From 486d7458bb195596020c4a74b2db92532bf8b58a Mon Sep 17 00:00:00 2001 From: Mauco03 <marco.gaibotti@skywarder.eu> Date: Wed, 12 Feb 2025 21:21:24 +0100 Subject: [PATCH] [handle-value-conversion][missions] Replaced xCg with xcg --- classes/misc/WindMatlab.m | 2 +- functions/miscellaneous/singleGArun.m | 2 +- functions/simulations/stdStability.m | 2 +- .../2021_Lynx_Portugal_October/config/rocketConfig.m | 10 +++++----- .../config/rocketConfig.m | 10 +++++----- .../2022_Pyxis_Portugal_October/config/rocketConfig.m | 10 +++++----- .../config/rocketConfig.m | 10 +++++----- .../2023_Gemini_Portugal_October/config/rocketConfig.m | 10 +++++----- .../config/rocketConfig.m | 10 +++++----- .../2024_Lyra_Portugal_October/config/rocketConfig.m | 10 +++++----- .../config/rocketConfig.m | 10 +++++----- .../config/rocketConfig.m | 10 +++++----- 12 files changed, 48 insertions(+), 48 deletions(-) diff --git a/classes/misc/WindMatlab.m b/classes/misc/WindMatlab.m index b47c45d..393a034 100644 --- a/classes/misc/WindMatlab.m +++ b/classes/misc/WindMatlab.m @@ -1,4 +1,4 @@ -classdef WindMatlab < Component +classdef WindMatlab < Config % WindMatlab: Represents matlab wind variables. % % Constructor: diff --git a/functions/miscellaneous/singleGArun.m b/functions/miscellaneous/singleGArun.m index 483a62a..f30e478 100644 --- a/functions/miscellaneous/singleGArun.m +++ b/functions/miscellaneous/singleGArun.m @@ -78,7 +78,7 @@ input.fltcon.ALT = environment.z0; input.fltcon.NALPHA = length(input.fltcon.ALPHA); % [-] Number of alphas input.fltcon.NMACH = length(input.fltcon.MACH); -xcg = rocket.xCg; +xcg = rocket.xcg; input.refq.XCG = xcg(1); [coeff] = dissileMatcom(input); diff --git a/functions/simulations/stdStability.m b/functions/simulations/stdStability.m index 969c9fc..7898fa5 100644 --- a/functions/simulations/stdStability.m +++ b/functions/simulations/stdStability.m @@ -58,7 +58,7 @@ alpha = stability.interp.alpha(end); beta = stability.interp.beta(end); alt = env.z0 + env.effectiveRampAltitude; mach = stability.interp.mach(end); -xcg = interpLinear(rocket.motor.time, rocket.xCg, tPad); +xcg = interpLinear(rocket.motor.time, rocket.xcg, tPad); %%% create dissileMatcom input data struct dissileVars.alpha = sort([-rad2deg(alpha), rad2deg(alpha), 0, -1, 1]); diff --git a/missions/2021_Lynx_Portugal_October/config/rocketConfig.m b/missions/2021_Lynx_Portugal_October/config/rocketConfig.m index 692225f..4df34a1 100644 --- a/missions/2021_Lynx_Portugal_October/config/rocketConfig.m +++ b/missions/2021_Lynx_Portugal_October/config/rocketConfig.m @@ -23,7 +23,7 @@ parafoil = Parafoil(); parafoil.length = 0.31; % [m] Total bay length parafoil.mass = 0; % [kg] Total bay mass parafoil.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -parafoil.xCg = 0; % [m] Cg relative to bay upper side +parafoil.xcg = 0; % [m] Cg relative to bay upper side % !!!!! parafoil.noseLength = 0.26; % [m] Nosecone length @@ -39,7 +39,7 @@ recovery = Recovery(); recovery.length = 0; % [m] Total bay length recovery.mass = 0; % [kg] Total bay mass recovery.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -recovery.xCg = 0; % [m] Cg relative to bay upper side +recovery.xcg = 0; % [m] Cg relative to bay upper side % !!!!! %% ELC @@ -49,7 +49,7 @@ electronics = Electronics(); electronics.length = 0; % [m] Total bay length electronics.mass = 0; % [kg] Total bay mass electronics.