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Skyward
Matlab dependencies
Common
Commits
3dc2b208
Commit
3dc2b208
authored
1 year ago
by
giuliaghirardini
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[refactoring-ode][classes] Added some comments to Payload class
parent
93ff903e
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1 merge request
!3
Refactoring ODE functions
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classes/bays/Payload.m
+22
-21
22 additions, 21 deletions
classes/bays/Payload.m
with
22 additions
and
21 deletions
classes/bays/Payload.m
+
22
−
21
View file @
3dc2b208
...
@@ -24,29 +24,30 @@ classdef Payload < Bay
...
@@ -24,29 +24,30 @@ classdef Payload < Bay
length
% [m] Total bay length
length
% [m] Total bay length
mass
% [kg] Total bay mass
mass
% [kg] Total bay mass
inertia
% [kg*m^2] Total bay inertia (Body reference)
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
xCg
% [m] Cg relative to bay upper side
paraPrev
double
paraPrev
double
% Reference to the previous parachute in the multistage descent
semiWingSpan
double
semiWingSpan
double
% [m] semiwingspan
MAC
double
MAC
double
% [m] mean aero chord
surface
double
surface
double
% [m^2] payload surface
deltaSMax
double
deltaSMax
double
% [-] aerodynamic control coefficient - symmetric, max value
CD0
double
CD0
double
% [-] aerodynamic control coefficient - asymetric, CD0
CDAlpha2
double
CDAlpha2
double
% [-] aerodynamic control coefficient - asymetric, CDAlpha2
CL0
double
CL0
double
% [-] aerodynamic control coefficient - asymetric, CL0
CLAlpha
double
CLAlpha
double
% [-] aerodynamic control coefficient - asymetric, CLAlpha
Cm0
double
Cm0
double
% [-] aerodynamic control coefficient - asymetric, Cm0
CmAlpha
double
CmAlpha
double
% [-] aerodynamic control coefficient - asymetric, CmAlpha
Cmq
double
Cmq
double
% [-] aerodynamic control coefficient - asymetric, Cmq
CLDeltaA
double
CLDeltaA
double
% [-] aerodynamic control coefficient - asymetric, CLDeltaA
Cnr
double
Cnr
double
% [-] aerodynamic control coefficient - asymetric, Cnr
CnDeltaA
double
CnDeltaA
double
% [-] aerodynamic control coefficient - asymetric, CnDeltaA
CDDeltaA
double
CDDeltaA
double
% [-] aerodynamic control coefficient - asymetric, CDDeltaA
Clp
double
Clp
double
% [-] aerodynamic control coefficient - asymetric, Clp
ClPhi
double
ClPhi
double
% [-] aerodynamic control coefficient - asymetric, ClPhi
ClDeltaA
double
ClDeltaA
double
% [-] aerodynamic control coefficient - asymetric, ClDeltaA
end
end
properties
(
Dependent
)
properties
(
Dependent
)
...
@@ -71,7 +72,7 @@ classdef Payload < Bay
...
@@ -71,7 +72,7 @@ classdef Payload < Bay
methods
methods
function
inverseInertia
=
get
.
inverseInertia
(
obj
)
function
inverseInertia
=
get
.
inverseInertia
(
obj
)
inverseInertia
=
inv
(
obj
.
inertia
);
inverseInertia
=
inv
(
obj
.
inertia
Matrix
);
end
end
end
end
end
end
\ No newline at end of file
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