Aerospace MCP

from __future__ import annotations import sys from tests.tools.test_tools_common import StubModel, make_module class PropellerGeometry: def __init__(self, **kwargs): self.diameter_m = kwargs.get("diameter_m", 0.3) self.pitch_m = kwargs.get("pitch_m", 0.2) self.num_blades = kwargs.get("num_blades", 2) def test_propeller_and_uav_success(): def _bemt(geom, rpm_list, vel, alt): return [ StubModel( rpm=rpm, thrust_n=10.0, torque_nm=1.0, power_w=100.0, efficiency=0.8, advance_ratio=0.5, thrust_coefficient=0.1, power_coefficient=0.05, ) for rpm in rpm_list ] class UAVConfig: def __init__(self, **kw): self.mass_kg = kw.get("mass_kg", 5.0) self.wing_area_m2 = kw.get("wing_area_m2", 1.0) self.disk_area_m2 = kw.get("disk_area_m2", 0.0) class Battery: def __init__(self, **kw): self.capacity_ah = kw.get("capacity_ah", 10.0) self.voltage_nominal_v = kw.get("voltage_nominal_v", 22.2) self.mass_kg = kw.get("mass_kg", 1.0) class EnergyResult: flight_time_min = 30.0 range_km = 10.0 hover_time_min = None power_required_w = 200.0 energy_consumed_wh = 300.0 battery_energy_wh = 400.0 efficiency_overall = 0.8 sys.modules["aerospace_mcp.integrations.propellers"] = make_module( PropellerGeometry=PropellerGeometry, propeller_bemt_analysis=_bemt, UAVConfiguration=UAVConfig, BatteryConfiguration=Battery, uav_energy_estimate=lambda *a, **k: EnergyResult(), PROPELLER_DATABASE={"APC_10x4.7": {"diameter": 0.254}}, ) from aerospace_mcp.tools.propellers import ( get_propeller_database, propeller_bemt_analysis, uav_energy_estimate, ) assert "BEMT Analysis" in propeller_bemt_analysis( {"diameter_m": 0.3, "pitch_m": 0.2, "num_blades": 2}, {"rpm_list": [2000, 3000], "velocity_ms": 20.0, "altitude_m": 0.0}, {}, ) assert "UAV Energy" in uav_energy_estimate( {"mass_kg": 5.0, "wing_area_m2": 1.0}, {"capacity_ah": 10.0, "voltage_nominal_v": 22.2, "mass_kg": 1.0}, {}, ) assert "APC_10x4.7" in get_propeller_database() def test_propellers_import_errors(): import sys from aerospace_mcp.tools import propellers as prop_tools sys.modules["aerospace_mcp.integrations.propellers"] = make_module() assert "not available" in prop_tools.propeller_bemt_analysis({}, {}, {}).lower() assert "not available" in prop_tools.uav_energy_estimate({}, {}).lower() assert "not available" in prop_tools.get_propeller_database().lower() def test_propellers_exception_branches(): import sys def _boom(*a, **k): raise RuntimeError("boom") sys.modules["aerospace_mcp.integrations.propellers"] = make_module( PropellerGeometry=PropellerGeometry, propeller_bemt_analysis=_boom, UAVConfiguration=type("U", (), {}), BatteryConfiguration=type("B", (), {}), uav_energy_estimate=_boom, PROPELLER_DATABASE={"x": 1}, ) from aerospace_mcp.tools import propellers as ptools assert "error" in ptools.propeller_bemt_analysis({}, {}, {}).lower() assert "error" in ptools.uav_energy_estimate({}, {}).lower() # Force exception via database access class BadDB: def __iter__(self): raise RuntimeError("boom") sys.modules["aerospace_mcp.integrations.propellers"] = make_module( PROPELLER_DATABASE=BadDB() ) assert "error" in ptools.get_propeller_database().lower() def test_uav_energy_recommendations_branches(): import sys class UAV: def __init__(self, **kw): self.mass_kg = 5.0 self.wing_area_m2 = kw.get("wing_area_m2", 1.0) self.disk_area_m2 = kw.get("disk_area_m2", 0.0) class Bat: def __init__(self, **kw): self.capacity_ah = 10.0 self.voltage_nominal_v = 22.2 self.mass_kg = 1.0 # Case: very short (<10) and low efficiency class R1: flight_time_min = 5.0 range_km = None hover_time_min = 2.0 power_required_w = 100 energy_consumed_wh = 100 battery_energy_wh = 200 efficiency_overall = 0.5 # Case: short (<20) class R2(R1): flight_time_min = 15.0 efficiency_overall = 0.9 # Case: excellent (>120) class R3(R1): flight_time_min = 130.0 efficiency_overall = 0.9 sys.modules["aerospace_mcp.integrations.propellers"] = make_module( UAVConfiguration=UAV, BatteryConfiguration=Bat, uav_energy_estimate=lambda *a, **k: R1(), ) from aerospace_mcp.tools.propellers import uav_energy_estimate as uav out1 = uav( {"wing_area_m2": 1.0}, {"capacity_ah": 10.0, "voltage_nominal_v": 22.2, "mass_kg": 1.0}, ) assert "Very short" in out1 assert "Low system efficiency" in out1 sys.modules["aerospace_mcp.integrations.propellers"] = make_module( UAVConfiguration=UAV, BatteryConfiguration=Bat, uav_energy_estimate=lambda *a, **k: R2(), ) out2 = uav( {"wing_area_m2": 1.0}, {"capacity_ah": 10.0, "voltage_nominal_v": 22.2, "mass_kg": 1.0}, ) assert "Short flight time" in out2 sys.modules["aerospace_mcp.integrations.propellers"] = make_module( UAVConfiguration=UAV, BatteryConfiguration=Bat, uav_energy_estimate=lambda *a, **k: R3(), ) out3 = uav( {"wing_area_m2": 1.0}, {"capacity_ah": 10.0, "voltage_nominal_v": 22.2, "mass_kg": 1.0}, ) assert "Excellent endurance" in out3 # Multirotor branch (disk area) class UAV2(UAV): def __init__(self, **kw): super().__init__(**kw) self.wing_area_m2 = 0.0 self.disk_area_m2 = 2.0 sys.modules["aerospace_mcp.integrations.propellers"] = make_module( UAVConfiguration=UAV2, BatteryConfiguration=Bat, uav_energy_estimate=lambda *a, **k: R2(), ) out4 = uav( {"disk_area_m2": 2.0}, {"capacity_ah": 10.0, "voltage_nominal_v": 22.2, "mass_kg": 1.0}, ) assert "Rotor Disk Area" in out4