Probably the last time that a @vectorspacesys Block 1 vehicle (orbital/carbon fiber) shares an assembly line with an original Block 0 vehicle (Suborbital/Alum). Together here is the last Block 0.003 to fly in a month (without skins) & first Block 1 1001 vehicle for Oct launch.
Vector has completed an analysis of the nominal trajectory for a two-stage flight of the Vector-R. Thetimeline of mission events (Max Q, MECO, Stage Sep, etc..) is listed in the attached REF3. Max Q willoccur roughly 41 seconds after launch, where MECO will occur roughly 2 minutes and 7 seconds intothe launch. Stage separation will occur roughly 5 seconds after MECO. Maximum downrange distancewhere communication is required is 316 km. The maximum vehicle altitude will be 64 km, and themaximum slant range (crossrange) will be 242 km from the ground station to the vehicle.Under nominal flight conditions, after Stage 1 burnout and separation, Stage 2 is expected to tumbleand break up with an instantaneous impact point similar to that of Stage 1. These points will be offthe coast of Kodiak Island, approximately 316 km downrange into the Pacific Ocean; located at 54° 9'8.28''N, 149° 50' 14.64'' W.This application will cover a single flight of the Vector-R B0.101 launch vehicle. This launch willdemonstrate launch capability for the Vector-R B1 and B2 series. Separate STA applications will besubmitted for the follow-on Vector-R series.This application is for a single flight (estimated 3 hours of frequency usage) of the Vector launchvehicle. The launch vehicle maximum flight duration will be less than 10 minutes. Pre-flight transmitteroperation is expected to be less than 90 minutes. The maximum operating time is expected to be lessthan 3 hours from the commencement of launch activities. This is an absolute worst-case estimate asoperating longer than 30 to 60 minutes may require shut down of the transmitters due to thermalconcerns.The proposed launch site is Launch Pad C at Pacific Spaceport Complex - Alaska, located on KodiakIsland, Alaska at 57°25’50.57141” N, 152°21’10.93786” W. For this application we would like to submitapproval for the following range of dates; October 8th, 2018 to April 1st, 2019. However, the plannedlaunch date for Vector-R B0.101 is targeted for October 31st, 2018 from Kodiak Island, AK (PSCA)
1559-EX-ST-2018QuoteVector has completed an analysis of the nominal trajectory for a two-stage flight of the Vector-R. Thetimeline of mission events (Max Q, MECO, Stage Sep, etc..) is listed in the attached REF3. Max Q willoccur roughly 41 seconds after launch, where MECO will occur roughly 2 minutes and 7 seconds intothe launch. Stage separation will occur roughly 5 seconds after MECO. Maximum downrange distancewhere communication is required is 316 km. The maximum vehicle altitude will be 64 km, and themaximum slant range (crossrange) will be 242 km from the ground station to the vehicle.Under nominal flight conditions, after Stage 1 burnout and separation, Stage 2 is expected to tumbleand break up with an instantaneous impact point similar to that of Stage 1. These points will be offthe coast of Kodiak Island, approximately 316 km downrange into the Pacific Ocean; located at 54° 9'8.28''N, 149° 50' 14.64'' W.This application will cover a single flight of the Vector-R B0.101 launch vehicle. This launch willdemonstrate launch capability for the Vector-R B1 and B2 series. Separate STA applications will besubmitted for the follow-on Vector-R series.This application is for a single flight (estimated 3 hours of frequency usage) of the Vector launchvehicle. The launch vehicle maximum flight duration will be less than 10 minutes. Pre-flight transmitteroperation is expected to be less than 90 minutes. The maximum operating time is expected to be lessthan 3 hours from the commencement of launch activities. This is an absolute worst-case estimate asoperating longer than 30 to 60 minutes may require shut down of the transmitters due to thermalconcerns.The proposed launch site is Launch Pad C at Pacific Spaceport Complex - Alaska, located on KodiakIsland, Alaska at 57°25’50.57141” N, 152°21’10.93786” W. For this application we would like to submitapproval for the following range of dates; October 8th, 2018 to April 1st, 2019. However, the plannedlaunch date for Vector-R B0.101 is targeted for October 31st, 2018 from Kodiak Island, AK (PSCA)
What happened to B0.003? Has this flight been cancelled?
Our mobile launch pad @vectorspacesys (also known as TEL) being readied for a September Block 0 test launch and then shipment to Alaska for our Block 1 launch in October. Stay tuned
Our next @vectorspacesys Block 0 Vector-R undergoing testing on the mobile launch platform. Getting real ! The next gen Block 1 orbital vehicle will launch from this same platform in Alaska later this year
First, 1st stage engine test at our new engine test facility in Arizona.https://twitter.com/vectorspacesys/status/1041789850108735488
Greg Orndorff, Vector: planning a suborbital test flight of our Block 0 test vehicle this Friday in Mojave. Then start orbital launches from Kodiak, Alaska; awaiting FAA license. #AIAASpace
Greg also showed us a price list today.
Quote from: Steven Pietrobon on 09/07/2018 08:58 amWhat happened to B0.003? Has this flight been cancelled?I think this is the B0.003 flight. Maybe the paperwork has the model number instead of serial number? This permit is for a suborbital Block 0 flight.
Second orbital vehicle B1002 coming together @vectorspacesys Tucson facility for launch early 2019
We actually didn't have any launches scheduled for this week. We have a Block 0 vehicle that is going to fly in the next week or two and a Block 1 vehicle flying out of Kodiak Alaska later this year.
Interesting to see what Vector is patenting - nothing to do with rockets:https://patents.justia.com/assignee/vector-launch-inc
Enhanced liquid oxygen-propylene rocket enginePatent number: 10072612Abstract: Provided herein are various improvements to rocket engine components and rocket engine operational techniques. In one example, a rocket engine propellant injection apparatus is provided that includes a manifold formed into a single body by an additive manufacturing process and comprising a fuel cavity and an oxidizer cavity. The manifold also includes one or more propellant feed stubs, the one or more propellant feed stubs protruding from the manifold and formed into the single body of the manifold by the additive manufacturing process, with at least a first stub configured to carry fuel to the fuel cavity and at least a second stub configured to carry oxidizer to the oxidizer cavity. The manifold also includes a plurality of injection features formed by apertures in a face of the manifold, ones of the plurality of injection features configured to inject the fuel and the oxidizer for combustion.Type: GrantFiled: October 4, 2016Date of Patent: September 11, 2018Assignee: Vector Launch Inc.Inventors: Christopher Bostwick, John Garvey, Christopher Anderson, Eric Besnard
After a decade of testing, propylene rocket fuel may be ready for prime timeVector has received a patent for its liquid oxygen-propylene rocket engine.Eric Berger - 9/25/2018, 2:21 PM
Interesting: Jimmy is positioning Firefly as a "foreign" competitor:-https://twitter.com/jamesncantrell/status/1044608042296176640