Flight Control Design for a Tailless Aircraft Using Eigenstructure Assignment

Table 5

SVD of longitudinal control distribution matrix^a.

Left singular vectors						Singular values
−0.0028	−0.0169	0	−0.9623	0.2714	𝑢	0.0548
−0.0121	−0.0429	0	−0.2704	−0.9617	𝛼	0.0057
0	0	1	0	0	𝜃
−0.9201	−0.3906	0	0.0164	0.0244	𝑞
0.3915	−0.9194	0	0.0233	0.0295	∫𝑐^∗

^a 𝑉_𝑇 replaced by normalized velocity 𝑢, no weights.