SAWE Technical Papers

@inproceedings{0850,

title = {850. Automated Method for Calculating Mass Characteristics of Fuel in Tanks at Various Angles of Attack},

author = {E Jacobs and D P Gholson},

url = {https://www.sawe.org/product/paper-0850},

year  = {1970},

date = {1970-05-01},

booktitle = {29th Annual Conference, Washington, D. C., May 4-6},

pages = {29},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Washington, DC},

abstract = {(This paper is taken from a report entitled 'Automated Weight Control' which resulted from Avco's IRAD effort.) An automated process for the calculation of mass properties for fuel volumes is the subject for this paper. The tank shapes are such that they can be approximated by subdividing into tapered boxes with straight line edges. The data are calculated for levels incremented every .25 inches and oriented at any angle of attack. The mass properties consist of total weight, three axis center of gravity and moment of inertia (LB. - IN. 2) and a product of inertia in the X-Z plane. The input consists of coordinates for the tapered box corner points, the Z intercepts for planes oriented at the angle of attack and passing through the lowest and highest corners in the box, the Z intercept for the initial cutting plane, the angle of attack with its tangent plus the tangent for twice the angle of attack, fuel density and an indicator to signal program termination. Special use is made of the prismoidal equation (Reference: SAWE Handbook, Page 4.2.8},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0852,

title = {852. A Surface Integral Method for Computer Calculation of Mass Properties},

author = {A M Messner},

url = {https://www.sawe.org/product/paper-0852},

year  = {1970},

date = {1970-05-01},

booktitle = {29th Annual Conference, Washington, D. C., May 4-6},

pages = {18},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Washington, DC},

abstract = {A computer technique is described for the calculation of weights, moments, and centers of mass of general solids, the surfaces of which are defined in an incremental or digitized manner. The method is based on surface integral formulations and has the advantage of eliminating the need to decompose a given solid into standard geometrical forms. Experience with this technique over the past two years has proven it to be efficient and practical in terms of both computer usage and input-output considerations. The basic computation routine is particularly simple and could be adapted for use on small desk-top computers, although experience has been limited to Fortran implementation on an IBM 360-40 machine. The mathematical formulation is derived from the familiar volume integral definitions through application of Gauss' divergence theorem. Typical of this transformation is the moment equation about the x-axis in rectangular Cartesian coordinates given below. Details are presented for the application of these equations to two classes of solids: solids of revolution and general polyhedrons. Since any solid can be approximated by a polyhedron, this latter approach, theoretically, could be applied to all problems. However, practical input considerations often preclude such an approach unless a digitized surface description is available. In the solid-of-revolution program, direct solutions to the integral equations are presented for a straight-line element description of the cross section of the solid. This has proven to be the simplest input format encountered, and it is one that can be obtained directly from a mechanical digitizer. In the general polyhedron program, numerical integration techniques based on Gauss-Radau coefficients are employed. It has proved advantageous to obtain computer plots of the program outputs for checking results of individual components as well as complete assemblies. Examples of these plots and practical considerations of their use are discussed. Section views are shown for axisymmetric components, together with perspective projections of general polyhedrons with hidden lines eliminated. Experience with these programs to date is discussed and computer requirements, average run times, accuracies, and overall computational efficiencies are described.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0663,

title = {663. Mass Properties by Computerized Building Blocks},

author = {C E Belknap and D W Tucker},

url = {https://www.sawe.org/product/paper-0663},

year  = {1968},

date = {1968-05-01},

booktitle = {27th Annual Conference, New Orleans, Louisiana, May 13-16},

pages = {30},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {New Orleans, Louisiana},

abstract = {A computer program has been developed that affords rapid, accurate mass property data for use by engineering groups in the design evaluation of stability, strength, and vibration characteristics of an aerospace vehicle. 

