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  • COMPOSITE MATERIALS  (7)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (5)
  • 1
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    Materials and processes laboratory composite materials characterization task, part 1. Damage tolerance (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A test run was performed on IM6/3501-6 carbon-epoxy in which the material was processed, machined into specimens, and tested for damage tolerance capabilities. Nondestructive test data played a major role in this element of composite characterization. A time chart was produced showing the time the composite material spent within each Branch or Division in order to identify those areas which produce a long turnaround time. Instrumented drop weight testing was performed on the specimens with nondestructive evaluation being performed before and after the impacts. Destructive testing in the form of cross-sectional photomicrography and compression-after-impact testing were used. Results show that the processing and machining steps needed to be performed more rapidly if data on composite material is to be collected within a reasonable timeframe. The results of the damage tolerance testing showed that IM6/3501-6 is a brittle material that is very susceptible to impact damage.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-103553 , NAS 1.15:103553
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A novel method of testing the shear strength of thick honeycomb composites (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Sandwich composites of aluminum and glass/phenolic honeycomb core were tested for shear strength before and after impact damage. The assessment of shear strength was performed in two ways; by four point bend testing of sandwich beams and by a novel double lap shear (DLS) test. This testing technique was developed so smaller specimens could be used, thus making the use of common lab scale fabrication and testing possible. The two techniques yielded similar data. The DLS test gave slightly lower shear strength values of the two methods but were closer to the supplier's values for shear strength.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TP-3108 , NAS 1.60:3108
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    NASA rotor systems research aircraft: Fixed-wing configuration flight-test results (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The fixed-wing, airplane configuration flight-test results of the Rotor System Research Aircraft (RSRA), NASA 740, at Ames/Dryden Flight Research Center are documented. Fourteen taxi and flight tests were performed from December 1983 to October 1984. This was the first time the RSRA was flown with the main rotor removed; the tail rotor was installed. These tests confirmed that the RSRA is operable as a fixed-wing aircraft. Data were obtained for various takeoff and landing distances, control sensitivity, trim and dynamics stability characteristics, performance rotor-hub drag, and acoustics signature. Stability data were obtained with the rotor hub both installed and removed. The speed envelope was developed to 261 knots true airspeed (KTAS), 226 knots calibrated airspeed (KCAS) at 10,000 ft density altitude. The airplane was configured at 5 deg. wing incidence with 5 deg. wing flaps as a normal configuration. Level-flight data were acquired at 167 KCAS for wing incidence from 0 to 10 deg. Step inputs and doublet inputs of various magnitudes were utilized to acquire dynamic stability and control sensitivity data. Sine-wave inputs of constantly increasing frequency were used to generate parameter identification data. The maximum load factor attained was 2.34 g at 206 KCAS.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-86789 , A-85363 , NAS 1.15:86789
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Damage tolerance of candidate thermoset composites for use on single stage to orbit vehicles (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Four fiber/resin systems were compared for resistance to damage and damage tolerance. One toughened epoxy and three toughened bismaleimide (BMI) resins were used, all with IM7 carbon fiber reinforcement. A statistical design of experiments technique was used to evaluate the effects of impact energy, specimen thickness, and impactor diameter on the damage area, as computed by C-scans, and residual compression-after-impact (CAI) strength. Results showed that two of the BMI systems sustained relatively large damage zones yet had an excellent retention of CAI strength.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TP-3506 , M-758 , NAS 1.60:3506
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    NASA TECHNICAL REPORTS
  • 5
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    A statistical comparison of two carbon fiber/epoxy fabrication techniques (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A statistical comparison of the compression strengths of specimens that were fabricated by either a platen press or an autoclave were performed on IM6/3501-6 carbon/epoxy composites of 16-ply (0,+45,90,-45)(sub S2) lay-up configuration. The samples were cured with the same parameters and processing materials. It was found that the autoclaved panels were thicker than the platen press cured samples. Two hundred samples of each type of cure process were compression tested. The autoclaved samples had an average strength of 450 MPa (65.5 ksi), while the press cured samples had an average strength of 370 MPa (54.0 ksi). A Weibull analysis of the data showed that there is only a 30 pct. probability that the two types of cure systems yield specimens that can be considered from the same family.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TP-3179 , M-673 , NAS 1.60:3179
