diff --git a/classes/bays/Payload.m b/classes/bays/Payload.m
index 4b54423f198fbde8563a00e836f102a734d39f74..0f9f7edb3f5528648e3142d3cb85cfe508438e49 100644
--- a/classes/bays/Payload.m
+++ b/classes/bays/Payload.m
@@ -24,30 +24,7 @@ classdef Payload < Bay
length % [m] Total bay length
mass % [kg] Total bay mass
inertia % [kg*m^2] Total bay inertia (Body reference)
- inertiaMatrix % [kg*m^2] 3x3 Inertia Matrix (the diagonal is made of the inertia vector values)
xCg % [m] Cg relative to bay upper side
-
- paraPrev double % Reference to the previous parachute in the multistage descent
- semiWingSpan double % [m] semiwingspan
- MAC double % [m] mean aero chord
- surface double % [m^2] payload surface
-
- deltaSMax double % [-] aerodynamic control coefficient - symmetric, max value
-
- CD0 double % [-] aerodynamic control coefficient - asymetric, CD0
- CDAlpha2 double % [-] aerodynamic control coefficient - asymetric, CDAlpha2
- CL0 double % [-] aerodynamic control coefficient - asymetric, CL0
- CLAlpha double % [-] aerodynamic control coefficient - asymetric, CLAlpha
- Cm0 double % [-] aerodynamic control coefficient - asymetric, Cm0
- CmAlpha double % [-] aerodynamic control coefficient - asymetric, CmAlpha
- Cmq double % [-] aerodynamic control coefficient - asymetric, Cmq
- CLDeltaA double % [-] aerodynamic control coefficient - asymetric, CLDeltaA
- Cnr double % [-] aerodynamic control coefficient - asymetric, Cnr
- CnDeltaA double % [-] aerodynamic control coefficient - asymetric, CnDeltaA
- CDDeltaA double % [-] aerodynamic control coefficient - asymetric, CDDeltaA
- Clp double % [-] aerodynamic control coefficient - asymetric, Clp
- ClPhi double % [-] aerodynamic control coefficient - asymetric, ClPhi
- ClDeltaA double % [-] aerodynamic control coefficient - asymetric, ClDeltaA
end
properties (Dependent)
diff --git a/classes/components/Environment.m b/classes/components/Environment.m
index 4c6806100c2b9d00047b6260938f8d2b0cefdb89..e9b47cc6aa304805dea5d0c326ec95379bfcbc75 100644
--- a/classes/components/Environment.m
+++ b/classes/components/Environment.m
@@ -84,6 +84,9 @@ classdef Environment < Component
end
function obj = updateLocal(obj)
+ if isempty(obj.temperature), obj.temperature = 288.15; end
+ if isempty(obj.gamma), obj.gamma = 1.4; end
+
obj.local = [obj.z0, obj.temperature, ... % vector containing inputs for atmosphereData
obj.pressure, obj.rho];
end
diff --git a/classes/components/Parafoil.m b/classes/components/Parafoil.m
index 364256ba1714c63dbfd3c44f86b720026c371d2b..c79ac4ac1ff56f5804463748f37b1ea68acf7f5a 100644
--- a/classes/components/Parafoil.m
+++ b/classes/components/Parafoil.m
@@ -11,22 +11,34 @@ classdef Parafoil < Para
% file
properties
- name = ''
- surface double % [m^2] Surface
- mass double % [kg] Parachute Mass
- openingDelay double % [s] drogue opening delay
- finalAltitude double % [m] Final altitude of the parachute
- chordLength double % [m] Shock Chord Length
- chordK double % [N/m^2] Shock Chord Elastic Constant
- chordC double % [Ns/m] Shock Chord Dynamic Coefficient
- expulsionSpeed double
- cx double % [/] Parachute Longitudinal Drag Coefficient
- cd double % [/] Parachute Drag Coefficient
- cl double % [/] Parachute Lift Coefficient
- m double % [m^2/s] Coefficient of the surface vs. time opening model
- nf double % [/] Adimensional Opening Time
- deployDuration double % [s] Time to get the parachute to full aperture
- forceCoefficient double % [-] Empirical coefficient to obtain correct peak force at deployment
+ name = ''
+ surface double % [m^2] Surface
+ deltaSMax double % [-] aerodynamic control coefficient - symmetric, max value
+
+ mass double % [kg] Parachute Mass
+
+ inertia % [kg*m^2] 3x3 Inertia Matrix (the diagonal is made of the inertia vector values)
+
+ semiWingSpan double % [m] semiwingspan
+ MAC double % [m] mean aero chord
+
+ cd0 double % [-] aerodynamic control coefficient - asymetric, CD0
+ cdAlpha2 double % [-] aerodynamic control coefficient - asymetric, CDAlpha2
