impulsiveManeuver

Add, replace or remove impulsive maneuvers

Since R2026a

Syntax

impulsiveManeuver(sat, deltaV)

impulsiveManeuver(sat, Name,Value)

maneuvers = impulsiveManeuver(sat, ___)

Description

impulsiveManeuver(sat, deltaV) executes an impulsive maneuver at the current SimulationTime of the satellite scenario for each satellite in sat. This syntax can be used only when the AutoSimulate property of satelliteScenario is set to false, this syntax can be used when the SimulationStatus property is set to In Progress.

impulsiveManeuver(sat, Name,Value) specifies options using one or more name-value arguments.

maneuvers = impulsiveManeuver(sat, ___) additionally returns the updated maneuver schedule in maneuvers.

Input Arguments

sat — Satellite

row vector of Satellite objects

Satellite, specified as a row vector of Satellite objects.

deltaV — Change in velocity

3-by-m array

Change in velocity, specified as a 3-by-m array in meters/second. The rows represent the x, y and z components of delta-V.

• When m = 1, the same delta-v is applied to all satellites in sat.

• When m >1, each column represents the delta-V to be applied to the corresponding satellite in sat.

Name-Value Arguments

Specify optional pairs of arguments as Name1=Value1,...,NameN=ValueN, where Name is the argument name and Value is the corresponding value. Name-value arguments must appear after other arguments, but the order of the pairs does not matter.

Example: Insert = timetable adds a timetable object as an impulsive maneuver to the existing schedule.

Insert — Insert impulsive maneuvers

timetable object | 1-by-m cell array of timetable objects

Impulsive maneuvers to insert into the existing schedule, specified as a timetable or cell array of timetables.

• When specified as a timetable, the same maneuvers are inserted for all satellites.

• When specified as a cell array, its size must match sat. Each cell contains a timetable for the corresponding satellite.

The timetable has a column titled Delta-V corresponding to the row time. For each time, deltaV is specified as a 3-element row vector. Optionally, the timetable can have these columns:

• CoordinateFrame — Represents the coordinate frame in which the deltaV is defined.

  CoordinateFrame	Description
  "inertial"	The delta-V is represented in ICRF frame.
  "fixed-frame"	The delta-V is represented in the ECEF frame.
  "ned"	The delta-V is represented in the North-East-Down frame.
  "vnb"	The delta-V is represented in the VNB frame, where the x-axis is the ICRF velocity direction, z-axis is the orbital angular momentum direction, and y-axis completes the triad.
  "lvlh"	The delta-V is defined in the Local Vertical - Local Horizontal frame, where z-axis is along the negative position vector, y-axis is along the negative orbital angular momentum vector, and x-axis completes the triad.

  Note

  If the CoordinateFrame column is not included in the timetable, the coordinate frame defaults to inertial.

• Name — Represents the name of the maneuver. If this column is not included in the timetable, the name defaults to "". Name must not equal "all" in any combination of uppercase or lowercase letters.

Replace — Replace existing impulsive maneuvers

timetable object | 1-by-m cell array of timetable objects

Impulsive maneuvers that replace the existing schedule, specified as a timetable or cell array of timetables.

• When specified as a timetable, the same maneuvers are applied for all satellites, replacing their existing impulsive maneuver schedule.

• When specified as a cell array, its size must match sat. Each cell contains a timetable for the corresponding satellite.

The timetable has a column titled deltaV corresponding to the row time. Optionally, the timetable can have these columns:

• CoordinateFrame — Represents the coordinate frame in which the DeltaV is defined. For each time, DeltaV is specified as a 3-element row vector.

  CoordinateFrame	Description
  "inertial"	The delta-V is represented in ICRF frame.
  "fixed-frame"	The delta-V is represented in the ECEF frame.
  "ned"	The delta-V is represented in the North-East-Down frame.
  "vnb"	The delta-V is represented in the VNB frame, where the x-axis is the ICRF velocity direction, z-axis is the orbital angular momentum direction, and y-axis completes the triad.
  "lvlh"	The delta-V is defined in the Local Vertical - Local Horizontal frame, where z-axis is along the negative position vector, y-axis is along the negative orbital angular momentum vector, and x-axis completes the triad.

  Note

  If the CoordinateFrame column is not included in the timetable, the coordinate frame defaults to inertial.

• Name — Represents the name of the maneuver. If this column is not included in the timetable, the name defaults to "". Name must not equal "all" in any combination of uppercase or lowercase letters.

Remove — Remove existing impulsive maneuvers

vector of doubles | string vector | "all" | 1-by-m cell array

Rows to remove from the impulsive maneuver schedule, specified as:

• Vector of doubles — To indicate row indices of maneuvers to be removed from every satellite in sat.

• String vector — To indicate names of maneuvers to be removed from every satellite in sat.

• "all" — To remove all maneuvers from every satellite in sat.

• Cell array — Each element represents the maneuvers that must be removed from the corresponding satellite in sat. A given cell array element can be a vector of doubles, string vector or the string "all".

CoordinateFrame — Coordinate frame for deltaV

string scalar | 1-by-m vector

Coordinate frame for deltaV, specified as a string scalar or 1-by-m vector.

CoordinateFrame	Description
"inertial"	The delta-V is represented in ICRF frame.
"fixed-frame"	The delta-V is represented in the ECEF frame.
"ned"	The delta-V is represented in the North-East-Down frame.
"vnb"	The delta-V is represented in the VNB frame, where the x-axis is the ICRF velocity direction, z-axis is the orbital angular momentum direction, and y-axis completes the triad.
"lvlh"	The delta-V is defined in the Local Vertical - Local Horizontal frame, where z-axis is along the negative position vector, y-axis is along the negative orbital angular momentum vector, and x-axis completes the triad.

Output Arguments

maneuvers — Updated maneuvers

timetable object | 1-by-m vector

Updated maneuvers stored in the ImpulsiveManeuvers property of the satellites in sat.

• When sat is scalar, maneuvers is a timetable equal to ImpulsiveManeuvers property of sat.

• When sat is a 1-by-m cell array, each element contains a timetable equal to ImpulsiveManeuvers property of the corresponding satellite.

Version History

Introduced in R2026a