Scientific exploration of comets - A mission study.
Atlas-Agena and Atlas-Centaur launch vehicles to investigate comets
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A new instrument to measure charged and neutral cometary dust particles at low and high impact velocities
A new class of dust particle detector, the PVDF dust detector, was designed for space missions such as the Halley Comet missions where the particle impact velocity is very high. It is demonstrated that this same PVDF detector (operating in a different mode) also has the capability of detecting dust particles having low velocity (approx. 100 m/s). This low velocity detection capability is extremely important in terms of planned missions requiring measurement of low velocity dust particles such as comet rendezvous missions. An additional detecting element (charge induction cylinder) was also developed which, when combined with a PVDF detector, yields a system which will measure the charge (magnitude and sign) carried by a cometary particle as well as the particle velocity and mass for impact velocities in the range 100 to 500 m/s. Since the cylinder-PVDF detector system has a relatively small geometry factors, an array of PVDF detectors was included having a total sensing area of 0.1 sq m for measurements in regions of space where the dust flux is expected to be low. The characteristics of the detectors in this array have been chosen to provide optimum mass sensitivity for both low-velocity cometary dust as well as high-velocity asteroid associated and interplanetary dust.
Economon, T.↗
The Ion Propulsion System on NASA's Space Technology 4/Champollion Comet Redezvous Mission
The ST4/Champollion mission is designed to rendezvous with and land on the comet Tempel 1 and return data from the first-ever sampling of a comet surface.
Ion Propulsion Electric Propulsion SEP Space Techn↗
Interplanetary mission design for the Comet Rendezvous Asteroid Flyby mission
As part of the CRAF/Cassini Project, the Comet Rendezvous Asteroid Flyby (CRAF) mission will explore primitive solar system bodies. CRAF is unique in that there are a number of scientifically acceptable targets from which to choose. In principle, each may be reached with several types of trajectories. This results in a large number of potential mission opportunities which must be considered. The various mission modes being considered will be discussed along with the criteria by which these missions are evaluated in order to reduce them to a smaller set. Also, the current primary and backup missions will be discussed.
Williams, S. N.↗
Comments on comet shapes and aggregation processes
An important question for a comet mission is whether comet nuclei preserve information clarifying aggregation processes of planetary matter. New observational evidence shows that Trojan asteroids, as a group, display a higher fraction of highly-elongated objects than the belt. More recently evidence has accumulated that comet nuclei, as a group, also display highly-elongated shapes at macro-scale. This evidence comes from the several comets whose nuclear lightcurves or shapes have been well studied. Trojans and comet nuclei share other properties. Both groups have extremely low albedos and reddish-to neutral-black colors typical of asteroids of spectral class D, P, and C. Both groups may have had relatively low collision frequencies. An important problem to resolve with spacecraft imaging is whether these elongated shapes are primordial, or due to evolution of the objects. Two hypotheses that might be tested by a combination of global-scale and close-up imaging from various directions are: (1) The irregular shapes are primordial and related to the fact that these bodies have had lower collision frequencies than belt asteroids; or (2) The irregular shapes may be due to volatile loss.
Hartmann, William K.↗
Low Risk Technique for Sample Acquisition from Remote and Hazardous Sites on a Comet
This paper describes a mission comet sampling strategy, known as CORSAIR (COmet Rendezvous, Sample Acquisition, Investigation, and Return), which was proposed for NASA New Frontiers 2017. The proposal was led by Applied Physics Lab (APL) with partners Goddard Space Flight Center (GSFC) and Deutsches Zentrum für Luft- und Raumfahrt (DLR). The mission concept is to launch a projectile from a satellite that is capable of gathering a 300 cc sample. The projectile is tethered and is reeled back to the spacecraft after gathering the sample. Once back at the spacecraft, a robotic manipulator extracts the sample cartridge and places the cartridge into an earth return vehicle (ERV). This method has the following favorable characteristics: 1. Places the mission at minimal risk by isolating the spacecraft from the comet 2. Allows access to remote and otherwise inaccessible locations 3. Permits deep penetration into the surface
Comet Sample↗
The International Cometary Explorer mission to comets Giacobini-Zinner and Halley - An update
Aspects of the International Cometary Explorer (ICE) flight to the comet Giacobini-Zinner (GZ) are discussed. The most important experiments to be performed by ICE are reviewed, and the orbital parameters of GZ are described. The dust characteristics of GZ that pose a hazard to the spacecraft are addressed, and the ICE targeting strategy toward the comet is discussed. Requested ground-based coverage of GZ is indicated, and the complementarity of the GZ coverage with that given to the Halley mission is shown.
Brandt, J. C.↗
The international cometary explorer mission to comet Giacobini-Zinner
The encounter, on September 11, 1985, between the International Cometary Explorer (ICE) and the comet Giacobini-Zinner, is described in detail. The primary goal of this encounter was to study the interaction between the solar wind and the comet. At the time of the encounter, the spacecraft was approximately 50 times farther from the earth than it was designed to go, making it difficult to recover data. The seven instruments on board ICE which were operational in this mission were the plasma electron, magnetometer, plasma waves, radio waves, plasma composition, low-energy cosmic ray, and energetic proton instruments. The encounter is depicted schematically, showing the times different regions were crossed. The spacecraft velocity vector, measured relative to the comet, made a 93 deg angle with respect to the plasma tail axis. The spacecraft crossed the center of the comet ion tail at approximately 1102 U.T. A cold, dense plasma was found near the center of the tail; at the very center was a temperature reading of only 13,000 K and a density of 670 electrons/cu cm. Alfven's model of comet tail formation was confirmed and it was found that water group ions are the dominant comet component. Pulses were detected which were attributed to dust particles hitting the spacecraft.
Von Rosenvinge, T. T.↗
Space missions in comets
Recent advances in the techniques and instruments of cometary research are described. Consideration is given to the development of the first space-based platforms for cometary observations in the 1970s, including the OGO-5 and OAO-2 ultraviolet satellites, as well as IRAS. The expectations for the scientific return from space missions in the 1980s and 1990s are also discussed, with attention given to the Giotto flyby; the Soviet VEGA missions; and two Japanese spacecraft missions Sakigake and Suise. The imaging and spectroscopic experiments to be carried out during the Giotto mission are described in detail.
Neugebauer, M.↗
Comets: Scientific data and missions; Proceedings of the Tucson Comet Conference, University of Arizona, Tucson, Ariz., April 8, 9, 1970.
Current knowledge of comets is surveyed, and comet-rendezvous mission constraints, opportunities, modes, and spacecraft capabilities are discussed. Attention is given to cometary nuclei, infrared measurements of comets, the nature and origin of the cometary head, L-alpha photometry of Comet Bennett, Types I and II tails, comet spectra and orbits, and evidence from stream meteoroids. Some scientific criteria for a cometary mission are considered. Individual items are announced in this issue.
Kuiper, G. P.↗
Radio metric orbit determination for the Giotto mission to Comet Halley
An international fleet of five spacecraft will fly past Comet Halley as it travels through the inner solar system in early 1986. This paper discusses orbit determination problems associated with the Giotto spacecraft, sponsored by the European Space Agency. The large number of spin axis precession maneuvers required to maintain the desired spacecraft attitude creates a new kind of radio metric orbit determination problem for this mission. This paper investigates the accuracy with which the Giotto spacecraft orbit can be determined relative to the earth or the sun, and establishes the sensitivity of this accuracy to the selection of the parameters to be estimated, the form of estimator used, the number of tracking stations employed, the length of the data arc, the selection of data types processed, and the levels of various error sources.
Wood, L. J.↗
Halley Armada report
The international missions concerned with study of Comet Halley are examined. The difficulties encountered in the planning of the comet missions, due to the orbit and environment of Comet Halley and the need to protect the spacecraft from the comets, are discussed. The objectives of the U.S. Giotto, ESA and USSR Vega, and Japanese Suisei spacecraft were to examine the operation and cosmology of the comet. Diagrams of the spacecraft, and a table of the instruments on each of the spacecraft and their capabilities are presented. Preliminary results, obtained during the missions, on cosmic dust and gases and the interaction of the comet with solar wind are analyzed.
