sls block 2 payload

SLS Block 1 Crew.

%��������� Eight months after the conclusion of the final Space Shuttle mission, the iconic winged-vehicle’s successor continues to take shape at various NASA centers, as the U.S. space agency further defines the Space Launch System requirements – as seen in the expansive SLS Program Launch Vehicle Specifications document, which provides details on the latest design baseline requirements for SLS Block 1, Block 1A, and Block 2 configurations.As NASA refocuses its goals on exploration beyond Low Earth Orbit (LEO), one of the primary and important characteristics of the new SLS rocket is its heritage with the Space Shuttle and diversification in terms of payload requirements and Block variant requirements.To this end, the SLS Element Performance and Mass Constraints for the SLS’s Core Stage and Upper Stage engines – including the Shuttle holdover RS-25D engines, the under-development RS-25E engines, and the J-2X engine – have all been defined.For maximum power levels (percent RPL), the RS-25Ds will obtain 109 percent of rated thrust and have a standard throttle range of 65-109 percent – the same throttle range that could have been utilized by the engines with the Shuttle orbiters… though Shuttle typically defined a lower-limit 67 percent throttle and upper-limit 104.5 percent throttle range, with 109 percent reserved for abort contingencies.The RS-25D engines themselves will each weigh 7,816 lbs.The propellant mixture ratio range will be 5.85 to 6.10 +/- 1 percent with a Minimum Vacuum Thrust at Maximum power (lbf) of 511, 117 lbf and a Min Vac Isp (Specific Impulse) at maximum power (s) of 452.3 s.Comparatively, the RS-25E engines, which will enter service once the RS-25D manifest is depleted due to the lack of recoverability of the Core Stage of SLS to which the RS-25Ds will be mounted, will operate with a maximum power level (percent RPL) of 111 percent, a throttle range of 65-111 percent, and a total mass that is Not To Exceed 8,156 lbs.The RS-25Es will have a mixture ratio of 5.85 to 6.10 +/- 1 percent (identical to the RS-25Ds),  a min vac thrust at max power requirement of 515,700 lbf, and a min vac Isp at max power of 450.8 s.The mixture ratio will the 5.5 with a min vac thrust at max power of 276,450 lbf and a min vac Isp at max power of 435 s.In addition to the Core and Upper Stage engine specifications, the requirements for the Solid Rocket Boosters are also laid out in the SLSP Launch Vehicle Specification document.This represents a total solid PBAN propellant weight in each SRB of 1,170,875 lbs – for a total of 2,341,750 lbs of solid propellant for the SLS vehicle.Despite each SRB having one additional propellant segment over those used by the Space Shuttle launch vehicle, the SRBs for SLS will not be recoverable or reusable – As stated in the SLSP Launch Vehicle Specification document, “The Block 1 SLS configuration (~70 metric ton) is comprised of a 27.6-foot nominal outer wall diameter (cryogenic pressure vessels excluding thermal protection system foam and flanges) core stage, with propulsion provided by two five-segment PBAN solid rocket boosters and four RS-25D liquid hydrogen (LH2)/liquid oxygen (LO2) core stage engines.”While the RS-25D engines are holdovers from the Space Shuttle Program, as are the SRB casings themselves, the 5-segment SRB is a direct heritage component of the now-defunct Constellation Program and the impressive work accomplished by ATK in developing and testing the new hardware elements required for the massive 5-segment solids.Moreover, the basic design constraints for the Block 1 SLS include inclusion of an avionics unit and developmental flight instrumentation to verify vehicle performance during ascent.The SLS’s Block 1 Core Stage engines will include pogo suppression as prominently seen during the Apollo Saturn V era, and all Core Stage and Booster designs will include implementation of imagery assets for “mission critical and safety related events.”There will be no Reaction Control System (RCS) on the core stage.The Core Stage of the SLS Block 1 will also need to be “structurally stable without pressurization during all phases of ground transportation and processing,” incorporate STS/Shuttle heritage booster separation hardware, and contain an ICPS for “Orion MPCV Early Test Flight missions.”In all, the SLS Block 1 will stand 320.9 feet tall with a Core Stage height of 212.2 feet – a height roughly equivalent to the elevation of the Gaseous Oxygen Vent arm used to vent gaseous oxygen away from the top of the Space Shuttle stack… a point that will now be 108 feet below the top of the SLS Block 1.For the cargo configuration of the SLS Block 1A vehicle, the payload fairing will be a two-piece fairing to “maximize the payload volume while still retaining the ability to process the payload and vehicle in existing Kennedy Space Center (KSC) facilities.”Design limitations/requirements/constraints for the SLS Block 1A configuration include payload adapter(s), an avionics unit, and developmental flight instrumentation.The Core Stage engines will continue to include pogo oscillation suppression technology – as will the boosters’ engines if the boosters are liquid The Core Stage and Boosters will still provide all assets necessary for imagery of the launch vehicle through “mission critical and safety related events,” and no RCS will be including on the Core Stage.Moreover, the Core Stage and Booster (if liquid) will need to be “structurally stable without pressurization during all phases of ground transportation and processing.”Booster separation will be provided by “booster element” and will not necessarily be heritage from Shuttle.

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