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Title: Feasibility of the Implementation of Soft Landings in Sweden Authors: Sebastian Eddin & Nadja Pilav Supervisor: Stefan Olander Examiner: Rikard Sundling Close to 40 percent of global energy use is associated with the construction industry and building-related activities. Although several initiatives are underway both on national and international level from both the Swedish government and the European Union regarding energy efficiency, the construction industry is lagging behind, especially with regards to building performance. The difference between projected energy usage and actual energy usage in completed buildings is substantial, with handovers and poor commissioning having been identified as among the main underlying causes. The purpose of this thesis is to examine how Swedish handovers affect building performance in practice today, to review the Soft Landings framework and its efficacy, as well as analyse its potential as an addition to the Swedish procurement process. The thesis aims to answer these through a literature review and case studies to understand its uses and potential implementations, with an additional interview study conducted with industry actors to explore whether it can be implemented in Swedish procurement processes and tackle the performance gaps in the construction industry. The results from the literature review and case studies show that the Soft Landings framework can be effective in tackling the performance gap if it is implemented early in the procurement process along with incentives encouraging use or enforcing it. The interview study revealed that there is a fragmentation of contracts used to handle handovers today in the Swedish construction industry, causing confusion and a general lack of awareness concerning best practises of the handover process, with the participants suggesting that a standardised handover process could benefit the industry. In conclusion, the studies show that the Soft Landings does have the potentia, Titel: Möjligheten av implementering av Soft Landings i Sverige Författare: Sebastian Eddin & Nadja Pilav Handledare: Stefan Olander Examinator: Rikard Sundling Närmare 40 procent av den globala energianvändningen är kopplad till byggbranschen och byggrelaterade verksamheter. Trots att flera initiativ pågår både på nationell och internationell nivå från både den svenska regeringen och EU när det gäller energieffektivitet har det visat sig att byggbranschen släpar efter, särskilt när det gäller byggnadsprestanda. Skillnaden mellan beräknad energianvändning och faktisk energianvändning i färdiga byggnader är betydande, med överlämningar och dålig idrifttagning som två utav de främsta bakomliggande orsakerna. Syftet med avhandlingen är att undersöka hur svenska överlämningar påverkar byggnadsprestanda i praktiken idag, att se över Soft Landings ramverket och utvärdera dess effektivitet samt analysera om det har potential som ett tillägg till svensk bygg- /upphandlingsprocess. Avhandlingen syftar till att besvara dessa frågor dels genom en litteraturgenomgång och fallstudier för att förstå dess användningsområden och effektivitet gällande byggnadsprestanda och prestanda-gap, med en kompletterande intervjustudie utförd med branschaktörer med målet att undersöka om den kan implementeras i svenska bygg-/upphandlingsprocesser och tackla problemen kopplade till prestanda-gapen. Resultaten från litteraturgenomgången och fallstudierna visar att Soft Landings-ramverket kan vara effektivt för att hantera prestanda-gap om det etableras tidigt i upphandlingsprocessen tillsammans med incitament som uppmuntrar till användning eller tillämpning av det. Intervjustudien visade att det finns en fragmentering av kontrakt som används för att hantera överlämningar idag i den svenska byggbranschen, vilket orsakar förvirring och en allmän brist på medvetenhet om bästa praxis i överlämningsprocessen. Deltagarna föreslår att en standardiserad överlämningsprocess skulle kunna gynna industrin. S, Should Soft Landings be implemented in the procurement process in Swedish construction? The purpose of this thesis is to examine how Swedish handovers affect building performance in practice today, to review the Soft Landings framework and its efficacy, as well as analyse its potential as an addition to the Swedish procurement process. The thesis aims to answer research questions through a literature review and a multi-case study to understand its uses and potential implementations, with an additional interview study conducted with industry actors to explore whether it can be implemented in Swedish procurement processes and tackle the problems with discrepancies in delivered building performance in the construction industry. Several initiatives are underway both on national and international level from both the Swedish government and the European Union regarding energy efficiency, the construction industry is lagging behind, especially with regards to building performance. The difference between projected energy usage and actual energy usage in completed buildings is substantial, with handovers and poor commissioning having been identified as among the main underlying causes. The results from the literature review show that it is essential that frameworks such as Soft Landings be implemented early in the procurement process along with incentives encouraging use or enforcing it, in order for the involved actors to comply with the guidance provided. The interview study revealed that there is a fragmentation of contracts used to handle handovers today in the Swedish construction industry, causing confusion and a general lack of awareness concerning best practices of the handover process. The participants suggested that it could be beneficial for the construction industry to settle on a standardised approach to handovers, potentially through legislative means, in order to combat poor handovers and the performance gaps. The Soft Landings framework has achieved success in

Two instruments have been developed to soft-land species with less than 10eV. First is the laser ablation-coupled drift tube. The chamber was developed with the idea of using an inert gas, helium, to thermalize ions. This allows us to reduce the clusters KE from 40 eV to about 1 eV by producing thermal collisions between the gas and our sample. The drift chamber was assembled using a 6 four-way cross coupled with a 6 reducing cross housing the ion drift cell. Nd-YAG 532nm was utilized to ionize the sample. The clusters formed were then discriminated by cross-section and transported through the drift cell with a potential from -100 to -500 V to our mica surface. The isolated sample was then characterized using AFM and electrochemistry. The second instrument is a rectilinear ion trap with integrated ultra fast pulse valve. This instrument has some novel electronics to allow complete shut-down of the applied RF in 2 cycles. This coupled to the high pressure acquisition makes it an ideal mass filter for preparative mass spectrometry. Though the ion current is an order of magnitude less than the drift tube, the resolution is 2 orders of magnitude greater, making the two instruments complimentary. A preparative material instrument utilizing Soft Landing Ion Mobility (SLIM) to deposit and comb through the various ionized species formed using front end chemistry (figure 1.) was developed in our lab. This novel instrument has allowed us to deposit selected ions onto unmodified substrates with kinetic energies (KE) ranging from 1 eV to sub-eV. The instrument is unique in that surfaces can be created at pressures spanning from 1 100 Torr rather than usual UHV conditions. This method with low kinetic energies allows the soft-landed ions to remain intact, retaining structure for self-assembly followed by the characterization of novel materials. Recently research in the field of carbon containing clusters and nanostructures have experienced a wealth of novel research and de, The original document contains color images.

The U.S. Army Natick Soldier Center (NSC) is the lead agency for most U.S. Department of Defense (DoD) airdrop programs and is teamed with numerous DoD organizations and contractors to plan and execute numerous Joint Precision Airdrop System (JPADS) efforts to include an Advanced Concept Technology Demonstration (ACTD). The JPADS ACTD is integrating a USAF-developed laptop-computer-based precision airdrop planning system known as the Joint Precision Airdrop System Mission Planner (JPADS-MP) with the US Army Joint Precision Airdrop System (JPADS) in the 'light' category of weight (2,201-10,000 lbs rigged weights). The integrated system objectives include the ability to airdrop JPADS systems of up to 10,000 lbs rigged weight, from altitudes of up to 25,000 ft mean sea level (MSL), with up to 10+ kms of offset, and land precisely within 100 meters of a preplanned ground impact point. The JPACWG executed a Precision Airdrop Technology Conference and Demonstration (PATCAD) at the US Army Yuma Proving Ground on 17-21 Oct 05. The PATCAD-2005 event attracted 350 participants from throughout the world. During this week long event, 115 airdrops were conducted using five aircraft, demonstrating 23 different precision airdrop systems and numerous related technologies. This paper provides an overview of the current status of U.S. DoD precision airdrop programs, as well as recent activities of the NATO JPACWG. The paper also highlights the research, technology, and integration challenges associated with precision airdrop systems, and the airdrop community's Modeling and Simulation needs; including issues associated with personnel and all weights and sizes of cargo airdrop deployments from transport aircraft in order to help set the need for Fluid Dynamics of Personnel and Equipment Precision Delivery from Military Platforms., Presented at the RTO Applied Vehicle Technology Panel (AVT) Specialists' Meeting on "Fluid Dynamics of Personnel and Equipment Precision Delivery from Military Platforms" held in Vilnius, Lithuania on 2-3 Oct 2006. Published in RTO-MP-AVT-133, paper no. Keynote 2. See also ADM202394. The original document contains color images.

TSNIIMash was one of the first scientific centers were such investigations had been started dealing with force and heat loads from the engine jets acted on the space vehicle structure during soft landing on the lunar and Martian surfaces. Interaction of single/multiple jet with oncoming flow or surface is characterized by appearance of a large number of shock waves contact surfaces separated zones and other peculiarities and this defined the necessity of fulfillment of extensive experimental studies. For these aims U-22 and U-22M vacuum chambers were created in TSNIIMash in 1970-ies and 1980-ies. Some results regarding drag coefficient of the space vehicle with working jets are presented below., See also ADM001433. International Conference on Methods of Aerophysical Research (11th). Held in Novosibirsk, Russia on 1-7 Jul 2002.

The U.S. Army Soldier Systems Command's Natick Research, Development and Engineering Center (NRDEC) is currently examining a novel concept for reducing the impact shock sustained by airdropped payloads upon ground impact A device, called a parachute retractor, is placed between the payload and parachute confluence point, and when activated, accelerates the parachute and payload toward each other; slowing the payload prior to ground impact. The goal is to eliminate the cushioning material currently placed under airdrop loads, providing a roll-on/roll-off (RO/RO) capability. The retractor concept consists of a pneumatically driven piston/cylinder mechanism connected by cables to upper and lower pulley blocks to increase the system's overall mechanical advantage. Full scale testing of payload/retractor combinations is considered impractical, given the varied weights of military cargo presently airdropped and the multitude of retractor configurations possible. The need for a computational tool to determine the activation height and to optimize system design parameters, therefore, was recognized early on in the exploratory development effort. This report describes a predictive model, developed in response to that need, which couples a simplified parachute model to a model of the retractor mechanism. This model is able to predict the motion of the piston, payload and parachute confluence point, as well as the forces generated during retraction. This report first reviews the model's underlying theory and method of coupling. Computer program predictions are then compared to behavior observed in an experiment conducted on a instrumented prototype retractor device at Tustin Marine Corps Air Station, Santa Ana, CA in April 1994.

The HIPES Program was conducted for NASA-LeRC by TRW. The Basic Program consisted of system studies, design of testbed engine, fabrication and testing of engine. Studies of both pressure-fed and pump-fed systems were investigated for N204 and both MMH and N2H4 fuels with the result that N2H4 provides the maximum payload for all satellites over MMH. The higher pressure engine offers improved performance with smaller envelope and associated weight savings. Pump-fed systems offer maximum payload for large and medium weight satellites while pressure-fed systems offer maximum payload for small light weight satellites. The major benefits of HIPES are high performance within a confined length maximizing payload for lightsats which are length(volume) constrained. Three types of thrust chambers were evaluated-Copper heatsink at 400, 500 and 600 psia chamber pressures for performance(thermal, water cooled to determine heat absorbed to predict rhenium engine operation and rhenium to validate the concept. The HIPES engine demonstrated very high performance at 50 lbf thrust(epsilon= 150) and Pc=500 psia with both fuels:Isp=337 sec using N2O4-N2H4 and Isp=327.5 sec using N2O4-MMH indicating combustion efficiencies >98%. A powder metallurgy rhenium engine demonstrated operation with high performance at Pc=500 psia which indicated the viability of the concept. jg

