Update rendezvous.h to match new style

- Remove typedef from structs (LVLHRelativeState, CWValidityResult, CWGuidanceSolution)
- Convert comments to // style with descriptive comments above functions
- Move parameter comments inline
- Add return descriptions inline with function declarations
- Remove decorative section separators (// ======)
- Keep section headers as simple // comments

src/rendezvous.h

@@ -5,290 +5,183 @@
 #include "orbital_mechanics.h"
 #include "orbital_objects.h"
 
-/**
- * Rendezvous Module
- *
- * Provides Clohessy-Wiltshire (Hill's) equations-based guidance for spacecraft rendezvous.
- * Supports both spacecraft-to-spacecraft and spacecraft-to-body rendezvous in circular,
- * coplanar orbits.
- *
- * Validity Limits (dimensionless, scale with orbital radius):
- * - Spatial: 5% of orbital radius (x/r, y/r, z/r < 0.05)
- * - Time: 2.0 radians of orbital motion (n*dt < 2.0, ~1/3 orbit)
- */
+// Rendezvous Module
+// Provides Clohessy-Wiltshire (Hill's) equations-based guidance for spacecraft rendezvous.
+// Supports both spacecraft-to-spacecraft and spacecraft-to-body rendezvous in circular,
+// coplanar orbits.
+//
+// Validity Limits (dimensionless, scale with orbital radius):
+// - Spatial: 5% of orbital radius (x/r, y/r, z/r < 0.05)
+// - Time: 2.0 radians of orbital motion (n*dt < 2.0, ~1/3 orbit)
+
 
 // CW validity thresholds (dimensionless)
 #define CW_SPATIAL_LIMIT_FRACTION  0.05  // 5% of orbital radius
 #define CW_TIME_LIMIT_N_DT         2.0   // ~2 radians of orbital motion
 
 // Relative state in LVLH frame
-typedef struct {
+struct LVLHRelativeState {
     double radial;       // x: radial separation (positive outward)
     double along_track;  // y: along-track separation (positive in direction of motion)
     double cross_track;  // z: cross-track separation
     double v_radial;     // radial velocity
     double v_along_track;// along-track velocity
     double v_cross_track;// cross-track velocity
-} LVLHRelativeState;
+};
 
 // CW validity result
-typedef struct {
+struct CWValidityResult {
     bool spatial_valid;      // Within spatial limits
     bool time_valid;         // Within time limits
     bool overall_valid;      // Both spatial and time valid
     double spatial_fraction; // max(|x|,|y|,|z|) / orbital_radius
     double n_dt;             // n * time_since_linearization
     double expected_error;   // Estimated error percentage
-} CWValidityResult;
+};
 
 // CW guidance solution
-typedef struct {
+struct CWGuidanceSolution {
     bool valid;                        // Whether solution is valid
     double delta_v_magnitude;          // Required delta-v (m/s)
     double burn_direction_radial;      // Radial component (unit vector)
     double burn_direction_along_track; // Along-track component
     double burn_direction_cross_track; // Cross-track component
     double time_to_intercept;          // Time to reach target (s)
-} CWGuidanceSolution;
+};
+
 
-// ============================================================================
 // Utility Functions
-// ============================================================================
 
