SAWE Technical Papers

950. A Parametric Weights Study of a Composite Material Prop/Rotor Blade

Wisniewski, J S

In: 32nd Annual Conference, London, England, June 25-27, pp. 15, Society of Allied Weight Engineers, Inc., London, England, 1973.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

983. Advanced Design Mass Property Estimates by Detail Weight Calculations (A Case for the Rhoving Mass Properties Engineer)

Henderson, T E

In: 32nd Annual Conference, London, England, June 25-27, pp. 9, Society of Allied Weight Engineers, Inc., London, England, 1973.

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914. Rotary Wing Head Weight Prediction

Swan, R H

In: 31st Annual Conference, Atlanta, Georgia, May 22-25, pp. 17, Society of Allied Weight Engineers, Inc., Atlanta, Georgia, 1972.

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934. Advanced Design Weight Prediction - Passive Thermal Protection Systems

Roland, H L

In: 31st Annual Conference, Atlanta, Georgia, May 22-25, pp. 18, Society of Allied Weight Engineers, Inc., Atlanta, Georgia, 1972.

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935. Weight Estimation of Hydraulic Secondary Power System

Kaneshiro, R S

In: 31st Annual Conference, Atlanta, Georgia, May 22-25, pp. 68, Society of Allied Weight Engineers, Inc., Atlanta, Georgia, 1972.

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812. A Parametric Approach to Estimating Weights of Surface Control Systems of Combat and Transport Aircraft

Cate, Dudley M

In: 28th Annual Conference, San Francisco, California, May 5-8, pp. 27, Society of Allied Weight Engineers, Inc., San Francisco, California, 1969.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

@inproceedings{0812,

title = {812. A Parametric Approach to Estimating Weights of Surface Control Systems of Combat and Transport Aircraft},

author = {Dudley M Cate},

url = {https://www.sawe.org/product/paper-0812},

year  = {1969},

date = {1969-05-01},

booktitle = {28th Annual Conference, San Francisco, California, May 5-8},

pages = {27},

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

address = {San Francisco, California},

abstract = {This paper presents methods for estimating the weights of surface control systems for two major categories of aircraft: modern transonic and supersonic combat-type designs, and subsonic transport-type designs having hydraulically powered lateral, longitudinal, and directional controls. The methods are parametric in nature and are intended for use primarily during preliminary design. While they must be considered to have only 'ballpark' accuracy, it is felt that they will make it possible to avoid the large errors in Surface Controls Group estimates that have sometimes occurred in the past. The approach taken in developing the methods is to define a separate method, or group of methods, for each different type of control system - one group for the maneuvering systems controls (aileron controls, elevator controls, etc.), one for the trailing edge flap controls, etc. Moreover, each method takes into account the characteristics of the particular system as well as those of the overall aircraft. Application of the methods is illustrated by a sample calculation performed on an existing aircraft design, and the results are compared with the corresponding actual weights. An appendix to the paper defines some approximate relationships between the nature of several maneuvering controls system design characteristics and such overall aircraft parameters as design gross weight and maximum speed; these relationships will be useful to the weight engineer in making estimates during the preliminary phases of aircraft design.},

keywords = {25. Weight Engineering - System Estimation},

pubstate = {published},

tppubtype = {inproceedings}

}

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684. A Weight Comparison of Various Small Vehicle Recovery Systems

Nevinger, D O

In: 27th Annual Conference, New Orleans, Louisiana, May 13-16, pp. 20, Society of Allied Weight Engineers, Inc., New Orleans, Louisiana, 1968.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

@inproceedings{0684,

title = {684. A Weight Comparison of Various Small Vehicle Recovery Systems},

author = {D O Nevinger},

url = {https://www.sawe.org/product/paper-0684},

year  = {1968},

date = {1968-05-01},

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

pages = {20},

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

address = {New Orleans, Louisiana},

abstract = {Since the inception of target vehicles, recovery of the vehicle after a flight has been a major element in the cost effectiveness of the system. Extensive target re-use has been possible through use of proven recovery systems. This paper does not intend to encompass all the various types of recovery systems since their number is too many. The various systems that are covered are either being used or under study by the Ryan Aeronautical Company, 

Table 1 lists the various systems, advantages, disadvantages and associated weights. The weights of system are expressed in percentages of recovered weight. This basic percentage has been proven to be reliable for a 'first cut' estimation. The advantages and disadvantages use the Ground Impact Parachute Recovery System as a base point for comparisons. 

