NASA's in-space technology experiments program: Status and plans

Experience with the Shuttle and free-flying satellites as technology test beds has shown the feasibility and desirability of using space assets as facilities for technology development. Thus, by the time the space station era arrives, technologists will be ready for an accessible engineering facility in space. Along with the scientific and commercial space development communities, the technology development community has been participating in defining requirements for this in-space facility. As the 21st century is approached, it is expected that many flights to the Space Station Freedom will carry one or more RT&E experiments. The experiments are likely to utilize both the pressurized volume, and the external payload attachment facilities. Based on the success of instrumenting the Shuttle itself to obtain ascent and descent aerothermodynamic data a unique, but extremely important, class of experiments will use the space station itself as an experimental vehicle.     

基于在轨运行状态的卫星稳定性与可靠性研究

为解决卫星在轨运行故障率较高的问题,文章分析了卫星在轨运行的特点,定义了卫星在轨工作状态及其与系统稳定性变化的关系。研究表明:对在轨运行安全稳定状态进行控制,能使状态保持或向高级跃迁,可提升卫星稳态及可靠性。文章最后提出了提高卫星在轨运行稳定性与可靠性的在轨运行策略与技术方向。     

FPGA-based operational concept and payload data processing for the Flying Laptop satellite

Flying Laptop is the first small satellite developed by the Institute of Space Systems at the Universität Stuttgart. It is a test bed for an on-board computer with a reconfigurable, redundant and self-controlling high computational ability based on the field programmable gate arrays (FPGAs). This Technical Note presents the operational concept and the on-board payload data processing of the satellite. The designed operational concept of Flying Laptop enables the achievement of mission goals such as technical demonstration, scientific Earth observation, and the payload data processing methods. All these capabilities expand its scientific usage and enable new possibilities for real-time applications. Its hierarchical architecture of the operational modes of subsystems and modules are developed in a state-machine diagram and tested by means of MathWorks Simulink-/Stateflow Toolbox. Furthermore, the concept of the on-board payload data processing and its implementation and possible applications are described.     

FPGA-based operational concept and payload data processing for the Flying Laptop satellite

Flying Laptop is the first small satellite developed by the Institute of Space Systems at the Universität Stuttgart. It is a test bed for an on-board computer with a reconfigurable, redundant and self-controlling high computational ability based on the field programmable gate arrays (FPGAs). This Technical Note presents the operational concept and the on-board payload data processing of the satellite. The designed operational concept of Flying Laptop enables the achievement of mission goals such as technical demonstration, scientific Earth observation, and the payload data processing methods. All these capabilities expand its scientific usage and enable new possibilities for real-time applications. Its hierarchical architecture of the operational modes of subsystems and modules are developed in a state-machine diagram and tested by means of MathWorks Simulink-/Stateflow Toolbox. Furthermore, the concept of the on-board payload data processing and its implementation and possible applications are described.     

Robotic vision technology for space station and satellite applications

This paper presents the robotic vision technologies newly developed for satellites and space station robotic applications at the Pattern Analysis and Machine Intelligence (PAMI) Laboratory of the University of Waterloo and at the Vision, Intelligence and Robotics Technologies Corp. (VIRTEK). The first part of the paper presents how the PAMI-VIRTEK Vision technologies are engineered to support the STEAR (Space Station, Strategic Technologies in Automation and Robotics Program) sponsored by the Canadian Space Agency. The second describes the use of stereo CCD camera for sensing the deformed shape of a third generation satellite. It addresses the notion of shape interpolation and error reduction.     

Satellite-aided land mobile radio experiments,applications and problems

Radio communications between vehicles or individuals and base stations are essential to many public safety, law enforcement and commercial users in urban areas. Present day communications are limited to nearly line-of-sight distances from the vehicle or hand portable units to a base station or repeater. It is probable that many potential users in rural, remote and offshore areas would benefit if the communications were available everywhere on land and territorial waters. Geosynchronous satellites can serve as repeaters for mobile and personal radios, and they appear to be a cost effective means of providing the service.Voice bandwidth communication and automatic position monitoring of an automobile were tested using the VHF transponders of NASAs ATS-3 and ATS-1 satellites. Voice communications were reliable and position fixes were accurate to one fourth mile, with 0.3 mile precision of individual fixes.Demonstrations for potential users have included emergency medical voice and telemetry communications between ambulances and hospitals.While technical feasibility of satellite-aided mobile and personal communications has been demonstrated, and its potential value is appreciated by a small segment of the user community, many problems remain before an operational system could be implemented. Solutions to the problems require an experimental satellite with a multibeam antenna. The satellite or its associated ground terminals should incorporate computer controlled network switching to test demand assignment of channels. Prolonged experience by many users of the experimental satellite in their routine operations would aggregate user needs and define the capital investment that would be justified to implement a commercial operating system.     