The program determines the mass properties of a vehicle by a method similar to manual calculation. By the manual method, mass properties of a structure are calculated component by component; the component mass properties are then added to determine the mass characteristics of the complete assembly. In this paper, the geometric shapes, or 'building blocks, ' and associated equations have been programmed for computer calculation. The weight engineer can select shapes of various orientations, add them together to make an assembly, and add the assemblies to obtain the mass properties of a total vehicle. 

The final output of the program includes data that completely define the mass characteristics of a vehicle. These data are weight, center of gravity, moments of inertia, products of inertia, location of principal axes, radius of gyration, and moment of inertia and product of inertia about the principal axes. 

This paper describes a sample computer run with instructions and gives the basic equations formulating the computer program. The program allows the weight engineer to perform other important work while the computer laboratory keypunches and runs the program. Design changescan be made quickly, and mass property data can be keptcurrent with little effort. An average run takes from 40 to 60 sec on an IBM 360 Model 40 computer. 

The program was developed for small aerospace vehicles; however, it has been used for a large space station, a large space antenna ,and an airship envelope. The program can be expanded by adding geometric shapes and associated equations a sneeded.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0664,

title = {664. Transformations and Invariants of the Inertia Tensor},

author = {R L Johnson},

url = {https://www.sawe.org/product/paper-0664},

year  = {1968},

date = {1968-05-01},

booktitle = {27th Annual Conference, New Orleans, Louisiana, May 13-16},

pages = {12},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {New Orleans, Louisiana},

abstract = {The reader who has been required to develop the mass properties of an inclined body has probably discovered that information in this area is scarce and generally discussed too esoterically for the average man. While it is true that a complete understanding of of the theory involved requires a knowledge of tensor analysis and advanced classical mechanics, a background of matrix algebra and trigonometry is sufficient to follow this treatise. 

Starting with basic notions and definitions the direction cosine matrix and its relation to coordinate transformations will be demonstrated. With this development the generation of mass properties of a body around an arbitrary set of coordinate axes is readily accomplished.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0629,

title = {629. Mass Property Equations for a Minimum Weight Control Surface Ballast Design},

author = {S J Myzel},

url = {https://www.sawe.org/product/paper-0629},

year  = {1967},

date = {1967-05-01},

booktitle = {26th Annual Conference, Boston, Massachusetts, May 1-4},

pages = {39},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Boston, Massachusetts},

abstract = {Aerodynamic characteristics and control system performance requirements establish the four desired control surface properties of mass, static moment, product of inertia (P0I) about the control surface hinge line and missile centerline, and moment of inertia (MOI) about the hinge line. 

Normally all four criteria cannot be satisfied. The most important criteria are moment of inertia and product of inertia. These are considered in this paper. MOI and POI requirements are satisfied by incorporating a minimum weight ballast design. 

Before a ballast design is considered, however, it is important that the mass properties of the remaining control surface are accurately known. General equations are presented which yield exact mass properties. 

Ballast is moat efficient in the vicinity of the control surface apex. In this region a triangular wedge-shape ballast is used. General equations are presented which yield all the mass properties and geometry of such ballast with respect to the defined coordinate system. The apex of the ballast is at a fixed control surface location. 

A minimum weight ballast design can be selected from moment of inertia and product of inertia data as a function of variable wedge shape of constant volume. 

Such a selection yields a control surface with minimum ballast weight and a missile with increased performance due to reduced missile weight. Since the mass properties of a control surface can be accurately determined using the equations presented, a decision can readily be made concerning the need for equipment to measure moment of inertia and product of inertia. 

