Static-and-dynamic analysis of thin-walled structural members of space radio telescopes

Structural members of space radio telescopes made as large thin shells of revolution are analyzed. A twisting shell structure prestressed by inertia or surface-distributed forces (when in the unperturbed state) is used as the basis for the analysis. Loads due to solar wind, tides, control moments and nonuniform solar heating of the structure are considered as perturbations.A procedure for defining internal forces and moments and a varied structural geometry due to interaction of unperturbed and perturbed forces is given. The results of determining the frequencies of natural oscillations of the structure are also presented. Calculations are made on the basis of the obtained linearized equations reduced to quasi-univariate ones. A matrix factorization procedure allowing for constructing a stable-state numerical algorithm for solving the problem is employed.     

Export control regime for space items in China: Opportunities and challenges in the new era

Export control system is vital to effective control of sensitive items and technologies and thus an appropriate system is indispensable to the realization of the goal of non-proliferation. The progress so far shows that China has made great efforts in constructing a domestic regime for export controls. Nevertheless, it has also been recognized that the mere existence of a domestic regime is not sufficient and that the realization of export control should be complemented with effective and efficient enforcement. The paper examines the effectiveness of the current export control regime in China and explores means to strengthen the current regime to dispel the concerns from other nations. The paper concludes that China has been committed to export controls in sensitive space items in the past years; yet further improvements could be made to better serve China's national interests and its commitments under international nonproliferation export control regimes.     

Theory of type III radio bursts in the interplanetary space. II. Study of instability of the electron beam-solar wind plasma system in a linear approximation

Frequency characteristics of disturbances of a one-dimensionally inhomogeneous electron beam-solar wind plasma system are studied in the geometrical optics approximation on the basis of the Maxwell equations closed by the material equation obtained earlier. The corresponding dispersion equation is derived and solved. It is found that resonance interaction of a wave with an electron beam can occur only at two spatial points. Perhaps, such a short-time (point-like) mechanism of the resonance clarifies one of the main problems of physics of electron beams generated by solar flares: their time of existence is much longer than the time following from the previous theoretical estimates of the beam energy loss rate due to radiation.     

Spacecraft images obtained with a telescope at the Altai Optical Laser Center using adaptive optics

We present the results of experiments in which low-orbit spacecraft were observed from the Earth’s surface by the 600-mm optical telescope of the Altai Optical Laser Center. Thanks to the use of an adaptive optical unit, the angular resolution of images obtained is limited only by diffraction on the collective aperture of the telescope, and this angular resolution is better than that determined in a turbulent atmosphere without adaptive optics by a factor of 5 to 10.     

The use of radio images for analyzing the results of narrow-band radio location of asteroids

We investigate a method of getting radio images of asteroids by single-position radar with narrowband sounding signal. A model is presented for calculation of power spectra of echo signals of a rotating rough ellipsoid. This model is a useful tool for analyzing the results of radio-location experiments. The accuracy of determination of the shape of an asteroid and its roughness is estimated based on the analysis of two-dimensional radio images.     

A failure of international space cooperation: the International Earth Observing System

This paper examines the failure of the Earth Observation International Coordination Working Group to implement an International Earth Observation System. Tracing the history of both the Group and the mission concept, it explains the political and organizational failures that took place. It shows that these failures were linked to different approaches to international cooperation in Earth observation data policy. The main points of contention existed between Working Group members, NASA and ESA. NASA favored formal and binding legal arrangements, while ESA preferred to avoid institutionalized legal commitments. Success in coordinating and harmonizing data policy on a multilateral basis for Earth observation missions is more likely to be achieved by pursuing agreement on general principles and terms of reference than by seeking specific legal agreements.     

The UK parliamentary space committee: The emergence of a space lobby?

In the past few years the UK has become increasingly active as the financial conscience of the European Space Agency. This is not because the UK government has a wish to spend more on its national space effort; it is because it remains unconvinced of the benefits of certain European space activities, notably manned endeavours. In the absence of an effective UK space lobby, the government's policies have remained largely unchallenged. This article traces the growth of the Parliamentary Space Committee in the context of developments in recent European space policy and highlights the need for an active UK space lobby.     