For the selection of suitable system consideration is given to more than just the weight and volume aspect of each system. Other factors involved are the use of a recovery vehicle, cost, development time, terrain for recovery,etc. 

For target vehicles, other than the Precision Landing System, the recovery system forms an integral part of the aft portion of the fuselage. This concept allows for ease of deployment and packing. There is no weight allowance for the electronic or electrical portion of the recovery system as the basic target system can be utilized. 

For detail design data on parachute systems it is recommended that 'Perform-nce of and Design Criteria for Deployable Aerodynamic Deceleration' (Ref 1) be used.},

keywords = {25. Weight Engineering - System Estimation},

pubstate = {published},

tppubtype = {inproceedings}

}

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446. Weight Control and Estimating Techniques for Small Electronic Units

Welfer, R C

In: 23rd National Conference / Sheraton, Dallas Hotel, Southland Center, Dallas, Texas May 18-21, pp. 17, Society of Allied Weight Engineers, Inc., Dallas, Texas, 1964.

Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

447. Glide Slope Receivers, Electronic Weight Estimation by Multiple Correlation

Gardinier, V E

In: 23rd National Conference / Sheraton, Dallas Hotel, Southland Center, Dallas, Texas May 18-21, pp. 23, Society of Allied Weight Engineers, Inc., Dallas, Texas, 1964.

Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

413. A Weight Estimation Procedure for Voice Communication Systems

Gardinier, V E

In: 22nd National Conference, St. Louis, Missouri, April 29 - May 2, pp. 79, Society of Allied Weight Engineers, Inc., St. Louis, Missouri, 1963.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

322. Wire Weight Estimating

Reffalt, S D

In: 21st National Conference, Seattle, Washington, May 14-17, pp. 32, Society of Allied Weight Engineers, Inc., Seattle, Washington, 1962.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

@inproceedings{0322,

title = {322. Wire Weight Estimating},

author = {S D Reffalt},

url = {https://www.sawe.org/product/paper-0322},

year  = {1962},

date = {1962-05-01},

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

pages = {32},

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 provide a method of reducing the number of unsolved mysteries in wire weight predictions that have existed within the missile industry. The present method is specifically designed for use on hardware programs, but can be applied to advanced design programs with some reservations. 

Mathematical and physical analyses were used in the preparation of Wire Weight Estimating to determine wire weights. Only qualified weights personnel were used in determining actual measurements to validate values presented in this paper. 

For this study, various wire gages and insulations were used, ranging in size from 0 to 20 gage for both shielded and unshielded wires. Miscellaneous wire bundles were tightly tied in accordance with standard installation procedures to obtain circumference measurements. The actual weight per foot of the bundles was then compared to the respective measured circumferences. These circumferences versus weight comparisons were then tabulated and plotted on graphs. These graphs were surprisingly consistent for all of the weights and circumference comparisons made. The individual graphs were then superimposed to derive a single weight estimating curve. Ten or larger gage wire does not fall entirely within the span of the weight estimating curve. However, small amounts of this wire, (20% or less of the bundle end area) could be used within a bundle and the results proved satisfactory. 

The method presented has been used to calculate weights with a +/- 6% variation of the actual weight. This variation was strictly dependent on the detail and accuracy with which the estimator worked. A definite knowledge of wire types being evaluated can improve the accuracy and minimize the effort in wire weight estimating. Accurate wire length readings should be strongly emphasized. This length is the factor used in multiplying the established circumference unit weight per foot to determine the total wire weight.},

keywords = {25. Weight Engineering - System Estimation},

pubstate = {published},

tppubtype = {inproceedings}

}

Close

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 provide a method of reducing the number of unsolved mysteries in wire weight predictions that have existed within the missile industry. The present method is specifically designed for use on hardware programs, but can be applied to advanced design programs with some reservations.
Mathematical and physical analyses were used in the preparation of Wire Weight Estimating to determine wire weights. Only qualified weights personnel were used in determining actual measurements to validate values presented in this paper.
For this study, various wire gages and insulations were used, ranging in size from 0 to 20 gage for both shielded and unshielded wires. Miscellaneous wire bundles were tightly tied in accordance with standard installation procedures to obtain circumference measurements. The actual weight per foot of the bundles was then compared to the respective measured circumferences. These circumferences versus weight comparisons were then tabulated and plotted on graphs. These graphs were surprisingly consistent for all of the weights and circumference comparisons made. The individual graphs were then superimposed to derive a single weight estimating curve. Ten or larger gage wire does not fall entirely within the span of the weight estimating curve. However, small amounts of this wire, (20% or less of the bundle end area) could be used within a bundle and the results proved satisfactory.
The method presented has been used to calculate weights with a +/- 6% variation of the actual weight. This variation was strictly dependent on the detail and accuracy with which the estimator worked. A definite knowledge of wire types being evaluated can improve the accuracy and minimize the effort in wire weight estimating. Accurate wire length readings should be strongly emphasized. This length is the factor used in multiplying the established circumference unit weight per foot to determine the total wire weight.

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324. Fuel Cell Power Systems Weight Analysis

Thielman, J M

In: 21st National Conference, Seattle, Washington, May 14-17, pp. 28, Society of Allied Weight Engineers, Inc., Seattle, Washington, 1962.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

@inproceedings{0324,

title = {324. Fuel Cell Power Systems Weight Analysis},

author = {J M Thielman},

url = {https://www.sawe.org/product/paper-0324},

year  = {1962},

date = {1962-05-01},

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

pages = {28},

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 weight of electrochemical fuel cell systems is an important consideration, especially if these systems are to be used as secondary power sources for space vehicles. Fuel cells appear attractive in space vehicle applications because, theoretically, they can convert chemical energy to electricity with high efficiency and good reliability under space flight environment. In this paper, fuel cell systems are weight-analyzed, and a method of estimating their weight is presented. This method is based on values of pertinent weight-influencing parameters (power, time, current density, operating voltage, and cell spacing). 

The two most promising types of fuel cells for use in space appears to be hydrogen oxygen (hydrox) cells using aqueous potassium hydroxide electrolyte, and hydrox cells employing an ion-exchange membrane as the electrolyte. The following components are generally required in these systems: fuel cell generator, stored reactant and tanks, plumbing and heat exchanger, and system supports. Methods are presented for determining weight of each of these components, and these weights are summed to obtain a system weight. 

 The weight predication method reveals that a weight-trade must be accomplished between fuel cell generator and stored reactant to attain a minimum system weight. Minimum system weight occurs only when operating voltage is at an optimum value. A voltage optimization method is outlined and used to compute minimum system weights. These results are presented graphically as a function of power and time. Hydrox fuel cell systems are then compared to silicon solar cell systems, battery systems, and a regenerative fuel cell system on a weight basis. This comparison shows that lightweight hydrox fuel cells may compare favorably for operating times in the range from about one hour to one week.},

keywords = {25. Weight Engineering - System Estimation},

pubstate = {published},

tppubtype = {inproceedings}

}

Close

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 weight of electrochemical fuel cell systems is an important consideration, especially if these systems are to be used as secondary power sources for space vehicles. Fuel cells appear attractive in space vehicle applications because, theoretically, they can convert chemical energy to electricity with high efficiency and good reliability under space flight environment. In this paper, fuel cell systems are weight-analyzed, and a method of estimating their weight is presented. This method is based on values of pertinent weight-influencing parameters (power, time, current density, operating voltage, and cell spacing).
The two most promising types of fuel cells for use in space appears to be hydrogen oxygen (hydrox) cells using aqueous potassium hydroxide electrolyte, and hydrox cells employing an ion-exchange membrane as the electrolyte. The following components are generally required in these systems: fuel cell generator, stored reactant and tanks, plumbing and heat exchanger, and system supports. Methods are presented for determining weight of each of these components, and these weights are summed to obtain a system weight.
The weight predication method reveals that a weight-trade must be accomplished between fuel cell generator and stored reactant to attain a minimum system weight. Minimum system weight occurs only when operating voltage is at an optimum value. A voltage optimization method is outlined and used to compute minimum system weights. These results are presented graphically as a function of power and time. Hydrox fuel cell systems are then compared to silicon solar cell systems, battery systems, and a regenerative fuel cell system on a weight basis. This comparison shows that lightweight hydrox fuel cells may compare favorably for operating times in the range from about one hour to one week.

