Landing Capsule Research Articles

Improving the safety of the spacecraft landing capsule by optimizing its search

Taking into account the wide range of unforeseen factors during the landing of a spacecraft, a significant deviation of the actual landing point of its landing capsule from the expected one is possible. How and by what means to ensure the safety of astronauts before rescuers found them, how to carry out extremely rapid depressurization of the landing capsule by rescuers for outdoor air access, whether an ekranoplanee can help in solving these problems, taking into account the ocean specifics of the Vostochny cosmodrome, are analyzed in the article.

Development of three-dimensional rotated lattice Boltzmann flux solver for the simulation of high-speed compressible flows

A three-dimensional (3D) Rotated Lattice Boltzmann Flux Solver (RLBFS) is proposed and analyzed with matrix-based linear stability theory for simulating compressible flows in a wide range of Mach numbers. The 3D RLBFS applies the finite volume method to discrete the Navier-Stokes equations and evaluates its fluxes at each cell interface. To improve numerical stability, the convective fluxes are obtained in a hybrid way by using the D1Q4 lattice Boltzmann model in two perpendicular directions decomposed by the outer normal vector of each cell interface. The viscous fluxes are computed in a conventional way using the second-order central scheme. The stability performance and order accuracy of the proposed 3D RLBFS are examined by using the matrix-based stability theory and L2 errors on different meshes respectively. It is shown that the 3D RLBFS is stable even at high Mach number and has the second-order accuracy in space. The reliability and capability of the proposed method is further evaluated by simulating several challenging compressible flow problems, including subsonic flow over the DLR-F4, transonic flow over the ONERA M6 wing, supersonic flow around NACA0012 wing, hypersonic flow over the Viking lander capsule, hypersonic flow over a hemisphere and hypersonic flow around a blunt nose double cone. The obtained numerical results are in good agreement with experimental and/or numerical data published in the literature, indicating that the present method provides a reliable and effective tool for simulating practical three-dimensional compressible flow problems in aeronautics and astronautics.

Tianwen-1 MINPA observations in the solar wind

The Mars Ion and Neutral Particle Analyzer (MINPA) is one of the three scientific instruments onboard the Tianwen-1 orbiter to investigate the Martian space environment. During Tianwen-1’s transfer orbit to Mars, the MINPA was switched on to measure the solar wind ions. Here, we present the first results of the MINPA observations in the solar wind. During cruise, nearly half of the MINPA ion field-of-view (FOV) was blocked by the lander capsule; thus only the solar-wind ions with azimuthal speeds pointing towards the unblocked FOV sectors could be detected. We perform a detailed comparison of the MINPA’s solar wind observations with data from Earth-based missions when MINPA reached its count-rate peak, finding a general consistency of the ion moments between them. The blocking effect due to the lander is evaluated quantitatively under varying solar-wind velocity conditions. Despite the blocking effect, the MINPA’s solar wind measurements during the transfer orbit suggest a good performance.

Ai intelligent industrial design of Titan space probe (landing capsule and Saturn vehicle)

Exploring the solar system is of great significance for the realization of the community of human destiny. This article reviews the history of Saturn exploration and explores new directions in design aesthetics. The author designed a new type of Saturn’s sixth satellite (Titan) with three-dimensional software 3dsmax, including a landing capsule, a cruise vehicle (Saturn vehicle), involving the design of quantum communication, automatic driving, neural chain Ai chips, mechanical arms, etc. “Lack of beauty and tediousness”, pursue “characteristics, cultural innovation”. The new detector, with exquisite shapes and beautiful lines, combines the eastern cultural symbols of “Zhouyi and Dunhuang Feitian”, and uses memory metal and three-dimensional printing to manufacture, expanding the new Higgs boson, neutrino, and non-carbon-based life Explore the field, named “Hetu Jishu”, which closely combines mechanical aesthetics and the Silk Road.

