#Redundant flight control system software

Part of one string can be lost, and all avionics functions will still Which can be transferred to another GPC in case of failure. Provides failure protection during dynamic phases by allowingĮxclusive command of a specific group of vehicle hardware by one GPC, Redundant units are on different strings. All flight-critical hardware units are redundant, and the Redundant set, each is assigned a different string to maximize redundancy. GPC or MDM failure, and to allow for safe return to Earth in the eventĭuring ascent and entry, when there are four PASS GNC GPCs in the Mission operations in the event of a loss of one string caused by a Vehicle hardware is segmented into these groups to facilitate GPCĬommand of these components for redundancy, to allow for nominal (FC1, 2, 3, or 4) and one from the second group (FC5, 6, 7, or 8). The four strings relate to Shuttle's (generally) quad redundant avionics, the three strings in your question imply that Falcon has triple.Ī string is composed of two FC data buses: one from the first group

Here's a schematic from the Shuttle showing one flight computer (on the left, labled GPC for General Purpose Computer) interfacing to four separate flight control strings. 509–512.No specific knowledge of Falcon, but a 'string' in avionics terminology means a element of a redundant flight control system consisting of a flight computer and a data bus to a set of sensors and effectors. In: 10th International Conference on Control, Automation and Information Sciences, pp. Pang, H., Zheng, W.: Research on channel switching strategy of dual redundant flight control system under finite conditions.

Lei, Z., Shi, L.: Dual-redundancy flight control system for small UAV. In: Proceedings of the AIAA Guidance, Navigation, and Control Conference, AIAA, pp. Kim, K., Kimy, D.M., Kim, S., et al.: Flight test of a flying-wing type UAV with partial wing loss using neural network controller. Zhang, R., Chen, X.: Fault diagnosis of UAV’s distributed flight control computers. Su, M., Yan, M.: Research on the application of redundancy computer in UAV system. 6(22), 616–623 (1993)Ĭheng, J., Chen, Y., Liu, S.: Comparative research and development trend analysis of flight control computer system. NASA Technical Report NASA/TM-2011–217168 (2011)īriere, D., Traverse, P.: AIRBUS A320/ A330/ A340 electrical flight controls-A family of fault tolerant systems. Hodson, R.F., Morgan D.R., Butler A.M., et al.: Heavy lift vehicle (HLV) avionics flight computing architecture study. Zhang, X.: On designing the difficult-to-implement RPV computer.

#Redundant flight control system software

Sun, G., Xu, Z.: Application of redundancy flight control system software design technology in unmanned helicopter. Xu, J., Xia, S.: Redundancy analysis and design of flight control computer. 30(4), 835–847 (2007)įerrara, A., Liberatore, P., Schaerf, M.: The complexity of action redundancy. Pashilkar, A.A., Sundararajan, N., Saratchandran, P.: Adaptive nonlinear neural controller for aircraft under actuator failures. In: Proceedings of the 20th Digital Avionics Systems Conference (DASC) (2001)Ĭhowdhary, G., Johnson, N.E., Kimbrell, M.S., et al.: Flight test results of adaptive controllers in presence of severe structural damage. Yeh, Y.: Safety critical avionics for the 777 primary flight control system. According to the safety requirements of large unmanned airship, the physical architecture of dual-redundancy with self-detection of flight control system is proposed. Based on the overall redundancy architecture of flight control system, the redundancy configuration of main components of flight control system, such as flight control computer, inertial navigation system, thrust vector system and thrust system, is given, and the redundancy management strategy based on master-master/master-slave channel hybrid working mode is proposed. A fault tree model of flight control system is established, and the safety analysis based on the fault tree model is carried out, and compared with the architecture of dual-redundancy and triple redundancy. The results show that the proposed 2 × 2 redundancy flight control system can meet the safety requirements of the unmanned airship, and its compatibility with the unmanned airship is better than the triple redundancy system, which can be used as a reference for engineering development.