-/**
- * Transform Cartesian position/velocity to LVLH (Local Vertical Local Horizontal) frame
- *
- * LVLH basis vectors:
- * - r_hat: Radial direction (from parent to object)
- * - v_hat: Along-track direction (velocity direction for circular orbit)
- * - h_hat: Cross-track direction (orbit normal)
- *
- * @param position Position vector in inertial frame
- * @param velocity Velocity vector in inertial frame
- * @param parent_mass Mass of central body
- * @param out_r_hat Output: radial unit vector
- * @param out_v_hat Output: along-track unit vector
- * @param out_h_hat Output: cross-track unit vector
- */
+// Transform Cartesian position/velocity to LVLH (Local Vertical Local Horizontal) frame
+// LVLH basis vectors:
+// - r_hat: Radial direction (from parent to object)
+// - v_hat: Along-track direction (velocity direction for circular orbit)
+// - h_hat: Cross-track direction (orbit normal)
 void cartesian_to_lvlh_basis(
     Vec3 position,
     Vec3 velocity,
     double parent_mass,
-    Vec3* out_r_hat,
-    Vec3* out_v_hat,
-    Vec3* out_h_hat
+    Vec3* out_r_hat,    // Output: radial unit vector
+    Vec3* out_v_hat,    // Output: along-track unit vector
+    Vec3* out_h_hat     // Output: cross-track unit vector
 );
 
-/**
- * Project relative state onto LVLH basis
- *
- * @param rel_pos Relative position (target - chaser)
- * @param r_hat Radial unit vector
- * @param v_hat Along-track unit vector
- * @param h_hat Cross-track unit vector
- * @param rel_vel Relative velocity
- * @param out Relative state in LVLH frame
- */
+// Project relative state onto LVLH basis
 void project_to_lvlh_frame(
-    Vec3 rel_pos,
-    Vec3 r_hat,
-    Vec3 v_hat,
-    Vec3 h_hat,
-    Vec3 rel_vel,
-    LVLHRelativeState* out
+    Vec3 rel_pos,       // Relative position (target - chaser)
+    Vec3 r_hat,         // Radial unit vector
+    Vec3 v_hat,         // Along-track unit vector
+    Vec3 h_hat,         // Cross-track unit vector
+    Vec3 rel_vel,       // Relative velocity
+    LVLHRelativeState* out  // Output: Relative state in LVLH frame
 );
 
-/**
- * Transform LVLH relative state back to Cartesian
- *
- * @param lvlh Relative state in LVLH frame
- * @param r_hat Radial unit vector
- * @param v_hat Along-track unit vector
- * @param h_hat Cross-track unit vector
- * @param chaser_pos Chaser position (for absolute position calculation)
- * @param out_r_cart Output: relative position in Cartesian
- * @param out_v_cart Output: relative velocity in Cartesian
- */
+// Transform LVLH relative state back to Cartesian
 void lvlh_to_cartesian(
-    LVLHRelativeState* lvlh,
-    Vec3 r_hat,
-    Vec3 v_hat,
-    Vec3 h_hat,
-    Vec3 chaser_pos,
-    Vec3* out_r_cart,
-    Vec3* out_v_cart
+    LVLHRelativeState* lvlh,   // Relative state in LVLH frame
+    Vec3 r_hat,                // Radial unit vector
+    Vec3 v_hat,                // Along-track unit vector
+    Vec3 h_hat,                // Cross-track unit vector
+    Vec3 chaser_pos,           // Chaser position (for absolute position calculation)
+    Vec3* out_r_cart,          // Output: relative position in Cartesian
+    Vec3* out_v_cart           // Output: relative velocity in Cartesian
 );
 
-// ============================================================================
+
 // CW Validity Functions
-// ============================================================================
 
-/**
- * Check if CW equations are valid for current relative state
- *
- * Validity criteria:
- * - Spatial: max(|x|,|y|,|z|) / orbital_radius < 0.05
- * - Time: n * dt < 2.0 (where dt is time since last linearization)
- *
- * @param chaser Chaser spacecraft
- * @param target Target (body or spacecraft)
- * @param parent Central body
- * @param current_time Current simulation time
- * @return CWValidityResult with validity flags and error estimates
- */
-CWValidityResult check_cw_validity(
-    Spacecraft* chaser,
-    void* target,  // Can be Spacecraft* or CelestialBody*
-    CelestialBody* parent,
-    double current_time
+// Check if CW equations are valid for current relative state
+// Validity criteria:
+// - Spatial: max(|x|,|y|,|z|) / orbital_radius < 0.05
+// - Time: n * dt < 2.0 (where dt is time since last linearization)
+CWValidityResult check_cw_validity( // Returns: CWValidityResult with validity flags and error estimates
+    Spacecraft* chaser,     // Chaser spacecraft
+    void* target,           // Target (body or spacecraft)
+    CelestialBody* parent,  // Central body
+    double current_time     // Current simulation time
 );
 
