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Pinot User-friendly system for Small Satellites

Pinot

Pressurization in orbit

Name of “Pinot” is an acronym of Pressurization in Orbit system and it was inspired by small satellites stored in a rocket resembled to a bunch of grapes.

Green Propellant

Pinot –”G” represents safe and environmental friendliness of the product. HNP225 has developed as green propellant for safer handlings at the launch site. As small satellites are resemble as Pinot Grapes, Pinot-Blanc wine is to represents fuel of Pinot-G.

Feature

High Pressure Gas regulations Free / Air-transportable package.

Enhanced Safety

Zero usage of Hydrazine Non-explosive Propellant.

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All in One

All required elements are integrated in one unit.
All You have to do is to plug into the connector.

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Cost Efficiency

Utilizing Additive Manufactured Thrusters.
Propellants are loaded and ready to be assemble.

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Enhanced Safety

Zero usage of Hydrazine
Non-explosive Propellant.

Handling safety will be enhanced with newly developed HNP225 (Green Propellant).
The propellant is officially endorsed as “Not a Class 1 substance” by NKKK*.
(NKKK: Nippon Kaiji Kentei Kyokai)

HNP225

HNP225 Green Propellant has been developed by IHI Aerospace.
It enables us to ship the product by air.

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All in One

All required elements are integrated in one unit.
All You have to do is to plug into the connector.

Integrated components

- Thrusters
- Propellant Tanks and feed system ( Filled in Japan and ship it to you)
- Built-in control electronics

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Cost Efficiency

Utilizing Additive Manufactured Thrusters

Additive Manufacturing technology enabled to reduce its lead-time and cost.

Less work at the launch site

Propellants are already loaded at shipping and ready to be assembled at the site.

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pinot-g

( TypeG-01 )Specification

Number of Thrusters 4
Number of Tanks 2
Propellant HNP225
Inlet Pressure Range [MPa] 0.3 – 2.4
Wet Mass [kg] 10
Usable Propellant [kg] 0.4
Dimensions [mm] F320 x 135
Operational Temp [℃] 0 – 60
Catalyst Bed Heater Power [W] 16 (for 4ea)
Electrical I/F RS – 422
Individual Thruster
 Thrust Range [N] 0.2 – 0.5
  Pulse 10000@ BBM
  Prop. Throughput [kg] 2.5@ BBM
  Longest Continues Firing [s] 1000@ BBM
  Accumulated Firing Time [hr] 1@ BBM
  MIB (BOL) [N – s] 0.004
  Isp (@ 0.5N) [s] 170

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