+ cdDeltaA double % [-] aerodynamic control coefficient - asymetric, CDDeltaA
+ cl0 double % [-] aerodynamic control coefficient - asymetric, CL0
+ clAlpha double % [-] aerodynamic control coefficient - asymetric, CLAlpha
+ clDeltaA double % [-] aerodynamic control coefficient - asymetric, CLDeltaA
+ clP double % [-] aerodynamic control coefficient - asymetric, Clp
+ clPhi double % [-] aerodynamic control coefficient - asymetric, ClPhi
+ cm0 double % [-] aerodynamic control coefficient - asymetric, Cm0
+ cmAlpha double % [-] aerodynamic control coefficient - asymetric, CmAlpha
+ cmQ double % [-] aerodynamic control coefficient - asymetric, Cmq
+ cnR double % [-] aerodynamic control coefficient - asymetric, Cnr
+ cnDeltaA double % [-] aerodynamic control coefficient - asymetric, CnDeltaA
+ end
+
+ properties(SetAccess = private)
+ inverseInertia
end
methods
@@ -39,5 +51,9 @@ classdef Parafoil < Para
obj@Para(mission, varIn);
obj = obj(:, :, 1);
end
+
+ function updateAll(obj)
+ obj.inverseInertia = obj.inertia\eye(3);
+ end
end
end
\ No newline at end of file
diff --git a/functions/odeFunctions/descentParafoil.m b/functions/odeFunctions/descentParafoil.m
index c6590ad22673c2aa0fa3a91a44f05b5df1a05b72..1a328c55fa82631a0cf1e562d9d60b9f89d9b374 100644
--- a/functions/odeFunctions/descentParafoil.m
+++ b/functions/odeFunctions/descentParafoil.m
@@ -51,11 +51,11 @@ parafoil = rocket.parachutes(descentData.para, descentData.stage);
% saturation on servo angle, needed if the actuation is faster than the
% integration step
-% if deltaA > contSettings.rocket.payload.uMax
-% deltaA = contSettings.rocket.payload.uMax;
+% if deltaA > contSettings.parafoil.uMax
+% deltaA = contSettings.parafoil.uMax;
% flagAngleSaturation = true;
-% elseif deltaA < contSettings.rocket.payload.uMin
-% deltaA = contSettings.rocket.payload.uMin;
+% elseif deltaA < contSettings.parafoil.uMin
+% deltaA = contSettings.parafoil.uMin;
% flagAngleSaturation = true;
% else
% flagAngleSaturation = false;
@@ -64,31 +64,30 @@ parafoil = rocket.parachutes(descentData.para, descentData.stage);
%% CONSTANTS
% environment
g = environment.g0/(1 + (altitude*1e-3/6371))^2; % [N/kg] module of gravitational field
-local = [environment.z0, environment.temperature, ... % vector containing inputs for atmosphereData
- environment.pressure, environment.rho];
+local = environment.local; % vector containing inputs for atmosphereData
% geometry
-semiWingSpan = rocket.payload.semiWingSpan; % [m] wingspan
-MAC = rocket.payload.MAC; % [m] mean aero chord
-surface = rocket.payload.surface; % [m^2] payload surface
-mass = rocket.payload.mass; % [kg]
-inertia = rocket.payload.inertia; % 3x3 inertia matrix
-inverseInertia = rocket.payload.inverseInertia; % 3x3 inverse inertia matrix
+semiWingSpan = parafoil.semiWingSpan; % [m] wingspan
+MAC = parafoil.MAC; % [m] mean aero chord
+surface = parafoil.surface; % [m^2] payload surface
+mass = parafoil.mass; % [kg]
+inertia = parafoil.inertia; % 3x3 inertia matrix
+inverseInertia = parafoil.inverseInertia; % 3x3 inverse inertia matrix
% aerodynamic coefficients
-CD0 = rocket.payload.CD0; CDAlpha2 = rocket.payload.CDAlpha2;
-CL0 = rocket.payload.CL0; CLAlpha = rocket.payload.CLAlpha;
-Cm0 = rocket.payload.Cm0; CmAlpha = rocket.payload.CmAlpha; Cmq = rocket.payload.Cmq;
-Cnr = rocket.payload.Cnr;
-Clp = rocket.payload.Clp; ClPhi = rocket.payload.ClPhi;
+CD0 = parafoil.cd0; CDAlpha2 = parafoil.cdAlpha2;
+CL0 = parafoil.cl0; CLAlpha = parafoil.clAlpha;
+Cm0 = parafoil.cm0; CmAlpha = parafoil.cmAlpha; Cmq = parafoil.cmQ;
+Cnr = parafoil.cnR;
+Clp = parafoil.clP; ClPhi = parafoil.clPhi;
% aerodynamic control coefficients - asymmetric
-CnDeltaA = rocket.payload.CnDeltaA;
-CDDeltaA = rocket.payload.CDDeltaA;
-CLDeltaA = rocket.payload.CLDeltaA;
-ClDeltaA = rocket.payload.ClDeltaA;
+CnDeltaA = parafoil.cnDeltaA;
+CDDeltaA = parafoil.cdDeltaA;
+CLDeltaA = parafoil.clDeltaA;
+ClDeltaA = parafoil.clDeltaA; % !!!
