1、BRITISH STANDARD BS 185-3: 1969 Incorporated amendment No. 1 Glossary of Aeronautical and astronautical terms Section 3: Structures UDC 001.4:629.7BS185-3:1969 This British Standard, having been approved by the AerospaceIndustry Standards Committee, was published underthe authority of the Executive
2、Board of the Institutionon 31July1969 BSI 11-1999 The following BSI references relate to the work on this standard: Committee reference ACE/1 Draft for comment67/17817 ISBN 580059502 A British Standard does not purport to include all the necessary provisions of a contract. Users of British Standards
3、 are responsible for their correct application. Compliance with a British Standard does not of itself confer immunity from legal obligations. Summary of pages This document comprises a front cover, an inside front cover, pages i and ii, pages 1 to 8 and a back cover. This standard has been updated (
4、see copyright date) and may have had amendments incorporated. This will be indicated in the amendment table on the inside front cover. Amendments issued since publication Amd. No. Date of issue Comments 1032 November 1972 Indicated by a sideline in the marginBS185-3:1969 BSI 11-1999 i Contents Page
5、Subsection 31. General 1 Subsection 32. Detail parts 3 Subsection 33. Aeroelasticity 4 Subsection 34. Fatigue 6ii blankBS185-3:1969 BSI 11-1999 1 (Notes on the arrangement and scope of the glossary are contained in the Foreword to Section1.) Subsection 31. General No. Term Definition 3101 buckling A
6、 structural deformation due initially to instability under load, irrespective of whether the deformation is elastic or permanent and whether it leads at once to collapse or not. 3102 creep buckling Critical terminal buckling resulting from slow and steady increase in the deformation of a structure u
7、nder a constant load. 3103 thermal buckling Buckling induced wholly or in part by thermal stress or by thermal distortion. 3104 factor of safety The factor by which a limit load is multiplied to produce the load to be used in the design of an aircraft or part of an aircraft. It is introduced to prov
8、ide a margin of strength against loads greater than the limit loads, and against uncertainties in materials, construction, load estimation and stress analysis. 3105 proof factor The factor of safety corresponding to the proof load. 3106 ultimate factor The factor of safety corresponding to the load
9、which is regarded as the ultimate for design propose, i.e. the fully-factored load. 3107 fineness ratio The ratio of the length of a body to its maximum transverse dimension or, sometimes, to some equivalent dimension. 3108 flight envelope MANOEUVRING V-n DIAGRAM A diagram in which, for a particular
10、 aircraft type, the specified design normal accelerations (as multiples of g) form the ordinates and the corresponding equivalent airspeeds the abscissae. The boundary of the diagram forms a closed figure which defines the design limits for the aircraft concerned. 3109 fully-factored load The maximu
11、m load which a structure is required to be capable of withstanding. 3110 geodetic construction A method of making curved space frames in which the principal structural members follow geodesics in the surface, so that the forces set up in the members are either tensile or compressive. 3111 gust allev
12、iation factor ALLEVIATION FACTOR A correction factor which allows for gust shape, aircraft flexibility, freedom in pitch and delay in the growth of the lift increment. The factor is applied to the increment in accleration found from a simple calculation of the response to a sharp-edged gust in which
13、 no allowance is made for these effects. 3112 gust envelope GUST V-n DIAGRAM A diagram in which, for a particular aircraft type, the gust load factors form the ordinates and the corresponding equivalent airspeeds the abscissae, and on which contours of constant vertical gust velocity can be drawn. I
14、t is often superposed on the flight envelope because of the common abscissae. 3113 gust frequency The number of discrete gusts encountered per unit horizontal distance (usually one mile) having vertical velocity equal to or greater than a given value. 3114 integral construction The formation of a st
15、ructural member as a single whole instead of by the assembly of a large number of separate elements. 3115 limit load UNFACTORED LOAD The maximum load expected to be applied, in a particular condition of operation, to the aircraft or to any part of it.BS185-3:1969 2 BSI 11-1999 No. Term Definition 31
