1、 INCH-POUND MIL-STD-3033 28 July 2010 _ DEPARTMENT OF DEFENSE TEST METHOD STANDARD PARTICLE / SAND EROSION TESTING OF ROTOR BLADE PROTECTIVE MATERIALS AMSC N/A FSC 1615 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-3033 FOREWORD 1. This sta
2、ndard is approved for use by all Departments and Agencies of the Department of Defense. 2. The purpose of this standard is to provide a standardized test for particle/sand erosion resistance of materials used in leading edge erosion protection systems of helicopter rotor blades. This standard does n
3、ot duplicate the real flight environment. The test measures the amount of material eroded from a stationary specimen by particles accelerated in a high-speed gas jet. These materials can be but are not limited to elastomers, other polymers (including reinforced plastics and composites), metals (incl
4、uding metal matrix composites), ceramics and coatings. 3. This pre-screening test does not, on its own, qualify a material for application onto a rotorblade. Many other material characterizations should be required to qualify a material. They may include but are not limited to additional erosion tes
5、ting (whirling-arm sand, rain and/or combined particle/sand/rain), adhesion, large particle impact, impact (simulated tree strikes), hydrolysis, solar radiation, oxidation, extreme temperatures, temperature shock, fungus, salt fog, electromagnetic compatibility, thermal conductivity, fluid compatibi
6、lity, radar cross section and integration onto an aircraft. Operational experience has shown that a variance exists between the two erosion mechanisms of particle/sand and rain. Therefore, additional qualification tests for combined particle/sand and rain erosion tests are suggested. The qualifying
7、organization will define the specific requirements to fully qualify a material for overall acceptance. 4. The need for this standard is due mostly to the deployment in hot-arid regions and the effects the desert particle/sand has on current rotor blade protective systems. The development and selecti
8、on of erosion resistant protective materials for rotor blades directly impacts aircrew survivability and mission completion. The availability of a standardized test to better assess the durability and repairability of rotor blade materials in these environments is needed. It is anticipated that this
9、 test standard will significantly increase the time on wing of protective systems thereby increasing the duration between repair intervals and reducing the frequency of removal and replacement procedures all of which are labor and material cost intensive. 5. Comments, suggestions, or questions on th
10、is document should be addressed to: Director, U.S. Army Research Laboratory, Weapons and Materials Research Directorate, Materials Manufacturing Technology Branch, Specification and Standards Office, Attn: RDRL-WMM-D, Aberdeen Proving Ground, MD 21005-5069 or emailed to rsquillaus.army.mil. Since co
11、ntact information can change, you may want to verify the currency of this address information using the ASSIST Online database at https:/assist.daps.dla.mil/. iiProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-3033 CONTENTS PARAGRAPH PAGE FORE
12、WARD ii 1. SCOPE 1.1 Scope 1 1.2 Purpose. 1 1.3 Application 1 2. APPLICABLE DOCUMENTS 2.1 General. 1 2.2 Non-Government publications 1 2.3 Order of precedence. 1 3. DEFINITIONS 3.1 Erodent. 2 3.2 Erosion 2 3.3 Erosion failure 2 3.3.1 Cracking 2 3.3.2 Debonding. 2 3.3.3 Pitting. 2 3.3.4 Surface wear
13、2 3.3.5 Wrinkling 2 3.4 Impingement . 2 3.5 Impingement angle . 2 3.6 Mass load. 2 3.7 Particle/sand erosion rate. 2 3.8 Volume loss. . 3 4. GENERAL REQUIREMENTS 4.1 Application 4 4.2 Testing apparatus. 4 4.2.1 Standard test conditions 4 4.2.1.1 Pre-conditioning test specimens 4 4.2.1.2 Testing temp
14、erature and humidity . 4 4.2.1.3 Erodent . 4 4.2.1.3.1 Erodent sieve size . 4 4.2.1.3.2 Reuse of erosion media. . 5 4.2.1.4 Velocity. . 5 4.2.1.5 Impingement angle. 5 4.2.1.6 Sand particle mass loads. 5 4.3 Materials 5 4.4 Preparation of test specimens 5 iiiProvided by IHSNot for ResaleNo reproducti
15、on or networking permitted without license from IHS-,-,-MIL-STD-3033 CONTENTS PARAGRAPH PAGE 4.4.1 Sampling and inspection 5 4.4.2 Cleaning test specimens. 5 4.5 Erosion resistance 6 4.5.1 Pre-test inspection 6 4.5.2 Mass loss 6 4.5.2.1 Anomalous mass change 6 4.6 Testing facility 6 4.7 Test Report
16、6 5. DETAILED REQUIREMENTS 5.1 General. 6 5.2 Test method. 6 5.2.1 Test apparatus 6 5.2.1.1 Test apparatus description 6 5.2.1.2 Sand erosion facility. 7 5.2.2 Test specimens. 8 5.2.3 Test conditions 8 5.2.3.1 Erodent . 8 5.2.3.1.1 Sand particle size. 8 5.2.3.2 Velocity. 8 5.2.3.3 Impingement angle.
