Maneuver planning

Applies to Orbit Visualizer v1.1 · Updated July 5, 2026

Add impulsive ΔV burns to any scenario object. Each maneuver node can be a manual burn in the RIC or ECI frame, or a preset (Hohmann transfer, circularization, plane change, Lambert transfer). The post-burn arc is drawn in the 3D scene; a running total-ΔV budget appears on the object card.

▶ Open an ISS-class orbit to try maneuvers on

Quick start

1. Expand the object card in Scenario Objects by clicking the object name.
2. Click Add Maneuver at the bottom of the card.
3. Set the Maneuver time (minutes past the object’s epoch) to place the burn where you want it in the orbit.
4. For a manual burn, choose Manual burn (RIC/ECI ΔV) from the Maneuver type dropdown. Select the frame (RIC or ECI (J2000)) and enter the three ΔV components in m/s.
5. Click Save. The node appears in the maneuver list with its |ΔV|, and the post-burn arc is drawn in the 3D scene.

Manual burn — RIC and ECI frames

A manual burn takes three ΔV components in m/s, stored internally in km/s. Two frames are available:

• RIC (Radial, In-track, Cross-track) — components relative to the object’s own orbital frame at the burn time. Radial is aligned with the position vector (outward from Earth), In-track is along the velocity vector, and Cross-track is normal to the orbital plane. This is the most intuitive frame for orbit-raising and plane-change burns.
• ECI (J2000) — components in the inertial Earth-Centered Inertial frame. Use this when your ΔV comes from an external source already expressed in ECI.

The live |ΔV| readout updates as you type. The object card keeps a running Total ΔV budget in m/s across all nodes.

Presets

Three standard maneuvers are available as presets. Each uses two-body geometry to compute the required ΔV for preview, which is standard practice for quick maneuver planning. Select the preset from the Maneuver type dropdown:

Hohmann transfer

Two tangential in-track burns (both in the RIC frame) to move from the current circular orbit to a target semi-major axis. The first burn raises (or lowers) the orbit to an elliptical transfer arc; the second circularizes at the target altitude. Enter the target semi-major axis (km); the dialog computes both ΔVs and their magnitudes. The note “Two tangential burns; assumes a circular start.” is shown as a reminder.

Circularization

A single in-track burn at either apoapsis or periapsis to circularize an elliptical orbit at that altitude. Specify at apoapsis (circularizes the orbit at its farthest point, enlarging the periapsis) or at periapsis (circularizes at the closest point, reducing the apoapsis). The note “Single in-track burn at apoapsis/periapsis.” accompanies the result.

Plane change

Rotates the orbital plane to a target inclination. For a circular orbit this is: |ΔV| = 2v sin(Δi/2). Three timing options set when the burn fires:

• Ascending node (default) — places the burn at the next equatorial ascending-node crossing. At a node the burn changes inclination by exactly Δi with no right-ascension side effects on a circular orbit. Minimum ΔV for inclination-only changes.
• Max cross-track — places the burn 90° of argument of latitude past the ascending node (maximum cross-track offset). Rarely the most ΔV-efficient choice but sometimes operationally useful.
• Immediate — fires at the current scenario time regardless of orbital position.

Lambert transfer

An iterative Lambert solver finds two burns (departure and arrival) that connect the object’s position at departure time to a target object’s position at arrival time, with an optional RIC aim offset. The result is a rendezvous trajectory between two scenario objects over a specified time-of-flight.

ΔV budget

The object card shows “Total ΔV: X.X m/s · N/M nodes” where N is the number of existing nodes and M is the limit for your plan. Maneuver list rows show the label (or “Maneuver” if blank), the individual |ΔV| in m/s, and edit/delete buttons.

SGP4 objects: post-maneuver arc on J2 secular

SGP4 propagation requires TLE mean elements as input — it cannot ingest a post-burn osculating state. When you add a maneuver to an SGP4 object, the app automatically switches the post-burn arc to the J2 secular propagator, and the maneuver list shows the note:

post-maneuver arc: J2 secular

This is the app’s most physically honest choice: J2 adds Earth-oblateness drift on top of a Keplerian ellipse, which is more realistic than two-body for predicting where a post-burn orbit goes over hours to days. You can also switch the post-burn arc to two-body manually by editing the object’s propagator after the maneuver is added — but the honest-disclaimer warning (“TLE mean elements propagated as osculating — expect divergence”) will appear.

Escape trajectories

If a maneuver’s ΔV sends the orbit onto a hyperbolic escape trajectory (eccentricity ≥ 1), the app cannot render the post-burn arc. The node is still recorded and the ΔV budget is shown, but the card displays: “escape trajectory — rendering unsupported past the burn.”

Accuracy & model notes

Preset ΔVs are computed using two-body geometry, which is standard practice for initial sizing. This means the Hohmann and circularization ΔVs assume a perfectly circular orbit; any eccentricity in the actual orbit introduces a discrepancy. For the post-burn propagated arc, J2 secular adds mean orbital-plane drift but not drag, higher-order gravity, or resonance effects. Real mission planning requires higher-fidelity tools. The propagation disclaimer appears below each object: Propagation models explains what each model does and does not account for.

Related

• Ground sites & access — check how a post-maneuver orbit changes your pass times.
• Propagation models — why J2 is used for the post-burn arc.
• Plans & limits — maneuver-node caps per plan.