State of the art, lightweight scientific experiments available for small to micro satellite missions

A selection of light weight scientific instruments originally designed for major international missions but which, because of their modest resource requirements, can now in addition be flown aboard ‘small’ to ‘micro’ satellites are, briefly, described. These instruments have the capability to either make measurements of constituents of the Earth's energetic particle environment, or provide detailed monitoring of multiple parameters of the cold terrestrial ionospheric plasma. Scientific reasons for flying such instruments in LEO are, in each case, advanced. Individually, they constitute representative examples of a mature genre of commercially available (a cost parameter of £100k/kg can be achieved), light weight, space qualified, instruments which can contribute significantly to the implementation of first class scientific programs aboard small/micro satellites. Uniquely fault tolerant data processing units are a feature of these devices.     

Space experiments of deployable boom and umbrella test satellite (DEBUT)

This paper describes the results of the in-orbit performance testing of deployable and retractable umbrella and boom systems, which will be used as important subsystems of Boomerang/Tether satellites. The umbrella is one of the possible candidates of the aerodynamic braking system for boomerang satellite and the boom is also one of the possible candidates of relative position adjusting mechanism between center of mass and aerodynamic force center of the boomerang satellite and initial release/final recovery mechanism of the tethered satellite. For this technology verification, a small and inexpensive satellite, named DEBUT (Deployable Boom and Umbrella Test satellite), was developed in a short period of 1.5 years elapsing from the start of the detailed design until the launch of the mission. The lithium dry cell batteries were used as the primary power and functioned normally during 10 days mission lifetime.     

Paxsat and progress in arms control : Canadian research focuses on remote sensing applications

Verification of arms control treaties is essential to provide adequate international confidence in treaty compliance. This Viewpoint underlines the responsibility of non-superpower countries to become more closely involved in space surveillance of treaties to which they are parties. In Canada, Paxsat research has focused on two potential applications of space-based remote sensing to multi-lateral arms control verification. The necessary technology is readily available in non-superpower countries for the Paxsat concept to be put into operation.     

卫星面临的威胁及其防护

随着空间技术的发展,卫星在现代战争中的作用越来越突出,卫星系统的攻防对抗应运而生.分析了在未来空间战中卫星面临的主要威胁,阐述了卫星系统防护的思路:立足于体系对抗,提高空间态势感知能力、卫星自身防护能力、空间进攻威慑能力,技术防护和战术防护相结合,着眼于卫星系统信息资源流动的全程安全,对薄弱环节重点加强防护.     

Salt balance: From space experiments to revolutionizing new clinical concepts on earth – A historical review

For a long time, sodium balance appeared to be a “done deal” and was thought to be well understood. However, experiments in preparation of space missions showed that the concept of osmotic sodium storage and close correlations of sodium with water balance are only part of the regulatory mechanisms of body salt.     

Space capsule recovery—Evaluation of risk factors, safety plans and procedures and design of experiments for systems qualification

The Indian Space capsule (SRE-1) launched aboard PSLV-C7 rocket, was recovered successfully in the Bay of Bengal on January 22, 2007 after its orbital sojourn of 12 days. Apart from serving as a platform for micro-gravity experiments, SRE-1 demonstrated ISRO's capability in the field of orbital reentry and recovery technologies. Satish Dhawan Space Centre (SDSC SHAR), the Spaceport of India was given the prime responsibility of assessment of mission risk, formulation and execution of safety plans and procedures, design and conduct of trials for validating the mission-critical sub-systems as well as the physical recovery of the capsule. To achieve these objectives, a number of drop tests were designed and conducted by SDSC SHAR involving real time computer network, ground-based tracking and telemetry stations, communication systems, safety and material handling systems, target identification and recovery systems. Dissemination of relevant information and coordination with multiple external organizations such as Indian Coast Guard, Indian Air Force and Indian Navy is an important aspect of these experiments. This paper delineates the methodologies designed and implemented at SDSC SHAR for validating those critical systems whose functionality finally culminated in the success of the mission, enabling India to join the elite group of nations with reentry module recovery capability.     

