```
--[[
; Example for a script-driven vessel class definition.
; For implementation code, see Orbitersdk/samples/ScriptVessel
; This file contains both the configuration and script parts.
; The config part is terminated by 'END_PARSE' to prevent the
; Orbiter parser from reading the script, and enclosed in Lua
; comment brackets to make it a comment for the script interpreter.
; A. Configuration section
; -------------------------------------------
ClassName = ScriptPB
Module = ScriptVessel
Script = ScriptPB.cfg
END_PARSE
; B. Script section
; -------------------------------------------
--]]
-- Vessel parameters
vprm = { -- general Parameters
emass = 500, -- empty mass [kg]
fuelmass = 750, -- propellant mass [kg]
size = 3.5, -- mean radius [m]
pmi = {x=2.28,y=2.31,z=0.79}, -- principal moments of inertia [m^2]
cs = {x=10.5,y=15.0,z=5.8}, -- cross sections [m^2]
rd = {x=0.1,y=0.1,z=0.05}, -- rotation drag coefficients
co = {x=0,y=0.8,z=0}, -- cockpit camera offset
td1 = {x=0,y=-1.5,z=2}, -- touchdown point: front
td2 = {x=-1,y=-1.5,z=-1.5}, -- touchdown point: left
td3 = {x=1,y=-1.5,z=-1.5} -- touchdown point: right
}
afv = { -- parameters for vertical airfoil
cl = {-0.1,-0.5,-0.4,-0.1,0,0,0,0,0,0,0,0,0,0,-0.2,-0.6,-0.6,-0.4,0.2,0.5,0.9,0.8,0.2,0,0,0,0,0,0,0,0,0,0.1,0.4,0.5,0.3,-0.1,-0.5},
aoa_step = 10*RAD, -- step size for lift coeff samples
dp = 0.03, -- profile drag parameters
di = {A=2.5,e=0.5}, -- induced drag parameters
dw = {M1=0.75,M2=1.0,M3=1.1,cmax=0.04} -- wave drag parameters
}
afh = { -- parameters for horizontal airfoil
cl = {0,0.4,0,-0.4,0,0.4,0,-0.4,0,0.4}, -- lift coeffs in 45deg steps from -pi
aoa_step = 45*RAD, -- step size for lift coeff samples
dp = 0.03, -- profile drag parameters
di = {A=1.5,e=0.6}, -- induced drag parameters
dw = {M1=0.75,M2=1.0,M3=1.1,cmax=0.04} -- wave drag parameters
}
thmain_prm = { -- main thruster parameters
pos = {x=0,y=0,z=-4.35}, -- thrust attack point [m]
dir = {x=0,y=0,z=1}, -- thrust direction
maxth0 = 2e4, -- max. vacuum thrust [N]
isp0 = 5e4 -- vacuum ISP value [m/s]
}
thhovr_prm = { -- hover thruster parameters
pos = {x=0,y=-1.5,z=0}, -- thrust attack point [m]
dir = {x=0,y=1,z=0}, -- thrust direction
maxth0 = 1.5e4, -- max. vacuum thrust [N]
isp0 = 5e4 -- vacuum ISP value [m/s]
}
thrcs_prm = { -- RCS thruster parameters
maxth0 = 2e2, -- max. vaccum thrust [N]
isp0 = 5e4 -- vacuum ISP value [m/s]
}
dprm = { -- docking port parameters
pos = {x=0,y=1.3,z=-1}, -- position
dir = {x=0,y=1,z=0}, -- approach direction
rot = {x=0,y=0,z=-1} -- longitudinal alignment
}
trans_Laileron = { -- transformation for left aileron animation
type = 'rotation', -- transformation type
