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The reentry vehicle of the transportation spacecraft that is being created by RSC Energia in regular mode makes soft landing on land surface using a parachute system and thruster devices. But in not standard situations the reentry vehicle also is capable of executing a splashdown. In that case, it becomes important to define the hydrodynamics impact on the reentry vehicle at the moment of the first contact with the surface of water and during submersion into water medium, and to study the dynamics of the vehicle behavior at more recent moments of time.

This article presents results of numerical studies of hydrodynamics forces on the conical vehicle during splashdown, done with the FlowVision software. The paper reviews the cases of the splashdown with inactive solid rocket motors on calm sea and the cases with interactions between rocket jets and the water surface. It presents data on the allocation of pressure on the vehicle in the process of the vehicle immersion into water medium and dynamics of the vehicle behavior after splashdown. The paper also shows flow structures in the area of the reentry vehicle at the different moments of time, and integral forces and moments acting on the vehicle.

For simulation process with moving interphases in the FlowVision software realized the model VOF (volume of fluid). Transfer of the phase boundary is described by the equation of volume fraction of this continuous phase in a computational cell. Transfer contact surface is described by the convection equation, and at the surface tension is taken into account by the Laplace pressure. Key features of the method is the splitting surface cells where data is entered the corresponding phase. Equations for both phases (like the equations of continuity, momentum, energy and others) in the surface cells are accounted jointly.

The results of verification carried out for investigations of hydrodynamic effect on reentry conicalsegmental space vehicle are presented in the paper. The program complex Flow Vision is used for this analysis. The purpose of the study is verification of using Flow Vision program complex for problem solving mentioned above on the base of comparison between calculated and experimental data, obtained on the Apollo landing models and new development reentry spacecraft of manned transporting spaceship designed by RSC Energia. The comparison was carried out through the data of pressure values on spacecraft model surfaces during its water landing and inertia center motion parameters.

The results of study show good agreement between experimental and calculated data of force effects on vehicle construction during water landing and its motion parameters in the water medium. Computer simulation sufficiently well reproduces influence of initial velocities & water entry angles variations on water landing process.

Using of computer simulation provides simultaneous acquisition of all data information needed for investigation of water landing peculiarities during construction design, notably, hydrodynamic effects for structural strength calculations, parameters and dynamics of center mass motion and vehicle revolution around center mass for estimation water landing conditions, as well as vehicle stability after landing.

Obtained results confirm suitability of using Flow Vision program complex for water landing vehicle investigations and investigations of influence of different landing regimes through wide initial condition change range, that permits considerably decrease extent of expensive experimental tests and realize landing conditions which are sufficiently complicated for realizing in model physical experiments.

The article presents the intermediate results of the development of a control system for a remotely piloted agricultural aircraft (RPAA). The concept of using an automated complex for performing aerochemical work (ACW) designed for processing fields, water areas, forests with the purpose of protection from pests of plants, fertilization is developed. The basic component of the complex is a manned agricultural aircraft MV-500 developed by LLC “Firm “MVEN” (Kazan). The use of the aircraft in unmanned mode will provide an increase in the productivity of the aircraft, will increase the payload.

The article defines the composition of the complex for automation of ACW: aircraft, ground control center, onboard equipment for automated control of the aircraft and the formation of a map of the heights of the section being processed, and the satellite precise positioning system necessary to automate the control of the aircraft. The aircraft is equipped with an automated control system that provides remote control of take-off and landing and automatic control of the flight trajectory at extremely low altitude when performing ACW and performing spatial turns at the boundaries of the treated areas. It is proposed to take off, landing, dropping an aircraft into the ACW exercise area by means of a pilot operator from a ground control station. The ground control point should provide reception and display on the operator's screen of flight information and several types from the aircraft. The operator can control alternately several aircraft during these phases of flight with the help of ground control authorities. In the future, it is planned to automate these stages of flight, leaving behind the pilot-operator control functions and remote control capabilities in special cases. For the navigation of the aircraft, when performing ACW on board, RTK (Real Time Kinematic) equipment is installed, providing a measurement with centimeter accuracy of coordinates and aircraft heights relative to the base station installed in the ground control station. Before the implementation of ACW, a three-dimensional digital map of the processed area is built by adding existing cadastral maps with measurements of the elevations of the section carried out with the help of on-board radio and optical altimeters of the same aircraft.

