Neat to see a spacecraft taking form! What TPS material is used in the CST-100?
Will the service module, if that is what it's called, be attached for the environmental testing? If not, will the testing have a second round with a fully integrated system?
[p.24] The targeted CM landing is within a 1 km radius circle around the above center points. To allow margin based on the potential for changing winds, a 4 km radius circle will be cleared to allow a safe landing of the CM. All jettisoned pieces should nominally land within 8 km of this center point however, under worst case wind conditions, some of the smaller jettisoned parts could land up to 15 km from this center point. (See figures 2-3 and 2-4)...[p.25] The Starliner spacecraft jettisons several pieces of hardware during the landing phase of the mission (Figure 2-5). The FHS (less than 10 ft. in diameter, less than 2 feet tall, and less than 350 pounds) would jettison at approximately 30,000 feet altitude and parachute to the ground under two pilot chutes each less than 10 feet in diameter and weighing less than 15 pounds. The CM drogue parachutes (2 chutes each less than 25 feet in diameter and weighing less than 75 pounds) would jettison at approximately 8000 feet altitude just before deployment of the main parachutes and continue to the ground. Three additional pilot chutes, identical to the FHS chutes, pull out the main chutes before releasing and continuing to the ground. Seven mortar lids (thin plates less than 18 inches in diameter) and several mortar sabots (less than 18 inches and weighing less than 5 pounds) would jettison at various altitudes as part of the FHS and parachute deployments described above and would free fall to the ground. The Base Heat Shield (BHS), (less than 15 ft. in diameter, less than 4 feet tall and weighing less than 1700 pounds) would jettison at approximately 4400 feet altitude and would free fall until ground impact. The three main landing parachutes (less than 110 feet in diameter) would jettison at CM landing. All jettisoned pieces would land nominally land within an 8 km radius circle however, should the spacecraft land in a maximum wind condition scenario the higher energy (greater than 15 joules at landing) parts could drift up to 15 km from the center point. Some mortar lids having less than 15 joules at impact, and therefore below the risk threshold of injury to personnel or damage to structures (RCC 321-17), could land up to 18 km from the center point for these high wind cases. ... The CM would land on airbags that deploy just prior to landing. The weight of the CM at landing is less than 16,000 pounds, including dry weight, crew, and cargo....[p.38] 4.2.13 Hazardous Materials, Hazardous Waste, Solid Waste, and Pollution PreventionThe Starliner spacecraft contains the following hazardous materials:CM Fuel: Hydrazine (N2H4) – less than 200 poundsSM Fuel: Mono-Methyl Hydrazine (CH3(NH)NH2) – less than 2000 poundsSM Oxidizer: Dinitrogen Tetroxide (N2O4) – less than 3000 poundsLithium Ion Batteries: approximately less than 1000 poundsAmmonia-less than 0.5 poundsPerfluoropolyether heat transfer fluid (Galden HT) – CM: less than 110 pounds, SM: less than 100 poundsHFC-134a coolant – less than 2 poundsPyro material – less than 70 pounds...[p.74] Following a nominal landing, the only live ordnance devices would be in the NASA Docking System (NDS) Emergency Undock System and the Airbag Vent Cord Cable Cutters (AVCCC) in the landing airbag water drains and center airbag. These are in a safe configuration for landing and would require multiple failures to inadvertently fire post landing. In a failure case that required an emergency undock from the ISS, the docking system ordnance devices would be fired at undock so would already be expended during recovery operations. For an emergency water landing, the AVCCCs for the landing airbag water drains and center airbag fire at splashdown so would already be expended during the recovery operations. The majority of Starliner ordnance devices are Class 1 Division 1.4 per the Department of Transportation CFR 49, Part 173.50 (see definitions below). SureSep Expanding Tube Assemblies (XTAs), used to separate the Starliner from the launch vehicle during ascent, are division 1.1 and the drogue parachute mortars, fired as part of the parachute deploy sequence during landing, are division 1.2. All these division 1.1 and 1.2 ordnance would be expended prior to landing. The NDS ordnance is initiated via NASA standard detonators (NASA standard initiator + detonating booster assembly). The remainder of the ordnance devices, with the exception of the AVCC’s, are initiated via smart initiators. The AVCC has a built-in initiator. All ordnance devices receive command signals from ordnance controllers within the Starliner Command and Data Handling system. All ordnance is developed per MIL-HDBK-83578, Criteria for Explosive Systems and Devices used on Space Vehicles.The maximum explosive remaining unexploded in any ordnance after a nominal landing is just over half a gram. The total unexploded ordnance remaining on the vehicle after a nominal landing is approximately 30 grams.
ARTICLE: NASA announces test flight crew change for Boeing’s Starliner - https://www.nasaspaceflight.com/2019/01/nasa-test-flight-crew-change-boeings-starliner/ - by Chris Gebhardt Render by Nathan Koga for NSF/L2https://twitter.com/NASASpaceflight/status/1087823383256096768
Quote from: Chris Bergin on 01/22/2019 08:25 pmARTICLE: NASA announces test flight crew change for Boeing’s Starliner - https://www.nasaspaceflight.com/2019/01/nasa-test-flight-crew-change-boeings-starliner/ - by Chris Gebhardt Render by Nathan Koga for NSF/L2https://twitter.com/NASASpaceflight/status/1087823383256096768Names needed under the first picture.
Landing in Texas, huh. Could someone map out where the March Starliner reentry will be visible from? I need to know if and where to look.