Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

---

Atea-1

---

Status: Active. First Launch: 2009-11-30. Last Launch: 2009-11-30. Number: 1 . Payload: 2.00 kg (4.40 lb). Thrust: 6.70 kN (1,506 lbf). Gross mass: 60 kg (132 lb). Height: 6.00 m (19.60 ft). Diameter: 0.15 m (0.49 ft). Apogee: 150 km (90 mi).

Atea-1 was a two-stage (boost motor plus payload dart) sub-orbital vehicle. It could be launched by users from existing launch infrastructure or Rocket Lab provided complete launch and recovery services.

Rocket Lab's hybrid booster used a polymer-based fuel with liquid Nitrous Oxide. The engine's 45 kg propellant load was capable of producing a peak thrust of 6.7kN for up to 14.5s, resulting in a total impulse of 100 kN-s. The vehicle utilized composite materials for flight structures, pressure vessels and the combustion chamber. The entire vehicle had an inert, dry mass of less than 20 kg. The standard Atea-1 featured an in-house developed avionics package, recovery systems for land or sea, power supply and payload-avionics interface. Atea-1 characteristics:

• Inert shipping – no solid fuels or explosives
• ITAR free – Rocket Lab was able to export to customers from any friendly nation
• Land or sea-based recovery was possible
• Payload recovery – A GPS transceiver used the Inmarsat B satellite constellation to communicate the launch vehicle
• Max. Launch G-Force 15 g's
• Max. Velocity > Mach 5
• Standard Payload Size Ø 58mm x 900mm L

Payload: 2.00 kg (4.40 lb) to a 150 km altitude.

• Manu Karere - . Nation: New Zealand. Agency: RocketLab. Test vehicle.