— Methods for determining the coordinate of micron particles over the cross section of the accelerator channel are considered. Calculations and simulation of the sensor performance have been performed with the aim of measuring the particle distribution over the cross section of the accelerator channel, and experimental data are presented. It is shown that the particle distribution over the cross section of the channel at the entrance to the chamber is similar to the normal distribution law.

The paper presents the reconstruction results of rotational motion of the AIST-2D small spacecraft by onboard measurements of vectors of angular velocity and the strength of Earth’s magnetic field obtained in summer 2016. The reconstruction method is based on the reconstruction of kinematic equations of the rotational motion of a solid body. According to the method, measurement data of both types collected on a certain time interval are processed together. Measurements of the angular velocity are interpolated by piecewise-linear functions, which are replaced in kinematic differential equations for a quaternion that defines the transformation from the satellite instrument coordinate system to the inertial coordinate system. The obtained equations represent the kinematic model of the rotational motion of a satellite. A solution to these equations that approximates the actual motion is derived from the condition of the best (in the sense of the least squares method) match between the measurement data of the strength vector of Earth’s magnetic field and its calculated values. The initial conditions of the approximating solution, constant bias in angular velocity measurements, and angles specifying the matrices of transformation from magnetometer intrinsic coordinate systems to the instrument coordinate system of the satellite (measurements of the angular velocity are specified in it) are refined. The described method makes it possible to reconstruct the actual rotational motion of a satellite using one solution of kinematic equations over time intervals longer than 10 h.

The results of reconstructing the uncontrolled rotational motion of the Aist small spacecraft prototype during its flight in early 2014 have been presented. The reconstruction was carried out by processing data from onboard measurements of the Earth’s magnetic field. The processing procedure used portions of data covering intervals of time with durations ranging from a few dozen minutes to three hours. Data obtained in each such interval were processed jointly by the least-squares method by integrating the equations of the satellite motion relative to the center of mass. The initial conditions of the motion and the parameters of the used mathematical model during processing have been estimated. The results of processing for several data intervals have provided a fairly complete picture of the satellite motion. This was the weakly disturbed Euler–Poinsot motion.

The Shtil-М equipment is described, which is installed on board the Resurs-P spacecraft (SC) and is intended for measuring interferences via the power-supply bus, the voltage between the power-supply circuit and the SC housing, magnetic fields, and also for detecting electrostatic discharges. Maximum attention is drawn to the latter procedure. The module for registering electrostatic discharges is described in detail. A theoretical calculation of the voltage that is induced in the cable during land and full-scale experiments is presented. A technique for conducting land experiments is described and the obtained results are presented. The fact of the registration of an electrostatic discharge on board the Resurs-P spacecraft is confirmed.

Some questions on the theory of charging particles in the charging chamber of an injector are considered. Two mechanisms (contact and contactless) for charging conducting particles in the region of the charging needle of an injector and the processes of charging microparticles by dark currents are considered. The value of the particle charge that is formed upon the occurrence of a microdischarge between the particle surface and the charging needle is evaluated. The results of the experimental study of the injector operation are presented: the plots that describe the dependence of the particle-escape frequency on the voltage at the charging electrode and the particle flow as a function of the diameter of the injector output aperture.

The design details and parameters of an induction sensor for a linear accelerator that is used to measure the velocity and charge of accelerated particles are described. A theoretical calculation of the voltage picked up from the Faraday cup of the induction sensor versus the particle parameters is presented. The essential feature of this calculation is the fact that the induction-sensor voltage is considered not only as a function of the velocity and charge of a detected charged particle, but also as a function of the coordinate of this particle. The experimental data that characterize the performance of the induction sensor are presented.

The article presents the results of a space experiment that analyzed the process of electrization of low-orbit satellites. The research of the process of electrization took place on the small spacecraft "AIST-L" (flight) and "AIST-T" (technological) using the "Meteor scientific equipment. The equipment includes multi-sensors that measure the temperature, illumination and electrification. The experiment revealed significant correlation between the process of differential charging of the apparatus and the external factors of space environment. The influence of both controlled and uncontrolled flight modes on the electrization of low-orbit satellites was estimated. The mode of micro acceleration compensation is controlled by three orthogonally arranged solenoids. The data obtained make it possible to assess the density of the flow of electrons falling on the surface of the sensor, and confirm the mathematical model of spacecraft electrization proposed in the article and based on the method of integral equations. The model takes into account the effect of shielding the redistribution of charges on the surface of the spacecraft by plasma.

