cmflannery · cmflannery · Nov 26, 2025 · Nov 26, 2025 · Nov 26, 2025 · Nov 26, 2025
diff --git a/.github/workflows/python-package.yml b/.github/workflows/python-package.yml
@@ -5,7 +5,7 @@ name: Python package
 
 on:
   push:
-    branches: [ master, cameron/revival ]
+    branches: [ master ]
   pull_request:
     branches: [ master ]
 

diff --git a/README.md b/README.md
@@ -1,8 +1,8 @@
-# OpenRocketEngine
+# Rocket
 
 ![Python package](https://github.com/cmflannery/openrocketengine/workflows/Python%20package/badge.svg)
 
-Tools for liquid rocket engine design and analysis.
+Tools for rocket vehicle design and analysis.
 
 ## Installation
 
@@ -16,14 +16,14 @@ brew install gcc
 sudo apt-get install gfortran
 
 # Then install
-pip install openrocketengine
+pip install rocket
 ```
 
 ## Quick Start
 
 ```python
-from openrocketengine import EngineInputs, design_engine, plot_engine_dashboard
-from openrocketengine.units import kilonewtons, megapascals
+from rocket import EngineInputs, design_engine, plot_engine_dashboard
+from rocket.units import kilonewtons, megapascals
 
 # Design from propellant selection (thermochemistry auto-calculated)
 inputs = EngineInputs.from_propellants(
@@ -50,10 +50,20 @@ plot_engine_dashboard(inputs, performance, geometry)
 - **Type-safe**: Runtime type checking with beartype
 - **Units handling**: Built-in `Quantity` class prevents unit errors
 - **Fast**: Numba-accelerated isentropic flow calculations
-- **Visualization**: Engine cross-sections, performance curves, dashboards
 - **NASA CEA**: Accurate thermochemistry via RocketCEA
+- **Visualization**: Engine cross-sections, performance curves, dashboards
 - **Nozzle contours**: Rao bell and conical nozzle generation with CSV export
 
+## Modules
+
+- `rocket.engine` - Engine design and performance analysis
+- `rocket.nozzle` - Nozzle contour generation
+- `rocket.units` - Physical quantity handling with units
+- `rocket.plotting` - Visualization tools
+- `rocket.propellants` - NASA CEA thermochemistry integration
+- `rocket.tanks` - Propellant and tank sizing (coming soon)
+
+
 ## References
 
 1. [GATech: Bell Nozzles](http://soliton.ae.gatech.edu/people/jseitzma/classes/ae6450/bell_nozzle.pdf)

diff --git a/docs/conf.py b/docs/conf.py
@@ -19,7 +19,7 @@
 
 # -- Project information -----------------------------------------------------
 
-project = "openrocketengine"
+project = "rocket"
 copyright = "2018, cmflannery"
 author = "cmflannery"
 
@@ -106,7 +106,7 @@
 # -- Options for HTMLHelp output ---------------------------------------------
 
 # Output file base name for HTML help builder.
-htmlhelp_basename = "openrocketenginedoc"
+htmlhelp_basename = "rocketdoc"
 
 
 # -- Options for LaTeX output ------------------------------------------------
@@ -132,8 +132,8 @@
 latex_documents = [
     (
         master_doc,
-        "openrocketengine.tex",
-        "openrocketengine Documentation",
+        "rocket.tex",
+        "rocket Documentation",
         "cmflannery",
         "manual",
     ),
@@ -145,7 +145,7 @@
 # One entry per manual page. List of tuples
 # (source start file, name, description, authors, manual section).
 man_pages = [
-    (master_doc, "openrocketengine", "openrocketengine Documentation", [author], 1)
+    (master_doc, "rocket", "rocket Documentation", [author], 1)
 ]
 
 
@@ -157,10 +157,10 @@
 texinfo_documents = [
     (
         master_doc,
-        "openrocketengine",
-        "openrocketengine Documentation",
+        "rocket",
+        "rocket Documentation",
         author,
-        "openrocketengine",
+        "rocket",
         "One line description of project.",
         "Miscellaneous",
     ),

diff --git a/docs/getting_started.rst b/docs/getting_started.rst
@@ -4,9 +4,9 @@ Getting Started
 Designing a Rocket Engine
 -------------------------
 
-What does OpenRocketEngine Do?
+What does Rocket Do?
 ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
-OpenRocketEngine will perform some basic calculations for rocket thrust chamber designs. Additionally,
+Rocket will perform some basic calculations for rocket thrust chamber designs. Additionally,
 it will be able to perform comparisions of different configurations.
 