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -electronics.xCg = 0; % [m] Cg relative to bay upper side +electronics.xcg = 0; % [m] Cg relative to bay upper side % !!!!! %% ARB @@ -59,7 +59,7 @@ airbrakes = Airbrakes(); airbrakes.length = 0; % [m] Total bay length airbrakes.mass = 0; % [kg] Total bay mass airbrakes.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -airbrakes.xCg = 0; % [m] Cg relative to bay upper side% !!!!! +airbrakes.xcg = 0; % [m] Cg relative to bay upper side% !!!!! % !!!!! airbrakes.enabled = true; % If true, multiple and smooth airbrakes opening will be simulated @@ -93,7 +93,7 @@ rear.position = 0; % [m] offset fr rear.length = 0; % [m] Total bay length rear.mass = 0; % [kg] Total bay mass rear.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -rear.xCg = 0; % [m] Cg relative to bay upper side +rear.xcg = 0; % [m] Cg relative to bay upper side % !!!!! rear.boatType = ''; % [-] Boat type diff --git a/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m b/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m index fa07215..83f6476 100644 --- a/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m +++ b/missions/2021_Lynx_Roccaraso_September/config/rocketConfig.m @@ -23,7 +23,7 @@ parafoil = Parafoil(); parafoil.length = 0.31; % [m] Total bay length parafoil.mass = 0; % [kg] Total bay mass parafoil.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -parafoil.xCg = 0; % [m] Cg relative to bay upper side +parafoil.xcg = 0; % [m] Cg relative to bay upper side % !!!!! parafoil.noseLength = 0.26; % [m] Nosecone length @@ -39,7 +39,7 @@ recovery = Recovery(); recovery.length = 0; % [m] Total bay length recovery.mass = 0; % [kg] Total bay mass recovery.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -recovery.xCg = 0; % [m] Cg relative to bay upper side +recovery.xcg = 0; % [m] Cg relative to bay upper side % !!!!! %% ELC @@ -49,7 +49,7 @@ electronics = Electronics(); electronics.length = 0; % [m] Total bay length electronics.mass = 0; % [kg] Total bay mass electronics.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -electronics.xCg = 0; % [m] Cg relative to bay upper side +electronics.xcg = 0; % [m] Cg relative to bay upper side % !!!!! %% ARB @@ -59,7 +59,7 @@ airbrakes = Airbrakes(); airbrakes.length = 0; % [m] Total bay length airbrakes.mass = 0; % [kg] Total bay mass airbrakes.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -airbrakes.xCg = 0; % [m] Cg relative to bay upper side% !!!!! +airbrakes.xcg = 0; % [m] Cg relative to bay upper side% !!!!! % !!!!! airbrakes.enabled = true; % If true, multiple and smooth airbrakes opening will be simulated @@ -93,7 +93,7 @@ rear.position = 0; % [m] offset fr rear.length = 0; % [m] Total bay length rear.mass = 0; % [kg] Total bay mass rear.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -rear.xCg = 0; % [m] Cg relative to bay upper side +rear.xcg = 0; % [m] Cg relative to bay upper side % !!!!! rear.boatType = ''; % [-] Boat type diff --git a/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m b/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m index 285238c..8cdcf2b 100644 --- a/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m +++ b/missions/2022_Pyxis_Portugal_October/config/rocketConfig.m @@ -23,7 +23,7 @@ parafoil = Parafoil(); parafoil.length = 0.31; % [m] Total bay length parafoil.mass = 0; % [kg] Total bay mass parafoil.