% aerodynamic control coefficients - symmetric
-deltaSMax = rocket.payload.deltaSMax; % max value
+deltaSMax = parafoil.deltaSMax; % max value
%% ROTATIONS
@@ -97,7 +96,7 @@ Q = Q/norm(Q);
%% ADDING WIND (supposed to be added in NED axes);
if isa(wind, 'WindMatlab')
- [uw, vw, ww] = wind.getVels(-altitude, t);
+ [uw, vw, ww] = wind.getVels(altitude, t);
else
[uw, vw, ww] = wind.getVels(altitude);
end
@@ -113,19 +112,18 @@ ur = abs(u - windVels(1)); % abs to evade problem of negative vx body in forces
vr = v - windVels(2);
wr = w - windVels(3);
-
% Body to Inertial velocities
-Vels_NED = dcm'*[u; v; w];
+vNED = dcm'*[u; v; w];
% relative velocity norm
-V_norm = norm([ur vr wr]);
+nNorm = norm([ur vr wr]);
%% ATMOSPHERE DATA
absoluteAltitude = altitude + environment.z0;
[~, ~, ~, rho] = atmosphereData(absoluteAltitude, g, local);
%% AERODYNAMICS ANGLES
-if not(abs(ur) < 1e-9 || V_norm < 1e-9)
+if not(abs(ur) < 1e-9 || nNorm < 1e-9)
alpha = atan(wr/ur);
% beta = atan(vr/ur); % beta = asin(vr/V_norm) is the classical notation, Datcom uses this one though.
% alpha_tot = atan(sqrt(wr^2 + vr^2)/ur); % datcom 97' definition
@@ -138,29 +136,27 @@ end
deltaANormalized = deltaA / deltaSMax;
%% FORCES
-qFactor = 0.5*rho*V_norm; % [Pa * s / m] dynamic pressure/vNorm
+qFactor = 0.5*rho*nNorm; % [Pa * s / m] dynamic pressure/vNorm
-LIFT = qFactor * (CL0 + alpha * CLAlpha + deltaANormalized * CLDeltaA) * [wr; 0; -ur];
-DRAG = qFactor * (CD0 + alpha^2 * CDAlpha2 + deltaANormalized * CDDeltaA) * [ur; vr; wr];
+lift = qFactor * (CL0 + alpha * CLAlpha + deltaANormalized * CLDeltaA) * [wr; 0; -ur];
+drag = qFactor * (CD0 + alpha^2 * CDAlpha2 + deltaANormalized * CDDeltaA) * [ur; vr; wr];
-F_AERO = (LIFT - DRAG)*surface;
+forceAero = (lift - drag)*surface;
% Inertial to body gravity force (in body frame):
Fg = dcm*[0; 0; mass*g]; % [N] force due to the gravity in body frame
% total force assembly
-F = Fg + F_AERO; % [N] total forces vector
+F = Fg + forceAero; % [N] total forces vector
%% MOMENT
-Mx = (eul(1) * ClPhi *V_norm + 0.5 * semiWingSpan* Clp * p + deltaANormalized * ClDeltaA *V_norm) * semiWingSpan;
-My = (alpha * CmAlpha *V_norm+ 0.5 * MAC * Cmq * q + Cm0*V_norm) * MAC;
-Mz = (r * 0.5 * semiWingSpan* Cnr + deltaANormalized * CnDeltaA*V_norm) * semiWingSpan; % bizzarre
-
-M_AERO = [Mx; My; Mz] * qFactor * surface;
-M = M_AERO; % no inertia considerations in this model
+Mx = (eul(1) * ClPhi *nNorm + 0.5 * semiWingSpan* Clp * p + deltaANormalized * ClDeltaA *nNorm) * semiWingSpan;
+My = (alpha * CmAlpha *nNorm+ 0.5 * MAC * Cmq * q + Cm0*nNorm) * MAC;
+Mz = (r * 0.5 * semiWingSpan* Cnr + deltaANormalized * CnDeltaA*nNorm) * semiWingSpan; % bizzarre
+momentAero = [Mx; My; Mz] * qFactor * surface;
%% derivatives computations
-omega = [p;q;r];
+omega = [p; q; r];
% acceleration
bodyAcc = F/mass - cross(omega,[u;v;w]);