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    NASA rotor system research aircraft flight-test data report: Helicopter and compound configuration (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The flight test activities of the Rotor System Research Aircraft (RSRA), NASA 740, from June 30, 1981 to August 5, 1982 are reported. Tests were conducted in both the helicopter and compound configurations. Compound tests reconfirmed the Sikorsky flight envelope except that main rotor blade bending loads reached endurance at a speed about 10 knots lower than previously. Wing incidence changes were made from 0 to 10 deg.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85843 , NAS 1.15:85843
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Comparison of analytical and flight test identified aerodynamic derivatives for a tandem-rotor transport helicopter (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight tests for verifying an analytical aerodynamic derivative model of a CH-47 helicopter were conducted for low cruise speeds and transition to hover portions of curved, decelerating landing approach trajectories. All testing was performed on a closed loop basis with the stability augmentation system of the helicopter operating, and response data were obtained using both manual and computer generated input maneuvers. The results indicate some differences between the measured response time histories and those predicted by both analytical and flight test identified derivatives. With some exceptions the discrepancies are not severe, and the overall agreement between the measured and computed time histories is reasonably good. No adverse effects attributable to closed loop testing were noted, and the use of computer generated inputs proved to be superior to manual ones.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1581 , L-13228
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    An examination of impact damage in glass-phenolic and aluminum honeycomb core composite panels (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An examination of low velocity impact damage to glass-phenolic and aluminum core honeycomb sandwich panels with carbon-epoxy facesheets is presented. An instrumented drop weight impact test apparatus was utilized to inflict damage at energy ranges between 0.7 and 4.2 joules. Specimens were checked for extent of damage by cross sectional examination. The effect of core damage was assessed by subjecting impact-damaged beams to four-point bend tests. Skin-only specimens (facings not bonded to honeycomb) were also tested for comparison purposes. Results show that core buckling is the first damage mode, followed by delaminations in the facings, matrix cracking, and finally fiber breakage. The aluminum honeycomb panels exhibited a larger core damage zone and more facing delaminations than the glass-phenolic core, but could withstand more shear stress when damaged than the glass-phenolic core specimens.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TP-3042 , NAS 1.60:3042
    Format: application/pdf
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  • 9
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    VALT parameter identification flight test (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The paper describes a method of establishing the accuracy of previously developed analytical models of research vehicles for a program for developing avionics technology for VTOL aircraft. The research vehicle is a Boeing-Vertol CH-47 tandem rotor transport helicopter equipped with a fly-by-wire control system. The specialized flight test was designed to take into account the presence of winds at flight conditions from hover through transition to cruise. The test provided data to obtain estimates of derivatives by parameter identification.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: European Rotorcraft and Powered Lift Aircraft Forum; Sept. 13-15, 1978; Stresa; Italy
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Compression-after-impact testing of thin composite materials (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new method has been devised to test composite specimens as thin as 8 plies and up to 7.6 cm in width for compression strength. This method utilizes a fixture incorporating the best features of the Celanese and IITRI fixtures combined with an antibuckling jig developed at the University of Dayton Research Institute. This new method uses up to 83 percent less material than the most commonly used compression-after-impact technique (which calls for a 48 ply test specimen) and can also be performed on smaller loading frames since a much smaller force is needed to fail the specimen. The thickness of the test specimen can be fabricated to exactly match production part thickness, thus yielding more meaningful results. CAI tests were performed on IM6/3501 carbon/epoxy utilizing this new method. To verify the design, a series of tests were performed in which undamaged specimens were tested using the new fixture and ASTM D 3410-87 (Celanese compression test) and the results compared. The new fixture works well and will be a valuable asset to MSFC's damage tolerance program.
    Keywords: COMPOSITE MATERIALS
    Type: International SAMPE Technical Conference; Oct 21, 1991 - Oct 24, 1991; Kiamesha Lake, NY; United States
    Format: text
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    NASA TECHNICAL REPORTS
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