• 항공우주시스템공학회지
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• 제8권3호
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• pp.20-26
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• 2014

This paper presents the procedures and the results of the pitch control force via flight test for a light airplane in order to make out the stability of the aircraft and the compliance with concerned regulation. The flight test procedures were determined in order to obtain the aircraft type certification. The instrumentation equipments including airspeed indicator, accelerometer, and pitch control force measurement tools are used to perform the flight test. For the flight test, the airspeed and the pitch control force with related normal acceleration are measured sustaining turn flight with bank angle derived from trim speed. The flight test results showed that the handling qualities of the airplane are complied with the KAS-23, the regulation of the Korean government for the light airplane type certification.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2008년도 추계학술대회A
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• pp.762-767
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• 2008

Estimated values for maximum lift coefficients of a light airplane, ChanGong-91, derived from an analytical method using a test database, a computational fluid dynamic method, a wind tunnel test, and a flight test are compared. The DATCOM method and VSAERO code are applied as the analytical method and the computational fluid dynamic method, respectively, in order to estimate the maximum lift coefficients of a light airplane. The wind tunnel test is conducted using a 1/14.5 scaled model installed in a closed circuit type wind tunnel. For the flight test approach, the wings-level power-off stall tests are performed to obtain the maximum lift coefficients. As a point of reference for the flight test results of the maximum lift coefficients, the differences of both estimates derived from the DATCOM method and the wind tunnel test data are smaller than those derived from VSAERO.

• 한국항공운항학회지
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• 제16권3호
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• pp.1-6
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• 2008

The stalling speed flight test of light airplane, ChangGong-91, was performed to acquire the certification. With power-off engine condition, the wings level stall flight tests were conducted at the aircraft configuration of various flap angle - clean, 20degree, and full flap, respectively. They were performed considering with the combination of the maximum and minimum test weight, and forward and afterward center of gravity. The stalling speeds and the minimum speeds of light airplane were determined from the results of flight test. Also, the appropriateness of stall warning speeds are evaluated through the flight test measures. The airplane is recoverable only with pitch control and engine throttle from stall state without exceptional operation.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2007년도 춘계학술대회A
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• pp.891-896
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• 2007

This paper contained the flight test calibration for the airspeed indicator and the altimeter of the light airplane ChangGong-91, which is the first type certified aircraft from Korean Ministry of Construction and Transportation, as a part of the flight test validation. The flight test for airspeed position error calibration was performed using tower fly by method in order to calibrate swivel head testboom which is attached to the right wing tip of the airplane, and using system to system method for airspeed indicator. The altimeter calibration was calculated using flight test data for airspeed calibration. The flight test was conducted at the basis of the 'Korean Airworthiness Standard' regulation of Korean Ministry of Construction and Transportation.

• 한국항공운항학회지
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• 제11권2호
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• pp.43-58
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• 2003

To decide the type of airplane to purchase in air service agencies is a typical matter of multi-criteria decision making process. The selection of airplane type is very important because it has great impact on the budget and management of air service agency, once the decision has been made. AHP is being recognized as one of many effective methods of multi-criteria decision making processes. In this study, checklist for the selecting optimum type of light airplane to be purchased is developed by the AHP.

• 한국항공우주학회지
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• 제35권4호
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• pp.308-315
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• 2007

연구는 경비행기인 창공-91의 인증 획득을 위한 비행시험의 일부로서 상승성능을 파악하기 위하여 수행되었다. 창공-91은 1993년에 대한민국의 건설교통부로부터 최초로 인증을 취득한 단발엔진을 장착한 일반유형의 5인승 항공기이다. 상승을 위한 비행시험 절차 및 자료는 형식증명을 획득하는데 사용되었다. 톱니형 상승 데이터로부터 양항곡선방법으로 데이터를 처리하여 창공-91의 최대상승률, 최대상승각 속도, 최대상승률 속도, 그리고 절대상승한도를 구하였다. 또한, 상승성능의 결과로부터 양항곡선식을 구함으로써 형상항력계수와 오스왈드 효율계수를 비행기 설계시의 값과 비교하였다.

• 한국항공우주학회지
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• 제41권7호
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• pp.552-560
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• 2013

부활호는 한국최초로 설계 제작된 국산 경비행기이며 복원된 부활호는 2004년 공군이 복원한 부활호의 기본 형상을 기준으로 하되, 날개는 알루미늄합금 재질로 적용하고, 전자식계기를 사용하며, 비행 안전성 확보를 위해 비행기용 낙하산과 소형블랙박스를 장착하는 등 최신 기술의 적용과 성능 개량을 병행하였다. 본 논문에서는 복원된 부활호의 주요 설계 변경 내역을 소개하고 구조, 공력 및 안정성 해석 결과와 풍동 시험, 비행시험을 통하여 입증된 성능향상 내용을 소개한다. 본 연구 결과는 향후 국산 개발 경비행기 연구에 큰 도움이 될 것으로 생각된다.

• 한국항공운항학회지
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• 제5권1호
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• pp.17-30
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• 1997

FAR 23, AC 23-8, 그리고 Order 8110.7을 이용하여 경비행기의 비행 시험 절차에 대한 연구를 수행하였다. 본 연구에서는 창공-91의 비행 시험을 통한 경험을 바탕으로 형식증명을 위한 주요 절차에 대한 연구를 수행하였다. 본 연구는 소형 비행기의 제작자, 항공관련 기술자, 비행 시험 기술자, 비행 시험 조종사, 그리고 관련 정부 관계자들에게 비행 시험에 관련된 기준을 이해하도록 하기 위해 수행된 연구이다. 본 연구에서 비행 시험 방법과 절차는 주로 소형 비행기의 형식증명에 관련된 것으로 관련자들에게 큰 도움이 될 것이다.

• 항공우주시스템공학회지
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• 제7권2호
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• pp.42-46
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• 2013

In 2010, Airworthiness standard for VLA(Very Light Airplane) category was newly introduced as KAS Part VLA. KAS Part VLA is an adaption of EASA CS-VLA which was developed to reduce unnecessary burden of manufacturer of very light, simple, single-reciprocating-engine/propeller powered airplanes having low stall speeds by tailoring some requirements of Part 23. In this paper, difference and similarity of structural requirements between Part 23 and VLA was analyzed.

• 제어로봇시스템학회논문지
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• 제14권7호
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• pp.629-634
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• 2008

This paper presents the flight test procedure and the results for the airspeed indicator calibration of a light airplane the name of ChangGong-91, which is the first type certified aircraft from Korean Ministry of Construction and Transportation, as a part of the flight test validation to get the certification. The flight tests for airspeed position error calibrations are conducted using tower fly by method in order to calibrate swivel head testboom which is attached to the right wing tip of the airplane. Also system to system method is applied in order to calibrate the airspeed indicator of the cockpit. The flight test is conducted at the basis of the 'Korean Airworthiness Standard' which is the regulation of Korean Ministry of Construction and Transportation. The airspeed error range for the testboom and the airspeed indicator are determined to $-0.75{\sim}+0.75$ knot and to $-4.0{\sim}+2.0$ knots, respectively. The calibration results are applied to ChangGong-91 Flight Operation Manual.