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Additional file 2: Figure S1. Veen diagram for the MAPK signaling pathway in the contrast of knockdown of RIP2 HD11 cells (shRIP2) vs. wild type HD11 cells (WT) and knockdown of RIP2 combined with avian pathogenic E. coli infection HD11 cells (shRIP2 + APEC) vs. avian pathogenic E. coli infection HD11 cells (APEC), as well as the apoptosis pathway in the contrast of shRIP2 vs. WT and shRIP2 + APEC vs. APEC. Figure S2. Full-length blot of GAPDH protein expression level for Fig. 1B. Figure S3. Full-length blot of RIP2 protein expression level for Fig. 1B. Figure S4. Full-length blot of BID protein expression level for Fig. 10D. Figure S5. Full-length blot of CASP9 protein expression level for Fig. 10D. Figure S6. Full-length blot of HSP90AB1 protein expression level for Fig. 10D. Figure S7. Full-length blot of GAPDH protein expression level for Fig. 10D.

Additional file 1: Table S1. shRNA information for RIP2. Table S2. Primers for candidate genes in qRT-PCR validation experiment. Table S3. Characteristics of RNA sequencing data before or after quality control. Table S4. The reads mapping information for each sample. Table S5. The significantly enriched gene ontology (GO) in the comparison of shRIP2 vs. WT with adjusted p-value ≤0.05. Table S6. The significantly enriched gene ontology (GO) in the comparison of shRIP2 + APEC vs. APEC with adjusted p-value ≤0.05. Table S7. The significantly enriched pathways in the comparison of shRIP2 vs. WT with adjusted. p_value ≤0.05. Table S8. The significantly enriched pathways in the comparison of shRIP2 + APEC vs. APEC with adjusted p-value ≤0.05. Table S9. The differentially expressed genes involved in the MAPK signaling pathway in the comparison of shRIP2 vs. WT. Table S10. The differentially expressed genes involved in the MAPK signaling pathway in the comparison of shRIP2 + APEC vs. APEC. Table S11. The differentially expressed genes involved in the apoptosis pathway in the comparison of shRIP2 vs. WT. Table S12. The differentially expressed genes involved in the apoptosis pathway in the comparison of shRIP2 + APEC vs. APEC.

Fault subsystems are entirely isolated on the fault-detected epoch in traditional fault-tolerant integrated navigation systems. However, this strategy ignores the asymptotic change and component differences of the soft failure influence. This study proposes a resilient fusion navigation algorithm based on the failure influence level evaluation. The failure influence mapped on the local estimation components is modelled. Then, the influential level of soft failure on the locally estimated states is evaluated. The failure influence levels are used for asymptotic resilience tuning in the global fusion. The simulation results indicate that the fault-tolerant performance under soft failure is improved significantly when using the proposed resilient fusion navigation algorithm based on the failure influence level evaluation.

An aerospace vehicle in high-speed flight involves distributed multiple fields of view (FoVs) of a star sensor, and the maneuvering of the vehicle requires inertial-aided star pattern matching. Accordingly, an inertial-aided star pattern matching method for distributed multiple FoVs is proposed. First, the observation and fusion principles of distributed multiple FoVs are illustrated. Then, an inertial-aided star pattern matching scheme is designed based on the space-time distribution of the line-of sight (LoS) vector and inertial measurement information. Next, an LoS vector estimation method assisted by inertial information and the dynamic establishment of a distributed local catalog are proposed. Finally, in a simulation, the dynamic establishment of the part catalog improves the efficiency of star pattern matching by reducing the catalog scale, and the usability of inertial-aided star pattern matching is analyzed for different gyro and accelerometer precisions.

In high-altitude, long-endurance unmanned aerial vehicles, a celestial attitude determination system is used to enhance the inertial navigation system (INS)/global positioning system (GPS) to achieve the required attitude performance. The traditional federal filter is not applicable for INS/GPS/celestial attitude determination system information fusion because it does not consider the mutually coupled relationship between the horizontal reference error in the celestial attitude determination system and the navigation error; this limitation results in reduced navigation accuracy. This article proposes a novel stepwise fusion algorithm with dual correction for multi-sensor navigation. Considering the horizontal reference error, the celestial attitude determination system measurement model is constructed and the issues involved in applying the federal filter are discussed. Then, preliminary error estimation and horizontal reference compensation are added to the navigation architecture. In addition, a sequential update strategy is derived to estimate the attitude error with the compensated celestial attitude determination system based on the preliminary estimation. A stepwise correction filtering algorithm with interactive preliminary and sequential updates that can effectively fuse celestial attitude determination system measurements with the INS/GPS is constructed. High-altitude, long-endurance unmanned aerial vehicle navigation in a remote sensing task is simulated to verify the performance of the proposed method. The simulation results demonstrate that the horizontal reference error is effectively compensated, and the attitude accuracy is significantly improved after stepwise error estimation and correction. The proposed method also provides a novel multi-sensor integrated navigation architecture with mutually coupled errors; this architecture is beneficial in unmanned aerial vehicle navigation applications.