The equations presented are applicable to a variety of problems encountered in weight control analysis and design.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0528,

title = {528. A General Method for the Determination of Principal Axes and Moments of Inertia},

author = {R D Manners},

url = {https://www.sawe.org/product/paper-0528},

year  = {1966},

date = {1966-05-01},

booktitle = {25th Annual Conference, San Diego, California, May 2-5},

pages = {48},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {San Diego, California},

abstract = {Equations describing the principal axes and moments of inertia in two dimensions are developed from basic principles, introducing the concepts of direction cosines and the momental ellipsoid. An extension of these equations leads to the three dimensional case and a general solution of the eigenvalue problem suitable for hand computation. Details are provided on Mohr's construction for the determination of inertias on any plane through the origin of the momental ellipsoid. The application of matrix tensor methods is illustrated by the development of the second order inertia tensor and Mohr's two dimensional representation of inertia. The Appendix contains the completely detailed solution to a three dimensional inertia problem using methods developed in the paper.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0480,

title = {480. Mass Properties Program for the 156-Inch Diameter Solid Propellant Rocket Motor},

author = {R N Cazier and D J Williams},

url = {https://www.sawe.org/product/paper-0480},

year  = {1965},

date = {1965-05-01},

booktitle = {24th Annual Conference, Denver, Colorado, May 17-19},

pages = {51},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Denver, Colorado},

abstract = {On 12 December 1964, the largest, most powerful solid propellant rocket motor ever tested to that date was fired by Thiokol's Wasatch Division for the U.S. Air Force. 

That successful firing of the 156 inch diameter large booster motor verified the accuracy of the techniques and procedures used to determine theoretical and actual mass properties data. This paper describes the analytical procedures used for mass properties predictions and the techniques for obtaining actual weights during the fabrication and test of the 156 inch diameter motor. This motor employed an omniaxial gimbaled nozzle thrust vector control system and attained a thrust level of 1.4 million lb during the 130 sec static test firing. It weighed 772,216 lb, was 78 ft in length, and had a mass fraction of 0.894. 

Mass properties analyses were performed utilizing a new computer program (1) to insure that contractual incentive requirements were met, (2) to support weight versus cost tradeoff studies, and (3) to provide weight control of components and assemblies. Motor weight was predicted to within 0.6 percent of the measured weight. 

Methods for determination of actual mass properties measurements utilized a unique 100,000 lb capacity hook, an advanced storage and transporting trailer and a computer calculated correction table to translate the weighing system indications to weight. The corrective procedure represents a considerable improvement over the linear or additive correction factors normally used. 

The handling techniques, linear measurements, and methods used to determine the longitudinal coordinates of the centers-of-gravity for the nozzle and loaded case segments are discussed. 

Results of the program have demonstrated that (1) an efficient mass properties program can be conducted at minimum cost; (2) there is a need for positive vendor mass properties control programs; (3) computer techniques reduce costs when applied to the generation of mass properties data; and (4) the weighing of motor segments ranging up to 400,000 pounds is feasible.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0496,

title = {496. Mass Moment of Inertia Computer Program Used in Optimizing a Gravity Gradient System},

author = {L R Zanchettin},

url = {https://www.sawe.org/product/paper-0496},

year  = {1965},

date = {1965-05-01},

booktitle = {24th Annual Conference, Denver, Colorado, May 17-19},

pages = {22},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Denver, Colorado},

abstract = {A wide variety of avionic devices and techniques, expected to have broad application to future meteorological, communication, navigation and military systems, will be evaluated on NASA's Applications Technology Satellite. A Gravity Gradient Stabilization System constitutes one of the primary experiments to be flown on ATS. 

There are three systems to be launched in the following sequence by Atlas-Agena boosters: 

1. Medium Altitude Orbit, Gravity Gradient Stabilized - One Vehicle 

2. Synchronous Orbit, Spin-Stabilized - Two Vehicles. 

3. Synchronous Orbit, Gravity Gradient Stabilized Satellite - Two Vehicles 

The primary purpose of the Medium Altitude Satellite will be to conduct a wide range of gravity gradient experiments to verify analytical models heretofore investigated only by computer studies. 

A digital computer program has been constructed for rapid calculations of mass moments of inertia, which are changed by deploying booms (with tip masses) at various attitudes. The description of this computer program and gravity gradient stabilization are the main object of this presentation. 

