Using a planet’s atmosphere to reduce velocity and achieve orbit or entry.

A low-energy maneuver to slowly capture a spacecraft into orbit using gravity.

A three-burn maneuver, transferring through an intermediate orbit that extends further than the target orbit.

Adjusting an orbit to match another object's velocity and position.

A repeated trajectory that cycles between planets, minimizing propellant use.

A burn to achieve escape velocity and leave a celestial body's sphere of influence.

Using the gravitational pull of a celestial body to change trajectory and increase/decrease velocity.

A two-burn maneuver used to transfer between two coplanar circular orbits.

A single burn to adjust the inclination of an orbit.

A burn to leave a planet's sphere of influence and enter an interplanetary trajectory.

A maneuver to position a spacecraft at one of the stable Lagrange points (e.g., L1, L2).

Using low-thrust propulsion (e.g., ion engines) to spiral outward/inward to a target orbit.

A maneuver performed near a planet or celestial body where orbital velocity is highest, maximizing delta-v efficiency.

A burn to adjust an elliptical orbit into a circular one.

Burns to counteract atmospheric drag or gravitational perturbations.

A burn to establish orbit after reaching a target body.

A burn to adjust the orbital period, allowing synchronization with another object (e.g., docking or rendezvous).

Aligning the spacecraft for atmospheric entry, ensuring safe descent.

Aligning the spacecraft for atmospheric entry, ensuring safe descent.

Small burns to maintain a spacecraft's position in a stable orbit.

Adjusting trajectory to approach the Sun closely.

Final adjustments to relative velocity and position for docking.

Matching a Trojan object's orbit (leading or trailing 60° of a planet’s orbit).