Which one of the following statements best reflects the idea behind the "Fractional Orbital Bombardment System" often talked about in media ?

Defines asteroids as rocky debris of varying size orbiting the Sun, establishing what a target would be.

A student could combine this with basic orbital-distance facts to judge whether a missile could realistically reach typical asteroid orbits for interception.

States most asteroids are found between Mars and Jupiter, clarifying typical asteroid orbital zones.

Use a simple solar-system map to compare those orbital distances with the range/altitude implied by 'hypersonic missile into space' to assess feasibility.

Describes that many asteroids have collided with terrestrial planets during the Late Heavy Bombardment, showing asteroids can intersect planetary paths.

Combine with orbital mechanics basics to consider whether an incoming asteroid would be in near-Earth space (more interceptable) or in main-belt orbits (farther, harder to reach).

Reinforces that asteroid impacts on Earth have occurred, indicating the practical problem such a system would aim to solve.

A student could infer that intercepting an Earth-bound asteroid requires timing and trajectory considerations beyond merely 'launching a missile into space.'

Notes existence of rocket launch infrastructure (sounding rockets launched from Thumba), showing national capability to send vehicles into near-space.

Extend by comparing the documented sounding-rocket role to the much greater requirements of reaching asteroid distances/orbital rendezvous to evaluate whether a hypersonic missile launch is analogous.

Kepler's laws and the definition of orbits show what it means for a body to make orbital revolutions around a central body.

A student could combine this with knowledge of trajectories to judge whether a system described as 'orbital' could plausibly perform multiple revolutions before a planned descent to another body's surface.

Examples of lunar missions show both orbiting (Apollo 8) and subsequent landings (Apollo 11) — indicating a pattern where spacecraft can first orbit a body and then land.

A student could compare mission profiles (orbiter-then-lander) to the statement to see if 'several orbital revolutions then landing' matches known operational patterns for interplanetary/planetary landings.

The Mars Orbiter Mission example demonstrates a distinction between spacecraft that reach orbit around another planet and those that perform landings.

A student can use this to ask whether the system in question is described as an 'orbiter' (stays in orbit) versus a 'lander' (touches down), to accept or reject the landing claim.

The exosphere/satellite snippet highlights that satellites occupy high orbits with little atmospheric drag and can remain in orbit for extended periods.

A student could use this to assess feasibility: if a system remains in high orbit for many revolutions, atmospheric considerations differ from those for a craft designed to descend and land.

The Van Allen belt description shows environmental hazards for spacecraft spending time in certain orbital zones.

A student might use this to question whether a system intended to make several revolutions near Earth would need shielding or avoid those zones, affecting mission profiles (orbit-only vs. descent/landing).

Gives the basic definition of an 'orbit' as the path of an object revolving around another, establishing what 'placing a missile into orbit' would mean.

A student could combine this with knowledge of ICBM vs. orbital trajectories to assess whether putting a payload into a sustained orbit fits the described system.

States that man-made satellites commonly orbit about 800 km above Earth and complete periodic orbits, showing typical altitudes and that objects can remain in orbit.

Compare typical satellite orbital altitudes to reported FOBS altitudes to judge feasibility of deploying then deorbiting a weapon.

Notes that satellites in medium/high Earth orbit reside in the exosphere where atmospheric drag is minimal, indicating sustained orbital residence is possible at certain heights.

Use this to evaluate whether a weapon placed in such regions could remain orbiting before a planned deorbit burn.

Explains that orbits can be elliptical with defined closest (perigee) and farthest (apogee) points, showing orbits can be adjusted in altitude.

A student could infer that changing perigee (e.g., lowering it into atmosphere) is a mechanism by which an orbital object could be deorbited to strike Earth.

Describes the Van Allen belts as zones that 'endanger satellites' and that spacecraft traveling beyond low Earth orbit enter higher radiation zones, indicating environmental constraints on orbital dwell and payload design.

Use this to assess practical constraints (radiation, shielding) on keeping a weapon in orbit for extended periods before deorbiting.

Comets have highly elliptical orbits and are composed of volatile ices and rock.

A student could reason that a spacecraft attempting to land on a comet must accommodate large orbital eccentricity and land on an icy, low-gravity, potentially outgassing body.

Long-period comets originate in the distant Oort cloud and show activity (outgassing) when heated by the Sun.

Combine this with a world map/timing facts to infer large travel distances and timing constraints for rendezvous missions to active comets.

Historical examples show spacecraft have both orbited (Apollo 8) and made hard landings (Luna 2) on celestial bodies.

A student could compare those known mission types to the requirements of matching velocity with and landing on a moving comet to judge feasibility.

Some artificial objects have achieved escape velocity sufficient to leave the Solar System.

This suggests spacecraft can be engineered for very large delta-v missions; a student could assess whether matching a comet’s heliocentric velocity is within known mission capabilities.

The snippet contrasts asteroid and comet locations and observable tails (activity).

A student could use the difference in typical orbital regions and comet activity to infer differing mission profiles needed for rendezvous versus asteroid missions.