-/**
- * Compute mean motion for given orbital radius
- *
- * @param parent_mass Mass of central body
- * @param orbital_radius Orbital radius
- * @return Mean motion n = sqrt(mu / a^3)
- */
-double compute_mean_motion(
-    double parent_mass,
-    double orbital_radius
+// Compute mean motion for given orbital radius
+double compute_mean_motion( // Returns: Mean motion n = sqrt(mu / a^3)
+    double parent_mass,     // Mass of central body
+    double orbital_radius   // Orbital radius
 );
 
-// ============================================================================
+
 // CW Guidance Functions
-// ============================================================================
 
-/**
- * Solve CW equations for rendezvous guidance
- *
- * Uses closed-form CW solutions to compute required delta-v for interception
- *
- * CW Equations (linearized relative motion):
- *   x'' - 2n*y' - 3n^2*x = 0
- *   y'' + 2n*x' = 0
- *   z'' + n^2*z = 0
- *
- * @param chaser Chaser spacecraft
- * @param target Target
- * @param parent Central body
- * @param time_to_intercept Desired time to intercept
- * @param current_time Current simulation time
- * @return CWGuidanceSolution with required delta-v
- */
-CWGuidanceSolution solve_cw_guidance(
-    Spacecraft* chaser,
-    void* target,
-    CelestialBody* parent,
-    double time_to_intercept,
-    double current_time
+// Solve CW equations for rendezvous guidance
+// Uses closed-form CW solutions to compute required delta-v for interception
+// CW Equations (linearized relative motion):
+//   x'' - 2n*y' - 3n^2*x = 0
+//   y'' + 2n*x' = 0
+//   z'' + n^2*z = 0
+CWGuidanceSolution solve_cw_guidance( // Returns: CWGuidanceSolution with required delta-v
+    Spacecraft* chaser,          // Chaser spacecraft
+    void* target,                // Target
+    CelestialBody* parent,       // Central body
+    double time_to_intercept,    // Desired time to intercept
+    double current_time          // Current simulation time
 );
 
-/**
- * Calculate optimal time to intercept for minimum delta-v
- *
- * For circular coplanar orbits, optimal intercept occurs at:
- * - Half the relative orbital period for along-track separation
- * - Adjusted for radial separation
- *
- * @param lvlh Relative state in LVLH frame
- * @param mean_motion Mean motion of reference orbit
- * @return Optimal time to intercept
- */
-double calculate_optimal_intercept_time(
-    LVLHRelativeState* lvlh,
-    double mean_motion
+// Calculate optimal time to intercept for minimum delta-v
+// For circular coplanar orbits, optimal intercept occurs at:
+// - Half the relative orbital period for along-track separation
+// - Adjusted for radial separation
+double calculate_optimal_intercept_time( // Returns: Optimal time to intercept
+    LVLHRelativeState* lvlh,   // Relative state in LVLH frame
+    double mean_motion         // Mean motion of reference orbit
 );
 
-// ============================================================================
+
 // Rendezvous Target Management
-// ============================================================================
 
