僅供翻譯

<event name="Terminate">
<description>
When the aircraft arrives back at Ellington
Field (fifth waypoint) then terminate the simulation.
</description>
<condition>
fcs/wp-distance lt 100
ap/active-waypoint eq 5
</condition>
<set name="simulation/terminate" value="1"/>
<notify/>
</event>
<event name="Set last waypoint">
<description>
When the distance to the fourth waypoint (northeast end of
Galveston Island) is less than 100 feet, then set the last
waypoint (back to Ellington Field).
</description>
<condition>
fcs/wp-distance lt 100
ap/active-waypoint eq 4
</condition>
<set name="ap/wp_latitude_rad" value="0.516512"/>
<set name="ap/wp_longitude_rad" value="-1.660922"/>
<set name="ap/active-waypoint" value="5"/>
<notify>
<property>fcs/wp-distance</property>
</notify>
</event>
<event name="Set fourth waypoint">
<description>
When the distance to the third waypoint (southwest end of
Galveston Island) is less than 800 feet, then set the fourth
waypoint (northeast end of Galveston Island).
</description>
<condition>
fcs/wp-distance lt 800
ap/active-waypoint eq 3
</condition>
<set name="ap/wp_latitude_rad" value="0.511661"/>
<set name="ap/wp_longitude_rad" value="-1.653510"/>
<set name="ap/active-waypoint" value="4"/>
<notify>
<property>fcs/wp-distance</property>
</notify>
</event>
<event name="Set third waypoint">
<description>
When the distance to the second waypoint (Hobby Airport) is
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less than 300 feet, then set the third waypoint.
</description>
<condition>
fcs/wp-distance lt 300
ap/active-waypoint eq 2
</condition>
<set name="ap/wp_latitude_rad" value="0.507481"/>
<set name="ap/wp_longitude_rad" value="-1.660062"/>
<set name="ap/active-waypoint" value="3"/>
<notify>
<property>fcs/wp-distance</property>
</notify>
</event>

<event name="Set second waypoint">
<description>
When the distance to the first waypoint (Hobby
Airport threshold) is less than 700 feet, then
set the second waypoint.
</description>
<condition>
fcs/wp-distance lt 700
ap/active-waypoint eq 1
</condition>
<set name="ap/wp_latitude_rad" value="0.517533"/>
<set name="ap/wp_longitude_rad" value="-1.663076"/>
<set name="ap/active-waypoint" value="2"/>
<notify>
<property>fcs/wp-distance</property>
</notify>
</event>

</run>
</runscript>
[Article in-work … ]
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6. Rocket with GNC and Scripting
For a long time now, rocket-propelled flight models in JSBSim have been possible (the X-15
was the first vehicle modeled for JSBSim), but in actually making a vertical, guided, rocket flight
model, some new capabilities were added to support modeling of launch vehicles. This section
will cover some of the techniques used in executing launch vehicle flight in JSBSim.
Some of the major differences in modeling vertical takeoff launch vehicle flight (compared to
modeling aircraft) are:
• Takeoff is (obviously) vertical; ground reactions are tougher because they are stiffer.
• Guidance in first stage (often corresponding roughly to the atmospheric flight phase) is
typically open loop, with second stage flight following a more complicated guidance
scheme such as “Powered Explicit Guidance” (PEG).
• Control involves gimbaled effectors (thrusters, or nozzles).
• Control is normally completely
• Aerodynamic modeling is different.
automatic.
• Sensor modeling can be more complicated, since sensors such as accelerometers
cannot necessarily be placed at the center of mass (which may be inside a propellant
tank!)
At this time, it is easy to model single stage rocket flight using JSBSim, but multi-stage flight is
more cumbersome.
6.1 Addressing the ground reactions
For a vertically launched rocket, a way was needed to keep the vehicle firmly attached to one
spot, as if it was mounted on a launch platform. It was not easy to make the standard ground
reactions work well, particularly after the engines had been started, but before thrust had built up
to the point where the vehicle lifted off the platform. So, a new flag was created (a property)
which, if set, causes a ground reaction force equal and opposite to the aerodynamic,
gravitational, and propulsive forces, and so the vehicle stays put. The property name for the holddown
flag is forces/hold-down.
6.2 Simple rocket guidance
The path a rocket takes in vertical flight is not normally manually flown, because the total
angle of attack must be kept low to keep structural loads small, and to minimize aerodynamic
drag. One key measurement tracked is q*alpha – that is, dynamic pressure multiplied by the
angle of attack.
There are several phases of flight for an ascending launch vehicle:
• The vertical rise phase
• The kick angle or tilt phase
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• The gravity turn phase
During the vertical rise period, the vehicle ascends straight up to clear the launch platform and
then rolls to align to the appropriate heading. Sometimes, as it was in the case of the Apollo
Saturn V, a slight yaw is introduced away from the launch tower just after liftoff. In the kick angle
phase, the vehicle is commanded to an initial pitch angle, after which it begins the zero-lift (zeroalpha)
gravity turn phase as it flies through the lower, most dense portion of the atmosphere at an
increasingly higher velocity. Control during these phases is normally exercised by gimballing the
main rocket engines, and/or through the use of auxiliary reaction control jets (RCS).
In JSBSim, we encounter a few new situations that must be addressed when modeling vertical
rocket flight. First of all, in the vertical rise period, the question can be asked: how do we
command the vehicle to roll to the appropriate heading, since the vehicle is pointed vertically?
The frames of interest here are the local frame, which is a frame that is always underneath the
aircraft, with the X axis pointing north, the Y axis pointing East, and the Z axis pointing downward.
The origin of the local frame is at sea level. The vehicle body frame has the X axis along the
vehicle centerline pointing forward out the nose, the Y axis pointing out the “right”, and the Z axis
pointing “down” out the bottom of the vehicle. For a rocket, the Y and Z directions seem
somewhat arbitrary. Placing the rocket initially on a launch pad at Kennedy Space Center,
Kourou, or Baikonur (for example), involves setting the initial latitude, longitude, and altitude, and
orienting the vehicle on the launch pad. Since the order of rotations used in JSBSim to describe
the orientation of a vehicle (that is, the orientation of the body frame for the vehicle) relative to the
local frame is yaw, then pitch, then roll, it can be seen that the vehicle orientation can be
described as having a pitch angle of +90 degrees relative to the local frame. If the vehicle has a
particular roll orientation on the pad, the vehicle can be rolled after it is initially pitched. The initial
orientation can be specified in the initialization file as having a particular psi, theta, and phi (Euler
angles).
During the vertical rise period, the vehicle is pointed nearly straight upwards, which can cause
problems in any guidance we might use to keep the vehicle pointed straight up, and also to roll it
to a particular heading. One way to get around this is to simply devise a controller that both keeps
the pitch and yaw rates at zero (which keeps the vehicle pointed up), and commands a roll rate to
achieve the desired heading once the pitchover begins. The roll rate needs to be carefully
controlled to ramp up, then back down to zero, prior to beginning to pitch over.
Control of the vehicle is performed (as mentioned before) by gimballing engines for pitch and
yaw control. Roll control can be implemented by differentially gimballing multiple engines, or for a
single engine vehicle by using RCS thrusters or turbine exhaust through a gimbaled nozzle. For
the vertical rise period, it is not too hard to set up a control law for the pitch and yaw axes that
take the pitch (or yaw) rate as input and generates a pitch (or yaw) engine gimbal command to
counter that and bring the respective rate back to zero.
6.3 “Moding” and Timing
A question can be addressed at this time regarding how to command the various portions of
the flight – that is, when should the vertical rise, or the tilt, or the gravity turn phases be initiated?
This is related in a way to the subject of how to organize the guidance, navigation, and control
(referred to as GNC) aspects of a simulated launch vehicle in JSBSim. We could call this the
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simulated “flight software” (FSW), which is really what is being represented. The question to
address can be summed up: is the timing of the mode changes during the flight controlled from
the ground (which might be modeled in a script), or onboard the launch vehicle? If it originates on
the launch vehicle, we might assert that the timing is part of the flight software. The various
modes are then, in fact, initiated from aboard the vehicle itself. It’s the safest approach; think of
what would happen in the case of a momentary communications loss.
So, for first stage flight we need a vertical rise phase, followed by a tilt phase, followed by a
gravity turn phase – all controlled from the launch vehicle itself. For JSBSim that means we need
the sequencing function to be present in the flight control or system section of the vehicle
configuration file.
The system section is a relatively recent addition in the latest version of JSBSim. Any number
of systems can be defined, and they use the same syntax as the flight control section. The
system section is useful when a guidance, or navigation, or electrical system is desired to be
modeled in JSBSim using the suite of system components.
6.4 Where to Start?
As with all JSBSim aircraft models, vehicle characteristics will need to be known:
• Mass properties
• Geometry
• Control
• Propulsion
• Aerodynamics
• Ground contacts
Geometry is almost always quite easy. Mass properties are little bit harder, but one can make
fairly good guesses at this. [Note: for some historic rockets such as the Saturn V or Saturn IB,
there may be reference material available on the web and/or in technical papers.] Fuel burn-off
might be a complicating factor because the CG may shift, there may be fuel slosh (for liquid
propellant rockets), and moments of inertia will change. Control (Guidance, Navigation, and
Control, actually) is the most involved part of modeling a rocket. Propulsion for rockets can be
modeled rather simply in JSBSim. Aerodynamics is second to control as far as level of difficulty.
Ground contacts are straightforward.
6.5 Aerodynamics
Let’s look at aerodynamics first. We can determine the aerodynamic characteristics of a
simple axisymmetric body using DATCOM+ (see www.holycows.net), or – if you have access to it
– Missile DATCOM. There are other software titles out there as well. We will use the lift and drag
curves for the V-2 missile (as found in Sutton’s Rocket Propulsion Elements book) to model our
example rocket. We will also assume that the aerodynamics will be completely modeled by
proper placement of the aerodynamic center of pressure, coupled with the lift and drag curves,
and that the side force is the same as the lift force.
6.6 Mass Properties
Since we know the mass characteristics of the Little Joe, we will scale the moments and
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products of inertia of that vehicle once we specify the weight of our example rocket.
[Article in-work … ]
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140
Appendices
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141
Native properties
accelerations/Nz
accelerations/a-pilot-x-ft_sec2
accelerations/a-pilot-y-ft_sec2
accelerations/a-pilot-z-ft_sec2
accelerations/n-pilot-x-norm
accelerations/n-pilot-y-norm
accelerations/n-pilot-z-norm
accelerations/pdot-rad_sec2
accelerations/qdot-rad_sec2
accelerations/rdot-rad_sec2
accelerations/udot-ft_sec2
accelerations/vdot-ft_sec2
accelerations/wdot-ft_sec2
aero/alpha-deg
aero/alpha-max-rad
aero/alpha-min-rad
aero/alpha-rad
aero/alpha-wing-rad
aero/alphadot-deg_sec
aero/alphadot-rad_sec
aero/beta-deg
aero/beta-rad
aero/betadot-deg_sec
aero/betadot-rad_sec
aero/bi2vel
aero/ci2vel
aero/cl-squared
aero/h_b-cg-ft
aero/h_b-mac-ft
aero/mag-beta-deg
aero/mag-beta-rad
aero/qbar-area
aero/qbar-psf
aero/qbarUV-psf
aero/qbarUW-psf
aero/stall-hyst-norm
atmosphere/P-psf
atmosphere/P-sl-psf
atmosphere/T-R
atmosphere/T-sl-R
atmosphere/T-sl-dev-F
atmosphere/a-fps
atmosphere/a-ratio
atmosphere/a-sl-fps
atmosphere/crosswind-fps
atmosphere/delta
atmosphere/delta-T
atmosphere/density-altitude
atmosphere/gust-down-fps
atmosphere/gust-east-fps
atmosphere/gust-north-fps
atmosphere/headwind-fps
atmosphere/p-turb-rad_sec
atmosphere/psiw-rad
atmosphere/q-turb-rad_sec
atmosphere/r-turb-rad_sec
atmosphere/rho-sl-slugs_ft3
atmosphere/rho-slugs_ft3
atmosphere/sigma
atmosphere/theta
atmosphere/turb-gain
atmosphere/turb-rate
atmosphere/turb-rhythmicity
atmosphere/wind-from-cw
attitude/heading-true-rad
attitude/phi-rad
attitude/pitch-rad
attitude/psi-rad
attitude/roll-rad
attitude/theta-rad
fcs/aileron-cmd-norm
fcs/center-brake-cmd-norm
fcs/elevator-cmd-norm
fcs/elevator-pos-deg
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fcs/elevator-pos-norm
fcs/elevator-pos-rad
fcs/flap-cmd-norm
fcs/flap-pos-deg
fcs/flap-pos-norm
fcs/flap-pos-rad
fcs/left-aileron-pos-deg
fcs/left-aileron-pos-norm
fcs/left-aileron-pos-rad
fcs/left-brake-cmd-norm
fcs/mag-elevator-pos-rad
fcs/mag-left-aileron-pos-rad
fcs/mag-right-aileron-pos-rad
fcs/mag-rudder-pos-rad
fcs/mag-speedbrake-pos-rad
fcs/mag-spoiler-pos-rad
fcs/pitch-trim-cmd-norm
fcs/right-aileron-pos-deg
fcs/right-aileron-pos-norm
fcs/right-aileron-pos-rad
fcs/right-brake-cmd-norm
fcs/roll-trim-cmd-norm
fcs/rudder-cmd-norm
fcs/rudder-pos-deg
fcs/rudder-pos-norm
fcs/rudder-pos-rad
fcs/speedbrake-cmd-norm
fcs/speedbrake-pos-deg
fcs/speedbrake-pos-norm
fcs/speedbrake-pos-rad
fcs/spoiler-cmd-norm
fcs/spoiler-pos-deg
fcs/spoiler-pos-norm
fcs/spoiler-pos-rad
fcs/steer-cmd-norm
fcs/yaw-trim-cmd-norm
flight-path/gamma-rad
flight-path/psi-gt-rad
forces/fbx-aero-lbs
forces/fbx-gear-lbs
forces/fbx-prop-lbs
forces/fbx-total-lbs
forces/fby-aero-lbs
forces/fby-gear-lbs
forces/fby-prop-lbs
forces/fby-total-lbs
forces/fbz-aero-lbs
forces/fbz-gear-lbs
forces/fbz-prop-lbs
forces/fbz-total-lbs
forces/fwx-aero-lbs
forces/fwy-aero-lbs
forces/fwz-aero-lbs
forces/hold-down
forces/lod-norm
gear/gear-cmd-norm
gear/gear-pos-norm
gear/num-units
ic/alpha-deg
ic/alpha-rad
ic/beta-deg
ic/beta-rad
ic/gamma-deg
ic/gamma-rad
ic/h-agl-ft
ic/h-sl-ft
ic/lat-gc-deg
ic/lat-gc-rad
ic/long-gc-deg
ic/long-gc-rad
ic/mach
ic/p-rad_sec
ic/phi-deg
ic/phi-rad
ic/psi-true-deg
ic/psi-true-rad
ic/q-rad_sec
ic/r-rad_sec
ic/roc-fpm
ic/roc-fps
ic/sea-level-radius-ft
ic/terrain-altitude-ft
ic/theta-deg
ic/theta-rad
ic/u-fps
ic/v-fps
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ic/vc-kts
ic/vd-fps
ic/ve-fps
ic/ve-kts
ic/vg-fps
ic/vg-kts
ic/vn-fps
ic/vt-fps
ic/vt-kts
ic/vw-bx-fps
ic/vw-by-fps
ic/vw-bz-fps
ic/vw-dir-deg
ic/vw-down-fps
ic/vw-east-fps
ic/vw-mag-fps
ic/vw-north-fps
ic/w-fps
inertia/cg-x-in
inertia/cg-y-in
inertia/cg-z-in
inertia/empty-weight-lbs
inertia/mass-slugs
inertia/weight-lbs
metrics/Sh-sqft
metrics/Sv-sqft
metrics/Sw-sqft
metrics/aero-rp-x-in
metrics/aero-rp-y-in
metrics/aero-rp-z-in
metrics/bw-ft
metrics/cbarw-ft
metrics/eyepoint-x-in
metrics/eyepoint-y-in
metrics/eyepoint-z-in
metrics/iw-deg
metrics/iw-rad
metrics/lh-ft
metrics/lh-norm
metrics/lv-ft
metrics/lv-norm
metrics/runway-radius
metrics/vbarh-norm
metrics/vbarv-norm
metrics/visualrefpoint-x-in
metrics/visualrefpoint-y-in
metrics/visualrefpoint-z-in
moments/l-aero-lbsft
moments/l-gear-lbsft
moments/l-prop-lbsft
moments/l-total-lbsft
moments/m-aero-lbsft
moments/m-gear-lbsft
moments/m-prop-lbsft
moments/m-total-lbsft
moments/n-aero-lbsft
moments/n-gear-lbsft
moments/n-prop-lbsft
moments/n-total-lbsft
output-norm
position/distance-from-start-lat-mt
position/distance-from-start-lon-mt
position/distance-from-start-mag-mt
position/epa-rad
position/geod-alt-ft
position/h-agl-ft
position/h-sl-ft
position/h-sl-meters
position/lat-gc-deg
position/lat-gc-rad
position/lat-geod-deg
position/lat-geod-rad
position/long-gc-deg
position/long-gc-rad
position/radius-to-vehicle-ft
position/terrain-elevation-asl-ft
propulsion/active_engine
propulsion/cutoff_cmd
propulsion/fuel_dump
propulsion/magneto_cmd
propulsion/pt-lbs_sqft
propulsion/refuel
propulsion/set-running
propulsion/starter_cmd
propulsion/starter_cmd
propulsion/tat-c
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propulsion/tat-r
propulsion/total-fuel-lbs
sim-time-sec
simulation/cycle_duration
simulation/do_simple_trim
simulation/do_trim_analysis
simulation/frame_start_time
simulation/integrator/position/rotational
simulation/integrator/position/translational
simulation/integrator/rate/rotational
simulation/integrator/rate/translational
simulation/terminate
simulation/write-state-file
systems/stall-warn-norm
velocities/eci-velocity-mag-fps
velocities/h-dot-fps
velocities/mach
velocities/machU
velocities/p-aero-rad_sec
velocities/p-rad_sec
velocities/phidot-rad_sec
velocities/psidot-rad_sec
velocities/q-aero-rad_sec
velocities/q-rad_sec
velocities/r-aero-rad_sec
velocities/r-rad_sec
velocities/thetadot-rad_sec
velocities/u-aero-fps
velocities/u-fps
velocities/v-aero-fps
velocities/v-down-fps
velocities/v-east-fps
velocities/v-fps
velocities/v-north-fps
velocities/vc-fps
velocities/vc-kts
velocities/ve-fps
velocities/ve-kts
velocities/vg-fps
velocities/vt-fps
velocities/w-aero-fps
velocities/w-fps
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145
Glossary
FCS Flight Control System
JSBSim-ML JSBSim Markup Language
NED North East Down
VRP Vehicle Reference Point
XML eXtensible Markup Language
