Icon of program: Grain Design Program Pro

Grain Design Program Pro for Windows

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Editors’ Review

Download.com staff
Grain Design Program Lite (GDP) is a robust tool for designing 2D rocket motor grains. It handles various shapes and complex burnback scenarios, offering precise calculations for gas generating devices.

  • Pros

    • Supports analytical and graphical calculation of diverse grain geometries.
    • Automatic burnback calculation including slivers and cracks.
    • Full transient burnback with ignitor and engine dynamics.
    • Allows different propellant types per segment.
    • Models nozzle erosion over time.

  • Cons

    • Limited to 2D grain designs.
    • Requires external drawing programs for complex shapes.
    • Graphical input relies on image file formats (.pcx, .gif, .bmp).
    • Tabular input required for erosion and some grain parameters.
Icon of program: Grain Design Program Pro

Grain Design Program Pro for Windows

Download now

Used Grain Design Program Pro for Windows?

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Full Specifications

GENERAL
Release
Latest update
Version
3.03
OPERATING SYSTEMS
Platform
Windows
Operating System
  • Windows XP
  • Windows 2000
  • Windows 10
  • Windows NT
  • Windows 98
  • Windows ME
  • Windows 95
Additional Requirements
None
POPULARITY
Total Downloads
318
Downloads Last Week
1
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Developer’s Description

By AED
Design rocket motors and other gas generating devices.
Grain Design Program Lite (GDP) is capable of calculating all 2D-grains, like stars, moonburners, slotted grains, and BATES grains. Geometries are devided into four categories as simple stars are treated analytically, simple cylinders (like BATES), treated analytically, and aAll other shapes are calculated graphically. The user provides a file (.pcx, .gif, or .bmp) of the grain. GDP automatically finds burning areas and calculates burnback. This options allows full burn-back, including slivers. Even cracks can easily be drawn with a drawing program, and modeled. Tabular input allows grain input by entering burning area and burning volume as function of burn depth. Full transient burn-back (include ignitor mass flow, and engine filling and blow-down). Each propellant segment can be of a different propellant type. Burn options for each propellant segment (start burning of a segment x seconds after ignition, or start burning of a segment after another segment has burned a certain distance). Nozzle erosion (tabulated input of erosion vs. time). Checks for possible erosive burning of the rocket motor. No total propellant mass limitations.
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