Method and device for enhancing the braking efficiency of an aircraft during the ground run thereof
View Patent ↗According to the invention, the elevators ( 8 ) and/or the adjustable horizontal stabilizer ( 6 ) are operated in such a way that a negative lift (DP 2 ) is generated and a nose-up moment (CDP) is thus created to counter the nose-down moment (CB) resulting from braking. The value of the negative lift (DP 2 ) matches the vertical force exerted by the ground on the front landing gear ( 12 ), which force is subject to a reference value (Fav 3 ).
1. A method for enhancing the braking efficiency of an aircraft ( 1 ) taxiing on the ground (S), said aircraft ( 1 ) comprising an elongated fuselage ( 2 ) and being provided:
with a main landing gear ( 10 ), disposed in an intermediate position of said fuselage ( 2 ) and comprising wheels ( 11 ) provided with brakes;
with a steerable front landing gear ( 12 ), disposed at the front of said fuselage ( 2 ) and being used to laterally guide said aircraft ( 1 ) on the ground, said front landing gear ( 12 ) comprising wheels ( 13 ) without brakes; and
with controllable aerodynamic surfaces ( 6 , 8 ) disposed at the rear of the fuselage ( 2 ) and capable of generating a variable negative lift force (DP), wherein:
in a preliminary phase, a reference value (Fav 3 ) is determined for the vertical force (Fav) exerted by the ground (S) on said front landing gear ( 12 ), said reference value being capable of ensuring a satisfactory efficiency of said front landing gear ( 12 ) for the lateral guiding of said aircraft ( 1 ) when the latter is taxiing on the ground (S); then
while said aircraft ( 1 ) taxiing on the ground (S) is braking:
the instantaneous vertical force (Fav) actually exerted by the ground (S) on said front landing gear ( 12 ) is measured; and
said rear aerodynamic surfaces ( 6 , 8 ) are controlled so that they generate a negative lift value (DP 2 ) capable of maintaining said instantaneous vertical force (Fav) at a value at least approximately equal to said reference value (Fav 3 ).
2. The method as claimed in claim 1 ,
wherein said negative lift value (DP 2 ) decreases with the speed of said aircraft ( 1 ).
3. The method as claimed in claim 1 , applied to an aircraft ( 1 ) comprising an adjustable horizontal stabilizer ( 6 ) and elevators ( 8 ) hinged on said adjustable horizontal stabilizer ( 6 ), wherein said negative lift value (DP 2 ) is obtained at least partly by controlling said adjustable horizontal stabilizer ( 6 ).
4. The method as claimed in claim 1 , applied to an aircraft ( 1 ) with rear aerodynamic surfaces that include elevators ( 8 ), wherein said negative lift value (DP 2 ) is obtained at least partly by controlling said elevators ( 8 ).
5. The method as claimed in claim 4 ,
wherein said negative lift value (DP 2 ) is obtained by controlling the elevators ( 8 ) alone and in that the characteristic giving the deflection angle (δq) of said elevators ( 8 ) is modified according to the deflection command (δm), such that, when said deflection command (δm) is zero, the deflection angle (δq) assumes a nose-up value (−δqo).
6. The method as claimed in claim 5 ,
wherein the absolute value |δqo| of said nose-up value (−δqo) decreases with the speed of said aircraft ( 1 ).
7. A device for implementing the method as claimed in claim 6 , provided with means ( 17 , 19 ) generating a characteristic ( 14 ) giving the deflection angle (δq) of the elevators ( 8 ) according to a deflection command (δm), said characteristic ( 14 ) having a neutral point (N) (for which δq=0 and δm=0),
wherein it comprises:
means ( 22 ) for continuously measuring the vertical force (Fav) exerted on said steerable front landing gear ( 12 ), when said aircraft ( 1 ) is taxiing on the ground with the brakes being applied;
memory means ( 23 ), in which is stored said reference value (Fav 3 );
comparison means ( 24 ) receiving said continuous measurement of said vertical force (Fav) and said reference value (Fav 3 ) and calculating the difference;
computation means ( 27 ) receiving said difference and a measurement of the taxiing speed (V) of said aircraft and delivering, for the deflection angle (δq) of said elevators ( 8 ), a nose-up value (−δqo) that is nonzero when the deflection command (δm) is zero, said nonzero nose-up value decreasing with the speed (V) of the aircraft;
computation means ( 29 ) which, from said nonzero nose-up value, determine a modified characteristic ( 15 , 16 ) giving the deflection angle (δq) of the elevators ( 8 ) according to the deflection command (δm); and
switching means ( 18 ) for applying to said elevators ( 8 ) either said usual characteristic ( 14 ), or said modified characteristic ( 15 , 16 ), depending on whether the wheels ( 11 ) of the main landing gear ( 10 ) have the brakes applied or not.