In Memoriam

In Memoriam

Application Analysis of Swietenia Mahagoni (Mahogany) Seed’s Unique Aerodynamical Landing Characteristics

A model of safe landing capsule and ICBM multi war head transportation system for cluster type bomb attack by analysis of seed landing trajectory. Swietenia mahagoni (mahogany) seed has the uniqueness on its falling characteristics. At the time of falling, mahogany seed rotates in the axis center which is similar to the gyration of propeller towards its pivot point. The seeds look and behave like helicopter rotors. The gyration slows down the landing time whereby it is furthering the landing distance of the mahogany seeds. In this paper focused on this characteristic of the mahogany seed for real world application analysis and also the whole seed model application analysis also including some tests on the seeds.

Historical perspective - Viking Mars Lander propulsion

Developed for the Viking mission to Mars in 1975-76, the Viking Lander Capsule terminal descent monopropellant hydrazine rocket engine assemblies represented unique technology for an unusual mission. Intended solely for the purpose of landing an unmanned spacecraft on Mars in support of scientific exploration of the planet, the design and construction of the engines was so optimized for the mission that it is literally unusuable for any other application. It was required that the engine have twice the thrust of the largest monopropellant hydrazine engine ever developed, but weigh considerably less. It had to have 18 nozzles, the capability of 10:1 throttling, a new catalyst, be totally sealed until fired, employ no organic unsealed materials, be 100% germ free, utilize a new propellant, and start at a temperature more than 45°F below the propellant's freezing point. The schedule was short and inviolate. The contract was firm-fixed price. After 30 months, the flight engines were delivered, capable of a mission firing time of 45 seconds. They encompassed technology advances that were the foundation for longer life, lower cost monopropellant hydrazine thrusters and gas generators now in use with operational lifetimes that are longer by 3-4 orders of magnitude.

Thermal death of Bacillus subtilis var. niger spores on selected lander capsule surfaces.

Dry-heat sterilization of planetary lander capsules requires a knowledge of the thermal resistivity of microorganisms in the environment to which they will be subjected during sterilization of the space hardware. The dry-heat resistance of Bacillus subtilis var. niger spores on various lander capsule materials was determined at 125 C. Eight surface materials were evaluated, including a reference material, stainless steel. Survivor curves were computed, and decimal reduction times (D values) were obtained by a linear regression analysis. In four tests on stainless steel, the average value of D at 125 C was 17.07 min. The D values for the other seven materials tested ranged from 18.64 min on magnesium surfaces to 20.83 min on conversion-coated magnesium. Of the materials evaluated, the results indicate that there is only a significant difference in the thermal resistance of B. subtilis var. niger spores on conversion-coated magnesium and conversion-coated aluminum from that on the reference material, stainless steel. The differences in D values for all the test surfaces may be the result of variations in test procedures rather than the effect of the surfaces on the thermal resistivity of the spores.

Thermal Death of Bacillus subtilis var. niger Spores on Selected Lander Capsule Surfaces

Dry-heat sterilization of planetary lander capsules requires a knowledge of the thermal resistivity of microorganisms in the environment to which they will be subjected during sterilization of the space hardware. The dry-heat resistance of Bacillus subtilis var. niger spores on various lander capsule materials was determined at 125 C. Eight surface materials were evaluated, including a reference material, stainless steel. Survivor curves were computed, and decimal reduction times (D values) were obtained by a linear regression analysis. In four tests on stainless steel, the average value of D at 125 C was 17.07 min. The D values for the other seven materials tested ranged from 18.64 min on magnesium surfaces to 20.83 min on conversion-coated magnesium. Of the materials evaluated, the results indicate that there is only a significant difference in the thermal resistance of B. subtilis var. niger spores on conversion-coated magnesium and conversion-coated aluminum from that on the reference material, stainless steel. The differences in D values for all the test surfaces may be the result of variations in test procedures rather than the effect of the surfaces on the thermal resistivity of the spores.

Nonhomogeneous Impact Attenuator for Spherical Landing Capsule

Covers advancements in spacecraft and tactical and strategic missile systems, including subsystem design and application, mission design and analysis, materials and structures, developments in space sciences, space processing and manufacturing, space operations, and applications of space technologies to other fields.