Theory of type III radio bursts in the interplanetary space: I. Derivation of permittivity tensor for the system consisting of electron beam and solar wind plasma

The tensor of permittivity for the system “electron beam - plasma of the interplanetary space” is derived in the approximation of geometrical optics. The problem is one-dimensional; all parameters such as density of the beam and of the solar wind plasma, and the induction of the interplanetary magnetic field are assumed to be dependent only on the distance to the Sun. The beam is generated by an active region during a solar flare, and it is a source of radio bursts of type III in the interplanetary space. The tensor of permittivity was obtained to close field equations by a material equation. On the basis of these equations it becomes possible to study theoretically the amplitude-frequency characteristics of the radio bursts as disturbances of the above-described beam-plasma system.     

Controlling the motion of a spacecraft when approaching a large object of space debris

The problem of calculating the parameters of maneuvering a spacecraft as it approaches a large object of space debris (LOSD) in close near-circular noncoplanar orbits has been considered. In [1–4], the results of analyzing the problem of the flyby of the separated LOSD groups have been presented. It has been assumed that a collector spacecraft approaches the LOSD and captures it or it is inserted into the nozzle of a small spacecraft that has a proper propulsion system (PS). However, in these papers, the flight from one object to another was only analyzed and the problem of approaching to LOSD with a given accuracy was not considered. This paper is a supplement to the cycle of papers [1–4]. It is assumed that, the final stage of approaching the LOSD is implemented by maneuvering in many orbits (up to several dozens) with low-thrust engines, but the PS operating time is fairly small compared with the orbit period in order to make it possible to use impulse approximation in the calculations.     

The space elevator in the context of current space exploration policy

The space elevator is an advanced space transportation system that someday could replace chemical rockets as humanity's primary means of reaching Earth's orbit. However, before this can occur, a number of enabling technologies will need to be developed, and a variety of economic and policy questions must be addressed. The goal of this paper is to examine the feasibility of the space elevator in the context of current space exploration policy. The paper reviews the space elevator's critical enabling technologies and presents their wide variety of applications. The challenges of funding the space elevator and of building support for the program are discussed. The potential for international cooperation is considered, and the role of the space elevator in the Vision for Space Exploration is examined. The paper argues that each of the space elevator's component technologies ought to be developed independently to meet separate nearer-term objectives. The space elevator should be just one of many applications considered in making decisions to pursue research and development related to each component technology. The enabling technologies, once mature, might eventually be integrated in the construction of a full-scale space elevator from the Earth's surface to geosynchronous orbit and beyond.     

The Soviet-Russian space suits a historical overview of the 1960's

The development of protective suits for space use started with the Vostok-suit SK-1, first used by Yu. Gagarin on April 12, 1961, and then used on all subsequent Vostok-flights. The technical background for the design of these suits was the work on full pressure protective suits for military pilots and stratospheric flights in the 1930's through 50's. The Soviet-Russian space programme contains a large number of 'firsts', and one of the most well known is the first EVA by Leonov in 1965. This event is also the starting point for a long series of space suit development for Extravehicular Activities over the last 35 years. The next step to come was the transfer in void space of crew members between the two spacecraft Soyuz 4 and 5 in 1969. As has later become known this was an essential element in the planned Soviet lunar exploration programme, which in itself required a new space suit. After the termination of the lunar programme in 1972, the space suit development concentrated on suits applicable to zero-gravity work around the manned space stations Salyut 6, Salyut 7 and MIR. These suits have become known as the ORLAN-family of suits, and an advanced version of this suit (ORLAN-M) will be used on the International Space Station together with the American EMU. This paper covers the space suit development in the Soviet Union in the 1960's and the experience used from the pre-space era.     

Monitoring of the space system

We have performed monitoring of the space system that includes the Earth, the Moon, the Sun, and the GPS satellite group. We have discovered semi-diurnal and diurnal periodicities in the number of satellites detected as well as in the altitude, latitude and longitude by a GPS receiver. We have revealed tidal deformations related to changes in the Earth?s orientation with respect to the Moon and the Sun.     

Overview of physiological principles to support thermal balance and comfort of astronauts in open space and on planetary surfaces

Although specialists have attempted to improve the space suit to provide better protection in open space or on planetary surfaces, there has been a relative lack of attention to features of human thermoregulatory processes that influence comfort and therefore have an impact on the effectiveness of protective equipment. Our findings showed that different body tissues transfer heat in/out of the body in a different manner. There are also individual differences in thermal transfer through body areas with different proportions of tissues; therefore, data on the thermal profile of each astronaut needs to be used to estimate the optimal body areas for heat/cold transfer in and out of the body in an individually tailored cooling/warming garment. Principles for supporting thermal comfort in space were formulated based on a series of studies to evaluate the human body's response to uniform/nonuniform thermal conditions on the body surface. We conclude that future space suit design and comfort support of astronauts can be easier and more effective if these principles are incorporated.     