mesh = 0, -- mesh index
grp = 2, -- group indices
ref = {x=-1.3,y=-0.725,z=-1.5}, -- reference point
axis = {x=-0.9619,y=-0.2735,z=0}, -- rotation axis
angle = 20*RAD -- rotation angle
}
trans_Raileron = { -- transformation for right aileron animation
type = 'rotation', -- transformation type
mesh = 0, -- mesh index
grp = 3, -- group indices
ref = {x=1.3,y=-0.725,z=-1.5}, -- reference point
axis = {x=0.9619,y=-0.2735,z=0}, -- rotation axis
angle = 20*RAD -- rotation angle
}
trans_Lelevator = { -- transformation for left elevator animation
type = 'rotation', -- transformation type
mesh = 0, -- mesh index
grp = 2, -- group indices
ref = {x=-1.3,y=-0.725,z=-1.5}, -- reference point
axis = {x=-0.9619,y=-0.2735,z=0}, -- rotation axis
angle = -30*RAD -- rotation angle
}
trans_Relevator = { -- transformation for right elevator animation
type = 'rotation', -- transformation type
mesh = 0, -- mesh index
grp = 3, -- group indices
ref = {x=1.3,y=-0.725,z=-1.5}, -- reference point
axis = {x=0.9619,y=-0.2735,z=0}, -- rotation axis
angle = 30*RAD -- rotation angle
}
-- SetClassCaps implementation
function clbk_setclasscaps(cfg)
-- physical vessel parameters
vi:set_size(vprm.size)
vi:set_emptymass(vprm.emass)
vi:set_pmi(vprm.pmi)
vi:set_crosssections(vprm.cs)
vi:set_rotdrag(vprm.rd)
vi:set_touchdownpoints(vprm.td1,vprm.td2,vprm.td3)
-- docking port definitions
hDock = vi:set_dockparams(dprm.pos,dprm.dir,dprm.rot)
-- airfoil definitions
vi:create_airfoil(LIFT.VERTICAL,{x=0,y=0,z=-0.1},'vlift',2,2,2.5)
vi:create_airfoil(LIFT.HORIZONTAL,{x=0,y=0,z=-0.1},'hlift',2,1.5,2)
-- control surface animations
animcomp_Laileron = oapi.create_animationcomponent(trans_Laileron)
animcomp_Raileron = oapi.create_animationcomponent(trans_Raileron)
animcomp_Lelevator = oapi.create_animationcomponent(trans_Lelevator)
animcomp_Relevator = oapi.create_animationcomponent(trans_Relevator)
anim_Laileron = vi:create_animation(0.5)
anim_Raileron = vi:create_animation(0.5)
anim_elevator = vi:create_animation(0.5)
vi:add_animationcomponent(anim_Laileron,0,1,animcomp_Laileron)
vi:add_animationcomponent(anim_Raileron,0,1,animcomp_Raileron)
vi:add_animationcomponent(anim_elevator,0,1,animcomp_Lelevator)
vi:add_animationcomponent(anim_elevator,0,1,animcomp_Relevator)
-- aerodynamic control surface definitions
vi:create_controlsurface(AIRCTRL.ELEVATOR, 1.5, 0.5, {x=0,y=0,z=-2.5}, AIRCTRL_AXIS.XPOS, 1.0, anim_elevator);
vi:create_controlsurface(AIRCTRL.AILERON, 1.5, 0.25, {x=1,y=0,z=-2.5}, AIRCTRL_AXIS.XPOS, 1.0, anim_Laileron);
vi:create_controlsurface(AIRCTRL.AILERON, 1.5, 0.25, {x=-1,y=0,z=-2.5}, AIRCTRL_AXIS.XNEG, 1.0, anim_Raileron);
-- propellant resources