@@ -174,7 +170,7 @@ OM = [ 0 -p -q -r ;
dQQ = 1/2*OM*Q';
%% angular acceleration
-angAcc = inverseInertia*(M - cross(omega, inertia .* omega));
+angAcc = inverseInertia*(momentAero - cross(omega, inertia .* omega));
% %% actuator dynamics
%
@@ -195,9 +191,9 @@ angAcc = inverseInertia*(M - cross(omega, inertia .* omega));
% deltaA_ref = deltaA_ref_vec(idx_deltaA,2);
% end
%
-% ddeltaA = (deltaA_ref-deltaA)/contSettings.rocket.payload.deltaA_tau;
-% if abs(ddeltaA) >contSettings.rocket.payload.deltaA_maxSpeed
-% ddeltaA = sign(deltaA_ref-deltaA)*contSettings.rocket.payload.deltaA_maxSpeed; % concettualmente sta roba è sbagliata perchè dipende dal passo di integrazione, fixare
+% ddeltaA = (deltaA_ref-deltaA)/contSettings.parafoil.deltaA_tau;
+% if abs(ddeltaA) >contSettings.parafoil.deltaA_maxSpeed
+% ddeltaA = sign(deltaA_ref-deltaA)*contSettings.parafoil.deltaA_maxSpeed; % concettualmente sta roba è sbagliata perchè dipende dal passo di integrazione, fixare
% end
%
% if flagAngleSaturation
@@ -205,7 +201,7 @@ angAcc = inverseInertia*(M - cross(omega, inertia .* omega));
% end
%% FINAL DERIVATIVE STATE ASSEMBLING
-dY(1:3) = Vels_NED;
+dY(1:3) = vNED;
dY(4:6) = bodyAcc;
dY(7:9) = angAcc;
dY(10:13) = dQQ;
@@ -224,7 +220,7 @@ if nargout == 2 || ~isempty(wrapper)
parout.velocities = [u; v; w];
- parout.forces.aero = F_AERO;
+ parout.forces.aero = forceAero;
parout.forces.gravity = Fg;
parout.air = [];
diff --git a/missions/2024_Lyra_Portugal_October/config/paraConfig.m b/missions/2024_Lyra_Portugal_October/config/paraConfig.m
index d8e1d5dbacd4b82de6b2b66c81b0365fbcddd22b..24ff5c0a1a827f43fc34bab0787f04d4eda068aa 100644
--- a/missions/2024_Lyra_Portugal_October/config/paraConfig.m
+++ b/missions/2024_Lyra_Portugal_October/config/paraConfig.m
@@ -2,22 +2,22 @@
% parachute 1
para(1, 1) = Parachute();
-para(1,1).name = 'DROGUE chute';
-para(1,1).surface = 0.6; % [m^2] Surface
-para(1,1).mass = 0.15; % [kg] Parachute Mass
-para(1,1).cd = 0.75; % [/] Parachute Drag Coefficient
-para(1,1).cl = 0; % [/] Parachute Lift Coefficient
-para(1,1).openingDelay = 1; % [s] drogue opening delay
-para(1,1).finalAltitude = 350; % [m] Final altitude of the parachute
-para(1,1).cx = 1.4; % [/] Parachute Longitudinal Drag Coefficient
-para(1,1).chordLength = 1.5; % [m] Shock Chord Length
-para(1,1).chordK = 7200; % [N/m^2] Shock Chord Elastic Constant
-para(1,1).chordC = 0; % [Ns/m] Shock Chord Dynamic Coefficient
-para(1,1).m = 1; % [m^2/s] Coefficient of the surface vs. time opening model
-para(1,1).nf = 12; % [/] Adimensional Opening Time
-para(1,1).expulsionSpeed = 5; % [m/s] Expulsion Speed
-para(1,1).forceCoefficient = 1.8; % [-] Empirical coefficient to obtain correct peak force at deployment
-para(1,1).deployDuration = 0.1; % [s] Time to get the parachute to full aperture
+para(1, 1).name = 'DROGUE chute';