Gravity Gradient Stabilization offers a means of significantly improving the reliability of long-life earth satellites. Gravity Gradient Stabilization is based on the principle that any earth satellite will align its long axis, or axis of minimum moment of inertia, with the local vertical. By properly configuring a satellite, it is possible to make the satellite point to the earth. Since a long slender shape is desired but is inconvenient to launch, this shape is achieved after launch by deploying long booms with tip masses at the end. 

The ATS Gravity Gradient Experiment requires that the inertial properties of the satellite be varied during orbit by 'scissoring' the booms. A computer program has been set up in FORTRAN IV for use with the I.B.M. 7094 computer to compute these inertias. The program has been set up so that the inputs are direction cosines, boom lengths, tip masses, rod inertias, and pivot point locations. Previous programs used required detail center of gravity locations for each item that was moved (for example the Nimbus Solar Paddle movement). 

The main advantage of this computer program is its efficiency. Also, it should point out the fact that there are probably many ways which the computer can be used to our advantage that have not as yet been tried.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0498,

title = {498. Introduction to and Remarks About the Inertia Panel},

author = {D O Nevinger},

url = {https://www.sawe.org/product/paper-0498},

year  = {1965},

date = {1965-05-01},

booktitle = {24th Annual Conference, Denver, Colorado, May 17-19},

pages = {4},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Denver, Colorado},

abstract = {Inertia is defined as 'a property manifested by all matter, representing the resistance to any alteration in its state of motion.' This panel is concerned with the calculation and measurement of this resistance. The Panel is orientated to the field of space and missiles. Many papers of inertia have been made to combine them into a panel presentation. The Panel has been arranged to cover aspects from computation to actual measuring systems. 

The Panel consists of the following Technical Papers: 

T.P. $#$499 A Rapid Inertia Estimation for Space Boosters by George R. Welsby of Martin Marietta, Denver. 

T.P. $#$ 500 

T. P. $#$501 Have been cancelled. 

T.P. $#$502 Computer Analysis of Dynamics Mass Characteristics by B. C. Spencer of Douglas Aircraft Company Inc. 

T.P. $#$503 Selection of Techniques for Measurement of Mass Moment of Inertia by E. C. Harris of Douglas Aircraft Co., Inc. 

T.P. $#$504 Determining Moments of Inertia by Using Period Decay Rate of a Mechanical Oscillating System by L.M. Majeski of SPACO Inc. and G. T. Carpenter of NASA-Marshall Space Flight Center. 

T.P. $#$505 An Approach to an Automated System for Determination of Mass Moment of Inertia by Claude S. Bridges, Jr. of SPACO, Inc., Lewis E. Booker of SPACO, Inc., and G. T. Carpenter of NASA-Marshall Space Flight Center. 

The Panel will be divided into two parts. The first part consists of each panel member presenting his paper and after the 'coffee break' the second part will be devoted to a question and answer period. 

This is part of a coordinated project to collect and publish a handbook on the subject of Inertia that will benefit both the individual weight engineer and the Society of Aeronautical Weight Engineers, Inc. 

The handbook will cover all fields with the incorporation of papers written for past conferences. A list of these papers are attached and credit will be given to all papers used. 

In order to make the handbook a success, each society member is encouraged to participate by sending any literature he has in his possession concerning the subject matter of 'Inertia.' Remember, this handbook will be representative of our organization and we want it to be the best. 