The results of the reconstruction of uncontrolled attitude motion of the satellite Aist during its flight in May 2013 are presented. The reconstruction was performed by the processing of data from onboard measurements of the Earth’s magnetic field. The processing technique was applied to data segments covering time intervals of about 100 min. The data obtained at each such interval were processed jointly using the least squares method by integrating the equations of the satellite motion relative to its center of mass. When processing, the initial conditions of motion and parameters of the used mathematical model were estimated. The results of processing several data intervals made it possible to obtain sufficiently complete information about the motion of the satellite.

Methods of determining the coordinates of points of impact of micron particles at the target are considered, the calculations and simulation results of the operation of a sensor for measuring the particle distribution over the accelerator-channel cross section and data for conducting the experiment are given. It is shown that the particle distribution over the channel cross section at the output of the charged micron particle injector is close to the normal distribution law.

The description of the experiments conducted using the equipment MAGCOM installed on board the spacecraft small type Aist, which is designed to measure the Earths magnetic field by means of two ternary magnetometers, as well as for compensation arising in flight angular perturbations using three orthogonally arranged solenoids. The measurements of the geomagnetic field are transmitted as part of software and telemetry data to Earth, where they are processed for the purpose of reconstruction of the parameters of the rotational motion of the spacecraft, certain lighting conditions Sun sensors and other scientific instruments on board the calculation of the value of the residual disturbances.

The MAGCOM equipment, installed on the Aist small spacecraft and intended for measuring the terrestrial magnetic field using two three-component magnetometers in a range of ±120 μT and compensating microaccelerations of the small spacecraft by means of three orthogonally located electromagnets, is described. The measured data of magnetic fields and the operating results of the relay microacceleration-compensating mode are given. It is shown that the angular velocity of the Aist small spacecraft decreases from 2.5 to 0.2 deg/s for less than 20 min.

Various types of accelerators particulate analysis examined the suitability of designs to simulate collisions of cosmic rays, as well as elements of the space debris from the surface of the spacecraft. The evolution of accelerators and basic directions for their further development.

Sensor equipment Shtil-M is described which is designed to monitor the magnetic environment of the Resource-P spacecraft with six three-component magnetometer sensors, to measure the magnetic field vector with a three-component magnetometer sensor, and to control the noise in power lines and possible electrostatic discharge registration. The results of measurements of the observed values are given.

Using the conformal mapping method, we calculate the electric field at the tip of a high-voltage electrode mounted in the injector of fluid particles. The space charge of the dielectric fluid charged from the high-voltage electrode of the injector of the fluid charged particles is determined. We present the results of simulation of the charge and field in the meniscus for VM-1vacuum oil.

Are presented, the theory, settlement parameters and a principle of action of the resonant electromagnetic accelerator, allowing to disperse firm ferromagnetic particles and bunches of particles till the speeds of 30 km/s. Essential difference of the described accelerator from existing that at shell movement on an accelerating path, solenoids are connected serially, and in each new oscillatory contour occurs a resonant recharge of the store to increasing frequency of free fluctuations.

Pulse method is considered to accelerate and conditions for the implementation of this method. The analysis of the design of the accelerator operating at pulse method of particle acceleration. Mathematical modeling of the one-stage pulsed accelerator. The possible ways to control voltage pulse generator based on a physical model. The possible improvement of pulsed accelerator.

Researches directed on increase of efficiency of the resonant electromagnetic accelerator are resulted. The modernized system of the accelerator, different is offered by presence of system of additional charge of the store. The offered system with application of the developed recommendations has theoretical efficiency of transformation of energy of the store in kinetic energy of a flying body of equal 70 %.

The design of an injector of charged liquid particles with diameters of 1–10 μm that move at velocities of up to 1400 m/s is described. The injector stably operates at a potential difference of 5–20 kV between the needle, on which charged droplets form, and the focusing electrode with a distance between the electrodes of 5–20 mm. The diameter of the metal needle was varied from 0.1 to 10 μm. Experiments showed that, depending on the needle length, the source can stably operate in two modes: at a needle length of ≤1.7 and ≥2.7 mm. The experimental technique and results are presented. The dependences of the characteristics of accelerated particles on the voltages across the plates of the electrostatic particle accelerator are determined. The experimental results are in good agreement with the computer simulation results.

Results of experiments with a multiparameter detector of high-speed dust particles are presented. This detector is composed of induction (a Faraday cup), ionization, and photoelectric sensors. It allows simulation of micrometeorites over wide ranges of masses and velocities by measuring secondary effects due to collisions of particles with a wall. Experiments aimed at detecting high-speed dust particles have been carried out using an electrodynamical accelerator with an effective accelerating voltage of ∼650 kV.