Method and system for determining a minimum-thrust synchronous descent and rejoining profile for an aircraft
First Claim
1. A method for determining a minimum-thrust descent and rejoining profile in respect of a target point by an aircraft,the permanently minimum-thrust descent profile being defined from a first initial state of the initial aircraft up to a second final state of the aircraft temporally constrained,the first initial state of the aircraft comprising a first geodesic position Qi of departure, an initial time ti, a first initial altitude hi, a first initial speed of the aircraft {right arrow over (Vι
- )} relative to the ground and a first wind speed {right arrow over (Wι
)},the second final state of the aircraft comprising a second geodesic position Qf of arrival at the target point, a final constraint time tf, a second final altitude hf, a second final speed of the aircraft {right arrow over (Vf)} relative to the ground and a second wind speed {right arrow over (Wf)}, the method comprisinga first step of computing an energy differential of the aircraft in the air Δ
Ea between the first initial state of the aircraft and the second final state of the aircraft; and
a second step, subsequent to the first step ofproviding an adjustable modelled profile of altitude hm(t) and of air speed Vam(t) of the aircraft, corresponding to an air descent strategy which permanently ensures an engine regime at minimum thrust and using one or more adjustable parameters, and thenadjusting the adjustable parameter or parameters so that an adjusted profile of altitude h(t) and of air speed va(t) of the aircraft ensures the consumption of the variation of energy of the aircraft in the air Δ
Ea within the required timespan Δ
trequired, and the required altitude variation hi−
hf within the required timespan with permanently an engine regime with constant and minimum thrust; and
a third step, subsequent to the second step, of determining a lateral geodesic trajectory P(t) of the aircraft on the basis of the adjusted altitude profile h(t), of the adjusted air speed profile Va(t) and of the knowledge of the speeds of the winds in the aircraft'"'"'s scheduled geographical traversal zone.
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Abstract
A method for determining a minimum-thrust descent and rejoining profile in respect of a target point by an aircraft comprises a first step of computing an energy differential of the aircraft in the air ΔEa between a first initial state of the aircraft at an initial geodesic point Qi and a second final state of the aircraft at the final arrival target point Qf. The method comprises a second step of adjusting an adjustable modelled profile of altitude hm(t) and of air speed Vam(t) of the aircraft with the aid of parameters so the adjusted modelled profile of altitude h(t) and of air speed Va(t) of the aircraft ensures the consumption of the variation of energy of the aircraft in the air ΔEa in a fixed required timespan Δtrequired and a fixed required altitude variation tf−ti in the required time timespan, the aircraft operating permanently in an engine regime with constant and minimum thrust. The method comprises a third step of determining a lateral geodesic trajectory of the aircraft on the basis of the adjusted altitude profile h(t), of the adjusted air speed profile Va(t) and of the knowledge of the speeds of the winds in the aircraft'"'"'s scheduled geographical traversal zone.
15 Citations
16 Claims
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1. A method for determining a minimum-thrust descent and rejoining profile in respect of a target point by an aircraft,
the permanently minimum-thrust descent profile being defined from a first initial state of the initial aircraft up to a second final state of the aircraft temporally constrained, the first initial state of the aircraft comprising a first geodesic position Qi of departure, an initial time ti, a first initial altitude hi, a first initial speed of the aircraft {right arrow over (Vι - )} relative to the ground and a first wind speed {right arrow over (Wι
)},the second final state of the aircraft comprising a second geodesic position Qf of arrival at the target point, a final constraint time tf, a second final altitude hf, a second final speed of the aircraft {right arrow over (Vf)} relative to the ground and a second wind speed {right arrow over (Wf)}, the method comprising a first step of computing an energy differential of the aircraft in the air Δ
Ea between the first initial state of the aircraft and the second final state of the aircraft; anda second step, subsequent to the first step of providing an adjustable modelled profile of altitude hm(t) and of air speed Vam(t) of the aircraft, corresponding to an air descent strategy which permanently ensures an engine regime at minimum thrust and using one or more adjustable parameters, and then adjusting the adjustable parameter or parameters so that an adjusted profile of altitude h(t) and of air speed va(t) of the aircraft ensures the consumption of the variation of energy of the aircraft in the air Δ
Ea within the required timespan Δ
trequired, and the required altitude variation hi−
hf within the required timespan with permanently an engine regime with constant and minimum thrust; anda third step, subsequent to the second step, of determining a lateral geodesic trajectory P(t) of the aircraft on the basis of the adjusted altitude profile h(t), of the adjusted air speed profile Va(t) and of the knowledge of the speeds of the winds in the aircraft'"'"'s scheduled geographical traversal zone. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
- )} relative to the ground and a first wind speed {right arrow over (Wι
-
14. A system for determining a minimum-thrust descent and rejoining profile in respect of a target point by an aircraft, the permanently minimum-thrust descent profile being defined from a first initial state of the initial aircraft up to a second final state of the aircraft constrained temporally by a final arrival time tf or a required temporal timespan Δ
- trequired,
the first initial state of the aircraft comprising a first geodesic position Qi of departure, an initial time ti, a first initial altitude hi, a first initial speed of the aircraft {right arrow over (Vι
)} relative to the ground and a first wind speed {right arrow over (Wι
)},the second final state of the aircraft comprising a second geodesic position Qf of arrival at the target point, a final constraint time tf, a second final altitude hf, a second final speed of the aircraft {right arrow over (Vf)} relative to the ground and a second wind speed {right arrow over (Wf)}, the said determining system comprising a database of the performance of the aircraft, a means for providing meteorological data of the environment wherein the aircraft is deploying, a ground station for providing the required final time or a required temporal timespan to the aircraft, and one or more electronic computers for computing the minimum-thrust descent and rejoining profile in respect of a target point, the said determining system being configured to in a first step, compute an energy differential of the aircraft in the air Δ
Ea between the first initial state of the aircraft and the second final state of the aircraft, and thenin a second step, provide an adjustable modelled profile of altitude hm(t) and of air speed Vam(t) of the aircraft corresponding to an air speed strategy with permanently a minimum engine thrust, and then adjust parameters of the said adjustable modelled profile so that the adjusted modelled profile obtained of altitude h(t) and of air speed Va(t) of the aircraft ensures the consumption of the variation of energy of the aircraft in the air Δ
Ea within the required timespan Δ
trequired, and the required altitude variation hi−
hf in the required time with permanently a minimum engine thrust; and
thenin a third step, determine a geodesic trajectory of the aircraft and a lateral geodesic trajectory on the basis of a type of lateral manoeuvre, of the adjusted altitude profile h(t), of the adjusted air speed profile va(t) and of the knowledge of the speeds of the winds in the aircraft'"'"'s scheduled geographical traversal zone. - View Dependent Claims (15, 16)
- trequired,
Specification