Newburn, Ray L., Jr.↗
System definition for Cometary Explorer: A mission to intercept the comets Grigg-Skjellerup (1977) and Giacobini-Zinner (1979)
Its purpose was to define a low cost dual-comet intercept mission. The study established the framework for investigating future ballistic intercept missions to comets.
Source record↗
Imaging on ballistic missions to comet Encke
Imaging for navigation and science has been studied for a 1980 Encke flyby at 0.4 to 0.8 AU from the sun with spinning and three-axis spacecraft. Trajectory errors, maneuvers, encounter geometry, imaging performance, and data transmission were considered. Onboard comet sightings are needed for navigation. Recommended for a three-axis spacecraft are two vidicon cameras and a nucleus sensor for closed-loop pointing control. The cameras are essentially the Mariner 9 and Mariner 10 instruments; the nucleus sensor is an updated version of a sensor flown on Mariners 6 and 7. For a spinning spacecraft, a framing camera using a charge-coupled device and a spin-scan photometer are proposed. The framing camera would be a new design; it would not be despun, but the spin axis should point along the comet-centered velocity vector. The photometer is essentially that flown on Pioneer 10 and 11.-
Jaffe, L. D.↗
Astrometric needs for the ISEE-3/ICE mission to Comet Giocobini-Zinner
The Third International Sun-Earth Explorer satellite (ISEE-3) was rechristened Internation Cometary Explorer (ICE) when the spacecraft left the Earth-Moon system after a close Lunar flyby on 1983 December 22. On 1985 September 11, ICE will pass through the inner parts of the tail of Comet Giacobini-Zinner to obtain the first in-situ measurements of any comet. Since the spacecraft has no cameras, its trajectory will be determined only from radio tracking. Astrometric updates of Comet Giacobini-Zinner will be critical for the final targeting of the spacecraft to achieve a successful encounter. ICE's flyby of Comet Giacobini-Zinner will provide valuable experience for the astrometry needed to target other spacecraft to encounter Hally's Comet six months later.
Dunham, D. W.↗
The International Cometary Explorer (ICE) mission to Comets Giacobini-Zinner and Halley
Use of the ISEE-3 satellite (renamed ICE) to study the interaction between the solar wind and a cometary atmosphere by passing through the plasma tail by intercepting Comet Giacobini-Zinner on 11 September 1985 is described. Details of the targeting strategy are discussed. Additional scientific objectives following the tail intercept of Comet Giacobini-Zinner include the support of Comet Halley studies through the measurement of solar-wind conditions upstream of P/Halley in October 1985 and March 1986.
Brandt, J. C.↗
The International Cometary Explorer mission to comet Giacobini-Zinner
The International Cometary Explorer (ICE), scheduled to pass the tail of Comet Giacobini-Zinner on September 11, 1985, was expected to address first-order questions bout the interaction between solar wind and comets. Since ICE was not initially intended for comet studies, it did not have sun-sensitive imaging instruments designed to image the comet nucleus. In effect, ICE was free to pass through the tail of the comet. The ICE spacecraft, a 16-faceted cylindrical drum just over five ft high with a spin axis normal to the ecliptic plane, was designed to encounter the comet at a distance of 0.47 AU from the earth. Scientific instruments on board the spacecraft include: (1) the electron plasma experiment, (2) the vector helium magnetometer, (3) the plasma wave experiment, (4) the radio waves experiment, (5) the plasma ion experiment, (6) the low-energy cosmic ray experiment, and (7) the energetic protons experiment. Targeting error was expected as a result of solar-wind induced plasma tail wagging. Comet interception was planned to be at a distance of 10,000 km from the nucleus.
Von Rosenvinge, T. T.↗
Ballistic comet exploration mission options
To attain the fundamental goals of cometary exploration, rendezvous and sample return missions are necessary. This paper investigates various trajectory options and provides a comprehensive set of mission opportunities available for launches in the 1990s. The modes of explorations considered are rendezvous and flybys with atomized-sample-return missions. For each type of exploration, the paper describes various classes and modes of trajectories available, their inherent characteristics, and the techniques of identifying useful trajectories. The energy requirement associated with these missions and the performance possibilities are provided.
Yen, Chen-Wan L.↗