The National Environmental Policy Act (NEPA), the Council on Environmental Quality (CEQ) regulations implementing NEPA (40 CFR Parts 1500- 1508), and U.S. Department of Defense (DoD) Directive 6050.1 direct that decision-makers take into account environmental consequences when authorizing or approving major federal actions. This environmental assessment (EA) evaluates the environmental consequences of conducting activities for the SSRT test program. The purpose of the proposed action is to provide SDIO with a suborbital, recoverable rocket (SRR) capable of lifting up to 3,000 pounds of payload to an altitude of 1.5 million feet; returning to the launch site for a precise soft landing; with the capability to launch for another mission within three to seven days. To support these requirements, the proposed action involves validation and testing of a DC-X vehicle. Component assembly of the vehicle will take place at Scaled Composites, Inc., Mojave, CA; Chicago Bridge and Iron, Cordova, AL; Pratt and Whitney, West Palm Beach, FL, Aerojet, Sacramento, CA; and McDonnell Douglas Space Systems Company, Beach, CA. Static test firing activities will occur at NASA/White Sands Test Facility Huntington (WSTF), WSMR, New Mexico, and launch activities will occur at White Sands Space Harbor (WSSH), WSMR, New Mexico. No significant impacts are anticipated to the environment at the engineering contractor facilities, NASA/WSTF, or WSSH.

Airbags are currently being investigated as a ground impact energy absorber for U.S. Army airdrops. Simple airbags with constant vent areas have been studied previously by numerous investigators. In this research effort, a method of controlling the vent area and a method of injecting gas into a simple airbag to improve its performance, i.e., to decrease its peak C force, were analytically and experimentally investigated. In addition, augmented simple airbags using paper honeycomb as an auxiliary energy absorber were also experimentally investigated. Complex airbags using vent-control and gas- injection and augmented airbags were found to decrease the peak G forces of simple airbags by 30%. Results of these investigations are presented in this report. Test and evaluation, Airbags, Impact attenuation, Energy absorbers, Soft landing, Airdrop Operations, Ground impact.

This study investigates soft and semisoft impact velocity limits of two frequently airdropped, uncushioned and semicushioned, military vehicles. A jeep and 2 1/2-ton truck were tied down to an airdrop platform, raised to various heights, and released. Semisoft impacts were those in which some various heights, and released. Semisoft impacts were those in which some paper honeycomb stacks were slipped between the vehicle frame and platform. Time variation of vehicle acceleration, suspension travel, and bump stop contact were recorded; data for nineteen jeep drops and seven 2 1/2-ton truck drops is presented here. The results of this study provide baseline data for design of a soft or semisoft-landing airdrop platform or airdrop system. Keywords include: Soft landing, Impact testing, Military vehicles, Airdrop operations, Aerial delivery, and Landing Impact.

Airbags are currently being investigated by the Army as an alternative to paper honeycomb and retrorockets for soft landing of airdropped payloads. A double-chamber balloon skirt airbag developed by a French company was claimed to provide low impact G forces and ground gliding capability. The performance of an eight balloon-skirt airbag-platform system was investigated in a previous study at NRDEC. The performance of the system was not satisfactory. In an attempt to improve the performance, a single balloon-skirt was modified in the current study and its performance was investigated at various test conditions. Test results showed that the double-chamber design of the balloon- skirt airbag is moderately better than the single-chamber design but its performance is still not as good as the manufacturer claimed.

A retrorocket soft landing system for airdropped cargo is described and mathematically analyzed. Solid propellant rockets and fixed height ground sensing, previously used in the experimental Parachute Retrorocket Airdrop System (PRADS), are assumed for this system. Seventeen variables affecting the load impact velocity are defined and used to write the one-body equations of motion for the system. A computer is used to generate 500 constrained random values for each independent variable, to calculate the impact velocity for 500 cases by solving the equations of motion, and to statistically analyze the results. It is concluded that 95% of the soft landings can be expected to have impact velocities between 2.0 and 3.4 m/s (6.1 and 10.3 ft/s).