 This code was originally created with the intention of automating vehicle sizing trade studies.
@@ -29,17 +29,17 @@ The inputs are classified as either required or optional.
 
 Configuration Files
 ~~~~~~~~~~~~~~~~~~~
-openrocketengine takes a configuration file as the only input, specifying the engine propellant properties, pressures desired,
+rocket takes a configuration file as the only input, specifying the engine propellant properties, pressures desired,
 and geometric design choices. Right now, there is only one possible combination of parameters that all have to be included in
 the config file. In the future, there may be additional options to automatically retrieve propellant properties from CEA.
 
 Config files are usually named with the engine name and the revision number with a '.cfg' suffix. I.e. RBF-rev01.cfg.
 
 A typical configuration file looks like the following::
 
-    # This is a test configuration file for openrocketengine
+    # This is a test configuration file for rocket
     #
-    # The parameters listed here are all the known parameters that openrocketengine can take as inputs.
+    # The parameters listed here are all the known parameters that rocket can take as inputs.
     # Refer to the official documentation for more implementation and usage details.
     name RBF1
     units SI
@@ -57,13 +57,13 @@ A typical configuration file looks like the following::
 
 Running the program
 ~~~~~~~~~~~~~~~~~~~
-openrocketengine can be fun from the command line with the command `rocket`::
+rocket can be fun from the command line with the command `rocket`::
 
