def test_stage_mass_sum(self):
stage0 = document.Stage("Booster")
stage0.components = [
document.Nosecone(document.Noseshape.CONE, 0, 0.7, 1.4),
document.Bodytube("body", 0, 1),
document.Bodytube("body", 24.1, 1),
]
self.assertEqual(24.8, stage0.mass)
def __init__(self, Isp, thrust, impulse, CD):
"""Take variables as input, build a rocket"""
# Create an engine document
engine = document.Engine('Motor')
# Set our design
engine.Isp = Isp
engine.thrust_avg = thrust
engine.I_total = impulse
# volume of propellent needed
prop_volume = engine.m_prop / self.prop_density
# Solve for the radius/length of the fuel grain (assume solid, end burning)
engine.diameter = 2 * (prop_volume / (2 * self.LD * pi))**(1 / 3.0)
engine.length = engine.diameter * self.LD
# Add a nose
nose = document.Nosecone(
document.Noseshape.TANGENT_OGIVE, # Shape
1.0, # shape_parameter
3.5, # mass
engine.diameter * self.Nose_LD, # Length
diameter=engine.diameter,
)
# Payload section
payload = document.Bodytube(
"Payload", # Name
3.5, # mass
0.33, # length, fixed
diameter=engine.diameter,
)
# Body section the size of the engine
body = document.Bodytube(
"Body", # Name
20.0, # mass
engine.length,
diameter=engine.diameter,
)
body.components = [engine]
# Rocket:
rocket = document.Rocket("Rocket")
rocket.aero_properties['CD'] = CD
stage0 = document.Stage("Sustainer")
stage0.components = [nose, payload, body]
rocket.stages = [stage0]
self.rocket = rocket
def test_write_simple_JSBSimAircraft(self):
rocket = rdoc.Rocket("Rocket")
stage0 = rdoc.Stage("Sustainer")
body = rdoc.Bodytube("body", 1, 0.2, diameter=0.33)
engine = rdoc.Engine("test engine")
engine.manufacturer = "Open Aerospace"
engine.length = 0.1
engine.diameter = 0.2
engine.Isp = 169
engine.m_prop = 1.0
engine.thrust_avg = 1000
body.components = [engine]
stage0.components = [
rdoc.Nosecone(rdoc.Noseshape.VONKARMAN, 1, 0.2, 1.0), body
]
rocket.stages = [stage0]
rocket.aero_properties['CD'] = [(0.1, 0.8), (0.5, 0.6), (1.0, 0.8)]
str_file = writers.JSBSimAircraft.dump(rocket)
# print(str_file)
# smoke test
self.assertGreater(len(str_file), 150)
def _load_bodytube(self, tree):
tube = rdoc.Bodytube('bodytube', 0, 0)
# Read data
for element in tree:
if element.tag == 'name':
tube.name = element.text
if element.tag == 'length':
tube.length = float(element.text)
if element.tag == 'thickness':
tube.thickness = float(element.text)
if element.tag == 'finish':
tube.surface_roughness = self._read_surface(element.text)
if element.tag == 'material':
tube.material_name = element.text
tube.density = float(element.get('density', 0))
if element.tag == 'color':
tube.color = self._read_color(element)
if element.tag == 'radius':
if 'auto' not in element.text:
self.radius = float(element.text)
if self.radius is not None:
tube.diameter = self.radius * 2.0
# Compute mass:
r1 = self.radius
r2 = r1 - tube.thickness
tube.mass = tube.density * (pi * tube.length * (r1**2 - r2**2))
return tube
def test_rocket_length_sum(self):
stage0 = document.Stage("Booster")
stage0.components = [
document.Nosecone("", 1, 0.7, 1.2),
document.Bodytube("body", 0, 1),
document.Bodytube("body", 24.1, 1),
]
stage1 = document.Stage("Booster")
stage1.components = [
document.Bodytube("body", 4.87, 1),
document.Fin('fin', 1, 1, 1, sweepangle=45.0, mass=0.1),
]
rocket = document.Rocket("Rocket")
rocket.stages = [stage0, stage1]
self.assertAlmostEqual(rocket.length, 5.2)
def test_rocket_length_sum_0(self):
# just rocket
rocket = document.Rocket("Rocket")
self.assertEqual(rocket.length, 0)
# rocket and a stage
stage0 = document.Stage("sustainer")
rocket.stages = [stage0]
self.assertEqual(rocket.length, 0)
# zero length components in rocket
stage0.components = [
document.Nosecone("", 1, 0.7, 0),
document.Bodytube("body", 0, 0),
document.Bodytube("body", 24.1, 0)
]
self.assertEqual(rocket.length, 0)
def test_spec_a_rocket(self):
rocket = document.Rocket("Rocket")
stage0 = document.Stage("Booster")
stage0.components = [
document.Nosecone(document.Noseshape.VONKARMAN, 1, 0.7, 1.2),
document.Bodytube("body", 1.2, 0.5),
]
rocket.stages = [stage0]
def test_color(self):
tube = document.Bodytube("body", 24.1, 1)
# As string:
tube.color = "Brown"
self.assertEqual(tube.color, "Brown")
# As tuple:
tube.color = (240, 12, 0)
self.assertEqual(tube.color, (240, 12, 0))
def test_write_document_smoke(self):
rocket = rdoc.Rocket("Rocket")
stage0 = rdoc.Stage("Sustainer")
stage0.components = [
rdoc.Nosecone(rdoc.Noseshape.VONKARMAN, 1, 0.2, 1.0),
rdoc.Bodytube("body", 1, 0.2),
]
rocket.stages = [stage0]
str_file = writers.Document().dump(rocket)
# print("Output:")
# print(str_file)
self.assertGreater(len(str_file), 10)
def test_write_simple_svg(self):
rocket = rdoc.Rocket("Rocket")
stage0 = rdoc.Stage("Sustainer")
stage0.components = [
rdoc.Nosecone(rdoc.Noseshape.VONKARMAN, 1, 0.2, 1.0, diameter=0.2),
rdoc.Bodytube("body", 1, 1.2, diameter=0.2),
]
rocket.stages = [stage0]
str_file = writers.SVG.dump(rocket)
# print("Output:")
# print(str_file)
# with open("testdraw.svg", "w") as testwrite:
# testwrite.write(str_file)
self.assertGreater(len(str_file), 10)
def test_component_name_slug(self):
# replace spaces with dashes
c = document.Bodytube("My Rocket Tube", 1, 1)
self.assertEqual(c.name_slug, "my-rocket-tube")
def test_no_color(self):
tube = document.Bodytube("body", 24.1, 1)
# No color defined
self.assertEqual(tube.color, None)
"""
# Build a rocket
# Nosecone
nose = document.Nosecone(
document.Noseshape.TANGENT_OGIVE, # Shape
1.0, # shape_parameter
3.5, # mass [kg]
1.0, # length [m]
diameter=0.28, # diameter [m] ~8 inches
)
# Payload section
payload = document.Bodytube(
"Payload", # Name
10.0, # mass [kg]
0.5, # length [m]
diameter=0.28, # diameter [m] ~8 inches
)
# Body section
body = document.Bodytube(
"Body", # Name
30.0, # mass
2.0, # length [m]
diameter=0.28, # diameter [m] ~8 inches
)
def rocket():
# parametric thrust curve:
