Rapid detector of a wind gradient

Details Rapid detector of a wind gradient Rapid detector of a wind gradient

1980-01-07

1983-11-01

Smith, Jerry

Boots, shoes, and leggings

244181, 244183, 364434, G06G 770

Patent

active

044133219

DESCRIPTION:

BRIEF SUMMARY
The present invention concerns improvements in the process and in the system for the rapid detection of a wind gradient according to U.S. Pat. No. 4,281,383.
One will recall that the process according to the principal patent utilizes, for the detection of wind gradients, the relationship existing between the aerodynamic slope .gamma. a, the total slope .gamma..sub.T and the anemometric speed V, this relationship being expressed; ##EQU2## In this formula, g is the acceleration of gravity, s is the Laplace operator, Vsel is an assigned speed and A is a value which is substantially constant or zero, in the case of normal flight without disturbances, and which increases in the case of a gradient of wind, wind changing direction.
This process consists more particularly in detecting the variations of the magnitude A and delivering a warning signal when this value rises above a predetermined threshold.
It has been thought at first to attribute to this threshold a fixed value.
Such a solution presents, however, the drawback of not taking into account the ability of the aircraft to overcome the disturbances caused by the wind gradient.
The invention has therefore, from the outset, an object of eliminating this drawback. It proposes, to this effect, the improvement which consists, instead of comparing the value A to a fixed or variable reference value, to mixing this value A with a value representative of the capacity of the aircraft to overcome the wind gradient, in such a way as to obtain a composite signal which is compared to a reference value.
According to one feature of the invention, the value representative of the capacity of the aircraft to overcome the gradient of wind is the value of the incidence .alpha. of the aircraft, the value of the reference then being related to this incidence.
The invention has moreover for its purpose a process for the rapid detection of a wind gradient utilizing in the calculation the magnitude A, instead of the parameters .gamma. a and .gamma..sub.T as previously defined, the information thereon being supplied by an inertial guidance unit.
In order to achieve this goal, the invention proposes to obtain the magnitude A by effecting the derivative in relation to time of the difference between the speed V, supplied by a central anemometric unit, and the ground speed V.sub.x, detected by the inertial guidance unit.
Some embodiments of the invention will be described hereafter as non-limiting examples, with reference to the annexed drawings in which:
FIG. 1 is a block-diagram for a detection system for a gradient of wind, taking into account the present incidence of the aircraft, in the case where the magnitude A is calculated with the help of the parameters .gamma. a and .gamma..sub.T ;
FIG. 2 is a block-diagram of a circuit allowing the working out of the magnitude A, with the help of information supplied by an inertial guidance unit;
FIG. 3 is a diagram representing the variations of the wind speed, and of the aerodynamic speed of the aircraft, as a function of time, during a period when a wind gradient is produced;
FIGS. 4, 5 and 6 represent schematically a variometer equipped with a luminous signal of alarm of a rapid detection system of a wind gradient, the indications supplied by this improved variometer corresponding respectively to the three principal phases of the wind gradient.
With reference to FIG. 1, the signal representative of the magnitude A which can be furnished (arrow 1) by a circuit solving the equation: ##EQU3## is first transmitted to a filter 2 of the transfer function in the form ##EQU4## which serves to avoid instrument errors (in particular those which serve for the determination of .gamma..sub.T and of .gamma. a ) and which is sensitive to the change of direction of the magnitude A.
This filter 2 is itself connected to a directional circuit conductor 3 such as a diode whose function is to transmit only the signals (generally positive) corresponding to dangerous wind gradients being expressed by a sharp reduction in the anemometric speed of the airplane.


REFERENCES:
patent: 3265333 (1966-08-01), Montooth
patent: 3379396 (1968-04-01), Patterson
patent: 3510090 (1970-05-01), Falkner et al.
patent: 3614036 (1971-10-01), Foster
patent: 3618002 (1971-11-01), Stinson
patent: 3686626 (1972-08-01), Bateman et al.
patent: 3814912 (1974-06-01), Manke et al.
patent: 3840200 (1974-10-01), Lambregts
patent: 4012713 (1977-03-01), Greene et al.
patent: 4021010 (1977-05-01), Bliss
patent: 4281383 (1981-07-01), LeBrun

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