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326. An Approach to Environmental Control System Weight Estimation in Advanced Design

Frahm, J R; Harris, J B

In: 21st National Conference, Seattle, Washington, May 14-17, pp. 80, Society of Allied Weight Engineers, Inc., Seattle, Washington, 1962.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

@inproceedings{0326,

title = {326. An Approach to Environmental Control System Weight Estimation in Advanced Design},

author = {J R Frahm and J B Harris},

url = {https://www.sawe.org/product/paper-0326},

year  = {1962},

date = {1962-05-01},

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

pages = {80},

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. This paper presents a rational, semi analytical approach to the estimation of the weight of a manned spacecraft environmental control system. The presentation is limited to the orbit phase requirements of an early capability space laboratory. Such a vehicle might be designed for a two to six man crew and for a 100 to 300 n mi earth orbit. These limitations minimize radiation and meteoroid hazards and large weight penalties. 

Environmental control system weight is defined as the sum of the functional subsystem weight increments. These increments are identified as the weights of the thermal control subsystem, atmosphere constituent control subsystem, cabin pressure control subsystem, and other miscellaneous subsystems such as waste collection and disposal, water supply, and emergency environmental control. 

This paper describes typical system operations and requirements. Typical functional subsystems are defined, their major parameters are discussed, and a step by step procedure for weight analysis is presented. Empirical functions and graphical aids are employed to illustrate how analysis may be simplified and expedited. 

A weight summary for the environmental control system of a typical vehicle is presented. Sample weight estimate are outlined to illustrate how the weight summary was derived. A weight tradeoff between a stored gas atmosphere subsystem and an atmosphere regeneration subsystem is discussed and sample results are shown. The method of analysis and the data presented introduce a new phase of weight estimation of great importance in the study and production of manned space vehicles.},

keywords = {25. Weight Engineering - System Estimation},

pubstate = {published},

tppubtype = {inproceedings}

}

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210. Rolling Type Alighting Gear Weight Estimation

Liebermann, C R

In: 18th National Conference, Henry Grady Hotel, Atlanta, Georgia, May 18-21, pp. 73, Society of Allied Weight Engineers, Inc., Atlanta, Georgia, 1959.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

217. A Method of Preliminary Weight Estimation for Liquid Rocket Propulsion Systems

Carter, D L; King, L G

In: 18th National Conference, Henry Grady Hotel, Atlanta, Georgia, May 18-21, pp. 82, Society of Allied Weight Engineers, Inc., Atlanta, Georgia, 1959.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

232. Aircraft Fuel System Weight Estimation for the Tri-Sonic Era

Crooker, W C

In: 18th National Conference, Henry Grady Hotel, Atlanta, Georgia, May 18-21, pp. 22, Society of Allied Weight Engineers, Inc., Atlanta, Georgia, 1959.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

181. Weight Estimating Problems of Airborne Electronics Equipment

Reichel, R

In: 17th Annual Conference, Belmont Plaza Hotel, New York, New York, May 19-22, pp. 12, Society of Allied Weight Engineers, Inc., New York, New York, 1958.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation

147. A Rational Method for Estimating Fuel System Weight in Preliminary Design

Holzmeier, G R

In: 16th National Conference, Broadview Hotel, Wichita, Kansas, April 29 - May 2, pp. 24, Society of Allied Weight Engineers, Inc., Wichita, Kansas, 1957.

Abstract | Buy/Download | BibTeX | Tags: 25. Weight Engineering - System Estimation