ASTM F320-2010 Standard Test Method for Hail Impact Resistance of Aerospace Transparent Enclosures《航空航天用透明外壳的抗冰雹撞击性能的标准试验方法》.pdf
《ASTM F320-2010 Standard Test Method for Hail Impact Resistance of Aerospace Transparent Enclosures《航空航天用透明外壳的抗冰雹撞击性能的标准试验方法》.pdf》由会员分享,可在线阅读,更多相关《ASTM F320-2010 Standard Test Method for Hail Impact Resistance of Aerospace Transparent Enclosures《航空航天用透明外壳的抗冰雹撞击性能的标准试验方法》.pdf(7页珍藏版)》请在麦多课文档分享上搜索。
1、Designation: F320 10Standard Test Method forHail Impact Resistance of Aerospace TransparentEnclosures1This standard is issued under the fixed designation F320; the number immediately following the designation indicates the year of originaladoption or, in the case of revision, the year of last revisi
2、on.Anumber in parentheses indicates the year of last reapproval.Asuperscriptepsilon () indicates an editorial change since the last revision or reapproval.This standard has been approved for use by agencies of the Department of Defense.1. Scope1.1 This test method covers the determination of the imp
3、actresistance of an aerospace transparent enclosure, hereinaftercalled windshield, during hailstorm conditions using simulatedhailstones consisting of ice balls molded under tightly con-trolled conditions.1.2 The values stated in inch-pound units are to be regardedas standard. The values given in pa
4、rentheses are mathematicalconversions to SI units that are provided for information onlyand are not considered standard.1.3 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-pr
5、iate safety and health practices and determine the applica-bility of regulatory limitations prior to use. For specific hazardstatements see Section 7.2. Terminology2.1 Definitions:2.1.1 damageany modification in visual properties orintegrity of a windshield as a result of hail impact includingscratc
6、hes, crazing, delamination, cracks, or shattering.2.1.2 ice balla frozen mass of water, with filler, thatsimulates a natural hailstone in weight, size, and toughness.2.1.3 impact anglethe angle between the ice ball flightpath and the target normal.2.1.4 sabota plastic device for protecting the ice b
7、allwhile in the launch tube. One type of sabot (see Fig. 1) consistsof a split polycarbonate rod containing a central cavity forholding the ice ball. Each sabot half is designed to assureaerodynamic separation from the ice ball after ejection fromthe launch tube.3. Summary of Test Method3.1 The test
8、 method involves launching a series of ice ballsof specified sizes at a sample windshield at a designatedvelocity and angle and in a specified pattern. Requirements arespecified for the ice ball, test specimen, procedure, and dataacquisition. The ice ball is photographed in flight to verify itsinteg
9、rity.3.2 Requirements are specified for a particular apparatusand test procedure, but options are permitted for certain areas.However, it must be possible to demonstrate that the optionsused result in an ice ball impacting the test panel with the samesize, consistency, and velocity as with the speci
10、fied apparatusand procedure. Following are areas where options are allowed:3.2.1 Ice Ball Mold Material.1This test method is under the jurisdiction of ASTM Committee F07 onAerospace and Aircraft and is the direct responsibility of Subcommittee F07.08 onTransparent Enclosures and Materials.Current ed
11、ition approved May 1, 2010. Published June 2010. Originallyapproved in 1978. Last previous edition approved in 2005 as F320 05. DOI:10.1520/F0320-10.FIG. 1 Sabot Configuration1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.3.2.2 Laun
12、cherAny type of launcher is allowable as longas the iceball reaches the test specimen intact at the correctspeed. The use of sabots and sabot material and geometry areoptional.3.2.3 Method of Determining Ice Ball Integrity.3.2.4 Ice Ball Speed Measurement, Optional as long asaccuracy standards are m
13、et.3.2.5 Test Specimen SizesThose given are minimum.3.2.6 SafetySafety must satisfy the safety standards of thetest facility being used.4. Significance and Use4.1 This test method may be used to determine the hailimpact resistance of windshields for acceptance, design, ser-vice, or research purposes
14、. By coupling this method with theinstalled angle and velocity of a specific aerospace vehicle,design allowables, criteria, and tolerances can be establishedfor that vehicles windshield.5. Apparatus5.1 The facilities and equipment required for the perfor-mance of this test procedure include a suitab
15、le firing rangeequipped with an ice ball mold, a launcher, blast deflector,sabot trap, velocity measuring system, test specimen holder,and a camera with strobe lights to verify ice ball integrity.Ancillary equipment required for this test include test speci-men, ice balls, sabots, and firing cartrid
16、ges.An example facilityis described below.5.2 Firing RangeThe firing range shall be a minimum of9 by 18 ft (3 by 6 m) enclosed to contain flying debris and toexclude unauthorized personnel.5.3 Ice Ball Mold, two aluminum blocks with hemisphericalcavities and vent holes for filling with water and for
17、 waterexpansion during freezing.5.4 Launcher, any launcher may be used as noted in 3.2.2.In addition to the powder gun described in this test method,laboratories have also successfully utilized compressed gas gunlaunchers. An example of a powder gun launcher is shown inFig. 2, consisting of a barrel
18、, breech, breech plug, and control.The barrel shall be made from high-qualityAISI 4130 seamlesssteel tubing, or equivalent, in the annealed condition. Thebreech shall be made from AISI 4130 steel rod, or equivalent,heat treated to a 160- to 180-ksi (1104- to 1242-MPa) ultimatetensile strength condit
19、ion. The size of cavity to be used in thebreech depends on the desired test velocity (see Table 1). Thebreech plug, which locks the cartridge in place and contains thefiring pin, shall be made of 4340 steel heat treated to a 160- to180-ksi ultimate tensile strength condition. The firing pin isactuat
20、ed by a kinetic impact air piston. Control is accomplishedby an electrically actuated air valve. For a 100-psi (0.69-MPa)air source, a 0.75-in.2(4.84-cm2) piston traveling 0.5 in. (13mm) is used.5.5 Blast DeflectorPlace a plate with a 4-in. (100-mm)diameter hole as shown in Fig. 3 between the sabot
21、trap and thefirst velocity measuring station. Then place a corrugatedcardboard plate over the hole. This deflector is not required forcompressed gas gun systems.5.6 Sabot Trap is made by placing two steel plates two tofour ice ball diameters apart, centered on the flight path andlocated a minimum of
22、 6 ft (1.82 m) from the launcher muzzleas shown in Fig. 4. This trap is not required for systems thatutilize aerodynamic separation of the sabot or other suitablemechanisms to ensure that the sabot does not impact the testarticle.5.7 Velocity Measurement SystemThe break-screen veloc-ity measurement
23、consists of a set of screens, power supply,wiring, and counters. Three screens shall be made from alightweight bond paper with an electrical circuit painted on theFIG. 2 Launcher DesignF320 102paper by the silk screen process. The paint for the circuit shallbe electronic grade electrical conducting
24、paint.2Do not thin thepaint. The break-screen shall be made with lines18 in. (3.2mm) wide by 18 in. (460 mm) long as shown in Fig. 5 givinga resistance of no more than 300 V. Fig. 6 shows thearrangement of components and gives the electronic circuit tobe used with the three screens. The system shall
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