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Vector

Vector-R Block 0.1 [Vector Space Systems]

Vector-R (mockup) [Vector Space Systems]

Vector-H [Vector Space Systems]

Vector is a small liquid fueled orbital launch vehicle, which is being developed by Vector Space Systems. Both stages use a proprietary densified Liquid Propylene (LPROP) and LOX as propellants.

The Vector launch vehicle was originally developped by Garvey Aerospace as the NLV-20 nanosat launch vehicle, which was later renamed Wolverine. With a stretched stage 2, it was developed into the Vector-R.

Vector-R is 13 m tall and 1.1 m in diameter and is build on carbon fiber structures. With a lift-off weight of 6060 kg it can put a 50 kg in a low inclination orbit or 25 kg into a polar orbit.

The vehicle uses three pressure fed engines of each 25 kN thrust for the first stage and one pressure fed engine of 3.5 kN thrust for the second stage. The first stage is designed to be reused. The baseline flight takes the first stage downrange 100 km until stage separation. The first stage deploys a parachute and aerial recovery and returns to the launch site for re-use. An optional electric powered third stage is also planned for higher performance at higher altitudes.

Vector-R is designed for small payloads up to 50 kg. CubeSats will be launched with out using deployers.

Planned launch sites are Kodiak (PCSA) for 90-100 orbits and Cape Canaveral AFS SLC-46 for 28-58 orbits. Also a barge launch capability off the coast of California is considered.

Vector Space Systems has already begun engine-level static fire testing and is working toward the start of sub-orbital test flights that will pathfind operations and manifest key technology experiments in Q3 2016, followed by large-scale sub-orbital test flights of a aluminium structure Block 0 prototype in 2017 and composite tank vehicle orbital launches in 2018.

An improved Vector-H is also planned with a payload capacity of 105 kg to low earth orbit. It is 16 m tall and has a lift off weight of 8690 kg.

Vector-H features a stretched stage one with five engines, also reusable, a full diameter stage 2 and reduced inert mass fractions. The optional electric powered third stage is also available. The first launch is planned for 2019.

First launch tests involve low altitude flights of a full size aluminium air-frame called Vector-R Block 0.1 with the technology of the Garvey/Vector P19 rocket and only one engine. Launch site is a rail launcher at the FAR site at Mojave.

Version Stage 1 Stage 2 Stage 3
Vector-R Block 0.1 (P-19h) Stage 1 frame / 1 × ? Dummy Stage 2 -
Vector-R Stage 1 / 3 × ? Stage 2 / ? -
Vector-RE1 Stage 1 / 3 × ? Stage 2 / ? Electric Stage
Vector-H Stretched Stage 1 / 5 × ? Widebody Stage 2 / ? -
Vector-HE1 Stretched Stage 1 / 5 × ? Widebody Stage 2 / ? Electric Stage
Performance (kg) LEO LPEO SSO GTO GEO MolO IP
Vector-R 50 37 - - - -
Vector-RE1 50 37 - - - -
Vector-H 105 82 - - - -
Vector-HE1 104 84 - - - -
No.  TypNo Type                   Date          LS           Payload 

 1    1    Vector-R Block 0.001   03.05.2017    FAR      *   (P19h R&D)
 2    1    Vector-R Block 0.002   03.08.2017    Cam      *   (R&D)


Planned

 x    1    Vector-R               xx.xx.2018    Kd ?         ?
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V1)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V2)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V3)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V4)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V5)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V6)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V7)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V8)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V9)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V10)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V11)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V12)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V13)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V14)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V15)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V16)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V17)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V18)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V19)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V20)
 x    x    Vector-RE1             xx.xx.201x    Kd           ICEYE (V21)
 x    1    Vector-H               xx.xx.2019    Kd           (York Space Systems)
 x    x    Vector-H               xx.xx.20xx    Kd           (York Space Systems)
 x    x    Vector-H               xx.xx.20xx    Kd           (York Space Systems)
 x    x    Vector-H               xx.xx.20xx    Kd           (York Space Systems)
 x    x    Vector-H               xx.xx.20xx    Kd           (York Space Systems)
 x    x    Vector-H               xx.xx.2022    Kd           (York Space Systems)
 

Launch sites:

Cam = Spaceport Camden, Woodbine, Georgia, USA USA
FAR = FAR Site, Mojave, California, USA USA
CC  = Cape Canaveral Air Force Station, Eastern Test Range, Cape Canaveral, Florida, USA USA
Kd  = Pacific Spaceport Complex - Alaska (Kodiak Launch Complex), Kodiak Island, Narrow Cape, Alaska, USA USA
  

References: