create parser test for apollo 11 models

gradle.properties

@@ -25,4 +25,4 @@ assertj_version    = 3.21.0
 junit_version      = 5.8.2
 
 # Version of published artifacts
-version            = 7.8.54
+version            = 7.8.55

language/src/test/java/parser/ApolloTest.java

@@ -0,0 +1,64 @@
+package parser;
+
+import de.monticore.lang.sysmlv2.SysMLv2Tool;
+import de.se_rwth.commons.logging.Log;
+import org.junit.jupiter.api.BeforeAll;
+import org.junit.jupiter.api.BeforeEach;
+import org.junit.jupiter.api.Test;
+import java.io.IOException;
+import java.nio.file.Files;
+import java.nio.file.Path;
+import java.util.stream.Collectors;
+import static org.assertj.core.api.Assertions.assertThat;
+
+/**
+ * Checks that the Apollo_11 can be parsed
+ * https://github.com/airbus/apollo-11-sysml-v2/tree/main
+ */
+public class ApolloTest {
+  private static final String APOLLO11_MODEL_PATH = "src/test/resources/apollo_11";
+
+  static SysMLv2Tool tool;
+
+  @BeforeAll
+  public static void setup() {
+    tool = new SysMLv2Tool();
+  }
+
+  @BeforeEach
+  public void init() {
+    tool.init();
+    Log.init();
+  }
+
+  @Test
+  public void testParseApollo11Models() throws IOException {
+    var models = Files.walk(Path.of(APOLLO11_MODEL_PATH))
+        .filter(p -> p.toString().endsWith(".sysml"))
+        .collect(Collectors.toList());
+
+    assertThat(models).hasSize(27);
+    var successful = 0;
+    var lines = 0;
+
+    Log.enableFailQuick(false);
+    for(var model: models) {
+      try {
+        var ast = tool.parse(model.toString());
+        if(Log.getFindings().isEmpty()) {
+          successful++;
+        }
+      } catch (Exception e) {
+        // Erstmal nur messen
+      }
+      finally {
+        lines += Log.getFindingsCount();
+        Log.clearFindings();
+      }
+    }
+
+    assertThat(successful).isEqualTo(27);
+    assertThat(Log.getFindings()).isEmpty();
+  }
+
+}

language/src/test/resources/apollo_11/AnalysisPackage.sysml

@@ -0,0 +1,157 @@
+//
+// Copyright (c) 2026 AIRBUS and its affiliates.
+// This Source Code Form is subject to the terms of the Mozilla Public
+// License, v. 2.0. If a copy of the MPL was not distributed with this
+// file, You can obtain one at http://mozilla.org/MPL/2.0/.
+//
+
+package AnalysisPackage {
+
+	private import MissionPackage::*;
+	private import CoSMAPackage::*;
+	private import CoSMAQuantitiesAndUnitsPackage::*;
+	private import CoSMAPackage::*;
+	private import CalculationsPackage::*;
+	private import ISQ::*;
+	private import SI::*;
+	private import TechnicalComponentsPackage::*;
+	private import Apollo11MissionExecutionPackage::*;
+
+	analysis def SystemPowerAnalysis {
+		doc /* Analysis to calculate the total power generation, load, and margin for a composite system by iterating over its parts. */
+		subject systemToAnalyze : System;
+
+		out totalPowerGenerated :> ISQ::power = rollupPowerGeneration(systemToAnalyze);
+		out totalPowerLoad :> ISQ::power = rollupPowerConsumption(systemToAnalyze);
+		out powerMargin :> ISQ::power = calculatePowerMargin(totalPowerGenerated, totalPowerLoad);
+
+		assert constraint {
+			powerMargin > 0[W]
+		}
+	}
+
+	analysis Apollo11MissionSystemPowerAnalysis : SystemPowerAnalysis {
+		doc /* Runs the iterative power analysis on the entire Apollo 11 Mission System. */
+
+		subject apollo11MissionSystem : System;
+	}
+
+	analysis def SystemMassAnalysis {
+		doc /* An analysis to track the total mass of the spacecraft throughout the mission (mass budget). */
+		subject apollo11Mission : Apollo11Mission;
+
+		in initialLaunchMass :> ISQ::mass;
+		in propellantMassPerStage :> ISQ::mass[*];
+		in jettisonedComponentMass :> ISQ::mass[*];
+		out massAfterBurn :> ISQ::mass = calculateMassBudgetStep(initialLaunchMass, propellantMassPerStage, jettisonedComponentMass);
+	}
+
+	analysis Apollo11MissionSuccessAnalysis {
+		doc /* A top-level analysis to evaluate whether the primary mission objectives were met. */
+		subject apollo11Mission : Apollo11MissionIndividual;
+
+		out overallMissionSuccess : ScalarValues::Boolean = evaluateMissionSuccess(apollo11Mission.crewReturnedSafely, apollo11Mission.softLandingAchieved, apollo11Mission.requiredSamplesReturned, apollo11Mission.instrumentsDeployed);
+
+		assert constraint {
+			overallMissionSuccess = true;
+		}
+	}
+
+	analysis Apollo11LifecycleReliabilityAnalysis {
+		doc /* An analysis to predict the probability of mission success based on the reliability of critical components over time. */
+		subject apollo11Mission : Apollo11Mission;
+
+		out cmReliability : RatioValue = calculateReliability(
+			apollo11Mission.apollo11MissionSystem.spacecraft.csm.commandModule.failureRate,
+			apollo11Mission.plannedDuration
+		);
+		out smReliability : RatioValue = calculateReliability(
+			apollo11Mission.apollo11MissionSystem.spacecraft.csm.serviceModule.failureRate,
+			apollo11Mission.plannedDuration
+		);
+		out lmReliability : RatioValue = calculateReliability(
+			apollo11Mission.apollo11MissionSystem.spacecraft.lm.failureRate,
+			apollo11Mission.plannedDuration / 2 // LM is only used for half the mission
+		);
+	}
+
+	analysis def MissionCostAnalysis {
+		doc /* A budgetary analysis to determine the total financial cost of a mission. */
+		subject mission : Mission;
+
+		out totalMissionCost :> currency = sumCosts(mission.researchAndDevelopmentCost, mission.manufacturingCost, mission.operationsCost, mission.personnelCost);
+
+	}
+
+	analysis Apollo11MissionCostAnalysis : MissionCostAnalysis {
+		subject apollo11Mission : Apollo11Mission;
+	}
+
+	analysis Apollo11MissionDeltaVBudgetAnalysis {
+		doc /* Performs a full delta-v budget analysis for the Apollo 11 mission to verify that the propulsive capabilities of the hardware can meet the demands of the mission trajectory. */
+
+		subject apollo11Mission : Apollo11Mission;
+
+		launchVehicle : SaturnV = apollo11Mission.apollo11MissionSystem.launchVehicle;
+		spacecraft : ApolloSpacecraft = apollo11Mission.apollo11MissionSystem.spacecraft;
+
+		sic = launchVehicle.stage1;
+		sii = launchVehicle.stage2;
+		sivb = launchVehicle.stage3;
+		iu = launchVehicle.instrumentUnit;
+		les = spacecraft.launchEscapeSystem;
+		sla = spacecraft.spacecraftLMAdapter;
+		cm = spacecraft.commandServiceModule.commandModule;
+		sm = spacecraft.commandServiceModule.serviceModule;
+		lmds = spacecraft.lunarModule.lunarModuleDescentStage;
+		lmas = spacecraft.lunarModule.lunarModuleAscentStage;
+
+		// Define mass stacks for each phase
+		fullStack = (sii, sivb, iu, sla, sm, cm, lm);
+		secondStageStack = (sivb, iu, sla, sm, cm, lm);
+		tliStack = (sla, sm, cm, lm);
+		spacecraftStack = (sm, cm, lm);
+
+		// Calculate delta-v capability for each stage
+		dv_stage1 = calculateLaunchStageDeltaV(sic, fullStack);
+		dv_stage2 = calculateLaunchStageDeltaV(sii, secondStageStack);
+		dv_stage3_tli = calculateLaunchStageDeltaV(sivb, spacecraftStack);
+
+		dv_csm = calculateSpacecraftBurnDeltaV(sm);
+		dv_lm_descent = calculateSpacecraftBurnDeltaV(lmds);
+		dv_lm_ascent = calculateSpacecraftBurnDeltaV(lmas);
+
+		// Required delta-v for phases
+		dv_required_tli = calculateTliDeltaV(3.986E14 ['m³⋅s⁻²'], 6563 ['km'], 384400 ['km']);
+		dv_required_loi = calculateLoiDeltaV(1000 ['m⋅s⁻¹'], 4.9E12 ['m³⋅s⁻²'], 1839 ['km']);
+		dv_required_leo = 9400 ['m⋅s⁻¹'];
+		dv_required_landing = 2100 ['m⋅s⁻¹'];
+		dv_required_ascent = 1870 ['m⋅s⁻¹'];
+		dv_required_tei = 1000 ['m⋅s⁻¹'];
+
+		// S-IC and S-II combine to provide most of the velocity to orbit.
+		ascentCapability = dv_stage1 + dv_stage2;
+		ascentMargin = ascentCapability - dv_required_leo;
+
+		// S-IVB performs the final orbit insertion and the TLI burn.
+		tliMargin = dv_stage3_tli - dv_required_tli;
+
+		// Service module performs LOI and TEI
+		loiMargin = dv_csm - (dv_required_loi + dv_required_tei);
+
+		// LM Descent Stage must have enough delta-v to land
+		landingMargin = dv_lm_descent - dv_required_landing;
+
+		// LM Ascent Stage must have enough delta-v to reach orbit
+		ascentMargin_lunar = dv_lm_ascent - dv_required_ascent;
+
+		// The mission is feasible if all margins are positive.
+		assert constraint {
+			ascentMargin > 0 ['m⋅s⁻¹'] and
+			tliMargin > 0 ['m⋅s⁻¹'] and
+			loiMargin > 0 ['m⋅s⁻¹'] and
+			landingMargin > 0 ['m⋅s⁻¹'] and
+			ascentMargin_lunar > 0 ['m⋅s⁻¹']
+		}
+	}
+}