多波束及其在无人机上的应用

分析了现代作战环境下无人机面临的新威胁。介绍了多波束技术的原理和特点,分析了多波束干扰机对这些威胁的适应能力,包括对有源相控阵雷达的适应能力和多目标干扰能力。最后分析了多波束技术在无人机平台上的应用。     

Gravity-oriented satellite dynamics subject to gravitational and active damping torques

The dynamics of the rotational motion of a satellite moving in the central Newtonian field of force over a circular orbit under the effect of gravitational and active damping torques, which depend on the satellite angular velocity projections, has been investigated. The paper proposes a method of determining all equilibrium positions (equilibrium orientations) of a satellite in the orbital coordinate system for specified values of damping coefficients and principal central moments of inertia. The conditions of their existence have been obtained. For a zero equilibrium position where the axes of the satellite-centered coordinate system coincide with the axes of the orbital coordinate system, the necessary and sufficient conditions for asymptotic stability are obtained using the Routh–Hurwitz criterion. A detailed analysis of the regions where the conditions of the asymptotic stability of a zero equilibrium position are fulfilled have been obtained depending on three dimensionless parameters of the problem, and the numerical study of the process of attenuation of satellite’s spatial oscillations for various damping coefficients has been carried out. It has been shown that there is a wide range of damping parameters from which, by choosing the necessary values, one can provide the asymptotic stability of satellite’s zero equilibrium position in the orbital coordinate system.     

Design to safety: experience and plans of the Russian space suit programme

The paper presents the analysis of the Russian experience gained in the operations of Salyut-6, 7 and Mir orbital stations. The main factors determining their effectiveness and safety are considered and the main requirements to the EVA suit, as the most important tool for the EVA, are formulated.     

US export controls and Canadian autonomy to collaborate on international space missions

Canada is a space power with unique technical niches that support opportunities for collaboration on space technologies. When U.S.-origin space technologies are involved Canada's ability to collaborate internationally may be conditional on US law and policy. As a result, US export control law can be directly linked to the success or failure of Canadian collaboration. This article examines the strategic impact of U.S. export controls on Canadian autonomy to collaborate on international missions, including multi-use missions. Canadian space export control policy is also examined more broadly with the goal of providing specific policy recommendations that will enhance Canada's future as an international space actor.     

Developing countries and space: From awareness to participation

As space commercialization is becoming a reality, and with the growing tendency for such activity to be transferred to the private sector, it is time for developing countries to assume a role in space. Space law could be of help if the interpretation of terms such as ‘common heritage’ were agreed on and sensible rules for the regulation of competition in space elaborated. But it is up to the developing states themselves to become aware of the situation, educate their public and train their personnel through participation in cooperative space ventures with the developed world.     

General background and approach to multibody dynamics for space applications

Multibody dynamics for space applications is dictated by space environment such as space-varying gravity forces, orbital and attitude perturbations, control forces if any. Several methods and formulations devoted to the modeling of flexible bodies undergoing large overall motions were developed in recent years.Most of these different formulations were aimed to face one of the main problems concerning the analysis of spacecraft dynamics namely the reduction of computer simulation time. By virtue of this, the use of symbolic manipulation, recursive formulation and parallel processing algorithms were proposed. All these approaches fall into two categories, the one based on Newton/Euler methods and the one based on Lagrangian methods; both of them have their advantages and disadvantages although in general, Newtonian approaches lend to a better understanding of the physics of problems and in particular of the magnitude of the reactions and of the corresponding structural stresses. Another important issue which must be addressed carefully in multibody space dynamics is relevant to a correct choice of kinematics variables. In fact, when dealing with flexible multibody system the resulting equations include two different types of state variables, the ones associated with large (rigid) displacements and the ones associated with elastic deformations. These two sets of variables have generally two different time scales if we think of the attitude motion of a satellite whose period of oscillation, due to the gravity gradient effects, is of the same order of magnitude as the orbital period, which is much bigger than the one associated with the structural vibration of the satellite itself. Therefore, the numerical integration of the equations of the system represents a challenging problem.This was the abstract and some of the arguments that Professor Paolo Santini intended to present for the Breakwell Lecture; unfortunately a deadly disease attacked him and shortly took him to death, leaving his work unfinished. In agreement with Astrodynamics Committee it was decided to prepare a paper based on some research activities that Paolo Santini performed during almost 50 years in the aerospace field. His researches spanned many arguments, encompassing flexible space structures, to optimization, stability analysis, thermal analysis, smart structure, etc. just to mention the ones more related to the space field (Paolo Santini was also one the pioneers of the studies of composite wing structures, aeroelasticity and unsteady aerodynamics for aeronautical applications). Following notes have been prepared by Paolo Gasbarri who was one of Paolo Santini collaborators for almost 15 years, they will attempt to offer a sketch of Professor Santini's activity by focusing on three main topics: the stability of flexible spacecrafts, the dynamics of multibody systems and the use of the smart structure technology for the space applications.