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INDEX
<
<actuator>.............................. 55
<aero_centered> .................... 51
<aerodynamics>..................... 18
<aerosurface_scale>....13, 51, 52
<author>............................... 109
<autopilot>........................25, 26
<axis> .................................... 19
<bias> ...................50, 55, 56, 57
<bits>..................................... 56
<builduptime>........................ 65
<c1>..................................47, 48
<c2>....................................... 47
<c3>....................................... 47
<c4>....................................... 47
<channel> .........................13, 26
<clipto>.............................13, 47
<condition>............................ 69
<deadband_width> ...........55, 56
<deadband> ........................... 53
<default>.....................26, 49, 50
<delay>.....................See Scripts
<description>....................15, 69
<domain>............................... 51
<drift_rate>............................ 56
<event>.................................. 69
<fcs_function>....................... 54
<filecreationdate>................ 109
<fileheader>......................... 109
<flight_control>................13, 25
<function> 15, 19, 20, 24, 54, 55
<gain>...................13, 26, 51, 52
<hysteresis_width>...........55, 56
<independentVar>15, 20, 24, 52,
55
<input> .............................13, 26
<integrator> ........................... 48
<isp>...................................... 65
<kd>....................................... 26
<ki>........................................ 26
<kinematic>......................53, 54
<kp>....................................... 26
<lag_filter> ............................ 47
<lag>.................................55, 56
<lead_lag_filter>.................... 47
<max>.........................47, 56, 57
<metrics>............................. 109
<min> .........................47, 56, 57
<noise_variation> .................. 56
<notify> ..............69, See Scripts
<pid>...................................... 26
<position>.............................. 54
<product>........14, 15, 20, 24, 55
<property> ......14, 15, 20, 24, 69
<pure_gain>................13, 26, 51
<quantization>....................... 56
<range>.......................13, 51, 52
<rate_limit>......................55, 56
<rocket_engine>.....................65
<run>......................................69
<runscript> .............................69
<scheduled_gain>...................52
<second_order_filter> ............48
<sensor> .................................56
<set>..................... 69, See Scripts
<setting>.................................54
<sum>.....................................14
<summer> ........................13, 50
<switch>...........................26, 49
<system> ................................25
<table> ..... 15, 19, 20, 24, 52, 55
<tableData>.... 15, 20, 24, 52, 55
<test>.......................... 26, 49, 50
<thrust> ..................................65
<time> ....................................54
<total_isp>..............................65
<traverse>...............................54
<trigger>.................................48
<use>......................................69
<value>...................................14
<variation> .............................65
<version>..............................109
<washout_filter> ....................48
<width> ..................................53
<wingspan>............................11
A
Absolute Value Component.. See
Flight control components
actions ...................... See Scripts
Actuator Component ..See Flight
control components
Aerodynamic coefficients.......18
Aerodynamics.........................18
Aerosurface Scaling Component
..................See Flight control
components
Autopilot
Wing leveler....................119
axis elements..........................19
B
Body frame.......... See Frames of
reference
Building JSBSim......................1
C
Class heirarchy .......................81
Coefficient buildup method....21
conditions................. See Scripts
configure ................................92
continuous................ See Scripts