+para(1, 1).surface = 0.6; % [m^2] Surface
+para(1, 1).mass = 0.15; % [kg] Parachute Mass
+para(1, 1).cd = 0.75; % [/] Parachute Drag Coefficient
+para(1, 1).cl = 0; % [/] Parachute Lift Coefficient
+para(1, 1).openingDelay = 1; % [s] drogue opening delay
+para(1, 1).finalAltitude = 350; % [m] Final altitude of the parachute
+para(1, 1).cx = 1.4; % [/] Parachute Longitudinal Drag Coefficient
+para(1, 1).chordLength = 1.5; % [m] Shock Chord Length
+para(1, 1).chordK = 7200; % [N/m^2] Shock Chord Elastic Constant
+para(1, 1).chordC = 0; % [Ns/m] Shock Chord Dynamic Coefficient
+para(1, 1).m = 1; % [m^2/s] Coefficient of the surface vs. time opening model
+para(1, 1).nf = 12; % [/] Adimensional Opening Time
+para(1, 1).expulsionSpeed = 5; % [m/s] Expulsion Speed
+para(1, 1).forceCoefficient = 1.8; % [-] Empirical coefficient to obtain correct peak force at deployment
+para(1, 1).deployDuration = 0.1; % [s] Time to get the parachute to full aperture
% parachute 2
para(2, 1) = Parachute();
@@ -27,6 +27,7 @@ para(2, 1).surface = 14; % [m^2] Surface
para(2, 1).mass = 1.05; % [kg] Parachute Mass
para(2, 1).cd = 0.6; % [/] Parachute Drag Coefficient
para(2, 1).cl = 0; % [/] Parachute Lift Coefficient
+para(2, 1).openingDelay = 0; % [s] drogue opening delay
para(2, 1).finalAltitude = 0; % [m] Final altitude of the parachute
para(2, 1).cx = 1.15; % [/] Parachute Longitudinal Drag Coefficient
para(2, 1).chordLength = 6; % [m] Shock Chord Length
@@ -34,6 +35,7 @@ para(2, 1).chordK = 3000; % [N/m^2] Shock Chord Elastic Constant
para(2, 1).chordC = 0; % [Ns/m] Shock Chord Dynamic Coefficient
para(2, 1).m = 1; % [m^2/s] Coefficient of the surface vs. time opening model
para(2, 1).nf = 8.7; % [/] Adimensional Opening Time
+para(2 ,1).expulsionSpeed = 0; % [m/s] Expulsion Speed
para(2, 1).forceCoefficient = 2.2; % [-] Empirical coefficient to obtain correct peak force at deployment
para(2, 1).deployDuration= 0.9; % [s] Time to get the parachute to full aperture
@@ -55,21 +57,35 @@ para(1, 2).chordC = 0; % [Ns/m] Shock Chord Dynamic Coefficie
para(1, 2).m = 1; % [m^2/s] Coefficient of the surface vs. time opening model
para(1, 2).nf = 12; % [/] Adimensional Opening Time
para(1, 2).expulsionSpeed = 10; % [m/s] Expulsion Speed
-
+para(1, 2).forceCoefficient = 0; % [-] Empirical coefficient to obtain correct peak force at deployment
+para(1, 2).deployDuration = 0; % [s] Time to get the parachute to full aperture
+
+
% parachute 2
para(2, 2) = Parafoil();
para(2, 2).name = "Payload AIRFOIL";
-para(2, 2).mass = 0.50; % [kg] Parachute Mass
+para(2, 2).mass = 0.50; % [kg] Parafoil Mass
+
para(2, 2).surface = 0.11; % [m^2] Surface
-para(2, 2).cd = 0; % [/] Parachute Drag Coefficient
-para(2, 2).cl = 0; % [/] Parachute Lift Coefficient
-para(2, 2).openingDelay = 1; % [s] drogue opening delay