Longitude-dependent effects of fragmentation events in the geosynchronous orbit regime

The effects of on-orbit fragmentation events on localized debris congestion in each of the longitude slots of the geosynchronous orbit (GEO) regime are evaluated by simulating explosions and collisions of uncontrolled rocket bodies in multiple orbit configurations, including libration about one or both of the gravitational wells located at 75°E and 105°W. Fragmentation distributions are generated with the NASA Standard Breakup Model, which samples fragment area-to-mass ratio and delta-velocity as a function of effective diameter. Simulation results indicate that the long-term severity and consequence of a GEO fragmentation event is strongly dependent upon parent body longitude at the epoch of fragmentation, which can spawn bi-annual “fragment storms” in high-risk longitude slots, driven by lower-energy fragments that have been captured and have started librating around the nearby gravitational well.     

The physical price of a ticket into space

As a direct consequence of exposure to microgravity astronauts experience a number of physiological changes, which can have serious medical implications when they return to Earth. Most immediate and significant are the head-ward shift of body fluids and the removal of gravitational loading from bone and muscles, which lead to progressive changes in the cardiovascular and musculoskeletal systems. Cardiovascular adaptations result in an increased incidence of orthostatic intolerance (fainting) post-flight, decreased cardiac output and reduced exercise capacity. Changes in the musculoskeletal system contribute significantly to the impaired functions experienced in the post-flight period. The underlying factor producing these changes is the absence of gravity. Countermeasures, therefore, are designed primarily to simulate Earth-like movements, stresses and system interactions. Exercise is one approach that has received wide operational use and acceptance in both the US and Russian space programmes, and has enabled humans to stay relatively healthy in space for well over a year. Although it remains the most effective countermeasure currently available, significant physiological degradation still occurs. The development of other countermeasures will therefore be necessary for longer duration missions, such as the human exploration of Mars.     

Strategy for capturing of a tumbling space debris

In general space debris objects do not possess much convenient features and are non-cooperative. In such cases, since the conditions for capture are not favorable, tracking errors will lead to loading, and momentum transfer will occur during the capture process.In most cases, detailed mass and inertial characteristics of the target are unknown, either because design details are unavailable or due to changes as a result of damage sustained when failure occurred or gradual degradation over the years, and this makes impedance matching of the capture arm force control system difficult.This led to us to devise a “joint virtual depth control” algorithm for robot arm control, which brakes the rotation of a target with unknown inertia. This paper deals with a removal work strategy and control method for capturing and braking a tumbling, non-cooperative target space debris.We propose a new brush type contactor as end-effecter of a robot arm for reducing the rotational rate of the target debris. As a means for relieving the loads generated during target tapping, in addition to joint compliance control we propose a new control method that controls the arm tip force according to a contact force profile.     

Test results of the air turbo ramjet for a future space plane

The Institute of Space and Astronautical Science (ISAS) has been engaged in the development study on the Air Turbo Ramjet (ATR) engine since 1986 in cooperation with the Ishikawajima Harima Heavy Industries Co. Ltd (IHI). The ATR is one of the most preferable candidates for the propulsion system of a future space plane. Our ATR engine is a combined cycle air breathing propulsion system which consists of the turbojet and the fan boosted ramjet using the liquid hydrogen as a fuel. This engine system was named “ATREX” after employing the expander cycle. The ATREX is energized by thermal energy extracted regeneratively in both the pre-cooler installed in the air intake and the heat exchanger in combustion chamber. The ATREX works in the flight condition from sea level static up to Mach 6 at 35 km altitude. The ATREX employs the tip turbine configuration for compactness of turbo machinery. We are assessing the feasibility of the ATREX system by the sea level static tests using the 1/4-scale model (ATREX-500) with a fan inlet diameter of 300 mm and overall length of 2120 mm. In 1990, the ATREX-500 engine was tested in a sea level static condition to verify the performance characteristics of the turbo machinery and the combustor. In September of 1991, the heat exchanger was installed in the combustion chamber and tested independently from the turbo system. In November of 1991, the heat exchanger was coupled with the turbo system and tested to verify the overall system of the ATREX. In this paper are presented the test results of the ATREX-500 engine tested in the sea level static condition.