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Vesta was a planned multiple-asteroid-flyby mission that the Soviet Union assessed in the 1980s. The Vesta mission would have consisted of two identical probes (just like earlier Soviet Venus missions), to be launched in 1991. Similar to the Vega program, each spacecraft would deploy one or more landers or balloons into the Venusian atmosphere, and then proceed to its next _target.
| Operator | IKI |
|---|---|
| Spacecraft properties | |
| Launch mass | ~2,000 kg (4,400 lb) including 500 kg (1,100 lb) penetrator |
| Power | 350 W |
| Start of mission | |
| Launch date | 1994 (proposed) |
| Flyby of Mars | |
| Closest approach | proposed |
| Flyby of Asteroids | |
| Closest approach | various dates and bodies proposed |
| Asteroid impactor | |
| Impact date | various dates and bodies proposed |
At Venus, a French satellite dedicated to asteroid flybys would be released. It would return for an Earth gravity assist, and then reach about 3–3.3 au from the Sun. There they would fly by some smaller asteroids, and Vesta, if possible, with a small probe landing there.
The exact _targets would depend on the launch date. In the initial 1985 study, 2700 possible trajectories were analyzed for a launch date in 1991/1992. Considering all constraints, about 12 candidate trajectories were selected. The two identical spacecraft could have different trajectories and _targets. These included 5 Astraea, 53 Kalypso, 187 Lamberta, 453 Tea, 1335 Demoulina and 1858 Lobachevskij, and comet Encke.
Spacecraft design
editAround 1985 Vesta was changed to be a Mars mission, with the asteroid mission unchanged. Detailed plans called for each probe to visit four small bodies, including asteroids belonging to different classes - providing a representative sample of the diversity of asteroids - and probably one or two comets as well.
Visiting at least one Apollo-Amor (Earth-nearing) asteroid was also given a preference.[citation needed]
Preliminary studies called for [when?] at least the following scientific instruments to be included:[citation needed]
- a wide angle camera (~6.5° field of view, 512×512 pixel CCD)
- a narrow angle camera (~0.5° field of view, 512×512 pixel CCD - 3.9 arcsec/pixel)
- a near-infrared spectrometer (measuring between 0.5–5 μm with λ/Δλ = 50, 5 arcminutes per pixel)
Possible further instrumentation:[citation needed]
- UV spectrometer (for imaging during a comet flyby)
- radar altimeter/radiometer
- a dust detector
- ion or neutral gas detector
Onboard memory would be about 240 Mb. Images at closest approach (~500 km) could have a resolution of 10 m/pixel. Worst case downlink rate is 600 bit/second (if not using NASA's Deep Space Network (DSN)). The scientific payload is about 100 kg. The spacecraft had 750 kg dry mass, and carried 750 kg propellants, and possibly a 500 kg penetrator. 20 square meters of solar panels provided 350 W of power.[citation needed]
If DSN support could have been obtained, Doppler tracking of the Vesta spacecraft's movement could accurately determine the mass of the encountered bodies. Should it not, another possibility was considered: releasing a test mass, and observing its movement near the _target asteroid.
The spacecraft's structure was derived from telecommunication satellites (INMARSAT), having the required mass, volume, and delta-v capabilities (3-axis stabilized, with a pointing platform with 2 axes of freedom for scientific instruments).[citation needed]
Trajectory
editThe Mars gravity assist constrains the possible trajectories. The asteroid penetrator also imposes limits on the speed of the approach of the _target asteroid (less than 4 km/s).
Nevertheless, 3 possible trajectories were designed, with two Mars gravity assists.[1]
A single Mars swing-by is also possible, but the double gravity assist increases the mass budget of the spacecraft by 30%, at the cost of an additional 1.8 year in travel time to the asteroid belt. The following trajectories are for the 1994 launch window. The size and type of each asteroid is also shown here:[citation needed]
Trajectory 1:
- launch from Earth
- Mars gravity assist
- flyby of 2335 James (a 10 km X-type asteroid) (an Amor-asteroid)
- Mars gravity assist
- 109 Felicitas (C-type, 76 km)
- 739 Mandeville (EMP(?) type, 110 km)
- 4 Vesta (V-type, or Vestoid. Has a diameter of 570 km) flyby with 3.5 km/s. A penetrator is released.
Total delta-v: 450 m/s
Trajectory 2:
- launch from Earth
- Mars gravity assist
- flyby of the 157P/Tritton short period comet
- Mars gravity assist
- 2087 Kochera(30 km?)
- 1 Ceres (flyby & releasing a penetrator)
Total delta-v: 1150 m/s
Trajectory 3:
- launch from Earth
- Mars gravity assist
- 1204 Renzia (10 km?) (an Amor-asteroid)
- Mars gravity assist
- 435 Ella (U type, 30 km)
- 46 Hestia (F type, 165 km)
- 135 Hertha (M type, 80 km)
Total delta-v: 350 m/s
In other studies 11 Parthenope, 19 Fortuna and 20 Massalia were also considered.[citation needed]
Cancellation
editA combination of factors, probably including changing Franco-Soviet relations, the partial failure of the Phobos mission, financial troubles and the disbanding of the Soviet Union, prevented the project from advancing beyond the planning phase.
References
edit- ^ Harvey, Brian (2007). Russian planetary exploration : history, development, legacy, prospects. Berlin: Springer. ISBN 978-0-387-49664-1. OCLC 186566322.