IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0775126
(2001-02-01)
|
발명자
/ 주소 |
- Wang, Grant
- Chiang, Richard
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
4 |
초록
▼
A satellite system includes a solar wing moveably connected to a satellite central body. A sensor, also coupled to the satellite central body, detects the movement of the body and generates a rate signal based on that movement. Additionally, an actuator, which controls momentum, is coupled to the sa
A satellite system includes a solar wing moveably connected to a satellite central body. A sensor, also coupled to the satellite central body, detects the movement of the body and generates a rate signal based on that movement. Additionally, an actuator, which controls momentum, is coupled to the satellite central body with maximum torque along the thermal shock axis. Subsequently, a rate-dominated thermal shock suppression controller, which is coupled to the satellite central body, receives the rate signal from the sensor to control the actuator.
대표청구항
▼
A satellite system includes a solar wing moveably connected to a satellite central body. A sensor, also coupled to the satellite central body, detects the movement of the body and generates a rate signal based on that movement. Additionally, an actuator, which controls momentum, is coupled to the sa
A satellite system includes a solar wing moveably connected to a satellite central body. A sensor, also coupled to the satellite central body, detects the movement of the body and generates a rate signal based on that movement. Additionally, an actuator, which controls momentum, is coupled to the satellite central body with maximum torque along the thermal shock axis. Subsequently, a rate-dominated thermal shock suppression controller, which is coupled to the satellite central body, receives the rate signal from the sensor to control the actuator. im 1, wherein said airfoil has a Reynolds number in the range from 1,000,000 to 9,000,000. 6. The airfoil of claim 1, said airfoil having a minimum drag coefficient of approximately 0.004. 7. The airfoil of claim 1, wherein said airfoil is a main-wing airfoil of a general aviation aircraft. 8. An airfoil having an upper surface, a lower surface, a leading edge, a trailing edge, and a chord line, said airfoil providing primarily turbulent flow across the upper surface of said airfoil at the maximum lift coefficient, said airfoil having upper and lower surfaces, wherein the x/c locations and y/c distances correspond substantially to the following table: TBL Upper Surface Lower Surface x/c y/c x/c y/c 0.00001 0.00039 0.00009 -0.00147 0.00017 0.00217 0.00054 -0.00308 0.00357 0.01122 0.00151 -0.00454 0.01117 0.02128 0.00300 -0.00600 0.02281 0.03160 0.01018 -0.01065 0.03845 0.04166 0.02452 -0.01660 0.05803 0.05091 0.04424 -0.02243 0.08181 0.05887 0.06896 -0.02811 0.11019 0.06562 0.09830 -0.03357 0.14297 0.07163 0.13180 -0.03876 0.17954 0.07704 0.16902 -0.04357 0.21937 0.08178 0.20943 -0.04791 0.26191 0.08578 0.25250 -0.05166 0.30662 0.08892 0.29769 -0.05467 0.35296 0.09109 0.34441 -0.05678 0.40037 0.09215 0.39208 -0.05776 0.44828 0.09194 0.44011 -0.05736 0.49614 0.09013 0.48787 -0.05495 0.54379 0.08620 0.53570 -0.04955 0.59159 0.08025 0.58486 -0.04152 0.63946 0.07299 0.63544 -0.03252 0.68678 0.06502 0.68645 -0.02371 0.73290 0.05672 0.73682 -0.01572 0.77715 0.04842 0.78548 -0.00900 0.81885 0.04036 0.83135 -0.00377 0.85732 0.03272 0.87343 -0.00018 0.89191 0.02553 0.91073 0.00180 0.92221 0.01865 0.94228 0.00238 0.94818 0.01220 0.96734 0.00199 0.96965 0.00672 0.98544 0.00115 0.98603 0.00278 0.99636 0.00034 0.99642 0.00062 1.00000 0.00000 1.00000 0.00000 9. The airfoil of claim 8, said airfoil having a maximum thickness ratio of 15%. 10. The airfoil of claim 8, said airfoil having a maximum lift coefficient in the range of about 1.4 to 1.7. 11. The airfoil of claim 8, wherein said airfoil has a Reynolds number in the range from 1,000,000 to 9,000,000. 12. The airfoil of claim 8, said airfoil having a Reynolds number in the range from 2,000,000 to 3,000,000 and a maximum lift coefficient in the range of about 1.4 to 1.7. 13. The airfoil of claim 8, said airfoil having a minimum drag coefficient of approximately 0.004. 14. An airfoil for the main wing of a general aviation aircraft, said airfoil comprising an upper surface and a lower surface and having a chord line, wherein x/c values are dimensionless locations on the chord line and the y/c values are dimensionless distances from said chord line to points on said upper or lower surface, wherein said values correspond substantially to the following table for said surfaces: TBL Upper Surface Lower Surface x/c y/c x/c y/c 0.00001 0.00039 0.00009 -0.00147 0.00017 0.00217 0.00054 -0.00308 0.00357 0.01122 0.00151 -0.00454 0.01117 0.02128 0.00300 -0.00600 0.02281 0.03160 0.01018 -0.01065 0.03845 0.04166 0.02452 -0.01660 0.05803 0.05091 0.04424 -0.02243 0.08181 0.05887 0.06896 -0.02811 0.11019 0.06562 0.09830 -0.03357 0.14297 0.07163 0.13180 -0.03876 0.17954 0.07704 0.16902 -0.04357 0.21937 0.08178 0.20943 -0.04791 0.26191 0
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