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -parafoil.xCg = 0; % [m] Cg relative to bay upper side +parafoil.xcg = 0; % [m] Cg relative to bay upper side % !!!!! parafoil.noseLength = 0.31; % [m] Nosecone length @@ -39,7 +39,7 @@ recovery = Recovery(); recovery.length = 0; % [m] Total bay length recovery.mass = 0; % [kg] Total bay mass recovery.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -recovery.xCg = 0; % [m] Cg relative to bay upper side +recovery.xcg = 0; % [m] Cg relative to bay upper side % !!!!! %% ELC @@ -49,7 +49,7 @@ electronics = Electronics(); electronics.length = 0; % [m] Total bay length electronics.mass = 0; % [kg] Total bay mass electronics.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -electronics.xCg = 0; % [m] Cg relative to bay upper side +electronics.xcg = 0; % [m] Cg relative to bay upper side % !!!!! %% ARB @@ -59,7 +59,7 @@ airbrakes = Airbrakes(); airbrakes.length = 0; % [m] Total bay length airbrakes.mass = 0; % [kg] Total bay mass airbrakes.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -airbrakes.xCg = 0; % [m] Cg relative to bay upper side% !!!!! +airbrakes.xcg = 0; % [m] Cg relative to bay upper side% !!!!! % !!!!! airbrakes.enabled = true; % If true, multiple and smooth airbrakes opening will be simulated @@ -93,7 +93,7 @@ rear.position = 0; % [m] offset fr rear.length = 0; % [m] Total bay length rear.mass = 0; % [kg] Total bay mass rear.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -rear.xCg = 0; % [m] Cg relative to bay upper side +rear.xcg = 0; % [m] Cg relative to bay upper side % !!!!! rear.boatType = ''; % [-] Boat type diff --git a/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m b/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m index ed371b1..bec3d20 100644 --- a/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m +++ b/missions/2022_Pyxis_Roccaraso_September/config/rocketConfig.m @@ -25,7 +25,7 @@ parafoil = Parafoil(); parafoil.length = 0.31; % [m] Total bay length parafoil.mass = 0; % [kg] Total bay mass parafoil.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -parafoil.xCg = 0; % [m] Cg relative to bay upper side +parafoil.xcg = 0; % [m] Cg relative to bay upper side % !!!!! parafoil.noseLength = 0.31; % [m] Nosecone length @@ -41,7 +41,7 @@ recovery = Recovery(); recovery.length = 0; % [m] Total bay length recovery.mass = 0; % [kg] Total bay mass recovery.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -recovery.xCg = 0; % [m] Cg relative to bay upper side +recovery.xcg = 0; % [m] Cg relative to bay upper side % !!!!! %% ELC @@ -51,7 +51,7 @@ electronics = Electronics(); electronics.length = 0; % [m] Total bay length electronics.mass = 0; % [kg] Total bay mass electronics.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -electronics.xCg = 0; % [m] Cg relative to bay upper side +electronics.xcg = 0; % [m] Cg relative to bay upper side % !!!!! %% ARB @@ -61,7 +61,7 @@ airbrakes = Airbrakes(); airbrakes.length = 0; % [m] Total bay length airbrakes.mass = 0; % [kg] Total bay mass airbrakes.