-/**
- * Initialize rendezvous target structure
- *
- * @param target Target structure to initialize
- * @param target_index Index of target object
- * @param is_spacecraft_target True if target is spacecraft, false if body
- * @param approach_distance Distance to start approach phase
- * @param capture_distance Distance for capture
- * @param max_relative_velocity Max closing speed for capture
- */
+// Initialize rendezvous target structure
 void initialize_rendezvous_target(
-    RendezvousTarget* target,
-    int target_index,
-    bool is_spacecraft_target,
-    double approach_distance,
-    double capture_distance,
-    double max_relative_velocity
+    RendezvousTarget* target,         // Target structure to initialize
+    int target_index,                 // Index of target object
+    bool is_spacecraft_target,        // True if target is spacecraft, false if body
+    double approach_distance,         // Distance to start approach phase
+    double capture_distance,          // Distance for capture
+    double max_relative_velocity      // Max closing speed for capture
 );
 
-/**
- * Update rendezvous state machine based on current relative state
- *
- * State transitions:
- * - PLANNING -> APPROACHING: when within approach_distance
- * - APPROACHING -> MATCHING: when relative velocity < threshold
- * - MATCHING -> COMPLETE: when within capture_distance AND relative velocity < max
- * - Any -> FAILED: if CW validity is lost or distance increases
- *
- * @param chaser Chaser spacecraft
- * @param target Rendezvous target
- * @param parent Central body
- * @param current_time Current simulation time
- * @param target_obj Target object (Spacecraft* or CelestialBody*)
- */
+// Update rendezvous state machine based on current relative state
+// State transitions:
+// - PLANNING -> APPROACHING: when within approach_distance
+// - APPROACHING -> MATCHING: when relative velocity < threshold
+// - MATCHING -> COMPLETE: when within capture_distance AND relative velocity < max
+// - Any -> FAILED: if CW validity is lost or distance increases
 void update_rendezvous_state(
-    Spacecraft* chaser,
-    RendezvousTarget* target,
-    CelestialBody* parent,
-    double current_time,
-    void* target_obj  // Can be Spacecraft* or CelestialBody*
+    Spacecraft* chaser,     // Chaser spacecraft
+    RendezvousTarget* target,  // Rendezvous target
+    CelestialBody* parent,  // Central body
+    double current_time,    // Current simulation time
+    void* target_obj        // Target object (Spacecraft* or CelestialBody*)
 );
 
-// ============================================================================
+
 // Burn Application Functions
-// ============================================================================
 
-/**
- * Apply CW guidance burn to chaser spacecraft
- *
- * @param chaser Chaser spacecraft
- * @param solution CW guidance solution
- * @param parent Central body
- * @param current_time Current simulation time
- */
+// Apply CW guidance burn to chaser spacecraft
 void apply_cw_guidance_burn(
-    Spacecraft* chaser,
-    CWGuidanceSolution* solution,
-    CelestialBody* parent,
-    double current_time
+    Spacecraft* chaser,          // Chaser spacecraft
+    CWGuidanceSolution* solution, // CW guidance solution
+    CelestialBody* parent,       // Central body
+    double current_time          // Current simulation time
 );
 
-/**
- * Calculate relative velocity magnitude between chaser and target
- *
- * @param chaser Chaser spacecraft
- * @param target Target
- * @param parent Central body
- * @return Relative velocity magnitude (m/s)
- */
-double calculate_relative_velocity_magnitude(
-    Spacecraft* chaser,
-    void* target,
-    CelestialBody* parent
+// Calculate relative velocity magnitude between chaser and target
+double calculate_relative_velocity_magnitude( // Returns: Relative velocity magnitude (m/s)
+    Spacecraft* chaser,     // Chaser spacecraft
+    void* target,           // Target
+    CelestialBody* parent   // Central body
 );
 
-/**
- * Calculate distance between chaser and target
- *
- * @param chaser Chaser spacecraft
- * @param target Target
- * @return Distance (m)
- */
-double calculate_rendezvous_distance(
-    Spacecraft* chaser,
-    void* target
+// Calculate distance between chaser and target
+double calculate_rendezvous_distance( // Returns: Distance (m)
+    Spacecraft* chaser,  // Chaser spacecraft
+    void* target         // Target
 );
 
 #endif // RENDEZVOUS_H