To date, the following system components have been manufactured and tested: a remotely controlled model of the MV-500 aircraft at a scale of 1:5, a satellite positioning system; system for obtaining images and telemetry information from the board model; autopilot; methods of obtaining three-dimensional digital maps of sections and planning flight trajectories for ACW.

The data of episodic field measurements of carbon dioxide balance components (soil respiration — R_soil, ecosystem respiration — R_eco, net ecosystem exchange — NEE) of hayfields under use and abandoned one are interpreted by modelling. The field measurements were carried within five field campaigns in 2018 and 2019 on the drained part of the Dubna Peatland in Taldom District, Moscow Oblast, Russia. The territory is within humid continental climate zone. Peatland drainage was done out for milled peat extraction. After extraction was stopped, the residual peat deposit (1–1.5 m) was ploughed and grassed (Poa pratensis L.) for hay production. The current ground water level (GWL) varies from 0.3–0.5 m below the surface during wet and up to 1.0 m during dry periods. Daily dynamics of CO2 fluxes was measured using dynamic chamber method in 2018 (August) and 2019 (May, June, August) for abandoned ditch spacing only with sanitary mowing once in 5 years and the ditch spacing with annual mowing. NEE and Reco were measured on the sites with original vegetation, and Rsoil — after vegetation removal. To model a seasonal dynamics of NEE, the dependence of its components (Reco, Rsoil, and Gross ecosystematmosphere exchange of carbon dioxide — GEE) from soil and air temperature, GWL, photosynthetically active radiation, underground and aboveground plant biomass were used. The parametrization of the models has been carried out considering the stability of coefficients estimated by the bootstrap method. R2 (α = 0.05) between simulated and measured Reco was 0.44 (p < 0.0003) on abandoned and 0.59 (p < 0.04) on under use hayfield, and GEE was 0.57 (p < 0.0002) and 0.77 (p < 0.00001), respectively. Numerical experiments were carried out to assess the influence of different haymaking regime on NEE. It was found that NEE for the season (May 15 – September 30) did not differ much between the hayfield without mowing (4.5±1.0 tC·ha–1·season–1) and the abandoned one (6.2±1.4). Single mowing during the season leads to increase of NEE up to 6.5±0.9, and double mowing — up to 7.5±1.4 tC·ha–1·season–1. This means increase of carbon losses and CO2 emission into the atmosphere. Carbon loss on hayfield for both single and double mowing scenario was comparable with abandoned hayfield. The value of removed phytomass for single and double mowing was 0.8±0.1 tC·ha^–1·season^–1 and 1.4±0.1 (45% carbon content in dry phytomass) or 3.0 and 4.4 t·ha^–1·season^–1 of hay (17% moisture content). In comparison with the fallow, the removal of biomass of 0.8±0.1 at single and 1.4±0.1 tC·ha^–1·season^–1 double mowing is accompanied by an increase in carbon loss due to CO2 emissions, i.e., the growth of NEE by 0.3±0.1 and 1.3±0.6 tC·ha–1·season–1, respectively. This corresponds to the growth of NEE for each ton of withdrawn phytomass per hectare of 0.4±0.2 tС·ha–1·season–1 at single mowing, and 0.9±0.7 tС·ha^–1·season^–1 at double mowing. Therefore, single mowing is more justified in terms of carbon loss than double mowing. Extensive mowing does not increase CO2 emissions into the atmosphere and allows, in addition, to “replace” part of the carbon loss by agricultural production.