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -airbrakes.xCg = 0; % [m] Cg relative to bay upper side% !!!!! +airbrakes.xcg = 0; % [m] Cg relative to bay upper side% !!!!! % !!!!! airbrakes.enabled = true; % If true, multiple and smooth airbrakes opening will be simulated @@ -95,7 +95,7 @@ rear.position = 0; % [m] offset fr rear.length = 0; % [m] Total bay length rear.mass = 0; % [kg] Total bay mass rear.inertia = zeros(3,1); % [kg*m^2] Total bay inertia (Body reference) -rear.xCg = 0; % [m] Cg relative to bay upper side +rear.xcg = 0; % [m] Cg relative to bay upper side % !!!!! rear.boatType = 'OGIVE'; % [-] Boat type diff --git a/missions/2023_Gemini_Portugal_October/config/rocketConfig.m b/missions/2023_Gemini_Portugal_October/config/rocketConfig.m index 24d971d..610966a 100644 --- a/missions/2023_Gemini_Portugal_October/config/rocketConfig.m +++ b/missions/2023_Gemini_Portugal_October/config/rocketConfig.m @@ -22,7 +22,7 @@ parafoil = Parafoil(); parafoil.length = 638.89 * 1e-3; % [m] Total bay length parafoil.mass = 4.441; % [kg] Total bay mass parafoil.inertia = 1e-9*[12431765; 106903809; 106823939]; % [kg*m^2] Total bay inertia (Body reference) -parafoil.xCg = 479.24 * 1e-3; % [m] Cg relative to bay upper side +parafoil.xcg = 479.24 * 1e-3; % [m] Cg relative to bay upper side % !!!!! parafoil.noseLength = 0.32; % [m] Nosecone length @@ -38,7 +38,7 @@ recovery = Recovery(); recovery.length = 856 * 1e-3; % [m] Total bay length recovery.mass = 4.065; % [kg] Total bay mass recovery.inertia = 1e-9*[13422459; 217223325; 217296702]; % [kg*m^2] Total bay inertia (Body reference) -recovery.xCg = 564.41 * 1e-3; % [m] Cg relative to bay upper side +recovery.xcg = 564.41 * 1e-3; % [m] Cg relative to bay upper side % !!!!! %% ELC @@ -48,7 +48,7 @@ electronics = Electronics(); electronics.length = 440.5 * 1e-3; % [m] Total bay length electronics.mass = 2.474; % [kg] Total bay mass electronics.inertia = 1e-9*[8827093; 48462702; 48034980]; % [kg*m^2] Total bay inertia (Body reference) -electronics.xCg = 231.35 * 1e-3; % [m] Cg relative to bay upper side +electronics.xcg = 231.35 * 1e-3; % [m] Cg relative to bay upper side % !!!!! %% ARB @@ -58,7 +58,7 @@ airbrakes = Airbrakes(); airbrakes.length = 54.8 * 1e-3; % [m] Total bay length airbrakes.mass = 0.936; % [kg] Total bay mass airbrakes.inertia = 1e-9*[3086650; 1931082; 1889047]; % [kg*m^2] Total bay inertia (Body reference) -airbrakes.xCg = 30.54 * 1e-3; % [m] Cg relative to bay upper side +airbrakes.xcg = 30.54 * 1e-3; % [m] Cg relative to bay upper side % !!!!! airbrakes.enabled = true; % If true, multiple and smooth airbrakes opening will be simulated @@ -92,7 +92,7 @@ rear.position = 1.090; % [m] offse rear.length = 547 * 1e-3; % [m] Total bay length rear.mass = 1.623; % [kg] Total bay mass rear.inertia = 1e-9*[13074201; 44271226; 44270124]; % [kg*m^2] Total bay inertia (Body reference) -rear.xCg = 253.77 * 1e-3; % [m] Cg relative to bay upper side +rear.xcg = 253.77 * 1e-3; % [m] Cg relative to bay upper side % !!!!! rear.boatType = 'OGIVE'; % [-] Boat type diff --git a/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m b/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m index c15b52c..600065a 100644 --- a/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m +++ b/missions/2023_Gemini_Roccaraso_September/config/rocketConfig.m @@ -22,7 +22,7 @@ parafoil = Parafoil(); parafoil.length = 638.89 * 1e-3; % [m] Total bay length parafoil.mass = 4.441; % [kg] Total bay mass parafoil.inertia = 1e-9*[12431765; 106903809; 106823939]; % [kg*m^2] Total bay inertia (Body reference) -parafoil.xCg = 479.24 * 1e-3; % [m] Cg relative to bay upper side +parafoil.xcg = 479.24 * 1e-3; % [m] Cg relative to bay upper side % !!!!! parafoil.noseLength = 0.32; % [m] Nosecone length @@ -38,7 +38,7 @@ recovery = Recovery(); recovery.length = 856 * 1e-3; % [m] Total bay length recovery.mass = 4.065; % [kg] Total bay mass recovery.inertia = 1e-9*[13422459; 217223325; 217296702]; % [kg*m^2] Total bay inertia (Body reference) -recovery.xCg = 564.41 * 1e-3; % [m] Cg relative to bay upper side +recovery.xcg = 564.41 * 1e-3; % [m] Cg relative to bay upper side % !!!!! %% ELC @@ -48,7 +48,7 @@ electronics = Electronics(); electronics.length = 440.5 * 1e-3; % [m] Total bay length electronics.mass = 2.474; % [kg] Total bay mass electronics.inertia = 1e-9*[8827093; 48462702; 48034980]; % [kg*m^2] Total bay inertia (Body reference) -electronics.xCg = 231.35 * 1e-3; % [m] Cg relative to bay upper side +electronics.xcg = 231.35 * 1e-3; % [m] Cg relative to bay upper side % !!!!! %% ARB @@ -58,7 +58,7 @@ airbrakes = Airbrakes(); airbrakes.length = 54.8 * 1e-3; % [m] Total bay length airbrakes.mass = 0.936; % [kg] Total bay mass airbrakes.inertia = 1e-9*[3086650; 1931082; 1889047]; % [kg*m^2] Total bay inertia (Body reference) -airbrakes.xCg = 30.54 * 1e-3; % [m] Cg relative to bay upper side +airbrakes.xcg = 30.54 * 1e-3; % [m] Cg relative to bay upper side % !!!!! airbrakes.enabled = true; % If true, multiple and smooth airbrakes opening will be simulated @@ -92,7 +92,7 @@ rear.position = 1.090; % [m] offse rear.length = 547 * 1e-3; % [m] Total bay length rear.mass = 1.623; % [kg] Total bay mass rear.inertia = 1e-9*[13074201; 44271226; 44270124]; % [kg*m^2] Total bay inertia (Body reference) -rear.xCg = 253.77 * 1e-3; % [m] Cg relative to bay upper side +rear.xcg = 253.77 * 1e-3; % [m] Cg relative to bay upper side % !!!!! rear.boatType = 'OGIVE'; % [-] Boat type diff --git a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m index d19d37a..2369c08 100644 --- a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m +++ b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m @@ -15,7 +15,7 @@ parafoil = Parafoil(); parafoil.length = 647.25 * 1e-3; % [m] Total bay length parafoil.mass = 4.401; % [kg] Total bay mass parafoil.inertia = 1e-9*[12531966; 109986813; 109930516]; % [kg*m^2] Total bay inertia (Body reference) -parafoil.xCg = 487.78 * 1e-3; % [m] Cg relative to bay upper side +parafoil.xcg = 487.78 * 1e-3; % [m] Cg relative to bay upper side parafoil.noseLength = 0.32; % [m] Nosecone length parafoil.noseType = 'MHAACK'; % [-] Nosecone shape @@ -29,7 +29,7 @@ recovery = Recovery(); recovery.length = 826 * 1e-3; % [m] Total bay length recovery.mass = 4.261; % [kg] Total bay mass recovery.inertia = 1e-9*[13831051; 269596803; 269645059]; % [kg*m^2] Total bay inertia (Body reference) -recovery.xCg = 500.38 * 1e-3; % [m] Cg relative to bay upper side +recovery.xcg = 500.38 * 1e-3; % [m] Cg relative to bay upper side %% ELC electronics = Electronics(); @@ -37,7 +37,7 @@ electronics = Electronics(); electronics.length = 433.5 * 1e-3; % [m] Total bay length