16、16 load diffusion The process by which variation along any length of a structure of transverse distribution of stress, due to direct loads applied in the direction of that length, is established. 3117 shear lag The type of load diffusion in which the lag of longitudinal displacement of one part of a
17、 transverse section relative to that of another results primarily from shear loading applied along lines parallel to the length of the structure. 3118 load factor The ratio of the total load in a specified direction (usually along the normal axis) to the weight of the aircraft. Such load may arise f
18、rom the aerodynamic forces, gravity, ground or water reaction, or from combinations of these forces. 3119 primary structure Those portions of the structure the failure of which would seriously endanger the aircraft in flight. 3120 proof load The load which a structure is required to withstand and st
19、ill remain serviceable. 3121 reserve factor The ratio of the ultimate load of a structure to the fully-factored load. 3122 sharp-edged gust A hypothetical discrete vertical (or side) gust in which the velocity of the air changes abruptly, i.e. the gust gradient distance is zero. 3123 shear centre FL
20、EXURAL CENTRE That point in the plane of a section of a member of uniform cross-section at which a shear force, in whatever direction it is applied, produces only bending without twist. 3124 strain gauge A device, embodying a sensing element attached to the structure, which provides a direct measure
21、ment of strain at the point of attachment. 3125 rosette A set of strain gauges at a point on the surface of a structure, so arranged that the state of plane strain at the point can be fully determined. 3126 wire strain gauge A common form of strain gauge in which the sensing element comprises one or
22、 more lengths of fine wire, the change in whose electrical resistance under load provides a measure of the strain. 3127 stressed-skin structure A structure covered with sheet which contributes substantially to its strength and stiffness. 3128 temperature stress A stress induced when a structure embo
23、dying materials with different coefficients of linear expansion is exposed to a temperature other than that prevailing at the time of assembly. 3129 test frame An apparatus for subjecting aircraft structures to loads representing those occurring in operation. It comprises loading and supporting fram
24、eworks and a control mechanism for the application of loads by hydraulic jacks or other means. 3130 thermal stress TEMPERATURE GRADIENT STRESS The stress induced within a structure by changes in temperature. 3131 ultimate load The maximum load which a structure is capable of withstanding.BS185-3:196
25、9 BSI 11-1999 3 Subsection 32. Detail parts No. Term Definition 3201 astrodome A transparent dome, with known optical characteristics, through which astronomical observations can be made. 3201A blister A streamlined protuberance on an aircraft, designed to house equipment, to afford a place for obse
26、rvation or for other purposes. 3202 boat-tail The rear portion of an elongated body, as a rocket, having cross-sectional area decreasing toward the rear. 3203 bulkhead A transverse dividing wall within a structure. 3204 chine The extreme side member of the planing bottom running approximately parall
27、el to the keel in side elevation. 3205 clamshell Describes doors or other structural parts which open and close in the manner of clam-shells. 3206 DV window (panel) A quick-opening cockpit window (panel) allowing direct vision. 3207 explosive bolt A quick release device actuated by a small explosive
28、 charge detonated by an electrical or other signal. 3208 fairing A secondary structure added to any part to reduce its drag. 3209 fillet A fairing at the junction of two surfaces to improve the airflow. 3210 fin post The principal structural member of a fin, usually carrying the rudder. 3211 former
29、A structural member, the primary purpose of which is to preserve form or shape and to which the external skin is attached. In general, it carries structural loads. 3212 frame 1. Generally: a plane structure transverse to the axis of a tube and maintaining the shape of the cross section of the tube.