This bibliography contains unclassified and unlimited citations on Space Stations. These citations provide information emphasizing aerodynamic characteristics, checkout procedures, control systems, telemeter systems, electrical power systems, safety, navigation, space maintenance, space propulsion, and extravehicular activity. It also includes pertinent information on space shuttles and their operational characteristics. Four computer generated indexes are provided. (Author), Supersedes Rept. no. DDC-TAS-75-10, AD-A010 500 and DDC-TAS-70-20-1, AD-703 500.

Edited trans. of Letectvi Kosmonautika (Poland) v53 n14 p552-554 1977, by Alexander Kirjanov.

Eighty flight tests of the AeroFlyer are carried out in order to demonstrate that it can fly and in order to obtain flight performance data. All of these tests are summarized with particular emphasis on the data obtained from the three flight tests at Wright Field. These demonstrate that the AeroFlyer can take off directly from the ground, climb, turn right and left, glide and achieve a precision soft landing. The data from the three flights at Wright Field is analyzed and compared with performance predictions. The turns were accomplished by rudder, by wing deflection, and by combinations of both. The representative flight velocity is 29 mph and the rate of climb is 60 ft/min for an AeroFlyer weighing 579.3 lbs. using a 400 sq. ft. Parafoil. The horsepower required for level flight was 12. The minimum radius of turn demonstrated was 175 ft. and the nominal landing roll was estimated to be less than 20 ft. This performance data is used to predict optimum parafoil performance for flight system weights ranging from 10 lbs. to 10,000 lbs. (Author)

Studies have been conducted on an Air Cushion Landing System for the Australian Jindivik target drone aircraft. Analyses are presented of the airflow and yaw thruster control systems, and the vehicle stability with a deployed recovery trunk is assessed. The vehicle touchdown and slideout on a recovery trunk are presented, and the design of an improved retention/release system is shown. (Author)

Working copy machine trans. of Tsentralnyi Aerogidrodinamicheskii Institut. Uchenye Zapiski (USSR) v3 n3 p80-85 1972.

This report describes a bogie type landing gear especially suitable for providing soft landing capabilities for short take-off and landing (STOL) aircraft wherein fore and aft wheels are mounted on opposite ends of a vertical shock strut. In one embodiment, a torque link pivotally connects the aft end of the bogie to the shock strut such that, under normal landing conditions, the front wheel will touch down first thereby reducing and directing the landing forces to minimize shock to the aircraft. The aft mounted torque links also act as a tension member during the initial landing stroke. In another embodiment, a damper acts as a tension stop for a soft landing arrangement as well as to dampen bogie motion over bumps with the torque links being separate. (Author), Supersedes PAT-APPL-100 321-79, AD-D006 884.

An apparatus and method for soft recovery of a projectile is disclosed. A deformable element is placed in the path of the projectile, whereby the projectile becomes embedded in the element upon impact therewith. Gravitational or mechanical forces are applied to the combined projectile and deformable element to decelerate the same thereby making recovery possible. (Author), Supersedes PAT-APPL-158 556-80, AD-D007 911.

The overall objective of this Phase I project was to determine the feasibility of a soft landing, hydraulically powered penetrator for deploying seimometers at depths of 30 to 100 meters beneath the surface of the deep-ocean bottom. Seismometers deployed at these depths will be better coupled to the sediment and will be isolated from VLF/ULF noise signals associated with surface waves at the sediment/water interface and from current-induced noise. The primary application of the implantation system will be the deployment of seismometers with increased sensitivity to signals in the VLF/ULF band. These signals may be used in ASW activity, where ease of deployment is a primary consideration. A practical system will also be of interest to the marine seismology community. The primary objectives were to observe the penetration rate capability of a 130-mm-diameter prototype penetrator and to determine the size, logistics and cost of a complete deep-ocean deployment system. A prototype penetrator was fabricated and tested in clay bearing silt and sand. A Phase II proposal for a prototype seismometer deployment system, including cost estimates and deployment requirements, is being submitted. This system is designed to be a compact, self-contained package that can be deployed by ship or aircraft.