     $ rocket RBF-rev01.cfg
 
 Outputs
 ~~~~~~~
-openrocketengine generates an output excel workbook with two sheets; one geometric parameters, and one for performance parameters.
+rocket generates an output excel workbook with two sheets; one geometric parameters, and one for performance parameters.
 
 
 Recommended Workflow

diff --git a/docs/index.rst b/docs/index.rst
@@ -1,9 +1,9 @@
-.. openrocketengine documentation master file, created by
+.. rocket documentation master file, created by
    sphinx-quickstart on Sun Jul 29 01:55:39 2018.
    You can adapt this file completely to your liking, but it should at least
    contain the root `toctree` directive.
 
-Welcome to openrocketengine's documentation!
+Welcome to rocket's documentation!
 ============================================
 
 .. toctree::
@@ -19,14 +19,14 @@ Welcome to openrocketengine's documentation!
 Overview
 --------
 
-OpenRocketEngine performs the calculations for simple analysis and design of rocket engines. For a
+Rocket performs the calculations for simple analysis and design of rocket engines. For a
 general overview of the philosophy behind designing rocket engines, refer to the `rocket propulsion
 section`_ of General Body of Knowledge (GBOK).
 
 Installation
 ------------
 
-OpenRocketEngine only supports python 3.5 and above. Functionality with other python releases is
+Rocket only supports python 3.5 and above. Functionality with other python releases is
 untested and not guaranteed. Basic usage::
 
     $ rocket config_file.cfg

diff --git a/openrocketengine/examples/__init__.py b/openrocketengine/examples/__init__.py
diff --git a/pyproject.toml b/pyproject.toml
@@ -1,14 +1,14 @@
 [project]
-name = "openrocketengine"
-version = "0.2.0"
-description = "OpenRocketEngine - Tools for liquid rocket engine design and analysis"
+name = "rocket"
+version = "0.3.0"
+description = "Rocket - Tools for rocket vehicle design and analysis"
 readme = "README.md"
 requires-python = ">=3.11"
 license = "MIT"
 authors = [
     { name = "Cameron Flannery" }
 ]
-keywords = ["rocket", "propulsion", "aerospace", "engineering", "nozzle"]
+keywords = ["rocket", "propulsion", "aerospace", "engineering", "nozzle", "tanks", "vehicle"]
 classifiers = [
     "Development Status :: 3 - Alpha",
     "Intended Audience :: Science/Research",
@@ -37,9 +37,8 @@ dev = [
 ]
 
 [project.urls]
-Homepage = "https://github.com/openrocketengine/openrocketengine"
-Documentation = "https://openrocketengine.readthedocs.io"
-Repository = "https://github.com/openrocketengine/openrocketengine"
+Homepage = "https://github.com/cmflannery/rocket"
+Repository = "https://github.com/cmflannery/rocket"
 
 [build-system]
 requires = ["hatchling"]

diff --git a/openrocketengine/__init__.py → rocket/__init__.py b/openrocketengine/__init__.py → rocket/__init__.py
@@ -1,30 +1,27 @@
-"""OpenRocketEngine - Tools for liquid rocket engine design and analysis.
+"""Rocket - Tools for rocket vehicle design and analysis.
 
 This package provides a comprehensive toolkit for designing and analyzing
-liquid propellant rocket engines using isentropic flow equations.
+rocket vehicles, including propulsion, tanks, and structures.
 
 Example:
-    >>> from openrocketengine import EngineInputs, design_engine
-    >>> from openrocketengine.units import newtons, megapascals, kelvin, meters, pascals
+    >>> from rocket import EngineInputs, design_engine
+    >>> from rocket.units import kilonewtons, megapascals
     >>>
-    >>> inputs = EngineInputs(
-    ...     thrust=newtons(5000),
-    ...     chamber_pressure=megapascals(2.0),
-    ...     chamber_temp=kelvin(3200),
-    ...     exit_pressure=pascals(101325),
-    ...     molecular_weight=22.0,
-    ...     gamma=1.2,
-    ...     lstar=meters(1.0),
-    ...     mixture_ratio=2.0,
+    >>> inputs = EngineInputs.from_propellants(
+    ...     oxidizer="LOX",
+    ...     fuel="RP1",
+    ...     thrust=kilonewtons(100),
+    ...     chamber_pressure=megapascals(7),
+    ...     mixture_ratio=2.7,
     ... )
     >>> performance, geometry = design_engine(inputs)
     >>> print(f"Isp: {performance.isp.value:.1f} s")
 """
 
-__version__ = "0.2.0"
+__version__ = "0.3.0"
 
 # Core engine design
-from openrocketengine.engine import (
+from rocket.engine import (
     EngineGeometry,
     EngineInputs,
     EnginePerformance,
@@ -38,7 +35,7 @@
 )
 
 # Nozzle contour generation
-from openrocketengine.nozzle import (
+from rocket.nozzle import (
     NozzleContour,
     conical_contour,
     full_chamber_contour,
@@ -47,22 +44,35 @@
 )
 
 # Visualization
-from openrocketengine.plotting import (
+from rocket.plotting import (
     plot_engine_cross_section,
     plot_engine_dashboard,
+    plot_mass_breakdown,
     plot_nozzle_contour,
     plot_performance_vs_altitude,
 )
 
 # Propellants and thermochemistry
-from openrocketengine.propellants import (
+from rocket.propellants import (
     CombustionProperties,
     get_combustion_properties,
     get_optimal_mixture_ratio,
     is_cea_available,
     list_database_propellants,
 )
 
+# Tank sizing
+from rocket.tanks import (
+    PropellantRequirements,
+    TankGeometry,
+    format_tank_summary,
+    get_propellant_density,
+    list_materials,
+    list_propellants,
+    size_propellant,
+    size_tank,
+)
+
 __all__ = [
     # Version
     "__version__",
@@ -89,10 +99,20 @@
     "plot_nozzle_contour",
     "plot_performance_vs_altitude",
     "plot_engine_dashboard",
+    "plot_mass_breakdown",
     # Propellants
     "CombustionProperties",
     "get_combustion_properties",
     "get_optimal_mixture_ratio",
     "is_cea_available",
     "list_database_propellants",
+    # Tanks
+    "PropellantRequirements",
+    "TankGeometry",
+    "size_propellant",
+    "size_tank",
+    "get_propellant_density",
+    "list_propellants",
+    "list_materials",
+    "format_tank_summary",
 ]
diff --git a/openrocketengine/engine.py → rocket/engine.py b/openrocketengine/engine.py → rocket/engine.py
@@ -1,4 +1,4 @@
-"""Engine module for OpenRocketEngine.
+"""Engine module for Rocket.
 
 This module provides the core data structures and computation functions for
 rocket engine design and analysis.
@@ -15,7 +15,7 @@
 
 from beartype import beartype
 
-from openrocketengine.isentropic import (
+from rocket.isentropic import (
     G0_SI,
     area_ratio_from_mach,
     bell_nozzle_length,
@@ -31,7 +31,11 @@
     thrust_coefficient,
     thrust_coefficient_vacuum,
 )
-from openrocketengine.units import (
+from rocket.propellants import (
+    get_combustion_properties,
+    get_optimal_mixture_ratio,
+)
+from rocket.units import (
     Quantity,
     kelvin,
     kg_per_second,
@@ -182,11 +186,6 @@ def from_propellants(
             ... )
             >>> print(f"Tc = {inputs.chamber_temp}")
         """
-        from openrocketengine.propellants import (
-            get_combustion_properties,
-            get_optimal_mixture_ratio,
-        )
-
         # Default exit pressure to 1 atm
         if exit_pressure is None:
             exit_pressure = pascals(101325)

diff --git a/rocket/examples/__init__.py b/rocket/examples/__init__.py
@@ -0,0 +1,2 @@
+"""Example scripts for Rocket."""
+