Flight Control Design for a Tailless Aircraft Using Eigenstructure Assignment

Table 1

Eigenvalues and eigenvectors for the lateral dynamics^a.

	Open loop		Desired closed loop
Eigenvalues	𝜆1,2=−0.5197±𝑗0.4319			Dutch roll	(𝜁dr,𝜔ndr)=(0.4,3)
	𝜆3,4=0.0200±𝑗0.2251			Roll subsidence	1/𝜏roll=−4
				Dutch roll	Roll subsidence
Eigenvectors	0.0420±𝑗0.0031	0.0065±𝑗0.0244	𝛽	1±𝑗0	𝛽/𝑝	𝛽
	0.8278	0.9735	𝜙	|𝜙/𝛽|±𝑗0	𝑥	𝜙
	−0.4332±𝑗0.3514	0.0083±𝑗0.2139	𝑝	𝑥±𝑗𝑥	1	𝑝s
	0.0178±𝑗0.0389	0.0695±𝑗0.0328	𝑟	𝑥±𝑗𝑥	𝑥	𝑟s
				𝑥±𝑗𝑥	𝑥	𝑥wo

^aOpen loop is in body axis, no washout. Closed loop is in stability axis. |𝜙/𝛽|=|𝛽/𝑝|=0.