Integrity Review Report: Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process

Academic fraud report · Geng Detector

Summary

Verdict: Cleared (no fraud indicators detected). This 2019 paper by Xu, Han, Yun, and Chen in the International Journal of Aerospace Engineering (DOI: 10.1155/2019/9362629) was examined for data fabrication, image manipulation, and methodology issues. Finding 1 confirms internal physical consistency: the ratio of moment of inertia to mass (Iyy/m ≈ 5.47 m²) matches the 4.6 m wingspan plausibly, and steady-state trim values from ADAMS versus NASTRAN show realistic small discrepancies (e.g., 1.87° vs 1.87°, -5.15° vs -5.17°) characteristic of genuine multi-solver simulations rather than fabricated perfect matches. Finding 2 confirms the methodological toolkit (Craig-Bampton modal synthesis, Doublet Lattice Method, NASTRAN, ADAMS) and citations (Bampton & Craig 1968, Karpel 1982) are authentic and chronologically appropriate. Finding 3 is inconclusive because pixel-level image analysis could not be performed on the figures due to data access limitations. Overall confidence is moderate-to-high; the absence of text-level anomalies is consistent with a legitimate engineering simulation study.

Verdict

Cleared. The paper shows multiple positive authenticity indicators and no evidence of fraud, image manipulation, or fabricated data within the scope of the available evidence.

Key findings

Physical self-consistency of parameters: The derived radius of gyration from Iyy/m (≈ 5.47 m²) is plausible for an aircraft with a 4.6 m wingspan (Table 1, mass 823 kg, Xc = 2.12 m).
Realistic solver-to-solver discrepancies: ADAMS and NASTRAN steady-state trim values differ at the second decimal (AoA 1.87° vs 1.87°, aileron -5.15° vs -5.17° in Table 2), consistent with authentic multi-tool cross-validation rather than copied or generated values.
Methodological authenticity: The combination of Craig-Bampton modal synthesis, Doublet Lattice Method, ADAMS, and NASTRAN is standard aeroelastic practice; cited references (Bampton & Craig 1968; Karpel 1982 Roger rational approximation) are real and correctly applied.
Logical dynamic-response descriptions: Stated trends across folding times of 5 s, 10 s, 20 s, and 30 s (faster folding → longer settling time, larger steady-state method error) align with aerodynamics and flight-mechanics intuition.
Image analysis inconclusive: Pixel-level inspection of Figures 1–12 could not be performed because raw image data was not provided.

Evidence highlights

DOI: 10.1155/2019/9362629
Table 1: aircraft mass 823 kg, Xc = 2.12 m, Iyy = 4502 and 4675 kg·m²
Table 2: ADAMS vs NASTRAN trim comparison (AoA 1.87° vs 1.87°, aileron -5.15° vs -5.17°)
Folding-rate sweep: 5 s, 10 s, 20 s, 30 s
Methodology references: Bampton & Craig (1968), Karpel (1982); tools ADAMS, NASTRAN

Notes

The textual and numerical content is internally coherent and consistent with legitimate aerospace simulation work. Image-level verification was not possible due to input format limitations and is flagged as ⚠️ insufficient evidence rather than as a positive indicator of concern. Confidence in the cleared verdict is moderate-to-high; any definitive determination of image integrity would require access to the original PDF figures and pixel-level analysis.