lesson10solidpropulsionsystems-資料下載頁
2024-10-24 17:36本頁面
【導(dǎo)讀】Lesson10:. Dr.AndrewKetsdever. Titan. Earlyversionsused. tetroxide/UDMH. TitanIV. AthenaIandII. secondstage,andOAM. FormerlyLMLV(Lockheed-. Athena. StageData-Athena-1. SpaceShuttle
【正文】 lidfuel rocket。 2200 kN (500,000 lb) 2nd stage: Aerojet solidfuel rocket 3rd stage: Hercules solidfuel rocket 4th stage (postboost): Rocketdyne restartable liquidfuel rocket Warhead 10x W87 thermonuclear (300 kT) in 10x MIRV Peacekeeper A view you don’t want to see Minotaur – Minotaur IV ? Demissioned Minuteman (Minotaur) or Peacekeeper (Minotaur IV) boosters ? Manufacturer: OSC. Launches: 4 (Minotaur). Success Rate: % pct. First Launch Date: 27 January 2020. Last Launch Date: 23 September 2020. Launch data is: continuing. LEO Payload: 640 kg. to: 185 km Orbit. at: degrees. Payload: 335 kg. to a: Sun synchronous, 741 km, deg inclination trajectory. Apogee: 1,000 km. Liftoff Thrust: 73,000 kgf. Liftoff Thrust: kN. Total Mass: 36,200 kg. Core Diameter: m. Total Length: m. Recurring Price $: million. in 1999 price dollars. Minotaur ? Stage Number: 1. 1 x Minuteman1 Gross Mass: 23,077 kg. Empty Mass: 2,292 kg. Thrust (vac): 80,700 kgf. Isp: 262 sec. Burn time: 60 sec. Isp(sl): 237 sec. Diameter: m. Span: m. Length: m. Propellants: Solid No Engines: 1. M55/TX55/Tu122 Status: Out of Production. Comments: First stage of Minuteman I. Proposed as zero stage for various Saturn variants in 196039。s. Surplus motors used in ABM SDI tests in 198039。s and 199039。s. ? Stage Number: 2. 1 x Minuteman 22 Gross Mass: 7,032 kg. Empty Mass: 795 kg. Thrust (vac): 27,300 kgf. Isp: 288 sec. Burn time: 66 sec. Diameter: m. Span: m. Length: m. Propellants: Solid No Engines: 1. SR19 Status: Out of production. Comments: Second stage of Minuteman 2. Used as second stage of Minotaur launch vehicle and various SDI targets in 198039。s. ? Stage Number: 3. 1 x Pegasus XL2 Gross Mass: 4,331 kg. Empty Mass: 416 kg. Thrust (vac): 15,653 kgf. Isp: 290 sec. Burn time: 73 sec. Isp(sl): 240 sec. Diameter: m. Span: m. Length: m. Propellants: Solid No Engines: 1. Pegasus XL2 Status: In Production. ? Stage Number: 4. 1 x Pegasus3 Gross Mass: 985 kg. Empty Mass: 203 kg. Thrust (vac): 3,525 kgf. Isp: 293 sec. Burn time: 65 sec. Isp(sl): 240 sec. Diameter: m. Span: m. Length: m. Propellants: Solid No Engines: 1. Pegasus3 Status: In Production. Missile Defense Sensor Difficulties ? Where should the sensor be located? – Air (Airborne Laser) – Sea (Aegis) – Space (SBIRs, DSP) ? What wavelength should the sensor be tuned to? – Plume signature ? IR, Visible, UV – Hard body heating ? IR, Visible – Atmospheric windows (boost phase) ? Broad band wavelength or discrete capability? – Blackbody radiator – Atomic/Molecular radiator – Sensor resolution is key Missile Defense ? Plume signatures ? Hard body recognition ? Wavelength bands Plume Signatures ? Boost Phase – Huge IR signature from plume – Differentiation with the hard body ? Where is the needle in the haystack? ? Don’t want to shoot down the plume ? Midcourse Phase – Plume expansion – Evasion (liquid systems for maneuvers) – Decoys – Excitation due to AO and Solar UV
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