Any correspondence should be directed to the National Executive Secretary. Our present time limit, for the publication, is one year.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0499,

title = {499. A Rapid Inertia Estimating Method},

author = {G R Welsby},

url = {https://www.sawe.org/product/paper-0499},

year  = {1965},

date = {1965-05-01},

booktitle = {24th Annual Conference, Denver, Colorado, May 17-19},

pages = {15},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Denver, Colorado},

abstract = {During the advanced design phase and in project work also, it often becomes necessary to rapidly but accurately estimate booster vehicle mass moment of inertia. This paper presents the derivation of equations and a method by which this may be done. The rapid inertia calculating equations are not limited to booster vehicles, but apply to any system for calculating inertia. Since the mass moment of inertia of any system can be derived from I= ∑▒I_(o ) +∑▒〖wd〗^2 , the transfer equation (〖wd〗^2) is simplified without sacrificing any accuracy, and Io term is obtained from graphs. It has been proven that in most cases the Io term contributes much less to the total inertia than does the transfer term, so that small errors in estimating Io can be accepted. However, errors in calculating the transfer cannot be tolerated. 

In using the rapid inertia estimating method, more time can be saved when estimating inertia for mass systems with more than four masses if the equations in Table 1 can be combined. 

In any inertia calculating or estimating method the center of gravity is usually the first item to be calculated. Only now, with the rapid inertia calculating method, it can be determined last or not at all! Nevertheless, when the center of gravity has to be determined, it absorbs the same amount of time independent of inertia calculating method.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0502,

title = {502. Computer Analysis of Dynamic Mass Characteristics},

author = {B C Spencer},

url = {https://www.sawe.org/product/paper-0502},

year  = {1965},

date = {1965-05-01},

booktitle = {24th Annual Conference, Denver, Colorado, May 17-19},

pages = {29},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Denver, Colorado},

abstract = {This paper presents a discussion of a generalized method of computing in-flight mass characteristics, such as mass, center of gravity, moment of inertia about the center of gravity and about the principal axes, and principal angles. The method provides mass characteristics for all times during vehicle flight, and utilizes a data processing system having the IBM 7094 capability. 

Emphasis is given to the philosophy, methods, capabilities and uses of this type of computing program. 

The mechanics of programming, and the mathematics involved since they are basic in nature, will be mentioned by not emphasized. 

The versatile nature of this type program and its application to any vehicle that moves will be stressed.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0436,

title = {436. Fluid Angular Momentum},

author = {F H Wetmore},

url = {https://www.sawe.org/product/paper-0436},

year  = {1964},

date = {1964-05-01},

booktitle = {23rd National Conference / Sheraton, Dallas Hotel, Southland Center, Dallas, Texas May 18-21},

pages = {12},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Dallas, Texas},

abstract = {The object of this paper is to define angular momentum discuss a method of computing it, explain how it can be controlled, and present the role that the weight engineer can perform in the analysis. Angular momentum is the force produced by the circulation of a fluid about an axis in a closed loop system. This force will influence a space vehicle to rotate about an axis and therefore it must be controlled. 

Equations are derived for the purpose of computing angular momentum. The location of the fluid with respect to the axis, the distance the fluid travels about an axis, the rate of flow of the fluid, the direction the fluid travels about the axis, and the acceleration due to gravity are then necessary parameters which are consider to derive the equations . 

The techniques employed by the weight engineer with regards to weight, center of gravity and moment of inertia analysis are similar to the techniques require for the angular momentum analysis. It is therefore significant that the weight engineer is fully equipped to assume the responsibility of this analysis. 

In view of the relationship that the control of angular momentum will have with the weight and center of gravity of the vehicle, it will be a valuable asset to a program if the weight engineer can satisfy the angular momentum criteria at a minimum weight.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0457,

title = {457. Weight Moment of Inertia Nomographs},

author = {R R Emery and R F Lewis},

url = {https://www.sawe.org/product/paper-0457},

year  = {1964},

date = {1964-05-01},

booktitle = {23rd National Conference / Sheraton, Dallas Hotel, Southland Center, Dallas, Texas May 18-21},

pages = {27},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Dallas, Texas},

abstract = {Seventeen nomographs for the calculation of weight moments of inertia for various shapes have been developed. In a random sample of 373 calculations an accuracy of plus or minus 5 percent was achieved for 93 percent of the calculations. The theory of additive and 'N' nomographs is briefly outlined to facilitate the preparation of more specialized charts.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0386,

