Lunar apex–antapex cratering asymmetry as an impactor recorder in the Earth–Moon system

The degree of apex–antapex cratering asymmetry of a synchronously rotating satellite primarily depends on the mean encounter velocity of impactors with respect to the planetary system and the orbital velocity of the satellite. This means that we can estimate the mean encounter velocity of impactors by observing the apex–antapex cratering asymmetry, if the relationship between these is known. To apply this technique to the Moon, we attempt to derive the relationship between the mean encounter velocity of impactors and the degree of the lunar cratering asymmetry as a function of time, considering the temporal variation in the lunar orbital velocity during the last 4.0 Gyr. We used the cratering asymmetry of Zahnle et al. [Zahnle, K., Schenk, P., Sobieszczyk, S. et al. Differential cratering of synchronously rotating satellites by ecliptic comets. Icarus 153, 111–129, 2001] to obtain the relationship. Applying this relationship enables us to estimate the impactor’s velocity of the Earth–Moon system from an investigation of the spatial distribution of lunar craters. Furthermore, we re-evaluate the cratering asymmetry’s influence on lunar cratering chronology.     

Simulation of discharge impulses in GTE capacitance ignition systems

A possibility of enhancing the energy efficiency of the capacitance ignition system by realizing the batch mode of discharge impulse generation is substantiated. Using the numerical simulation methods, a problem is solved to study the voltage-current characteristics of such discharge units as a spark discharger and a spark plug and peculiarities of discharge formation in them; the batch mode is simulated with proper account for the influence of discharge-recurrence rate upon dynamics of electric strength recovery in the discharge units. A possibility of optimizing the capacitance ignition system parameters is theoretically evaluated to provide the maximum possible quantity of discharge impulse packet energy as well as the value of their peak capacity at the specified values of supply source power, discharge-recurrence rate, and total voltage of the entire ignition system.     

Joint effect of input asymmetrical velocity profile and initial turbulence intensity on hydraulics of a separated diffuser of GTE combustion chamber

This paper presents the regularities of effect of the input asymmetry of the velocity profile on the flow structure in a separated diffuser of the GTE annular combustion chamber. These regularities allow predicting the integral value of hydraulic resistance. We experimentally identified a kind of dependence between the hydraulic losses and Reynolds number in the case of asymmetric velocity profile in a prediffuser assessing the growth of pressure losses. Some updated dependencies are proposed that take into account the joint effect of the input parameters of the working fluid on the integral characteristics of its effectiveness.     

Roll control of a flight vehicle with the adjustable center of mass

We present the results of analytical research of flight dynamics for a flight vehicle that is controlled by the adjustable center of mass in the vertical symmetry plane. The roll oscillations, which appear perpendicular to the symmetry plane due to technological errors, are eliminated by means of control rocket engines, for which a control law is assigned.     

The problem of estimating microaccelerations aboard Foton-M4 spacecraft

The paper considers the special features of estimating microaccelerations aboard the Foton-M no. 4 spacecraft, which are connected with the decision on cancelling the spacecraft injection from the reference orbit into the operating one.     

The Deep Impact Earth-Based Campaign

Prior to the selection of the comet 9P/Tempel 1 as the Deep Impact mission target, the comet was not well observed. From 1999 through the present there has been an intensive world-wide observing campaign designed to obtain mission critical information about the target nucleus, including the nucleus size, albedo, rotation rate, rotation state, phase function, and the development of the dust and gas coma. The specific observing schemes used to obtain this information and the resources needed are presented here. The Deep Impact mission is unique in that part of the mission observations will rely on an Earth-based (ground and orbital) suite of complementary observations of the comet just prior to impact and in the weeks following. While the impact should result in new cometary activity, the actual physical outcome is uncertain, and the Earth-based observations must allow for a wide range of post-impact phenomena. A world-wide coordinated effort for these observations is described.     

Three-dimensional model of a dispersed-film flow in a cylindrical channel

A mathematical model of the dispersed-film two-phase flow with phase slip in the vertical cylindrical channel is described.     

An Overview of the Instrument Suite for the Deep Impact Mission

A suite of three optical instruments has been developed to observe Comet 9P/Tempel 1, the impact of a dedicated impactor spacecraft, and the resulting crater formation for the Deep Impact mission. The high-resolution instrument (HRI) consists of an f/35 telescope with 10.5 m focal length, and a combined filtered CCD camera and IR spectrometer. The medium-resolution instrument (MRI) consists of an f/17.5 telescope with a 2.1 m focal length feeding a filtered CCD camera. The HRI and MRI are mounted on an instrument platform on the flyby spacecraft, along with the spacecraft star trackers and inertial reference unit. The third instrument is a simple unfiltered CCD camera with the same telescope as MRI, mounted within the impactor spacecraft. All three instruments use a Fairchild split-frame-transfer CCD with 1,024× 1,024 active pixels. The IR spectrometer is a two-prism (CaF₂ and ZnSe) imaging spectrometer imaged on a Rockwell HAWAII-1R HgCdTe MWIR array. The CCDs and IR FPA are read out and digitized to 14 bits by a set of dedicated instrument electronics, one set per instrument. Each electronics box is controlled by a radiation-hard TSC695F microprocessor. Software running on the microprocessor executes imaging commands from a sequence engine on the spacecraft. Commands and telemetry are transmitted via a MIL-STD-1553 interface, while image data are transmitted to the spacecraft via a low-voltage differential signaling (LVDS) interface standard. The instruments are used as the science instruments and are used for the optical navigation of both spacecraft. This paper presents an overview of the instrument suite designs, functionality, calibration and operational considerations.