hProp = vi:create_propellantresource(vprm.fuelmass)
-- main engine
thmain_prm.hprop = hProp
thmain = vi:create_thruster(thmain_prm)
thgmain = vi:create_thrustergroup({thmain},THGROUP.MAIN)
-- hover engine
thhovr_prm.hprop = hProp
thhovr = vi:create_thruster(thhovr_prm)
thghovr = vi:create_thrustergroup({thhovr},THGROUP.HOVER)
-- RCS engines
th = thrcs_prm.maxth0
isp = thrcs_prm.isp0
thrcs0 = vi:create_thruster({pos={x=1,y=0,z=3},dir={x=0,y=1,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs1 = vi:create_thruster({pos={x=1,y=0,z=3},dir={x=0,y=-1,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs2 = vi:create_thruster({pos={x=-1,y=0,z=3},dir={x=0,y=1,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs3 = vi:create_thruster({pos={x=-1,y=0,z=3},dir={x=0,y=-1,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs4 = vi:create_thruster({pos={x=1,y=0,z=-3},dir={x=0,y=1,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs5 = vi:create_thruster({pos={x=1,y=0,z=-3},dir={x=0,y=-1,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs6 = vi:create_thruster({pos={x=-1,y=0,z=-3},dir={x=0,y=1,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs7 = vi:create_thruster({pos={x=-1,y=0,z=-3},dir={x=0,y=-1,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs8 = vi:create_thruster({pos={x=1,y=0,z=3},dir={x=-1,y=0,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs9 = vi:create_thruster({pos={x=-1,y=0,z=3},dir={x=1,y=0,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs10 = vi:create_thruster({pos={x=1,y=0,z=-3},dir={x=-1,y=0,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs11 = vi:create_thruster({pos={x=-1,y=0,z=-3},dir={x=1,y=0,z=0},maxth0=th,isp0=isp,hprop=hProp})
thrcs12 = vi:create_thruster({pos={x=0,y=0,z=-3},dir={x=0,y=0,z=1},maxth0=th,isp0=isp,hprop=hProp})
thrcs13 = vi:create_thruster({pos={x=0,y=0,z=3},dir={x=0,y=0,z=-1},maxth0=th,isp0=isp,hprop=hProp})
vi:create_thrustergroup({thrcs0,thrcs2,thrcs5,thrcs7},THGROUP.ATT_PITCHUP)
vi:create_thrustergroup({thrcs1,thrcs3,thrcs4,thrcs6},THGROUP.ATT_PITCHDOWN)
vi:create_thrustergroup({thrcs0,thrcs4,thrcs3,thrcs7},THGROUP.ATT_BANKLEFT)
vi:create_thrustergroup({thrcs1,thrcs5,thrcs2,thrcs6},THGROUP.ATT_BANKRIGHT)
vi:create_thrustergroup({thrcs0,thrcs4,thrcs2,thrcs6},THGROUP.ATT_UP)
vi:create_thrustergroup({thrcs1,thrcs5,thrcs3,thrcs7},THGROUP.ATT_DOWN)
vi:create_thrustergroup({thrcs8,thrcs11},THGROUP.ATT_YAWLEFT)
vi:create_thrustergroup({thrcs9,thrcs10},THGROUP.ATT_YAWRIGHT)
vi:create_thrustergroup({thrcs8,thrcs10},THGROUP.ATT_LEFT)
vi:create_thrustergroup({thrcs9,thrcs11},THGROUP.ATT_RIGHT)
vi:create_thrustergroup({thrcs12},THGROUP.ATT_FORWARD)
vi:create_thrustergroup({thrcs13},THGROUP.ATT_BACK)