17、 9 5.2.3.4 Sand particle mass load. 9 5.2.4 Test procedures. 9 5.3 Data Analysis . 9 5.3.1 Volume loss. 9 5.3.2 Ranking of the various materials. 9 5.3.3 Failure of a coating. 9 6. NOTES 6.1 Intended use. 10 6.2 Acquisition requirements 10 6.3 Material safety data sheets (MSDS) 10 6.4 Erosion resist
18、ance of an elastomer 11 6.5 Testing temperature. 11 6.6 Recommended post-test metallographic examination. 11 6.7 Source for the un-sieved synthetic particle/sand. 11 6.8 Subject term (key word) listing 11 CONCLUDING MATERIAL 12 ivProvided by IHSNot for ResaleNo reproduction or networking permitted w
19、ithout license from IHS-,-,-MIL-STD-3033 vCONTENTS FIGURE PAGE 1. Sand Particle Erosion Schematic 3 2. Particle / Sand Erosion Chamber. 3 3. Pressurized Screw-Feeder Sand Plenum. 7 4. Standard Square Test Specimen 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license
20、 from IHS-,-,-MIL-STD-3033 1. SCOPE 1.1 Scope. This standard describes a test method for testing the materials used as erosion protective systems of helicopter rotor blades for resistance to solid particle/sand erosion. These materials can be but are not limited to elastomers, other polymers (includ
21、ing reinforced plastics and composites), metals (including metal matrix composites), ceramics and coatings. 1.2 Purpose. The purpose of this standard is to provide a standardized test method for particle/sand erosion resistance of materials used as erosion protective systems of helicopter rotor blad
22、es. The test measures the amount of material eroded from a stationary specimen by particles accelerated in a high-speed gas jet. 1.3 Application. The various helicopter rotor blades that will be utilizing these coatings/appliqus are numerous. However, this test method is only one of many that is req
23、uired to determine the acceptability of these coatings/appliqus, such as additional erosion testing (whirling-arm sand, rain, and/or combined particle/sand/rain), adhesion, impact, hydrolysis, solar radiation, oxidation, extreme temperatures, temperature shock, fungus, salt fog, electromagnetic comp
24、atibility, thermal conductivity, fluid compatibility, radar cross section and integration onto an aircraft. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are specified in sections 3, 4, or 5 of this standard. This section does not include documents cited in other sections
25、 of this standard or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they must meet all specified requirements of documents cited in sections 3, 4, or 5 of this standard, whether or not
26、 they are listed. 2.2 Non-Government publications. The following documents form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those cited in the solicitation or contract. ASTM INTERNATIONAL ASTM E11 - Standard Specification for
27、Woven Wire Test Sieve Cloth and Test Sieves ASTM F1864 - Standard Test Method for Dust Erosion Resistance of Optical and Infrared Transparent Materials and Coatings (Copies of these documents are available from www.astm.org or ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken
28、, PA 19428-2959.) 2.3 Order of precedence. In the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence. Nothing in this 1Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-
29、STD-3033 document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3. DEFINITIONS 3.1 Erodent. The erodent is the sand particles used in the testing apparatus. 3.2 Erosion. Erosion is the progressive loss of original material from the surface of a t
30、est sample under investigation due to mechanical interaction between that surface and a stream of impinging solid particles. 3.3 Erosion failures. 3.3.1 Cracking. Cracking is generally a result of fatigue. Evidence of cracks exceeding established limits in the erosion protective system or blade requ
31、ires replacement. 3.3.2 Debonding. Debonding is most prevalent with non-metallics. Any evidence of debonding that exceeds established limits of the erosion protection system or substrate requires repair or replacement. 3.3.3 Pitting. Pitting has the same basic criteria as surface wear. Careful inspe
