Introducing the FBR
You have Nanosatellites to launch.
The FBR launches Nanosatellites to orbit.
You get a dedicated launch.
- No more waiting
- No more "close enough"
- No more limitations
- No more wasted consumables
- Orbital launch for $95K!
<
>
No more waiting
You get a dedicated launch. No more waiting for the
primary payload's schedule - launch on demand with as little as 2 weeks
notice.
<
>
No more "close enough"
Don't settle for the primary payload's launch trajectory - launch directly to your desired orbit.
<
>
No more limitations
No more propellant/energy limitations due to
primary payload risk concerns - launch anything you can convince the FAA
is safe.
<
>
No more wasted consumables
Don't waste your satellite's precious lifetime
getting into position from your drop off orbit - get inserted exactly
where you need to be.
<
>
Orbital launch for $95K!
Yep - $95K for 4kg, 3U Nanosatellites to any orbit
inclination between 0 degrees and SSO, up to 500 km altitude.
UTS was formed in 2007 and is dedicated to bringing spaceflight to the common man.
Our first step in this quest is to dramatically decrease
orbital launch costs with the FBR. The FBR uses unique engine and
structure technologies that
greatly reduce minimum vehicle scale and allow much simpler
operations.
Our team comes from various backgrounds and education -
business, engineering, military, marketing, finance, technology, and
media. Working together we have developed a revolutionary vehicle and
business concept.
FBR
The FBR is a near-SSTO that can lift 4 kg to a 500 km orbit.
Similar to the Atlas rocket, it is pressure stabilized to
achieve an incredible propellant mass ratio.
It is powered by a unique solid rocket motor that keeps the
propellant outside the combustion chamber until use, greatly increasing
system safety compared to both other solid and liquid
rocekts while also allowing incredibly high mass ratios.
We will launch from international waters south of the big
island of Hawaii. We can reach any inclination between 19 and 98
degrees.
(Expected, subject to change)
| Capabilities And Specifications |
| Height: | 3.2 m (10.5 ft) |
| Diameter: | 0.75 m (2.5 ft) |
| Gross Mass: | 700 kg |
| Dry Mass: | 10 kg |
| Max Propellant: | 685 kg |
| Max Thrust: | 7.5 kN |
| Stages: | nSSTO |
| Isp, Sea Level: | 180 seconds |
| Isp, Vacuum: | 270 seconds |
| Throttle Range: | 50:1 |
| Typical Burn Time: | 400 seconds |
| Propellant Type: | APCP |
| In Flight Restartable: | Yes |