-- engine exhaust definitions
vi:add_exhaust(thmain,8,1,{x=0,y=0.3,z=-4.35},{x=0,y=0,z=-1})
vi:add_exhaust(thhovr,8,1,{x=0,y=-1.5,z=1},{x=0,y=-1,z=0})
vi:add_exhaust(thhovr,8,1,{x=0,y=-1.5,z=-1},{x=0,y=-1,z=0})
-- exhaust particle stream definitions
contrail_main = {
srcsize = 5.0,
srcrate = 16,
v0 = 200,
srcspread = 0.15,
lifetime = 1.0,
growthrate = 5,
atmslowdown = 3.0,
ltype = PARTICLE.DIFFUSE,
levelmap = PARTICLE.LVL_PSQRT,
lmin = 0,
lmax = 2,
atmsmap = PARTICLE.ATM_PLOG,
amin = 1e-4,
amax = 1
}
exhaust_main = {
srcsize = 2.0,
srcrate = 20,
v0 = 200,
srcspread = 0.05,
lifetime = 0.1,
growthrate = 8,
atmslowdown = 1.0,
ltype = PARTICLE.EMISSIVE,
levelmap = PARTICLE.LVL_SQRT,
atmsmap = PARTICLE.ATM_PLOG,
amin = 1e-5,
amax = 0.1
}
vi:add_exhauststream(thmain,{x=0,y=0.3,z=-10},contrail_main)
vi:add_exhauststream(thmain,{x=0,y=0.3,z=-5},exhaust_main)
contrail_hovr = {
srcsize = 5.0,
srcrate = 8,
v0 = 200,
srcspread = 0.15,
lifetime = 1.0,
growthrate = 5,
atmslowdown = 3.0,
ltype = PARTICLE.DIFFUSE,
levelmap = PARTICLE.LVL_PSQRT,
lmin = 0,
lmax = 2,
atmsmap = PARTICLE.ATM_PLOG,
amin = 1e-4,
amax = 1
}
exhaust_hovr = {
srcsize = 2.0,
srcrate = 10,
v0 = 200,
srcspread = 0.05,
lifetime = 0.05,
growthrate = 8,
atmslowdown = 1.0,
ltype = PARTICLE.EMISSIVE,
levelmap = PARTICLE.LVL_SQRT,
atmsmap = PARTICLE.ATM_PLOG,
amin = 1e-5,
amax = 0.1
}
vi:add_exhauststream(thhovr,{x=0,y=-3,z=1},contrail_hovr)
vi:add_exhauststream(thhovr,{x=0,y=-3,z=-1},contrail_hovr)
vi:add_exhauststream(thhovr,{x=0,y=-2,z=1},exhaust_hovr)
vi:add_exhauststream(thhovr,{x=0,y=-2,z=-1},exhaust_hovr)
-- camera parameters
vi:set_cameraoffset(vprm.co)
-- associate a mesh for the visual
vi:add_mesh('ShuttlePB')
end
-- vertical airfoil definition
function vlift(hVessel,aoa,M,Re)
idx = math.floor((aoa+PI)/afv.aoa_step)
a = (aoa+PI-idx*afv.aoa_step)/afv.aoa_step
cl = afv.cl[idx+1]*(1-a) + afv.cl[idx+2]*a -- lift coefficient (linear interpolation)
-- cl = cl*0.5
cm = -0.03*math.sin(aoa-0.1) -- moment coefficient
saoa = math.sin(aoa)
cdp = afv.dp + 0.4*saoa*saoa -- profile drag
cdi = oapi.get_induceddrag(cl,afv.di.A,afv.di.e) -- induced drag
cdw = oapi.get_wavedrag(M,afv.dw.M1,afv.dw.M2,afv.dw.M3,afv.dw.cmax)
-- wave drag
cd = cdp + cdi + cdw -- drag coefficient
return cl,cm,cd
end
-- horizontal airfoil definition
function hlift(hVessel,aoa,M,Re)
idx = math.floor((aoa+PI)/afh.aoa_step)
a = (aoa+PI-idx*afh.aoa_step)/afh.aoa_step
cl = afh.cl[idx+1]*(1-a) + afh.cl[idx+2]*a
cdp = afh.dp
cdi = oapi.get_induceddrag(cl,afh.di.A,afh.di.e)
cdw = oapi.get_wavedrag(M,afh.dw.M1,afh.dw.M2,afh.dw.M3,afh.dw.cmax)
cd = cdp + cdi + cdw;
return cl,0,cd
end
```