Energy Protection Device For An Aircraft

Abstract

The device (1) comprises means (12, 14, 15) for automatically deactivating an energy protection function and for automatically managing an autothrottle (2), when the return of the aircraft in an operational flight domain is detected after the activation of the protection function.

Description

The present invention relates to an energy protection device for an aircraft, more specifically a transport airplane.

More precisely, said device is intended for protecting the aircraft from low energy situations (low speed, high incidence, low engine thrust) able to jeopardize the safety of the aircraft, more specifically near the ground.

Generally, such a device usually comprises:

• • means for monitoring, upon a flight of the aircraft, automatically and repeatedly, a plurality of data of the aircraft so as to be able to detect a low energy situation, for which conditions relative to a low energy are met; and
  • means for automatically activating, in the case where such a low energy situation is detected, a protection function involving automatically engaging an autothrottle (<<autothrust>> ATHR) and automatically controlling the engines of the aircraft so that they supply a maximum thrust.

The protection function being defined in guiding and flight control calculators for the aircraft, thus generates, in all cases where the aircraft is in a low energy situation, an automatic increase of the thrust so as to achieve the maximum engine thrust, and this whatever the initial position of the throttles of the aircraft.

From documents FR-2 890 645 and WO-2007/031634, an energy protection device is known for an airplane being provided with at least one engine arranged on each one of its wings and with at least one additional engine. Such a protection device has a broad domain of use, wherein the safety of the airplane is maintained. To this end, it comprises means for inhibiting the protection function, but inhibiting such a function only when all the engines being arranged on one single same wing of the airplane are simultaneously defective, such a situation making critical the dissymmetry created for the lateral control of the airplane, allowing the number of inhibition cases to be considerably reduced. Consequently, such a protection device has a much broader domain of use than a usual device, in particular in the case of one single engine becoming defective or in the case of two engines becoming defective, being arranged on different wings.

When the conditions for triggering a previously activated protection function are no longer met, the autothrottle remains engaged, the maximum thrust is still applied to the engines, and an appropriate message is displayed on a flight mode annunciator of the aircraft.

The protection function could, indeed, be disengaged thru disengaging the autothrottle, requiring a manual action from the pilot. More precisely, in order to disengage the autothrottle, the pilot should act on a dedicated disconnection means, or on the throttles so as to bring them in the idling position, or even on a controlling means relative to the autothrottle on a display of the FCU (<<Flight Control Unit>>) type.

Consequently, current airplanes exhibit the following restriction. In order to get out of the above mentioned protection mode, pilots have to disconnect manually the autothrottle as a result of the protection function being triggered and this even if the autothrottle was engaged before this protection function was triggered, in order to omit maintaining the blocked engine thrust at the maximum thrust of the TOGA type. The crew have afterwards to re-engage the autothrottle for continuing the flight, if the autothrottle is used for the remainder of the flight. So, the crew must sometimes carry out various successive actions so as to return back to a situation being compatible with the remainder of the flight. The crew's workload is thus significant in such a situation.

The present invention aims at solving these drawbacks. It relates to an energy protection method for an aircraft provided with at least one engine and one autothrottle allowing for automatically managing going out of a protection function.

To this end, according to the invention, said method wherein:

a) during a flight of the aircraft, automatically and repeatedly, a plurality of data of the aircraft is monitored, so as to be able to detect a triggering situation, for which conditions for triggering an energy protection are met; and

b) in the case where a triggering situation is detected, a protection function is automatically activated, involving automatically engaging said autothrottle if it is not already engaged and automatically controlling the engine(s) of the aircraft so that they provide a maximum thrust, is remarkable in that, in addition:

c) in the case where the protection function is triggered, the engagement state of the autothrottle is automatically recorded upon said triggering, and a monitoring is implemented, involving automatically and repeatedly monitoring parameters of the aircraft, so as to be able to detect a return back to a predetermined operational flight domain; and

d) in the case of a return of the aircraft back to said operational flight domain being detected, the protection function is automatically deactivated and the autothrottle is automatically brought in an engagement state depending on said recorded engagement state (upon triggering the protection).

Thus, thanks to the invention, in the case of a return of the aircraft back to a particular operational flight domain being detected, to be set forth hereinunder, the protection function is automatically deactivated and the state of the autothrottle is automatically managed. No action is thus required from a pilot in such a phase of going out of the energy protection mode, allowing, more specifically, overcoming the above mentioned drawbacks.

