded on the computer readable recording medium or the computer program may be those specially designed and constructed for the present invention or may be those known and available to those skilled in the computer software. Examples of the computer-readable recording medium or the computer program include magnetic media such as a hard disk, a floppy disk and a magnetic tape, optical media such as CD-ROM and DVD, optical disks such as floptical magneto-optical media such as disk, and hardware devices specifically configured to store and perform program instructions such as ROM, RAM, flash memory, USB memory, and the like. The computer readable recording medium or the computer program may be a transmission medium such as a light or metal line, a wave guide, or the like including a carrier wave for transmitting a signal designating a program command, a data structure, and the like. Examples of program instructions include machine language code such as those produced by a compiler, as well as 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 operations of the present invention, and vice versa.

As described above, the present invention has been described with reference to specific embodiments such as specific components and exemplary embodiments. However, the present invention is not limited to the above-described embodiments, And various modifications and changes may be made thereto by those skilled in the art to which the present invention pertains.

Accordingly, the spirit of the present invention should not be construed as being limited to the embodiments described, and all of the equivalents or equivalents of the claims, as well as the following claims, fall within the scope of the present invention .

S100 to S300: Each step of the onboard measurement method using the onboard measurement system optimized for the aircraft characteristics and the flight test purpose of the present invention

Claims (6)

Based on the design and analysis of the development aircraft defined by the conceptual design and the preliminary design of the aircraft development process and the measurement needs to verify the functions of each system, Step SlOO;
A measurement sensor is selected according to a parameter and a parameter characteristic to be measured by a detailed design of an aircraft development process, a mounting measurement system designed by the first step (S100) is mounted, (S200); And
When the normal operation state of the measurement sensors is confirmed by the second step S200,
A third step (S300) of acquiring flight data by performing a test & evaluation of the developed airplane manufactured by the manufacturer of the aircraft development process using the on-board measurement system;
And a load measurement method using an on-board measurement system optimized for flight characteristics.
The method according to claim 1,
In the first step S100,
A first step (S101) of selecting a corresponding flight test item among the predetermined flight test review fields according to the measurement request of the development aircraft;
A first step (S102) of selecting a development airplane for each flight test item selected in the step 1-1 (S101);
A 1-3 step (S103) of setting a measurement requirement for each flight test item selected in the 1-1 step (S101);
A step 1-4 (S104) of generating measurement parameters for each development aircraft selected in the step 1-2 (S102);
A step 1-5 (S105) of setting a measurement sensor and a measurement instrument of the measurement parameters generated in the step 1-4 (S104); And
Step 1-6 (S106) of setting the mounting position of the measuring sensor and the measuring instrument set in the step 1-5 (S105);
Lt; / RTI >
Wherein the on-board measurement system is designed using steps 1-11 (S101) to (1-6) (S106), and the on-board measurement method using the on-board measurement system optimized for flight characteristics.
The method according to claim 1,
In the second step S200,
The mounting measurement system designed in the first step S100 is mounted on the development aircraft, and whether or not the measurement sensor mounted on the development aircraft and the measurement equipment mounted on the development aircraft through the mounting measurement system and the normal operation of the measurement equipment and the flight data And determining whether or not communication with the ground measurement system is established and finalizing the mounting measurement system on the development aircraft. The method of the present invention is based on the characteristics of the aircraft and the onboard measurement system optimized for the flight test purpose.
The method according to claim 1,
In the third step S300,
Aircraft characteristics are measured by carrying out a test evaluation of the developed aircraft through the onboard measurement system mounted on the development aircraft, performing the validity check by measuring the flight test data, and operating the onboard measurement system by defining the failure investigation and measurement shape And onboard measurement method using onboard measurement system optimized for flight test purposes.
A computer-readable recording medium storing a program for implementing an on-board measurement method using an on-board measurement system optimized for an aircraft characteristic and a flight test objective according to any one of claims 1 to 4.
A computer program written with instructions for implementing the onboard measurement method using the onboard metrology system optimized for aircraft characteristics and flight test purposes as set forth in any one of claims 1 to 4.

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