CVS.......................................... 1
D
Deadband Component See Flight
control components
Downloading............................ 1
E
ECEF (Earth-Centered, EarthFixed)..............See
Frames of
reference
ECI (Earth-Centered, Inertial)
....... See Frames of reference
English Units............... See Units
Equations of Motion............... 97
event (script) .............See Scripts
F
FCS Function Component.....See
Flight control components
Filter Component ....... See Flight
control components
Flight control components
Absolute value .................. 53
Actuator............................ 55
Aerosurface scaling .......... 51
Deadband.......................... 53
Filters................................ 46
Function............................ 54
Gain .................................. 51
Hysteresis ......................... 53
Integrator .......................... 48
Kinematic ......................... 53
Lag filter........................... 47
Lead-lag filter ................... 47
Limiter.............................. 53
PID (Proportional-IntegralDerivative)
Controller
Component .................. 57
Positive or negative value . 53
Sample and hold ............... 50
Scheduled Gain Component
..................................... 52
Second order filter ............ 48
Sensor ............................... 56
Summer............................. 50
Switch............................... 49
Translational Accelerometer
..................................... 57
Washout filter ................... 48
Frames of reference
Body frame ....................... 10
Body-fixed........................ 97
ECEF ................................ 97
ECI.................................... 98
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NED.................................. 97
Stability frame .................. 10
Structural frame ................ 10
Wind frame....................... 11
Functions ............................... 14
G
Gain Component........ See Flight
control components
H
Hysteresis....... See Flight control
components
I
Isp See Specific Impulse
K
Kinematic ComponentSee Flight
control components
L
Limiter Component.... See Flight
control components
M
Math
Tables............................... 16
Metric Units.................See Units
mingw .................................... 92
N
NED (North-East-Down)...... See
Frames of reference
netcat ......................................61
O
Output.....................................59
P
persistent .................. See Scripts
PID (Proportional-IntegralDerivative)
Controller
ComponentSee Flight control
components
PID controller................. 31, 120
tuning ..............................121
Positive or Negative Value
ComponentSee Flight control
components
prep_plot ................................63
Properties................................12
R
Reference frames. See Frames of
reference
Rocket ....................................64
Running JSBSim ......................2
S
Sample and Hold ComponentSee
Flight control components
Scheduled Gain Component . See
Flight control components
Scripts.....................................69
actions...............................73
conditions..........................72
continuous......................... 71
delay ................................. 74
events.......................... 69, 71
notification........................ 74
notify................................. 74
persistent..................... 70, 72
set 73
Sensor Component..... See Flight
control components
Solid Rocket Motor................ 64
Specific Impulse ..................... 64
Stability frame......See Frames of
reference
stripchart ................................ 62
Structural frame ...See Frames of
reference
Summer Component .. See Flight
control components
Switch Component..... See Flight
control components
System components................ 25
T
Tables.......................... See Math
TCDS (Type Certificate Data
Sheet)................................ 20
Translational Accelerometer
ComponentSee Flight control
components
U
Units....................................... 11
W
Wind frame ..........See Frames of
reference
Wing leveler..........See Autopilot
wsock32 ................................. 92