Moreover, as set forth hereinunder, the autothrottle is (automatically) brought in a state depending on the previously recorded engagement state upon triggering the protection function, such a new state being adapted to the flight phase able to be implemented at the current time, as set forth hereinunder.

Advantageously, at step c), a return of the aircraft back to said operational flight domain is detected, when the two following conditions are simultaneously met:

• • the current corrected speed (of the VCAS type) of the aircraft is higher, during at least one predetermined period of time, than the sum of a reference speed (of the VLS type) depending on the current flight configuration of the aircraft and of a predetermined threshold value; and
  • the conditions for triggering the energy protection are not longer achieved.

Furthermore, in a first embodiment, at step d):

d1a) if the memorized engagement state indicates that the autothrottle was engaged upon triggering the protection function, said autothrottle is maintained engaged. In this case, the thrust applied to the engines of the aircraft is thus fully managed by the autothrottle; and

d1b) if the memorized engagement state indicates that the autothrottle was disengaged upon said triggering, said autothrottle is automatically disengaged, out of a particular situation of going around of the aircraft. In such a case, the thrust applied to the engines (upon going out of the energy protection function) corresponds to the manual thrust controlled by a pilot via the throttle.

Furthermore, advantageously, if the aircraft is in a going around situation in the case of a return back to the operation flight domain being detected, and if it is not in a smooth configuration, the autothrottle is maintained engaged at step dib), enabling to anticipate a homogeneous behaviour with the situation existing out of protection.

In addition, in a second embodiment, at step d)

d2a) if the memorized engagement state indicates that the autothrottle was engaged upon triggering the protection function, said autothrottle is maintained engaged; and

d2b) with the exception of two above described particular situations, if the memorized engagement state indicates that the autothrottle was disengaged upon said triggering, said autothrottle is maintained engaged, but the target speed of said autothrottle is synchronized with a maneuver speed. Such synchronization allows for a return back to a target speed adapted for the flight point.

Advantageously, said maneuver speed depends on the aerodynamic configuration of the aircraft upon the detection of a return of the aircraft back to the operational flight domain.

Moreover, advantageously, at step d2b), if the aircraft is in one of the two following particular situations: a going around situation in a hypersustained configuration and a selected approach situation, the speed of the autothrottle is not synchronized, as it is already adapted for the corresponding situation. Indeed:

• • the target speed upon going around is the current speed of the airplane as memorized upon going around; and
  • the target speed upon a selected approach is the approach speed as calculated by a flight management system of the FMS type.

The present invention further relates to an energy protection device for an aircraft, in particular a transport airplane, being provided with at least one engine and one autothrottle.

According to this invention, said device being embedded and comprising:

• • means for checking, upon a flight of the aircraft, automatically and repeatedly, a plurality of data of the aircraft so as to be able to detect a triggering situation, for which conditions for triggering an energy protection are met; and
  • means for automatically activating, in the case where a triggering situation is detected, a protection function involving automatically engaging said autothrottle and automatically controlling the engine(s) of the aircraft so that they supply a maximum thrust,is remarkable in that, in addition, it comprises:
  • means for automatically recording, in the case where the protection function is triggered, the engagement state of the autothrottle upon said triggering;
  • means for, in the case where said protection function is triggered, implementing a monitoring, involving automatically and repeatedly monitoring parameters of the aircraft, so as to be able to detect a return of the aircraft back to a predetermined operational flight domain; and
  • means for, in the case a return of the aircraft is detected back to said operational flight domain, automatically deactivating the protection function and automatically bringing the autothrottle in an engagement state depending on said recorded engagement state.

Such a device according to this invention thus allows to automatically go out of a preliminarily activated energy protection function, and to avoid maintaining the blocked engine thrust at the maximum thrust of the TOGA type.

The present invention further relates to an aircraft, in particular a transport airplane, comprising a device such as mentioned hereinabove.

The FIGS. of the appended drawing will better explain how this invention can be implemented. In these FIGS., like reference numerals relate to like components.

FIG. 1 is the block diagram of a device according to this invention.

FIG. 2 is the block diagram of a particular embodiment of means being part of a device according to this invention, being able to detect a return of the aircraft back to a predetermined operational flight domain.

