Vector-R

Vector-R

File:Vector-R Diagram.svg
Function	Small satellite launch vehicle
	Vector Launch
	United States
Cost per launch	2–3 million USD
Size
	12 m
	1.2 m
	5,000 kg
Stages	2/3
Capacity
Payload to LEO
	60 kg
Payload to SSO
	26 kg
Associated rockets
Family	Vector (rocket family)
	Vector-H
Comparable	Electron, Falcon 1, Firefly Alpha
Launch history
Status	Active
Launch sites	Mojave Air and Space Port Spaceport Camden Pacific Spaceport Complex – Alaska (planned) MARS Pad OB (planned) Spaceport Florida Launch Complex 46 (planned)
Total launches	2
Success(es)	2
Failure	0
First stage
	1.2 m (3 ft 11 in)
	3 X Hadley
	15,000 lbf (67,000 N)
Propellant	Kerosene / LOX
Second stage
	.635 m (2 ft 1.0 in)
	1 X LP-2
	1,000 lbf (4,400 N)
Burn time	433 seconds
Propellant	Propylene / LOX

Vector-R (Vector Rapid) is a two-stage orbital expendable launch vehicle under development by the American aerospace company Vector Launch to cover the commercial small satellite launch segment (CubeSats). Vector Launch went bankrupt in December 2019 and re-emerged in October 2020. Two prototypes were launched in 2017.

The rocket completed a maiden test flight at low altitude in May 2017. Vector Launch was planning the maiden orbital launch from the Pacific Spaceport Complex in Alaska in 2019, but paused operation in August 2019 due to an uncertain financing situation.

An upgraded version of the Vector-R, called the Vector-H (Heavy), is in development as well.

Design

Vector-R plans to use two stages with a 1.2-meter (3.9 ft) diameter first stage and 0.635-meter (2.08 ft) diameter second stage, both filled with propylene/LOX propellant. The main body of the rocket will be constructed using a lightweight carbon composite material.

The launch vehicle's first stage was to be powered by three LP-1 LOX/propylene engines, delivering 81,000 newtons of force. The second stage was to be powered by one LP-2 LOX/propylene engine, delivering 4,400 newtons of force. The engines used a 3D-printed engine injector, designed with help from NASA's Science, Technology and Mission Directorate (STMD) Flight Opportunities program. This allows the injector to be produced as a single piece of hardware, instead of as individual components.

Vector was aiming the rocket at a launch cadence of 100 vehicles per year.

Block 0.1

The first two sub-orbital flight tests used the Vector-R Block 0.1 prototype model, which was a full size aluminum air-frame of the Vector-R but with only one first stage engine.

Vector-RE1

The Vector-RE1, a planned variant, was planned to use the same body as the standard Vector-R but include an electric powered third stage.

Intended usage

Vector-R was designed to launch a 60 kg (130 lb) payload to a 1,000 km (620 mi) Sun-synchronous orbit, suitable for CubeSats and other small satellites. The cost per launch was planned to be less than US$3 million, a price point that the company hoped would have allowed it to attract one hundred launches per year. Customers could have chosen to encapsulate their spacecraft in payload fairings provided by the company, which could be attached to the rocket shortly before launch, in several different configurations, such as fitting CubeSats dispensers or multiple satellites in a single fairing.

Vector used on-site payload integration for the early launches. However it was expected to be able to integrate payloads at their Arizona and California payload facilities and ship them to their launch sites.

Launch sites

File:Kluft-photo-aerial-Mojave-Spaceport-Sept-2009-Img 0227.jpg

Mojave Spaceport

Vector-R launched from the Mojave Air and Space Port and Spaceport Camden for its flight tests. It had completed one test flight from each pad. Flight B0.002 was also the first launch from Spaceport Camden.

Vector planned to use the LC-46 launch site in Florida and the Mid-Atlantic Regional Spaceport (MARS) Pad 0B for the Vector-R rocket, with the first all-up launches would have occurred from MARS Pad 0B. Additionally, Vector investigated adding more minimal infrastructure launch pads either located on land in the US, or to launch the rocket from barges on the ocean.

Vector had planned for the maiden orbital launch from Kodiak Spaceport Launch Complex earlier in 2019.

Launch statistics

Two low altitude suborbital test flights were performed in 2017.

Launch sites

0.5

1

1.5

2

2017

2018

2019

•   Mojave
•   Camden

Launch outcomes

0.5

1

1.5

2

2017

2018

2019

2020

2021

2022

2023

•   Failure
•   Partial failure
•   Success
•   Scheduled

Launch history

Flight №	Date / time (UTC)	Rocket configuration	Launch site	Payload	Payload mass	Orbit	Customer	Launch outcome
B0.001	3 May 2017 19:00	Vector-R (P-19H)	Mojave	None	—	Sub-orbital	Vector Launch	Success
	Flight test; maiden flight of the Vector-R; first engineering test, scaled down version; scheduled altitude 4,500 feet (1,400 m).
B0.002	2 August 2017 16:15	Vector-R	Camden	Two customer payloads.		Sub-orbital	Astro Digital	Success
	Flight test; full prototype version, upgraded flight systems; the launch was delayed due to ignition detection failure; launch took place from a trailer; the peak altitude was about 5,000 ft (1,500 m).

Planned launches

Due to the bankruptcy and subsequent re-emergence of Vector, These launches are uncertain.

Date / time (UTC)	Rocket configuration	Launch site	Payload	Orbit	Customer
TBA	Vector-R	TBA	TBA	LEO?	TBA
	B1001; First launch since re-emergence of bankruptcy.
TBA	Vector-R	Camden		Sub-orbital	Vector Launch
	B0.003; Flight-Test; Testing fairings, avionics, and thrust vector control
TBA	Vector-R	PSCA	Unicorn 2A Delfi-PQ 1	LEO	Alba Orbital Delft University of Technology
	First orbital and commercial flight of the Vector-R. PocketQube launch.
TBA	Vector-R	MARS LP-0B / PSCA	Landmapper-HD	LEO	Astro Digital
	Earth observation
TBA	Vector-R				Open Cosmos

See also

• Small-lift launch vehicle