CS263822B1 - Wiring for indication of aircraft flight modes - Google Patents

Abstract

The solution relates to a circuit for indicating the limit flight modes, especially those approaching the aircraft crash limit. The circuit is formed in such a way that the output of the normal overload multiple sensor is connected to the input of a root-extraction circuit, the output of which is connected to the first input of at least one multiplier, while the constant input is connected to the second input of the multiplier and the output of the multiplier is connected to the first input of a comparator circuit, the second input of which is connected to the output of the instrument airspeed sensor and the output of the comparator circuit is connected to the indicator.

Description

(57) The solution concerns engagement to indicate limit flight modes, in particular those approaching the aircraft crash limit. The wiring is designed such that the output of the normal overload multiplier sensor is connected to the input of the rooting circuit, the output of which is connected to the first input of at least one multiplier, the constant input is connected to the second multiplier input and whose second input connects the instrument speed sensor output and the comparator circuit output is connected to the indicator.

CS 263 822 Bl

»R. X

The invention relates to circuitry for indicating flight limit modes of an aircraft, in particular those approaching the aircraft crash limit.

In prior art aircraft, the pilot either does not receive such instrument information at all, or receives instrument information obtained by measuring the approach angle. In this case it is necessary to place a sensor of attack angle on the surface of the aircraft, which both complicates the design of the aircraft and secondly the sensor can be easily damaged in operation.

These disadvantages are avoided by the circuitry for indicating the limit modes according to the invention. It consists in that it consists of a normal overload multiple sensor whose output is connected to the input of the rooting circuit, the output of which is connected to the first input of at least one multiplier, with the constant input connected to the second multiplier input and the multiplier output connected to the first a comparator circuit input to which a second instrument speed sensor output is connected and a comparator circuit output is connected to an indicator.

The advantage of the wiring according to the invention is that it does not require any special flight parameter sensors, but processes instrument information of the multiple of normal overload and instrument speed, which is measured on board as standard instrument basic information for practical piloting. The wiring of the invention can also advantageously be integrated with the on-board electronic systems.

Claims (2)

FIG. 1 shows an example of a circuit according to the invention. The output of the normal overload multiple sensor 1 is connected to the input of the square root circuit 2, whose output is connected to the first input of the multiplier 3, the constant input 7 is connected to the second input of the multiplier 3 and the output of the multiplier 3 is connected to the first input of the comparison circuit whose second input is connected to the output of the instrument speed sensor 5. The output of the comparator circuit 4 is connected to the indicator 6. The function of the circuit according to the invention is as follows: in a known manner, the 1-times normal overload sensor senses the instantaneous value of the normal overload multiple n _y . This value is fed to the Root 2 where it is rooted and the square root value is applied to the first input of the multiplier 3. A constant k is applied to the second input of the multiplier 3, the value of which corresponds to the minimum allowable instrument flight speed. The multiplier 3 performs the product of kin _y ⁰ · ⁵ , which is applied to the first input of the comparator circuit 4. The instrument speed sensor 5 senses in a known manner the instantaneous instrument speed value vp. This value is applied to the second input of comparison circuit 4. In comparison circuit 4, the values of the product Κην ^θ · ⁵ and the instrument speed vp are compared. The result of the comparison is applied to the input of indicator 6. In this example, indicator 6 is an incandescent lamp whose light indicates to the pilot that the instantaneous flight mode is a marginal mode, beyond which there is a real risk of aircraft falling. In FIG. 2 shows a branched limit flight signaling system using the circuitry of the invention. The description of the wiring and its functions are the same as in the previous example, except that the values of the constants k1, k2, k3 are suitably selected such that the sequence of operation of the indicators 6 expresses the nature of the flight mode change to the limit mode. ρΚεομϊτ A circuit for indicating flight limit modes of an aircraft, characterized in that it consists of a normal overload multiplier sensor (1), the output of which is connected to the input of the rooting circuit (2J), the output of which is connected to the first input of at least one multiplier (3); the multiplier (3) is connected to the first input of the comparison circuit (4), to the second input of which the output of the instrument speed sensor (5) is connected, the output of the comparison circuit (4) is connected to the indicator (6).