The velocity requirements to soft land on either Phobos or Deimos, the small Martian moons, are determined for the 1969 launch opportunity. A single impulse retro and plane change maneuver is applied at periapsis of the hyperbolic trajectory to achieve the desired final orbit about Mars. Less Delta-V is required to attain the orbit of Phobos. This fact, combined with the lower orbital altitude, makes Phobos the preferred target for a soft landing. The minimum Delta-V for a soft landing does not coincide with the minimum injection energy for a ballistic trajectory to Mars, so that a trajectory can be found that maximizes the payload landed on Phobos.

A study was conducted to develop new concepts and procedures for the airdrop of supplies and equipment which would significantly reduce the time and labor required to prepare airdrop loads for airdrop and retrieve them after the drop. A goal of equal importance is the reduction of airdrop malfunctions caused by improper rigging. Study of current rigging designs and procedures identified the tasks that were the most time consuming and the operations that contributed the higher rates of malfunctions. Thirty-two (32) concepts for equipment and procedures were developed which were judged to have sufficient merit to warrant consideration in the search for a system solution.

The 'Door Hinge' rotor, designated Model 540 by the manufacturer, is a two-bladed, semi-rigid type with a flapping hinge and underslung feathering axis, which incorporates a unique pitch-change bearing arrangement (door hinge). All the bearings in the hub assembly are Teflon-lined sleeves; therefore, the hub requires no lubrication. The 'Door Hinge' rotor was mounted on a commercial Model 204B Helicopter. The 204 B is similar to the UH-1B except that it has a longer tail boom to accept a 48-foot rotor blade. The test Objectives were to determine whether the 'Door Hinge' High-Speed Rotor System has advantages in speed and vibration level compared to the 44-foot and 48-foot rotor systems presently utilized in the UH-1 series helicopters. The Model 204B Helicopter with the 'Door Hinge' rotors system installed was flown a total of 5 hours and 35 minutes at gross weights of 7500, 8500, and 9500 pounds. A standard production UH-1B was flown once at a gross weight of 8500 pounds for a comparison of vibration levels and autorotational characteristics. Test results showed that the 'Door Hinge' rotor system offered significant advantages in the reduction of vibration at high speeds compared with rotor systems presently used in the UH-1 series helicopters. The approximate 70-percent increase in rotor inertia made autorotation touchdowns less critical to perform, particularly above gross weights of 8000 pounds. Blade slap noise was significantly reduced at high airspeeds and gross weights. Operational suitability was improved by higher speeds, greater maneuverability, and better and autorotative characteristics.

During Phase I of the program, a study was undertaken to establish the most favorable approach toward producing a wide-angle, infinite depth-of-field, inclined-image plane viewing probe for purposes of simulation. The second phase involved fabrication, test and evaluation of an engineering feasibility model of such a device. This report describes both phases of the program. Previous optical pickups for flight simulators were limited by slant range focus at close approaches to a model. Obtaining closer approaches has important size, cost and versatility advantages in making simulator terrain models and support equipment. Phase I study results indicated the feasibility of producing a 140 deg circular field pickup with full pitch capability and a close approach of 4.1 mm. A preliminary but realistic design was developed and evaluated. The design approach was confirmed by photographing a runway model with a modified 110 deg probe. Other concepts examined that had promise of improving resolution were dual sensor outputs and dual relays. Component trade-offs, simplifications, and techniques were sufficiently developed for the design and fabrication phase of the program to proceed directly.

