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FlightSuccess28 September 2026

Telem Flight 1

First flight of Starseek's Telem rocket. 3D printed from PLA, this is our first rocket with a small dedicated avionics bay - a key part to reaching the goal of getting real-time telemetry to a groundstation from a rocket. For this flight we'll just use this bay to house a Mercury altimeter, still a commercial off-the-shelf altimeter and not capable of transmitting real-time telemetry to the GS, but an upgrade from the Nano used on the earlier Origin flights and will provide more detailed, more accurate telemetry. Telem is significantly heavier than Origin, more robust and uses a 6mm launch rail vs a 3mm one. Internally, Telem features segregated areas to house the parachute and shockcord - preventing entanglement upon deployment. Telem also has hot swappable motor mounts - enabling rapid re-use on the unlikely off-chance the rocket lands in one piece. Telem is designed to be launched with B class motors and above, requiring a minimum of 5N/s of impulse. We'll be launching with a B4-4 (5N/s) and will need a local wind speed below 17.9mph for a go on launch.

Units
Apogee
40.3 m
Max acceleration
9.3 G
Time to apogee
3.4 s
Max speed
20.6 m/s

Footage

Flight video
Launch pad video

Flight data

Hover or drag across the charts to read values

Altitude

m

02040BurnoutApogee

Velocity

m/s

-20020BurnoutApogee

Acceleration

G

020400s10sBurnoutApogee

Altitude

Apogee
40.3 m
Time to apogee
3.44 s

Velocity

Max ascent
20.6 m/s
At burnout
18.0 m/s
At ejection
-14.1 m/s
Max descent
21.1 m/s
Landing
6.2 m/s

Acceleration

Max during burn
9.3 G
Average during burn
3.0 G
Max on ascent
9.3 G
Max on descent
37.6 G

Timing

Motor burnout
0.85 s
Parachute ejection
4.96 s

Stability

Launch rail tilt
13.0°
Max tilt to burnout
39.1°

Rocket & motors

Starseek-Telem-1

Starseek-Telem-1

Height
457 mm
Diameter
28 mm
Weight
135 g
Total impulse
5.0 N·s
Target apogee
40 m
Recovery
Single-deploy Parachute

Motor configuration

  • Klima B4-4KlimaClass B · 18 mm · 5 N·s

Simulation predictions

Before flight, the rocket was simulated across 6 weather scenarios.

Target apogee
40 m
Expected apogee
10–45 m
Max wind — nominal
8 m/s
Max wind — turbulence
8 m/s

Retrospective

Overall a huge success. Motor ejection charge was approx 2 seconds too slow as per expectations from the simulation, as a result of us using a slightly undersized B6 motor vs a C6. The result was parachute deployment too late on descent, with a high impact speed on landing. All expected, as per simulation and accepted ahead of the flight. The key areas we were testing all passed - we successfully designed, 3D printed, assembled and flew a rocket with an avionics bay, and with a weight 4x heavier than our previous Origin rocket. Other improvements include the slow-motion groundstation filming and longer launch rod.