title = {386. A Graphical Technique for Calculating Time-Changing Moments of Inertia},

author = {B R Kendall},

url = {https://www.sawe.org/product/paper-0386},

year  = {1963},

date = {1963-05-01},

booktitle = {22nd National Conference, St. Louis, Missouri, April 29 - May 2},

pages = {24},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {St. Louis, Missouri},

abstract = {This paper was presented at the Twenty-second Annual National Conference of the Society of Aeronautical Weight Engineers at St. Louis, Missouri, April 29-May 1, 1963. In this age of complex missiles and rapid technological advances the weight man finds himself continually facing new and more complex problems. The Emerson Electric Weight Department was recently faced with such a problem. 

The problem involved the weight moment of inertia of a propellant of complex design at any instant of burning during a period ranging from ignition to burn-out. To solve this problem we evaluated different techniques of approach in order to choose the one which combined accuracy with flexibility and low complexity. The techniques evaluated include curve filling and special formulae, extended use of standard formulae, scaling curves with the polar compensating planimeter, and the 'graphical summator'. 

The results of the evaluation proved the 'graphical summator' to be the only technique that combined high accuracy and flexibility with only a moderate degree of complexity. For this reason the 'graphical summator' was the technique utilized for the calculations. 

This graphical technique exploits the basic definition of areas and moments by the use of finite summations as accurate approximations to infinitesimal summations, or integrations. The 'graphical summator' is a polar coordinate grid in which the radial lines have a fixed angular spacing. Each polar cell will have an area and inertia that depends only upon its radial distance from the pole. A weighting factor for inertia is determined for each radial increment between polar cells. In actual use the summator is placed over the desired shape with the pole of the summator coincident with the axis of rotation. The cells falling under the desired curves are summed allowing for partial occultation of the cells. This sum is multiplied by the appropriate weighting factor and the inertia obtained. 

This technique can be adapted to many tasks requiring the calculation of area, volume, weight or moment of inertia. Only after weight engineers throughout the industry utilize, adapt and improve on the 'graphical summator' technique will its full potential is realized.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0313,

title = {313. Mass Moment of Inertia Estimation Methods - Manned Aircraft},

author = {D P Marsh},

url = {https://www.sawe.org/product/paper-0313},

year  = {1962},

date = {1962-05-01},

booktitle = {21st National Conference, Seattle, Washington, May 14-17},

pages = {35},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Seattle, Washington},

abstract = {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. The purpose of this paper is to furnish the engineer with a method for rapidly and accurately estimating the moment of inertia of manned aircraft during the advanced design period. Such inertias are needed so that dynamic load and stability characteristics of the aircraft may be evaluated. 

To evolve a method which would not be limited to any particular type of aircraft, empirical data were gathered from many types of combat and transport aircraft and combined with the results of a mass distribution parametric study. By this method, the moment of inertia for a complete aircraft can be computed with a total expended time of about three man hours. The prerequisite data needed are a group weight and balance statement, a three view drawing, and some knowledge of the design characteristics of the airplane. 

As with all procedures and methods based on empirical data, extrapolations by this method are limited to aircraft within the present state of the art. As advancements in the state of the art occur which significantly affect weight distribution, the method should be altered accordingly.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0078A,

title = {78A. Empirical Formulae for Radii of Gyration of Aircraft - Revision A},

author = {D Garcia},

year  = {1962},

date = {1962-05-01},

booktitle = {21st National Conference, Seattle, Washington, May 14-17},

pages = {-1},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Seattle, Washington},

abstract = {At the 1961 Society of Aeronautical Weight Engineers National Conference, the Long Island Chapter recommended that SAWE Paper No. 78, 'Empirical Formulae for Radii of Gyration of Aircraft,' dated l952, be revised by incorporating data generated during the past decade. The project was approved by the Board of Directors and the Long Island Chapter volunteered to undertake the task. Dr. J.P. Chawla, author of the original report (Reference 1), granted permission for the proposed revision. 

