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A display system for an aircraft includes a central unit configured to determine a speed vector of the aircraft and to determine a longitudinal margin of maneuver of the aircraft. The longitudinal margin of maneuver is expressed as a load factor and is related to one of a pitch-up maneuver and a pit

A display system for an aircraft includes a central unit configured to determine a speed vector of the aircraft and to determine a longitudinal margin of maneuver of the aircraft. The longitudinal margin of maneuver is expressed as a load factor and is related to one of a pitch-up maneuver and a pitch-down maneuver. The display system also includes a display unit connected to the central unit. The display unit includes a display screen configured to display a first characteristic sign illustrating the speed vector and a second characteristic sign illustrating the longitudinal margin of maneuver.

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1. A display system for an aircraft, comprising:a central unit configured to determine a speed vector of the aircraft and to determine a longitudinal margin of maneuver of the aircraft, wherein the longitudinal margin of maneuver is expressed as a load factor and is related to one of a pitch-up mane

1. A display system for an aircraft, comprising:a central unit configured to determine a speed vector of the aircraft and to determine a longitudinal margin of maneuver of the aircraft, wherein the longitudinal margin of maneuver is expressed as a load factor and is related to one of a pitch-up maneuver and a pitch-down maneuver; anda display unit connected to the central unit and including a display screen configured to display a first characteristic sign illustrating the speed vector and a second characteristic sign illustrating the longitudinal margin of maneuver, wherein a distance between the first characteristic sign and the second characteristic sign is proportional to the longitudinal margin of maneuver.2. The display system of claim 1, wherein the display screen is a heads-up display screen.3. The display system of claim 1, wherein the first characteristic sign is shaped as a diamond and the second characteristic sign is shaped as a chevron.4. The display system of claim 1, wherein the central unit includes:a first determining unit configured to determine a longitudinal margin of maneuver related to a pitch-up maneuver; anda second determining unit configured to determine a longitudinal margin of maneuver related to a pitch-down maneuver.5. The display system of claim 4, wherein the first determining unit determines the longitudinal margin by selecting the smaller of a first load factor margin and an angle of incidence margin.6. The display system of claim 5, wherein the angle of incidence margin is calculated from the following expression:Δα=1?[(Nz/ΔNmax)*((αmax?α)/(α?α0))],wherein Δα is the angle of incidence margin, Nz is a load factor, ΔNmax is a maximum value of margin of maneuver depicted, α is a angle of incidence, a max is a maximum angle of incidence, and α0 is a zero lift angle of incidence.7. The display system of claim 4, wherein the second determining unit determines the longitudinal margin by selecting the smaller of a first load factor margin and a speed margin.8. The display system of claim 7, wherein the speed margin is calculated from the following expression:ΔV=1?[(Nz+Kp(Vmax?V)?Kd(dV/dt))/ΔNmax],wherein ΔV is the speed margin, Nz is a load factor, ΔNmax is a maximum value of margin of maneuver depicted, V is a speed of the aircraft, Vmax is a maximum speed of the aircraft, (dV/dt) is a derivative with respect to time of the speed V, and Kp and Kd are predetermined parameters.9. The display system of claim 1, wherein the display unit displays the second characteristic sign only when the determined longitudinal margin of maneuver is less than a predetermined value.10. A display system for an aircraft, comprising:a central unit including a first determining unit configured to determine a speed vector of the aircraft and a second determining unit configured to determine a longitudinal margin of maneuver of the aircraft; anda display unit including a display screen configured to display a first characteristic sign illustrating the speed vector of the aircraft and a second characteristic sign illustrating the longitudinal margin of maneuver of the aircraft, wherein a distance between the first characteristic sign and the second characteristic sign is proportional to the longitudinal margin of maneuver.11. The display system of claim 10, wherein the second determining unit includes a first selecting unit configured to determine a longitudinal margin of maneuver related to a pitch-up maneuver by selecting the smaller of a pitch-up load factor margin and an angle of incidence margin.12. The display system of claim 11, wherein the second determining unit includes a second selecting unit configured to determine a longitudinal margin of maneuver related to a pitch-down maneuver by selecting the smaller of a pitch-down load factor margin and a speed margin.13. The display system of claim 12, wherein the second determining unit includes:a first margin calculating unit configured to determine the pitch-up load factor margin;a second margin calculating unit configured to determine the angle of incidence margin;a third margin calculating unit configured to determine the pitch-down load factor margin; anda fourth margin calculating unit configured to determine the speed margin.14. The display system of claim 13, wherein the second margin calculating unit determines the angle of incidence margin using the following expression:Δα=1?[(Nz/ΔNmax)*((αmax?α)/(α?α0))],wherein Δα is the angle of incidence margin, Nz is a load factor, ΔNmax is a maximum value of margin of maneuver depicted, α is a angle of incidence, αmax is a maximum angle of incidence, and α0 is a zero lift angle of incidence.15. The display system of claim 13, wherein the fourth margin calculating unit determines the speed margin using the following expression:ΔV=1?[(Nz+Kp(Vmax?V)?Kd(dV/dt))/ΔNmax],wherein ΔV is the speed margin, Nz is a load factor, ΔNmax is a maximum value of margin of maneuver depicted, V is the speed of the aircraft, Vmax is a maximum speed of the aircraft, (dV/dt) is a derivative with respect to time of the speed V, and Kp and Kd are predetermined parameters.16. A display system for an aircraft, comprising:a central unit configured to determine a speed vector of the aircraft and to determine a longitudinal margin of maneuver of the aircraft; anda display unit connected to the central unit and including a display screen configured to display a first characteristic sign illustrating the speed vector and a second characteristic sign illustrating the longitudinal margin of maneuver, wherein a distance between the first characteristic sign and the second characteristic sign is proportional to the longitudinal margin of maneuver.17. The display system of claim 16, wherein:the longitudinal margin of maneuver is expressed as a load factor and is related to one of a pitch-up maneuver and a pitch-down maneuver;the display screen is a heads-up display screen;the first characteristic sign is shaped as a diamond; andthe second characteristic sign is shaped as a chevron.18. The display system of claim 16, wherein the central unit includes:a first determining unit configured to determine a longitudinal margin of maneuver related to a pitch-up maneuver; anda second determining unit configured to determine a longitudinal margin of maneuver related to a pitch-down maneuver, wherein:the first determining unit determines the longitudinal margin by selecting the smaller of a first load factor margin and an angle of incidence margin; andthe second determining unit determines the longitudinal margin by selecting the smaller of a first load factor margin and a speed margin.19. The display system of claim 18, wherein:the angle of incidence margin is calculated from the following expression:Δα=1?[(Nz/ΔNmax)*((αmax?α)/(α?α0))],wherein Δα is the angle of incidence margin, Nz is a load factor, ΔNmax is a maximum value of margin of maneuver depicted, α is a angle of incidence, αmax is a maximum angle of incidence, and α0 is a zero lift angle of incidence; andthe speed margin is calculated from the following expression:ΔV=1?[(Nz+Kp(Vmax?V)?Kd(dV/dt))/ΔNmax],wherein ΔV is the speed margin, Nz is a load factor, ΔNmax is a maximum value of margin of maneuver depicted, V is a speed of the aircraft, Vmax is a maximum speed of the aircraft, (dV/dt) is a derivative with respect to time of the speed V, and Kp and Kd are predetermined parameters.20. The display system of claim 16, wherein the display unit displays the second characteristic sign only when the determined longitudinal margin of maneuver is less than a predetermined value.