The device 1 according to this invention and schematically shown on FIG. 1 is an energy protection device for an (not shown) aircraft, in particular a transport airplane, being provided with at least one, but preferably with a plurality of usual engines M, as well as with one autothrottle 2.

This device 1 comprises to this end means, to be set forth hereinunder, allowing to protect the aircraft from low energy situations (low speed, high incidence, low engine thrust) able to jeopardize the safety, more specifically near the ground.

To this end, said device 1 is of the usual type comprising:

• • monitoring means 3 for automatically monitoring, upon a flight of the aircraft, a plurality of data of said aircraft so as to be able to detect, in a usual way, a triggering situation, for which the conditions for triggering an energy protection are met; and
  • controlling means 4 being connected via a link 19 to said monitoring means 3 and being formed so as to automatically activate a protection function (preferably of the <<ALPHA FLOOR>> type), in the case a triggering situation is detected by said monitoring means 3. This protection function involves automatically controlling said engines M so as to modify the thrust being delivered so that they each supply a maximum thrust. To this end, said controlling means 4 are connected via links 5 to usual means 6 intended for modifying the thrust exerted by said engines M, more specifically modifying the fuel supply of said engines M. Said controlling means 4 also automatically engage (via a link 7) said autothrottle 2 being, for instance, connected via a link 8 to said means 6.

Obviously, if the protection function is not activated, the different engines M of the aircraft are usually controlled, following usual orders generated, more specifically, by the pilot of the aircraft using the (not shown) throttle.

Said device 1 could further comprise a display means 9 being connected via a link 10 to a unit 11 (to be set forth hereinunder) and being able to display a message warning a pilot of the aircraft about any activation of the protection function, for instance, displaying an appropriate message on a screen, such as a primary flight screen of the PFD (<<Primary Flight Display>>) type for instance.

In a particular embodiment, said monitoring means 3 comprise a plurality of (not shown) sensors for respectively measuring at least some of the following parameters: the incidence of the aircraft, the angle of pitch of the aircraft, the pitching rate, the speed of the aircraft, as well as its deceleration rate, the Mach number of the aircraft, the position of slats and flaps of the aircraft, the radio-altitude height of the aircraft. The means 3 monitor such parameters for being able to detect low energy situation of the aircraft.

Preferably, said monitoring means 3 detect a triggering situation for activating said protection function, if the energy of the aircraft is excessively low, in one of the two following cases:

• • the leading edge of the aircraft is larger than a protection value (or the angle of pitching is larger than a predetermined threshold and the order of the joystick is larger than a predetermined threshold to pull up); and
  • the filtered leading edge becomes larger than thresholds defined by the flight qualities.

Thus, upon the activation of the protection function, the different following actions are implemented:

• • an automatic engagement of the autothrottle 2;
  • an application of the maximum thrust to the engines M; and
  • a display of a corresponding message on a flight mode annunciator of the aircraft of the FMA (<<Flight Mode Annunciator>>) type, being, for instance, located on the upper part of a primary flight screen of the PFD type.

According to this invention, said device 1 further comprises:

• • means 12 (connected for instance via a link 13 to the autothrottle 2) for automatically recording, in the case where the protection function is triggered, on a usual storing means, the engagement state of the autothrottle 2 (engaged autothrottle or disengaged autothrottle) upon triggering an energy protection by the means 3 and 4;
  • means 14 for, in the case where said protection function is triggered, implementing a monitoring, involving automatically and repeatedly monitoring parameters of the aircraft, so as to be able to detect a return of the aircraft back to a predetermined operational flight domain; and
  • means 15 being connected via links 16 and respectively to said means 14 and 12 and being formed so as to automatically implement the following operations, in the case where the means 14 detect a return of the aircraft back to said operational flight domain:
    • automatically deactivating the protection function, for instance via a link 18; and
    • automatically bringing the autothrottle 2 in an engagement state depending on said engagement state recorded by the means 12, for instance via a link 20.

Thus, in the case of a detection of a return of the aircraft back to a particular operational flight domain, to be set forth hereinunder, the device 1 according to this invention automatically deactivates the protection function and automatically manages the state of the autothrottle 2. No action is thus required from the pilot in such a phase of going out of the energy protection mode.

Moreover, as set forth hereinunder, the autothrottle 2 is brought (automatically) in a state depending on the prior previously recorded engagement state, such a state being adapted for the flight phase able to be implemented at the current moment, as set forth hereinunder.