Mr. D'Amaso Garcia, SAWE Long Island Chapter 1961 Vice-chairman, was appointed Project Chairman, whereupon he initiated an industry survey. A total of 39 requests for data were distributed, and the 20 replies received added information on 73 aircraft for incorporation in the report.},

note = {Paper Missing},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0214,

title = {214. A Unique Solution to the Moment of Inertia Problem},

author = {J Skogh},

url = {https://www.sawe.org/product/paper-0214},

year  = {1959},

date = {1959-05-01},

booktitle = {18th National Conference, Henry Grady Hotel, Atlanta, Georgia, May 18-21},

pages = {51},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Atlanta, Georgia},

abstract = {A test facility for determining inertia and geometric properties of rotational symmetrical specimens, such as re-entry bodies, is described. While most of the properties are obtained in an orthodox way, a new method for determining the inclination at the principal axis is used, employing freedom torsional pendulum with an accelerometer that is caused by an inclined principal axis. 

Equations used in analyzing the test data are derived in four appendices},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0229,

title = {229. The Application of Digital Computers to the Calculation of Moments of Inertia of Aircraft Wings},

author = {D E Dudenhoefer},

url = {https://www.sawe.org/product/paper-0229},

year  = {1959},

date = {1959-05-01},

booktitle = {18th National Conference, Henry Grady Hotel, Atlanta, Georgia, May 18-21},

pages = {32},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Atlanta, Georgia},

abstract = {In order to demonstrate the use of computers in this paper, the terminology of moments of inertia is first defined, and then a specific example is outlined. The need for moments of inertia is described, and sectioning a wing for moment of inertia calculation is demonstrated. Next, the application of this problem to high speed digital computer use is demonstrated. A completely automatic method of moment of inertia calculation was developed. Finally, a brief cost analysis is included.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0165,

title = {165. Moments of Inertia and Centers of Gravity by the Mass Distribution Method},

author = {L W Dhanes},

url = {https://www.sawe.org/product/paper-0165},

year  = {1958},

date = {1958-05-01},

booktitle = {17th Annual Conference, Belmont Plaza Hotel, New York, New York, May 19-22},

pages = {16},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {New York, New York},

abstract = {With the advent and application of large memory high speed digital computing equipment it is now possible and advantageous to extend the philosophy of computing techniques. One region of concern has been the moment of inertia and center of gravity calculation. This report contains a method of obtaining moments of inertia and centers of gravity from the weight or mass distributions, thereby, eliminating the necessity of computing the centroid moments of inertia for individual parts. 

Up to the present time no successful machine technique has been discovered for this purpose. It appears that too much emphasis has been placed on the old hand computing methods. This report presents the mass distribution method and will endeavor to justify this method on both convenience and accuracy.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{0184,

title = {184. Moments of Inertia of Liquids in Cylindrical Tanks},

author = {T J Harvey},

url = {https://www.sawe.org/product/paper-0184},

year  = {1958},

date = {1958-05-01},

booktitle = {17th Annual Conference, Belmont Plaza Hotel, New York, New York, May 19-22},

pages = {34},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {New York, New York},

abstract = {A method is presented for calculation of the mass and mass moment of inertia of a liquid in a circular cylindrical tank. The tank is assumed to be similar to that of a vertically rising ballistic missile. That is, the acceleration is assumed to be parallel to the tank's longitudinal axis. It is found that for the moment of inertia to be of use, the method of treating the liquid must be coordinated between the Weights Department and the Dynamics Department. A solution is found which greatly simplifies the efforts of the weights and dynamics groups, while giving proper consideration to the physical effects involved.},

keywords = {05. Inertia Calculations},

pubstate = {published},

tppubtype = {inproceedings}

}