%0 Conference Paper %B 34th Annual Conference, Seattle, Washington, May 5-7 %D 1975 %T 1046. Use of Statistics in the Management of Mass Properties %A Erhard, M P %K 26. Weight Growth %X A recently developed method has proven useful in efficient management of properties tasks. The method is a statistical analysis for determining potential weight growth. Using data of estimated, calculated, and actual weights from past designs for similar end items, the percent differences between estimated and actual weights and calculated and actual weights we determined and standard deviations calculated. Using tolerance factors available from statistical tables, a family of curves is constructed for each end item showing weight potential growth versus time. The effects of potential weight growth on the useful load is then obtained. It can be determined if the useful load margin is adequate, if changes to the vehicle or software are required, and if the vehicle needs to be weighed. This method has the advantage of showing how the weight growth bf an end item varies with time. %B 34th Annual Conference, Seattle, Washington, May 5-7 %I Society of Allied Weight Engineers, Inc. %C Seattle, Washington %P 15 %8 5/5/75 %G eng %U https://www.sawe.org/papers/1046/buy %9 26. WEIGHT GROWTH %M 1046 %1 Non-Member Price: $20.00; Member Price: $10.00 Members: First 10 product downloads are Free. %2 10.00 %3 20 %4 SAWE1046 %0 Conference Paper %B 26th Annual Conference, Boston, Massachusetts, May 1-4 %D 1967 %T 644. Government-Industry Committee Workshop Panel Session %A Erhard, M P %K 30. Miscellaneous %X The primary purpose of the Government-Industry Workshop at the 26th Annual International Conference of the Society of Aeronautical Weight Engineers in May 1967 (Boston, Massachusetts), is to facilitate communication between industry mass properties personnel and their government counterparts. Mass properties problems will be discussed and either resolved or noted for further study by the Government-Industry Committee. The Workshop will be convened on Tuesday afternoon, May 2, in the Independence Room of the Boston-Sheraton Hotel. The workshop with each major system having its own panel is new this year. This replaces the Government-Industry meeting which covered everything from space to hipbuilding in one general session. The Workshop will have five panels covering the following major systems: 1. Missiles and Space Vehicles 2. Marine 3. Commercial Aircraft 4. Military Aircraft 5. Components and Equipment %B 26th Annual Conference, Boston, Massachusetts, May 1-4 %I Society of Allied Weight Engineers, Inc. %C Boston, Massachusetts %P 16 %8 5/1/67 %G eng %U https://www.sawe.org/papers/0644/buy %9 30. MISCELLANEOUS %M 0644 %1 Non-Member Price: $20.00; Member Price: $10.00 Members: First 10 product downloads are Free. %2 10.00 %3 20 %4 SAWE0644 %0 Conference Paper %B 21st National Conference, Seattle, Washington, May 14-17 %D 1962 %T 362. A Method of Using Cryogenic Propellants to Calibrate Space Vehicle Tanks %A Erhard, M P %A Simko, T %K 24. Weight Engineering - System Design %X This paper was presented at the Twenty-first Annual National Conference of the Society of Aeronautical Weight Engineers at Seattle, Washington, May 14-17, 1962. This paper presents a new technique for capacity calibration of space-vehicle cryogenic-propellant tanks. This new method, which uses cryogenic propellants instead of water as the calibration fluid, is being developed for the Saturn S-IV Stage Vehicle. This technique results in greater accuracy than that of the traditional water calibration system, which loses accuracy because of the need for extrapolating to cryogenic temperatures. The cryogenic calibration technique provides an end-to-end calibration of the propellant utilization and loading sensor against the accurately measured propellant mass. The calibration begins with the vehicle in the static test and calibration stand. First, the vehicle is protected from the indeterminate tares of ice formation and wind gusts by an environmentally controlled boot immediately surrounding the vehicle, and by a canvas wind shield attached to the test stand. The actual calibration is performed by filling and draining each propellant separately. At previously-determined intervals during the drain, the mass of propellant is measured by a test stand weighing system. Simultaneously, the propellant mass sensor (capacitance probe) signal output and propellant density and volume parameters are recorded. The weigh system output is corrected for load cell and measuring circuit non-linearity, recorder drift, air buoyancy, and such tare weights as umbilical connections, weigh ring weight, and dry vehicle weight. These data result in a propellant mass sensor calibration curve at the calibration conditions. %B 21st National Conference, Seattle, Washington, May 14-17 %I Society of Allied Weight Engineers, Inc. %C Seattle, Washington %P 12 %8 5/14/62 %G eng %U https://www.sawe.org/papers/0362/buy %9 24. WEIGHT ENGINEERING - SYSTEM DESIGN %M 0362 %1 Non-Member Price: $20.00; Member Price: $10.00 Members: First 10 product downloads are Free. %2 10.00 %3 20 %4 SAWE0362 %0 Conference Paper %B 18th National Conference, Henry Grady Hotel, Atlanta, Georgia, May 18-21 %D 1959 %T 215. Liquid Propellant Loading Techniques %A Erhard, M P %K 02. Aircraft Loading - Payload %X This paper discusses the need and methods for accurate determination amount of loaded propellant. This first method loads a constant volume of liquid oxygen and varies the fuel volume as a function of propellant densities with data for liquid oxygen and RP-1 propellants. Accuracy requirements for this system were stringent, being 1/4 per cent for everything except fuel density, which was 1/20 percent. The second method is based upon liquid oxygen density is measured in this system by barometric pressure. Problems in determining the density of liquid oxygen by other methods is discussed. In particular data is presented to verify the early work on liquid oxygen density measurements. Problems of proper tank vent sizing and the relationship to the barometric-density method are shown. The third method is based upon development of fuel density tester using a fully submerged hydrometer constructed of Vycor glass which requires no temperature correction. The forth method is based upon liquid oxygen volume measurement where the oxygen tanks are calibrated with water, and pre-determined corrections are made to obtain the true volume of liquid oxygen at firing time. The final method discussed is fuel volume measurement using a volumetric flow meter. %B 18th National Conference, Henry Grady Hotel, Atlanta, Georgia, May 18-21 %I Society of Allied Weight Engineers, Inc. %C Atlanta, Georgia %P 38 %8 5/18/59 %G eng %U https://www.sawe.org/papers/0215/buy %9 2. AIRCRAFT LOADING - PAYLOAD %M 0215 %1 Non-Member Price: $20.00; Member Price: $10.00 Members: First 10 product downloads are Free. %2 10.00 %3 20 %4 SAWE0215