In a particular embodiment, said means 4, 12, and 15 could, more specifically, be part of a control unit 11.

Furthermore, the means 14 detect a return of the aircraft back to said operational flight domain, when the two following condition are simultaneously met:

• • first condition: the current corrected speed VCAS of the aircraft is larger, during at least one predetermined period of time, than the sum of a reference speed depending on the current flight configuration of the aircraft, of the VLS type, and of a predetermined threshold value; and
  • second condition: the conditions for triggering the energy protection are no longer met, such a condition being, for instance, deduced from a piece of information received from the means 3 via a link 21.

In a particular embodiment, shown on FIG. 2, said means 14 comprise:

• • usual means 24 for determining a speed VLS of the aircraft;
  • means 25 for summing the speed VLS received from the means 24 and a threshold value being, for instance, recorded in a usual memory 26;
  • usual means 27 for determining a current corrected speed VCAS of the aircraft;
  • means 28 for comparing the received speed VCAS received from the means 28 with the sum received from the means 25 and for checking whether the speed VCAS is larger than said sum;
  • usual means 29 for checking that the speed VCAS is higher than said sum for a predetermined period of time; and
  • an AND logic gate 31 for detecting a return of the aircraft back to said operational flight domain when the two following conditions are simultaneously met:
    • the speed VCAS is larger than said sum for said predetermined period of time, such a condition being received from the means 29; and
    • the conditions for triggering the energy protection are no longer met, such a condition being, for instance, received from means 30. To this end, the means 30 reverse the piece of information of the achievement of the triggering conditions received via the link 21.

The above mentioned threshold value is defined so that the energy protection is not triggered again immediately after going out of the protection, so as to avoid too frequent switches.

Hereinafter, two embodiments are provided according to this invention, allowing to go out automatically of the protection function and to omit maintaining the blocked engine thrust at the maximum thrust TOGA.

In a first embodiment:

• • if the engagement state memorized by the means 12 indicates that the autothrottle 2 was engaged upon triggering the protection function, said autothrottle 2 is maintained engaged. In such a case, the thrust applied to the engines M of the aircraft is thus fully managed by the autothrottle 2 if the latter is active; and
  • if the engagement state memorized by the means 12 indicates that the autothrottle 2 was disengaged upon said triggering, said autothrottle 2 is automatically disengaged, outside of a particular going around situation of the aircraft. In such a case, the thrust applied to the engines M (upon going out of the energy protection function) corresponds to the manual thrust controlled by the throttle.

On the other hand, if the aircraft is in a particular <<Go-Around>> situation, in the case of a return back to the operational flight domain being detected, the autothrottle 2 is maintained engaged. This is therefore an exception to the principle involving memorizing the engagement state of the autothrottle 2 in a go around case, in the case where the aircraft is not in a smooth aerodynamic configuration (slats/flaps). In a go around case in a hypersustained aerodynamic configuration, after the protection function has been activated, the autothrottle 2 must remain engaged after the return back to the operational flight domain, even if it was initially disengaged. Indeed, generally (except for a protection case), the autothrottle 2 is engaged when the crew trigger the go around.

The exception involving maintaining the autothrottle 2 engaged even if it was not engaged before the protection function is triggered allows to recover a homogeneous behaviour with the out of protection function situation of the ALPHA FLOOR type.

Moreover, in a second embodiment:

• • if the engagement state memorized by the means 12 indicates that the autothrottle 2 was engaged upon triggering the protection function, said autothrottle 2 is maintained engaged by the means 15; and
  • with the exception of two particular situations, to be set forth hereinunder, if the engagement state memorized by the means 12 indicates that the autothrottle 2 was disengaged upon said triggering, said autothrottle 2 is maintained engaged. On the other hand, the device 1 (for instance via the means 15) synchronizes the target speed of the autothrottle 2, that is the speed that the autothrottle 2 tries to achieve, on a maneuver speed. Such synchronization enables to recover a target speed adapted for the flight point.

Advantageously, said maneuver speed depends on the aerodynamic configuration of the aircraft upon the detection of a return of the aircraft back to the operational flight domain.

By way of illustration, the maneuver speed is as set forth hereinunder, in the case of an airplane comprising the following usual aerodynamic configurations of its slats and flaps (that is, the position of the latter): a so-called <<smooth>> configuration, such a configuration being referred to as 1, a so-called configuration 2, a so-called configuration 3, and a so-called <<Full>> configuration.

