Flight Control Design for a Tailless Aircraft Using Eigenstructure Assignment

Table 3

Lateral eigenstructure assignment design^a.

	Feedback gain matrix				Achievable eigenvectors		Achievable eigenvalues
	𝛽	𝑝s	(𝑟s)wo		Dutch roll	Roll subsidence
Unweighted 𝐵; 𝜁dr=0.4	−1.7256	0.2945	0.2292	elevonL	1±𝑗0	0	(𝜁dr,𝜔dr)=(0.4,3.0)
	1.7256	−0.2945	−0.2292	elevonR	0±𝑗0	−0.2531	𝜆roll=−4
	0.7870	0.1188	−0.2387	amtL	0±𝑗0.0001	1	𝜆spiral=0.0077
	−0.7870	−0.1188	0.2387	amtR	1.1007±𝑗2.8348	−0.0106	𝜆filter=−1.33
	7.7741	−0.4185	−1.5142	yawTV	−1.0545±𝑗0.3236	0.0035
Weighted 𝐵; 𝑊=(1,1,1,1,0.25); 𝜁dr=0.4	−8.0478	0.6333	1.4730	elevonL	1±𝑗0	0	(𝜁dr,𝜔dr)=(0.4,3.0)
	8.0478	−0.6333	−1.4730	elevonR	0±𝑗0	−0.2531	𝜆roll=−4
	8.6966	−0.3052	−1.7949	amtL	0±𝑗0.0001	1	𝜆spiral=0.0077
	−8.6966	0.3052	1.7949	amtR	1.1166±𝑗2.8222	−0.0120	𝜆filter=−1.34
	3.3934	−0.1820	−0.6667	yawTV	−1.0504±𝑗0.3297	0.0040
Weighted 𝐵; 𝑊=(1,1,1,1,0.25); 𝜁dr=0.707	−10.5499	0.6535	2.7356	elevonL	1±𝑗0	0	(𝜁dr,𝜔dr)=(0.707,3.0)
	10.5499	−0.6535	−2.7356	elevonR	0±𝑗0	−0.2531	𝜆roll=−4
	11.8373	−0.3307	−3.3928	amtL	0±𝑗0	1	𝜆spiral=0.0077
	−11.8373	0.3307	3.3928	amtR	2.1068±𝑗2.2247	−0.0120	𝜆filter=−1.84
	4.5464	−0.1913	−1.2514	yawTV	−1.2299±𝑗0.3432	0.004

^aDesign model includes washout filter but no actuator dynamics.