Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
권호 표지
DOI QR코드

DOI QR Code

A Study on the Influence of Helicopter Main Rotor Inflow Model upon Launched Rocket Trajectory and Safe Launch Envelope

헬리콥터 유입류 모델에 따른 발사된 로켓의 비행궤적 영향성 및 안전발사 기동영역 해석 연구

  • Received : 2018.09.20
  • Accepted : 2019.05.22
  • Published : 2019.06.30
Download PDF
⟨ Previous Next ⟩

Abstract

This study presents the numerical investigation of the trajectory of rocket launched from a helicopter. The nonlinear mathematical model of armed configuration of UH-60 helicopter was developed while Hydra 70 unguided rocket was modeled to simulate the rocket behavior. The effects of various inflow models on the launched rocket trajectory are obtained. Similarly, rocket launch simulation was performed to determine the unsafe flight maneuver condition where the rocket trajectory is critically close to the helicopter main rotor tip path plane.

본 논문에서는 헬리콥터의 유입류 모델에 따라 헬리콥터에서 발사되는 로켓의 궤적에 대한 영향성을 비행역학 해석을 통해 검토하였다. 무장형상의 비선형 비행역학 해석모델은 UH-60 헬리콥터 형상으로 구성하고 헬리콥터에서 발사되는 발사체의 궤적예측에는 HYDRA 70 로켓을 이용하였다. 다양한 로터 유입류 모델을 사용하여 각각의 모델에 따라 로켓 발사궤적에 미치는 영향을 검토하였다. 또한 헬리콥터의 다양한 비행조건에 대해 로켓 발사 시뮬레이션 해석을 수행하고 로켓이 로터 디스크 면과 근접하는 위험한 로켓발사 비행영역을 검토하였다.

Keywords

OJSSBW_2019_v13n3_70_f0001.png 이미지

Fig. 1 Rotor Disk Clearance in MIL-STD-1289D

OJSSBW_2019_v13n3_70_f0002.png 이미지

Fig. 2 Flow Field at Hover, Modeled with Peter-He 15 State Dynamic Inflow Method

OJSSBW_2019_v13n3_70_f0003.png 이미지

Fig. 3 Flow Field at Hover, Modeled with Prescribed Vortex Wake Method

OJSSBW_2019_v13n3_70_f0004.png 이미지

Fig. 4 Hydra70 Rocket Configuration

OJSSBW_2019_v13n3_70_f0005.png 이미지

Fig. 5 Hydra 70 Rocket Thrust

OJSSBW_2019_v13n3_70_f0006.png 이미지

그림 6 Rocket Installed Position

OJSSBW_2019_v13n3_70_f0007.png 이미지

Fig. 8 Flow Chart of Rocket Launch Analysis

OJSSBW_2019_v13n3_70_f0008.png 이미지

Fig. 9 Downwash Velocity along the Flight Path of the Rocket

OJSSBW_2019_v13n3_70_f0009.png 이미지

Fig. 10 Rocket Pitch along Flight Path of Rocket

OJSSBW_2019_v13n3_70_f0010.png 이미지

Fig. 11 Effect of Main Rotor Interference on Rocket Trajectory

OJSSBW_2019_v13n3_70_f0011.png 이미지

Fig. 12 Main Rotor Disk Clearance

OJSSBW_2019_v13n3_70_f0012.png 이미지

Fig. 13 Launch in Forward Flight Maneuver

OJSSBW_2019_v13n3_70_f0013.png 이미지

Fig. 14 Launch in Rearward Flight Maneuver

OJSSBW_2019_v13n3_70_f0014.png 이미지

Fig. 15 Unsafe Rocket Launch Envelop in Vertical Climb Maneuver

OJSSBW_2019_v13n3_70_f0015.png 이미지

Fig. 16 Downwash Velocity in Vertical Climb Maneuver

OJSSBW_2019_v13n3_70_f0016.png 이미지

Fig. 17 Rocket Pitch Angle in Vertical Climb Maneuver

OJSSBW_2019_v13n3_70_f0017.png 이미지

Fig. 18 Unsafe Rocket Launch Envelop in Forward Climb Maneuver

OJSSBW_2019_v13n3_70_f0018.png 이미지

Fig. 7 The Validation of Rotor Induced Flow Distribution at Rocket Pod Waterline level

Table 2 Rocket Mass and Configuration

OJSSBW_2019_v13n3_70_t0001.png 이미지

References

  1. Hess J. L. and Clark R. W., "Improved trajectory calculation for helicopter launched missiles," Department of the Army U.S. Army Research Office, DAG29-76-C-0021, 1979.
  2. Wei, F.S. and Gjestvang, J., "Store Separation Analysis of the Penguin Missile from the SH-2G Helicopter," AIAA, 2001-0992, Reno., 2001.
  3. Taylor, R.B. and Landgrebe, A.J., "Investigation of the Airflow at Rocket Trajectory and Wind Sensor Locations of a Model Helicopter Simulating Low Speed Flight," UTRC Report No. R79-912985-5, 1979.
  4. Hee Dong Lee, "Aerodynamic Simulation of Air-Launched Missiles from a Complete Helicopter", J. of The Korean Society for Aeronautical and Space Sciences, vol. 39, no. 12, pp. 1097-1106, 2011. https://doi.org/10.5139/JKSAS.2011.39.12.1097
  5. Ozge Kapulu and Ozan Tekinalp, "Main Rotor Downwash Effect on Separation Characteristics of External Stores," AIAA Atmospheric Flight Mechanics Conference, 2017, Grapevine, Texas.
  6. U.S. Department of Defense, MIL-STD-1289D Airborne Stores Ground Fit and Compability, Requirements, 2003.
  7. Howlett, J.J., "UH-60A Black Hawk Engineering Simulation Program, Volume I - Mathematical Model," NASA CR-166309, Dec. 1981.
  8. Peters, D.A., and He, C.J., "Finite State Induced Flow Models Part II: Three-Dimensional Rotor Disk," JOURNAL OF AIRCRAFT, Vol. 32, No. 2, March-April, 1995.
  9. C. Wayne Dahlke, "Hydra 70 MK66 Aerodynaics and Roll Analysis", Technical Report RD-SS-90-6, 1990.