Maneuvers¶

Source: AI/Tools/ManeuverTools.cs

Closed-form (analytical) delta-V computations for the standard impulsive maneuvers. All magnitudes are returned positive; the sign of the burn direction is implied by whether you are raising or lowering. Times are in seconds, distances in meters, speeds in m/s, angles in radians.

For numerical propagation that integrates a maneuver chain into the trajectory, see Scenario simulation.

ComputeApogeeChangeDeltaV¶

Single-impulse vis-viva delta-V at perigee that changes the orbit's apogee radius.

Parameter	Type	Description
`perigeeRadius`	meters	Current perigee (= burn radius)
`currentApogeeRadius`	meters
`targetApogeeRadius`	meters
`centerOfMotion`	`CelestialItemsEnum`

ComputePerigeeChangeDeltaV¶

Symmetric counterpart: single impulse at apogee that changes the perigee radius.

Parameter	Type
`apogeeRadius`	meters
`currentPerigeeRadius`	meters
`targetPerigeeRadius`	meters
`centerOfMotion`	`CelestialItemsEnum`

ComputeInclinationChangeDeltaV¶

Pure plane change at constant speed at the node: Δv = 2v · sin(Δi/2).

Parameter	Type
`velocity`	m/s
`deltaInclinationRad`	radians

ComputeCombinedPlaneChangeDeltaV¶

Simultaneous inclination + RAAN change at constant speed. The equivalent rotation angle θ is derived from the spherical law of cosines, then Δv = 2v · sin(θ/2).

Parameter	Type
`velocity`	m/s
`currentInclinationRad`	radians
`targetInclinationRad`	radians
`deltaRaanRad`	radians (target − current)

ComputePhasingDeltaV¶

First impulse of a phasing rendezvous on a circular orbit. The spacecraft enters a phasing ellipse, completes the requested number of revolutions, then re-circularizes with an equal-magnitude second burn — so total cost = 2 × returned value.

Parameter	Type	Description
`currentCircularRadius`	meters
`centerOfMotion`	`CelestialItemsEnum`
`deltaTrueAnomalyRad`	radians, normalized to `[0, 2π)`	Angular lead of the target ahead of the spacecraft
`revolutions`	uint, ≥ 1	Number of phasing revolutions before rendezvous

ComputeHohmannTransferDeltaV¶

Two-impulse Hohmann transfer between coplanar circular orbits.

Parameter	Type
`currentCircularRadius`	meters
`targetCircularRadius`	meters
`centerOfMotion`	`CelestialItemsEnum`

Returns { deltaV1, deltaV2, transferTime }.

{
  "currentCircularRadius": 6778000,
  "targetCircularRadius": 42164000,
  "centerOfMotion": "EARTH"
}

ComputeBiEllipticTransferDeltaV¶

Three-impulse bi-elliptic transfer between coplanar circular orbits via an intermediate apogee. The intermediate radius must exceed both endpoints.

Parameter	Type
`currentCircularRadius`	meters
`intermediateRadius`	meters
`targetCircularRadius`	meters
`centerOfMotion`	`CelestialItemsEnum`

Returns { deltaV1, deltaV2, deltaV3, transferTime }.

ApplyImpulsiveDeltaV¶

Apply an instantaneous Δv to a state vector. Position, epoch, frame and center of motion are preserved; velocity becomes v + Δv.

Parameter	Type
`currentState`	`StateVector`
`deltaV`	`Vector` in the same frame, in m/s