32、ction is required to ensure that complete penetration to the substrate has not occurred. 3.3.4 Surface wear. Surface wear is when the blade erosion protection system surface is worn. Metals generally wear smooth, whereas nonmetals usually wear rough. If the blade erosion protection system contour ha
33、s been changed it should be checked to determine if it is within the established variation allowances. Even if the blade erosion protection system contour is satisfactory, once the substrate is exposed, the blade shall be repaired or replaced. 3.3.5 Wrinkling. Wrinkling is most prevalent with ductil
34、e metals that are worn to a specific minimum thickness. Once this occurs, repair or replacement is required. 3.4 Impingement. Impingement is a process resulting in a continuing succession of impacts between sand particles and a solid surface under test. 3.5 Impingement angle. An impingement (impact)
35、 angle that is normal to the stream of the dust jet shall be considered an angle of 90 degrees, and any deviation from this angle shall be measured countercurrent to the stream as shown in Figure 1. This angle may vary between 20oand 90o for the instrument shown in Figure 2. 3.6 Mass load. The mass
36、of particle/sand per unit of total exposed surface area (including the sample holder) that impinges on the specimen. (See ASTM F1864). 3.7 Particle/sand erosion rate. Particle/sand erosion rate is equal to the mass loss (mg) divided by the erodent mass (g). 2Provided by IHSNot for ResaleNo reproduct
37、ion or networking permitted without license from IHS-,-,-MIL-STD-3033 3.8 Volume loss. Volume loss is equal to the erosion rate divided by the density of the material and is reported in 10-3g/cm3. Figure 1. Sand Particle Erosion Schematic. Figure 2. Particle / Sand Erosion Chamber 3Provided by IHSNo
38、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-3033 4. GENERAL REQUIREMENTS 4.1 Application. All materials developed to protect the exterior surfaces of the rotor blade shall be tested to the methods of this standard. The erodent for hot-arid regions encount
39、ered by rotor blade erosion protective systems in DoD unique military environments shall be simulated in the test apparatus specified in this standard. Although this test method only generates results that approximate relative particle/sand erosion resistance, these qualitative and quantitative resu
40、lts allow the Procuring Activity to determine which product may provide better particle/sand erosion resistance in hot-arid regions. 4.2 Testing apparatus. The testing apparatus shall be capable of simulating the effects of flight through a concentration of airborne particles/sand. See Section 5 for
41、 a description of the testing apparatus. 4.2.1 Standard test conditions. The values listed for the various test conditions (velocity, load, etc.) were determined by measuring each condition on actual rotor blades during takeoff and landing. Caution should be taken to ensure that the same types of ma
42、terials are tested with the same parameters. The standard test conditions shall be as follows. 4.2.1.1 Pre-conditioning test specimens. All test specimens shall be pre-conditioned to the following requirements for at least 24 hours prior to testing: 75 F (23 C) and 50% Relative Humidity (RH). The to
43、lerance shall be 5F and 5% RH unless otherwise specified in the contract or purchase order (see 6.2). 4.2.1.2 Testing temperature and humidity. Unless otherwise specified in the contract or purchase order (see 6.2) for the specific material being tested, the testing shall be conducted at a temperatu
44、re of 75F 5F and at a Relative Humidity (RH) of 50%. (see 5.2.3 and 6.5). The temperature and RH shall be measured within the test chamber prior to testing. 4.2.1.3 Erodent. A synthetic mineral quartz sand formed by the fracture of quartz pebbles shall be the erodent. Shattering or crushing quartz pebbles is the source of the high degree of sharpness that makes this sand uniquely suited for this standard. There are currently no acceptable substitutions for this particle/sand. Sources for golf trap or bunker sand are av