The document consists of three selected articles concerning recent developments in Soviet space technology, e.g., the physical coupling of the unmanned satellites KOSMOS 186 and KOSMOS 188 in space, the collection of statistical data on solar x-ray flares by the satellite KOSMOS 166 and the soft landing on the surface of Venus by the interplanetory probe, Venus 4. (Author), Edited trans. of Aero-Sport (East Germany) n179 p32, 34-37 1968, by J. Stock.

The report describes the digital program that has been developed to evaluate the orbit navigation and retrograde time prediction modes of the Gemini B computer software. The formulation of the program performs the same functions (in fortran computer language) as the orbit navigation (ONAV) and retrograde time prediction (RTP) modes. In addition, this program provides the capability to determine retrograde times to land at particular landing sites and can be used, in general, for mission planning purposes. (Author)

Surface pressure tests were made on a scale model of the Viking Lander Capsule at Mach number 10 and Reynolds numbers, based on the model aeroshell radius. Angle of attack was varied from -26 to 26 deg. with yaw angles of -5 and -10 included at the capsule estimated trim angle of attack of 11.2 deg. Results show the effect of protuberances representing a camera bump, an antenna, a reaction control system, and other appendages on the base cover pressure distribution. Comparisons with data from another test facility are also presented. (Author), Prepared in cooperation with ARO, Inc., Tullahoma, Tenn. Rept. no. ARO-VKF-TR-72-158.

A test was conducted in the wind tunnel to determine deployment, inflation, and steady-state characteristics of attached inflatable decelerators. Deployments were made at a Mach number of 3.0 at a free-stream dynamic pressure of 120 psf. The mechanically deployed inlet system resulted in successful deployments of the five test models with rapid inflation times of approximately 0.2 sec. The attached decelerators were stable throughout the Mach number range from 2.6 to 4.5 and at angles of attack through 10 deg., Prepared in cooperation with ARO, Inc., Tullahoma, Tenn. Rept. no. ARO-PWT-TR-71-119.

A new procedure for the optimization of branched-path systems is successfully applied to flyback shuttle trajectories. The boundary and transversality conditions are satisfied by three extremals that meet at an arbitrarily chosen branch point. The position of the branch point is then improved, and the cycle repeated. The performance index for the orbiter branch is the weight place in orbit. For the booster-return branch it is the square of the distance between the final point and the landing field. he complete family of trajectories representing the various trade-offs between these two indices is calculated for a problem that specifies the landing field as coinciding with the launch site. The computer program also has the capability of handling down-range landing sites, orbital rendezvous and intercept, and aerodynamic load constraints. (Author)

The report describes work done in image processing using an interactive computer system. Techniques for image differencing are described and examples using images returned from Mars by the Mariner Nine spacecraft are shown. Also described are techniques for stereo image processing. Stereo processing for both conventional camera systems and the Viking 1975 Lander camera system is reviewed. (Author), Report on Stanford Artificial Intelligence Project.

All known space vehicles launched before 1 September 1970, excluding satellites in geocentric or its, are tabulated here. Details are given of mass, size, shape, orbit, time of launch and other useful information. The table is divided into four sections, under the headings heliocentric orbits, orbits in the Earth-Moon system, selenocentric orbits - Earth launch and selenocentric orbits - Moon launch. (Author)

The article discusses some of the problems involved in bringing a winged space apparatus down at a landing site from a circular orbit. It discusses longitudinal and lateral control of the aircraft in the descent process. A system for the automatic control of the space apparatus in the descent process is described, with emphasis on the effect of various disturbances.

Two three-man prototype liferafts were evaluated in Arctic waters off Kodiak Island, Alaska. Surface and core temperatures of each subject were monitored continuously during the 22 hour exposure in the TUL raft and 6 hour exposure in the P-B raft. Each subject wore a different clothing assembly: a NASA full pressure suit, the NASA flight clothing, and the Air Force Anti-exposure suit. None of the clothing assemblies was considered adequate to maintain a person in comfort. No significant biochemical shifts in the blood or urine were found. General tolerance times for a variety of cold water-raft exposures are depicted graphically. (Author)