• Aerospace Engineering and Technology
• /
• v.1 no.1
• /
• pp.117-127
• /
• 2002

In this paper, structure design of the payload section of the KSR-III was performed. The payload section of the KSR-III, which corresponds to the second stage, consists of the Scientific Payload Section for the mission of the rocket, the Payload Section (Electronics) for the communication between the rocket and the ground station, and the Payload Section (Attitude Control) for the attitude control of the rocket. In order to accomplish the mission, every payload and component should operate successfully during the mission period and the structure must satisfy the requirements of the payloads. In this research, precise composition of the payload section and payloads arrangement of the KSR-III were performed. And the modification of the structure to meet the requirements were described.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.32 no.3
• /
• pp.88-94
• /
• 2004

The KSR-III rocket is a liquid propellant sounding rocket and thrust vector control actuators and cold gas thrusters are used to control pitch and yaw, roll attitude respectively during thrusting phase. In this paper, the structure of designed attitude controller and gain scheduling, results of stability analysis for KSR-III rocket are presented. The attitude controller is implemented with flight software in the domestically developed INS and successfully performed its function in the flight test. The flight data are coincident with simulation results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 1999.10a
• /
• pp.5-5
• /
• 1999

3단형 과학로켓(KSR-III)의 기본형 및 응용형에 공통으로 사용되는 주엔진은 액체산소를 산화제로, 케로신을 연료로 사용하는 액체추진기관이다. 엔진 기본설계를 통하여 로켓 임무 요구사항에 부합되도록 엔진 각 부분의 기본제원을 설정하였고, 엔진의 형상을 결정하였다. 설계된 엔진의 성능검증 작업은 분사시험용 엔진, 축소형 엔진, 엔지니어링 모델 및 비행시험모델의 설계/제작/시험을 통하여 순차적으로 수행할 계획이다. 본 연구는 3단형 과학로켓 엔진의 기본설계 및 성능검증 계획에 관한 것이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.31 no.2
• /
• pp.80-88
• /
• 2003

This paper describes the development of an ozone detector and an electron probe as parts of scientific payloads for sounding rockets such as the KSR-III. Each detector consists of sensor parts and electronic parts. We successfully carried out the calibration tests with developed ozone detector and the space plasma simulation chamber tests with electron detector. These payloads could be onboard the KSR-III and with measured data, it is expected and temperature profile over the Korean Peninsular.

• Aerospace Engineering and Technology
• /
• v.1 no.2
• /
• pp.83-90
• /
• 2002

This paper describes the development of scientific payload system onboard the KSR-III. The ozone detector(UVR), Langmuir electron probe(LEP), airglow photometer(AGP), and magnetometer(MAG) constitute this system. The purpose of the ozone detector is to measure the ozone density profile and the LEP measures the electron density and temperature in the ionosphere over the Korean Peninsula. The AGP detects airglow in the mesosphere over the Korean Peninsular. The MAG provides rocket attitude and the magnetic fluctuation information during the flight. With the developed payloads, the ground calibration tests and the environmental tests have been performed.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.30 no.6
• /
• pp.116-123
• /
• 2002

This paper describes the development of gimbals engine actuation system for KSR(Korean Sounding Rocket)-III which performs the attitude control of pitch and yaw axes by thrust vector control of liquid propellant gimbals engine. The development requirements of configuration, performance and environment are introduced, and the principles and details of components and system development are discussed. The developed system successfully fulfilled its own performance and environmental evaluation. It will be planned to perform verification of interface and integration compatibility with other related systems, and then mounted on KSR-III as a flight hardware system.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.31 no.6
• /
• pp.96-101
• /
• 2003

Korea Sounding Rocket(KSR)-III onboard telemetry system has acquired various data from subsystems and sensors in the rocket, and radiated PCM/FM data using two S-band antennas during the flight. Simultaneously， it is necessary that the ground receiving systems track the rocket, and receive and decode telemetry data. Also post processed telemetry data are needed to be broadcasted on ethernet network in real time. Range safety display system displays flight trajectory using telemetry data in mission control center, and so flight manager makes a decision for flight termination from the trajectory This paper describes operating technique about telemetry reception, the development for the realtime data processing system, and the results for telemetering reception on fight test. We telemetered, processed, and broadcasted numerous telemetry data during the flight test successfully.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.30 no.2
• /
• pp.98-107
• /
• 2002

An experimental and numerical study of aerodynamic charateristics of KSR-III and jet impingement on a deflector during launch has been conducted. To investigate aerodynamic characteristics of KSR-III configuration, wind tunnel tests using 6.4% scale model were performed by 4x4 feet ADD trisonic wind tunnel on the Mach number range of 0.4~3.8. Solutions of Three dimensional Euler equations were also obtained and compared with test result. For the study of KSR-III jet impingement flowfield on a deflector during launch operation, unsteady computation using CFD-FASTRAN was performed.

• Aerospace Engineering and Technology
• /
• v.2 no.1
• /
• pp.117-123
• /
• 2003

This paper introduces ground feeding facility for flight test of sounding rocket(KSR-III) which use liquid propellants and addresses facility configuration, development process and results. Supply of propellants and pressurization gases to vehicle according to predefined launch scenario is the primary goal of ground feeding facility. It was constructed at KSR-III launch site, verified by several tests and used for the flight test successfully.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.8 no.3
• /
• pp.75-86
• /
• 2004

KSR-III is the first Korean sounding rocket propelled by a liquid propellant propulsion system and it has been developed over 5 years using purely domestic technologies. The propulsion system of KSR-III is a 13-ton class see-level thrust liquid rocket engine(LRE) which utilizes liquid oxygen and kerosene for its propellants and employed pressurized propellant feeding and ablative cooling system. The problem of combustion instabilities which has brought the most difficulty in the development was resolved by implementation of a baffle. Through the development of KSR-III LRE, meaningful achievements have been made in the core technologies of LRE such as design of injectors and combustion chambers and test, evaluation, and control of combustion instabilities. The acquired technologies will be applied to the development of higher performance LREs necessary for future space development programs such as Korean Small Launch Vehicles(KSLV) In this paper, the development of KRE-III LRE system is described including its design, analyses. performance tests and evaluation.