-para(2, 2).finalAltitude = 0; % [m] Final altitude of the parachute
-para(2, 2).cx = 1.4; % [/] Parachute Longitudinal Drag Coefficient
-para(2, 2).chordLength = 1.5; % [m] Shock Chord Length
-para(2, 2).chordK = 7200; % [N/m^2] Shock Chord Elastic Constant
-para(2, 2).chordC = 0; % [Ns/m] Shock Chord Dynamic Coefficient
-para(2, 2).m = 1; % [m^2/s] Coefficient of the surface vs. time opening model
-para(2, 2).nf = 12; % [/] Adimensional Opening Time
-para(2, 2).expulsionSpeed = 10; % [m/s] Expulsion Speed
+para(2, 2).deltaSMax = 0.1; % max value
+
+para(2, 2).semiWingSpan = 2.55/2; % [m] settings.para(2, 2).b: semiwingspan - vela nuova: 2.55/2; - vela vecchia: 2.06/2;
+para(2, 2).MAC = 0.8; % [m] mean aero chord
+para(2, 2).surface = 2.04; % [m^2] parafoil surface - vela nuova 2.04; - vela vecchia: 1.64;
+para(2, 2).inertia = [0.42, 0, 0.03;
+ 0, 0.4, 0;
+ 0.03, 0, 0.053]; % [kg m^2] [3x3] inertia matrix parafoil
+para(2, 2).cd0 = 0.25;
+para(2, 2).cdAlpha2 = 0.12;
+para(2, 2).cdDeltaA = 0.01;
+para(2, 2).cl0 = 0.091;
+para(2, 2).clAlpha = 0.9;
+para(2, 2).clDeltaA = -0.0035;
+para(2, 2).clP = -0.84;
+para(2, 2).clPhi = -0.1;
+para(2, 2).cm0 = 0.35;
+para(2, 2).cmAlpha = -0.72;
+para(2, 2).cmQ = -1.49;
+para(2, 2).cnR = -0.27;
+para(2, 2).cnDeltaA = 0.0115;
\ No newline at end of file
diff --git a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
index 5f3420171f1601851930a7eb159b39f834419b9d..ce5f8a07193d58592bc3d918c0e7462af0d3788f 100644
--- a/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
+++ b/missions/2024_Lyra_Portugal_October/config/rocketConfig.m
@@ -29,33 +29,6 @@ payload.nosePower = 3/4; % [-] No
payload.nosePMod = 1.291586e+00; % [-] P coefficient for modified nosecone shapes
payload.noseCMod = 9.272342e-03; % [-] C coefficient for modified nosecone shapes
-payload.paraPrev = [2, 1]; % Reference to the previous parachute in the multistage descent
- % (in this case, the payload drogue: 2nd stage, 1st parachute)
-payload.semiWingSpan = 2.55/2; % [m] settings.payload.b: semiwingspan - vela nuova: 2.55/2; - vela vecchia: 2.06/2;
-payload.MAC = 0.8; % [m] mean aero chord
-payload.surface = 2.04; % [m^2] payload surface - vela nuova 2.04; - vela vecchia: 1.64;
-payload.inertiaMatrix = [0.42, 0, 0.03;
- 0, 0.4, 0;
- 0.03, 0, 0.053]; % [kg m^2] [3x3] inertia matrix payload+payload
-%%% Aerodynamic constants
-% aerodynamic control coefficients - asymmetric
-payload.CD0 = 0.25;
-payload.CDAlpha2 = 0.12;
-payload.CL0 = 0.091;
-payload.CLAlpha = 0.9;
-payload.Cm0 = 0.35;
-payload.CmAlpha = -0.72;
-payload.Cmq = -1.49;
-payload.CLDeltaA = -0.0035;
-payload.Cnr = -0.27;
-payload.CnDeltaA = 0.0115;
-payload.CDDeltaA = 0.01;
-payload.Clp = -0.84;
-payload.ClPhi = -0.1;
-payload.ClDeltaA = 0.01;
-% aerodynamic control coefficients - symmetric
-payload.deltaSMax = 0.1; % max value
-
%% RCS
recovery = Recovery();