Astronomy & Celestial Mechanics
the sky, computed
Concept

Orbit-insertion — where it appears

The braking manoeuvre that turns a spacecraft's approach hyperbola into a bound orbit around its target. It is made near periapsis, where each metre per second removes most energy, and it is often the largest burn of a mission.

Named by 4 essays across one field — each of them below, with the objects they name alongside it.

The cheapest circular orbit to stop in at Mars is not the lowest. The speed change needed to capture into a circular orbit round Mars, in km/s, against the orbit's radius in Mars radii, for arrival excesses of 2.65, 4, 6 km/s — the first being a minimum-energy transfer from the Earth. One burn at periapsis, where the spacecraft is fastest, turns the hyperbola into the circle. The cost has a minimum, at a radius of 2μ/v∞² from the planet's centre, where it is exactly v∞/√2: 3.6 radii and 1.87 km/s for 2.65 km/s; 1.6 radii and 2.83 km/s for 4 km/s; 0.7 radii and 4.24 km/s for 6 km/s. Lower orbits cost more because the circular speed there is higher than the gain from arriving deeper in the well; higher orbits cost more because the burn is made where the spacecraft is moving slowly and the Oberth effect is lost. A faster arrival moves the optimum inward, and at a large enough excess it moves below the planet's surface, where every circular orbit is on the expensive side of the minimum.

The cheapest circle to stop in

A spacecraft arriving at a planet has to lose speed to stay, and the cheapest circular orbit to lose it into is not the lowest. It sits at a radius set only by the arrival speed — twice the planet's gravitational parameter divided by the square of the excess — where the braking costs exactly the excess divided by the square root of two. Most orbiters want something else, and the arithmetic of what they do instead decides which planets are cheap to stop at and which are not.

spaceflight · Escape Propellant a moon saves, against how close the flyby comes. The reduction in the Jupiter orbit-insertion burn bought by one flyby of a Galilean moon on the way in, in metres per second, against the flyby altitude, for an arrival at 5.6 km/s, a periapsis of five Jupiter radii and a capture orbit of 200 days, whose insertion alone costs 825 m/s. At 300 km: Io 268 m/s, Europa 122 m/s, Ganymede 191 m/s, Callisto 124 m/s. The saving falls with altitude because the turn angle does, roughly as one over the flyby distance once that is well above the moon's surface. Io saves most: it is deep in Jupiter's well, where it moves fastest, so a given turn of the relative velocity takes more energy from the spacecraft. Ganymede, the most massive, is second.

Braking on a moon before braking with the engine

A gravity assist is usually told as a way to gain speed, but the same exchange runs the other way. A spacecraft falling toward Jupiter can pass behind one of its moons on the way in, lose a few hundred metres per second of its speed to the moon's orbit, and arrive at its capture burn needing a fifth less propellant. Which moon brakes best depends on three things at once — its mass, how fast it is met and how fast it moves — and the best one sits in radiation no spacecraft wants to fly through.

spaceflight · Gravity assist Each kilometre of aim error, turned into a velocity error. The error in the outgoing velocity per kilometre of error in where a spacecraft passes a moon, in metres per second per kilometre, against the flyby altitude on a logarithmic scale, for the four large moons of Jupiter at an encounter speed of 6 km/s. The flyby turns the velocity through an angle δ with tan(δ/2) = aₕ/b, where b is the aim point's distance from the moon's centre and aₕ = μ/v∞²; missing the aim by a kilometre along b changes δ, and missing it by a kilometre across b rotates the plane of the turn, and both move the outgoing velocity by about 2v∞aₕ/b² per kilometre. At 300 km above Ganymede that is 0.32 m/s per km along and 0.32 across. The closer and more massive the flyby, the more it turns — and the more it amplifies whatever error the approach carried.

A flyby that multiplies its own aiming error

A close flyby of a moon turns a spacecraft's path by ten degrees for nothing, and it turns every error in the aim with it. A kilometre of miss at three hundred kilometres above Ganymede becomes a third of a metre per second of velocity error, and a week later two hundred kilometres of miss at the next moon. A tour of flybys is an amplifier that must be re-zeroed after every pass, and whether a small spacecraft can use one in place of an engine burn depends on how many kilometres it can aim to.

spaceflight · Gravity assist An arrival held without a burn, and released. A body approaching a planet from a heliocentric orbit just outside the planet's, drawn in the planet's rotating frame (the Sun far to the left, the planet's orbital motion upward), in units in which the Hill radius is 0.69. It drifts in along the shear of the differential rotation, passes through the neck at the Lagrange point L2 into the region the planet controls, loops round the planet 3.3 times and leaves through a neck again. No burn is drawn: the capture and the release are both the Sun's tide working against the planet's pull. For Mars one unit of distance is 1.56 million km and an orbit round the planet near the Hill radius takes about a year.

An arrival the Sun hands over

A spacecraft that reaches a planet with no speed to spare can be captured with no burn at all, passing through the neck between the planet's gravity and the Sun's into a loose, looping orbit. The capture is temporary and chaotic — a few revolutions, and arrivals a few hundred kilometres apart end differently — but while it lasts the spacecraft is already bound, and the burn that keeps it is taken from there.

spaceflight · Escape

Named alongside it

The objects these essays reach for when they reach for this one.

Gravity assistHyperbolic excess speedOberth effectTurn angleAerobrakingThe B-planeBallistic captureCapture orbitChaosΔvEscape velocityGalilean moons

All concepts