Flight Control Design for a Tailless Aircraft Using Eigenstructure Assignment

Table 6

Longitudinal feedback gain matrix 𝐾_𝐷.

𝑐^∗	𝛼	𝑞	∫𝑐^∗
−5.59	−5.59	−0.4979	8.32	𝛿pf
−2.89	−2.89	−0.2574	4.30	𝛿ptv