electronics.mass = 2.551; % [kg] Total bay mass electronics.inertia = 1e-9*[9358415; 49265825; 48770607]; % [kg*m^2] Total bay inertia (Body reference) -electronics.xCg = 229.9 * 1e-3; % [m] Cg relative to bay upper side +electronics.xcg = 229.9 * 1e-3; % [m] Cg relative to bay upper side %% ARB airbrakes = Airbrakes(); @@ -47,7 +47,7 @@ airbrakes.identification = false; % Control parameter airbrakes.length = 54.8 * 1e-3; % [m] Total bay length airbrakes.mass = 0.936; % [kg] Total bay mass airbrakes.inertia = 1e-9*[3086650; 1931082; 1889047]; % [kg*m^2] Total bay inertia (Body reference) -airbrakes.xCg = 30.54 * 1e-3; % [m] Cg relative to bay upper side +airbrakes.xcg = 30.54 * 1e-3; % [m] Cg relative to bay upper side airbrakes.enabled = true; % If true, multiple and smooth airbrakes opening will be simulated airbrakes.extension = [1]; % aerobrakes, 1-2-3 for 0%, 50% or 100% opened @@ -136,7 +136,7 @@ rear.position = 1.090; % [m] offse rear.length = 547 * 1e-3; % [m] Total bay length rear.mass = 1.623; % [kg] Total bay mass rear.inertia = 1e-9*[13074201; 44271226; 44270124]; % [kg*m^2] Total bay inertia (Body reference) -rear.xCg = 253.77 * 1e-3; % [m] Cg relative to bay upper side +rear.xcg = 253.77 * 1e-3; % [m] Cg relative to bay upper side rear.boatType = 'OGIVE'; % [-] Boat type rear.boatLength = 0.114; % [m] Boat length diff --git a/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m b/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m index bbaa3a5..b2ca5cb 100644 --- a/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m +++ b/missions/2024_Lyra_Roccaraso_September/config/rocketConfig.m @@ -21,7 +21,7 @@ parafoil = Parafoil(); parafoil.length = 647.25 * 1e-3; % [m] Total bay length parafoil.mass = 4.401; % [kg] Total bay mass parafoil.inertia = 1e-9*[12531966; 109986813; 109930516]; % [kg*m^2] Total bay inertia (Body reference) -parafoil.xCg = 487.78 * 1e-3; % [m] Cg relative to bay upper side +parafoil.xcg = 487.78 * 1e-3; % [m] Cg relative to bay upper side parafoil.noseLength = 0.32; % [m] Nosecone length parafoil.noseType = 'MHAACK'; % [-] Nosecone shape @@ -35,7 +35,7 @@ recovery = Recovery(); recovery.length = 826 * 1e-3; % [m] Total bay length recovery.mass = 4.261; % [kg] Total bay mass recovery.inertia = 1e-9*[13831051; 269596803; 269645059]; % [kg*m^2] Total bay inertia (Body reference) -recovery.xCg = 500.38 * 1e-3; % [m] Cg relative to bay upper side +recovery.xcg = 500.38 * 1e-3; % [m] Cg relative to bay upper side %% ELC electronics = Electronics(); @@ -43,7 +43,7 @@ electronics = Electronics(); electronics.length = 433.5 * 1e-3; % [m] Total bay length electronics.mass = 2.551; % [kg] Total bay mass electronics.inertia = 1e-9*[9358415; 49265825; 48770607]; % [kg*m^2] Total bay inertia (Body reference) -electronics.xCg = 229.9 * 1e-3; % [m] Cg relative to bay upper side +electronics.xcg = 229.9 * 1e-3; % [m] Cg relative to bay upper side %% ARB airbrakes = Airbrakes(); @@ -54,7 +54,7 @@ airbrakes.identification = false; % Control parameter airbrakes.length = 54.8 * 1e-3; % [m] Total bay length airbrakes.mass = 0.936; % [kg] Total bay mass airbrakes.inertia = 1e-9*[3086650; 1931082; 1889047]; % [kg*m^2] Total bay inertia (Body reference) -airbrakes.xCg = 30.54 * 1e-3; % [m] Cg relative to bay upper side +airbrakes.xcg = 30.54 * 1e-3; % [m] Cg relative to bay upper side airbrakes.enabled = true; % If true, multiple and smooth airbrakes opening will be simulated airbrakes.extension = [1]; % aerobrakes, 1-2-3 for 0%, 50% or 100% opened @@ -89,7 +89,7 @@ rear.position = 1.090 + 0.5; % [m] rear.length = 547 * 1e-3; % [m] Total bay length rear.mass = 1.623; % [kg] Total bay mass rear.inertia = 1e-9*[13074201; 44271226; 44270124]; % [kg*m^2] Total bay inertia (Body reference) -rear.xCg = 253.77 * 1e-3; % [m] Cg relative to bay upper side +rear.xcg = 253.77 * 1e-3; % [m] Cg relative to bay upper side rear.boatType = 'OGIVE'; % [-] Boat type rear.boatLength = 0.114; % [m] Boat length diff --git a/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m b/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m index 4f90b9b..dfc372f 100644 --- a/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m +++ b/missions/2025_Orion_Roccaraso_September/config/rocketConfig.m @@ -21,7 +21,7 @@ parafoil = Parafoil(); parafoil.length = 647.25 * 1e-3; % [m] Total bay length parafoil.mass = 4.401; % [kg] Total bay mass parafoil.inertia = 1e-9*[12531966; 109986813; 109930516]; % [kg*m^2] Total bay inertia (Body reference) -parafoil.xCg = 487.78 * 1e-3; % [m] Cg relative to bay upper side +parafoil.xcg = 487.78 * 1e-3; % [m] Cg relative to bay upper side parafoil.noseLength = 0.32; % [m] Nosecone length parafoil.noseType = 'MHAACK'; % [-] Nosecone shape @@ -35,7 +35,7 @@ recovery = Recovery(); recovery.length = 826 * 1e-3; % [m] Total bay length recovery.mass = 4.261; % [kg] Total bay mass recovery.inertia = 1e-9*[13831051; 269596803; 269645059]; % [kg*m^2] Total bay inertia (Body reference) -recovery.xCg = 500.38 * 1e-3; % [m] Cg relative to bay upper side +recovery.xcg = 500.38 * 1e-3; % [m] Cg relative to bay upper side %% ELC electronics = Electronics(); @@ -43,7 +43,7 @@ electronics = Electronics(); electronics.length = 433.5 * 1e-3; % [m] Total bay length electronics.mass = 2.551; % [kg] Total bay mass electronics.inertia = 1e-9*[9358415; 49265825; 48770607]; % [kg*m^2] Total bay inertia (Body reference) -electronics.xCg = 229.9 * 1e-3; % [m] Cg relative to bay upper side +electronics.xcg = 229.9 * 1e-3; % [m] Cg relative to bay upper side %% ARB airbrakes = Airbrakes(); @@ -53,7 +53,7 @@ airbrakes.identification = false; % Control parameter airbrakes.length = 54.8 * 1e-3; % [m] Total bay length airbrakes.mass = 0.936; % [kg] Total bay mass airbrakes.inertia = 1e-9*[3086650; 1931082; 1889047]; % [kg*m^2] Total bay inertia (Body reference) -airbrakes.xCg = 30.54 * 1e-3; % [m] Cg relative to bay upper side +airbrakes.xcg = 30.54 * 1e-3; % [m] Cg relative to bay upper side airbrakes.enabled = true; % If true, multiple and smooth airbrakes opening will be simulated airbrakes.extension = [1]; % aerobrakes, 1-2-3 for 0%, 50% or 100% opened @@ -88,7 +88,7 @@ rear.position = 1.090; % [m] offse rear.length = 547 * 1e-3; % [m] Total bay length rear.mass = 1.623; % [kg] Total bay mass rear.inertia = 1e-9*[13074201; 44271226; 44270124]; % [kg*m^2] Total bay inertia (Body reference) -rear.xCg = 253.77 * 1e-3; % [m] Cg relative to bay upper side +rear.xcg = 253.77 * 1e-3; % [m] Cg relative to bay upper side rear.boatType = 'OGIVE'; % [-] Boat type rear.boatLength = 0.114; % [m] Boat length -- GitLab