30、2. Specifically: a structural member lying in a transverse plane of a fuselage, hull or nacelle, and following the periphery. 3213 spar frame A specially strong frame in the plane of any spar. 3214 keelson A longitudinal member forming part of the main structure of a hull or float and running intern
31、ally along the bottom. 3215 longeron A main longitudinal member of a fuselage or nacelle. 3216 panel A portion of a stiffened sheet together with its stiffeners. 3217 plate 1. In structural theory, a portion of an unstiffened sheet. 2. A sheet having thickness greater than a specified amount. 3218 r
32、ib A member which maintains the required contour of the covering material of planes or control surfaces, and which may also act as a structural member. 3219 nose rib A former between the front spar and leading edge of an aerofoil. 3220 rudder post The principal structural member of a rudder, usually
33、 carrying the hinges. (Cf.3230.) 3221 sandwich A structural component consisting of two parallel, or nearly parallel, faces attached to either side of a core of material of different properties. 3222 core The material between the faces of a sandwich. It stabilizes them and may carry direct load. 322
34、3 corrugated sandwich A sandwich in which the core is built up from sheet having longitudinal corrugations, enabling it to carry direct load in the longitudinal direction.BS185-3:1969 4 BSI 11-1999 Subsection 33. Aeroelasticity No. Term Definition 3224 faces The external skins of a sandwich. 3225 ho
35、neycomb sandwich A sandwich in which the core is formed of thin-walled small cells, often, but not necessarily, hexagonal in shape. It is usual to assume that the core will carry negligible direct load parallel to the faces. 3226 sheet Material of which the thickness is small in comparison with the
36、other dimensions. 3227 shell A curved structure formed of sheet (either stiffened or unstiffened) generally closed on itself as in a tube. 3228 skin Sheet covering a framework of stiffeners. 3229 spar A principal spanwise structural member of an aerofoil or control surface. 3230 stern post A single
37、member terminating a fuselage, hull or float. (Cf. 3220.) 3231 stiffener A member attached to a sheet to restrain its movement normal to the surface. 3232 stringer A stiffener which also assists the sheet to carry direct load in the direction of its length. 3233 strut A structural member intended to
38、 resist compression. 3234 drag struts Struts incorporated in the framework of an aerofoil to carry the loads induced by the air forces in the plane of the aerofoil. 3235 interplane struts Struts connecting a plane to the plane above or below. 3236 wires anti-drag wires Wires or cables incorporated i
39、n the framework of an aerofoil and in its plane, complementary to the drag wires and resisting forces in the opposite direction. 3237 anti-lift wires LANDING WIRES Wires to resist forces in the opposite direction to the lift. 3238 drag wires Wires or cables incorporated in the framework of an aerofo
40、il and in its plane, to resist forces in the general direction of the drag. 3239 incidence wires Wires or cables bracing the main plane structure in the plane of a pair of front and rear struts. 3240 lift wires FLYING WIRES Wires or cables the principal function of which is to transfer the lift of t
41、he main planes to the main structure. 3241 streamline wire A wire the cross section of which is elongated to reduce its drag. 3301 aeroelastic divergence The aeroelastic instability which results when the rate of change of aerodynamic forces or couples with displacement exceeds that of the elastic r
42、estoring forces or couples. 3302 divergence speed The lowest equivalent air speed at which aeroelastic divergence occurs. 3303 aeroelasticity A branch of mechanics which treats of the phenomena resulting from the interaction of aerodynamic, inertial and elastic forces. 3304 aerothermoelasticity That
43、 branch of aeroelasticity in which aerodynamic heating (4402) of the structure is considered. 3305 aileron buzz CONTROL SURFACE BUZZ An oscillation, of limited amplitude, of a control surface about its hinge. It can occur at high subsonic and transonic speeds.BS185-3:1969 BSI 11-1999 5 No. Term Defi
44、nition 3306 buffeting An irregular oscillation of any part of an aircraft produced and maintained directly by an eddying flow. 3307 damping material damping The damping intrinsic to the material of the structure. 3308 structural damping The total damping of a built-up structure. 3309 flight flutter
45、test A flight test during which the structure of an aircraft is excited in order to observe its behaviour and to deduce its flutter characteristics. 3310 flutter A sustained oscillation due to the interaction between aerodynamic forces, elastic reaction and inertia. 3311 anti-symmetrical flutter Flu
46、tter in which the components on port and starboard sides of an aircraft undergo, at any instant, equal but asymmetrical displacement with respect to the plane of symmetry. 3312 asymmetrical flutter Flutter in which the components on the port and starboard sides of an aircraft undergo, at any instant
47、, asymmetrical and unequal displacements with respect to the plane of symmetry. 3313 classical flutter COUPLED FLUTTER Flutter which occurs because of coupling (inertial, aerodynamic or elastic) between two or more degrees of freedom. 3314 flutter speed The lowest equivalent airspeed at which flutte
48、r occurs. 3315 stalling flutter Flutter in one or more degrees of freedom near the angle of stall. 3316 symmetrical flutter Flutter in which the components on the port and starboard sides of an aircraft undergo, at any instant, equal and symmetrical displacements with respect to the plane of symmetr
49、y. 3317 frequency parameter REDUCED FREQUENCY The ratio of the product of the frequency of an oscillation and a representative length of an oscillating system to the true airspeed. 3318 mass-balance weight A mass normally attached to a control surface forward of the hinge line, for the purpose of reducing or eliminating the inertial coupling between angular movement of the control and some other degree of freedom of the aircraft. 3319 distributed mass-balance weight A mass-balance weight which is distributed along the span of the control surface. 3320 remote mass-balance weight