In such a case, the maneuver speed preferably corresponds:

• • in the smooth configuration, to the maximum fineness speed, referred to as <<green dot speed>>;
  • in the configuration 1, to a speed S recommended upon take-off for selecting the smooth configuration;
  • in the configuration 2, to a speed F2 recommended in configuration 2 in an approach for selecting the configuration 3;
  • in the configuration 3, to a speed F3 recommended in configuration 3 in an approach for selecting the configuration Full; and
  • in the configuration Full, to the sum of the speed VLS and of a predefined threshold.

An exception is applied (no re-synchronization of the target speed, even if the autothrottle 2 was disengaged before the protection function) in the case of a go around in a hypersustained aerodynamic configuration or if an approach FMS phase has been selected. In these two cases, the target speed is relevant, it is therefore not required to resynchronize it.

Indeed:

• • the target speed upon going around is the current speed of the aircraft as memorized upon going around; and
  • the target speed upon a selected approach is the approach speed calculated by the <<Flight Management System>> or FMS system.

Consequently, in this second embodiment, the autothrottle 2 is still maintained engaged after the protection function has been triggered, when the aircraft returns back to the operational flight domain, except in the two previous situations. However, if the autothrottle 2 was initially disengaged before the protection function was triggered, the target speed is resynchronized with the maneuver speed, so as to recover a relevant target speed as a function of the flight point.

Claims

1. An energy protection method for an aircraft being provided with at least one engine (M) and one autothrottle, said method enabling to protect the aircraft from low energy situations, said method wherein: a) upon a flight of the aircraft, automatically and repeatedly, a plurality of data of the aircraft is monitored, so as to be able to detect a triggering situation, for which conditions for triggering an energy protection are met; andb) in the case where a triggering situation is detected, a protection function is automatically activated, involving automatically engaging said autothrottle if it is not already engaged and automatically controlling said engine(M) so that it supplies a maximum thrust,

2. The method according to claim 1, wherein, at step c), a return of the aircraft back to said operational flight domain is detected, when the two following conditions are simultaneously met: the current corrected speed of the aircraft is larger, during at least one predetermined period of time, than the sum of a reference speed depending on the current flight configuration of the aircraft and of a predetermined threshold value; andthe conditions for triggering the energy protection are not longer achieved.

3. The method according to claim 1, wherein at step d):d1a) if the memorized engagement state indicates that the autothrottle was engaged upon triggering the protection function, said autothrottle is maintained engaged; andd1b) if the memorized engagement state indicates that the autothrottle was disengaged upon said triggering, said autothrottle is automatically disengaged, out of a particular situation of going around of the aircraft.

4. The method according to claim 3, wherein, if the aircraft is in a go around situation in the case a return back to the operational flight domain is detected and if it is not in a smooth configuration, the autothrottle is maintained engaged at step d1b).

5. The method according to claim 1, wherein at step d):d2a) if the memorized engagement state indicates that the autothrottle was engaged upon triggering the protection function, said autothrottle is maintained engaged; andd2b) with the exception of two particular situations, if the memorized engagement state indicates that the autothrottle was disengaged upon said triggering, said autothrottle is maintained engaged, but a target speed of the autothrottle is synchronized with a maneuver speed.

6. The method according to claim 5, wherein said maneuver speed depends on the aerodynamic configuration of the aircraft upon the detection of a return of the aircraft back to the operational flight domain.

7. The method according to claim 1, wherein at step d2b), if the aircraft is not in one of the two following particular situations: a go around situation in a hypersustained configuration and a selected approach situation, the speed of the autothrottle is not synchronized.

8. An energy protection device for an aircraft being provided with at least one engine (M) and one autothrottle, said device enabling to protect the aircraft from low energy situations, comprising: means for checking, upon a flight of the aircraft, automatically and repeatedly, a plurality of data of the aircraft so as to be able to detect a triggering situation, for which conditions for triggering an energy protection are met; andmeans for activating automatically, in the case where a triggering situation is detected, a protection function involving automatically engaging said autothrottle if it is not already engaged and automatically controlling said engine (M) so that it supplies a maximum thrust,

9. An airplane, wherein it comprises a device such as specified in claim 8.