System and method for monitoring an aircraft participating in a formation flight.

Abstract

System and method for monitoring an aircraft participating in a formation flight. The monitoring system (10) of an aircraft (1) participating in a formation flight as a follower aircraft (1S) or as a lead aircraft (1L), includes electronic circuitry (14) configured to repeatedly perform the following steps: - receive (31) barometric altitude information from the lead aircraft; - receive (32) barometric altitude information from the follower aircraft; - calculate (33) a difference between the barometric altitude of the lead aircraft and the barometric altitude of the follower aircraft; - determine (34) an inconsistency between the barometric altitude of the follow aircraft (1S) and the barometric altitude of the lead aircraft (1L), in the context of formation flying, if the calculated difference is greater than a height value (H) of the vortex (V) at a current position of the follow aircraft, increased by a height margin;and - if such an inconsistency is determined, order (35) the issuance of an alert in the aircraft cockpit. Figure for the abbreviation: Fig. 2;

Description

Title of the invention: System and method for monitoring an aircraft participating in a formation flight.

[0001] The invention relates to the field of formation flight. As is known, formation flight of a group of aircraft reduces the overall fuel consumption of the group. In formation flight, a follower aircraft flies near a vortex generated by the lead aircraft it is following. The various aircraft participating in a formation flight fly close to one another, respecting a specific geometry with regard to the relative positions of the different aircraft participating in the formation flight. It is therefore important to ensure the safety of the different aircraft participating in the formation flight by preventing any risk of collision between them. All transport aircraft are equipped with a collision avoidance system called TCAS (Traffic Collision Avoidance System).This system is designed to detect a risk of collision between aircraft and to command an avoidance maneuver when such a risk is detected.

[0002] During formation flight, given that the aircraft fly close to one another, it would be advantageous to find a solution providing redundancy in the anti-collision monitoring of aircraft flying in formation. Description of the invention

[0003] The present invention aims in particular to provide a solution to this problem. It relates to a monitoring system for an aircraft participating in a formation flight in which a follower aircraft flies near a vortex generated by a lead aircraft, the aircraft corresponding to either the follower or the lead aircraft, the monitoring system comprising electronic circuitry integrated into at least one avionics computer of the aircraft, in which the electronic circuitry is configured to repeatedly implement the following steps during the aircraft's participation in the formation flight:

[0004] - receive barometric altitude information from the lead aircraft;

[0005] - receive barometric altitude information from the following aircraft;

[0006] - calculate a difference between the barometric altitude of the lead aircraft and the altitude barometric of the following aircraft;

[0007] - determine an inconsistency between the barometric altitude of the following aircraft and the barometric altitude of the lead aircraft, in the context of formation flight, if the calculated difference is greater than a vortex height value at a current position of the follow aircraft, plus a height margin; and

[0008] - if such an inconsistency is determined, order the issuance of an alert in the aircraft cockpit.

[0009] During a formation flight, the various aircraft participating in this formation flight are supposed to be positioned relative to each other according to a specific geometry such that a follow aircraft flies close to a vortex generated by a lead aircraft, the various aircraft being sufficiently spaced to avoid any risk of collision. The monitoring system according to the invention makes it possible to detect and report an inconsistency in the calculated difference between the barometric altitude of the lead aircraft and the barometric altitude of the follow aircraft, compared to a difference between the altitude of the lead aircraft and the altitude of the follow aircraft compatible with formation flight (corresponding at most to the height of the vortex plus the altitude margin). Consequently, the system allows monitoring of compliance with said specific geometry by the lead aircraft and the follow aircraft.Since this particular geometry is designed to avoid any risk of collision between aircraft participating in formation flight, the system's monitoring of compliance with said particular geometry is thus complementary to the collision avoidance monitoring performed by the TCAS system. Consequently, the monitoring system according to the invention is redundant with the TCAS system.

[0010] According to various embodiments which can be taken individually or in combination:

[0011] - the electronic circuitry comprises a first part integrated into a system TCAS type anti-collision monitoring and a second independent part of the TCAS type anti-collision monitoring system, in which the step of calculating the difference between the barometric altitude of the lead aircraft and the barometric altitude of the follow aircraft is implemented in the first part of the electronic circuitry and the step of determining an inconsistency between the barometric altitude of the follow aircraft and the barometric altitude of the lead aircraft is implemented in the second part of the electronic circuitry;

[0012] - the electronic circuitry is further configured to implement a step of receiving identification information from the lead aircraft when the aircraft matches the follow aircraft or a step of receiving identification information from the follow aircraft when the aircraft matches the lead aircraft;

[0013] - the electronic circuitry is further configured to determine in a way automatically provides identification information for the lead aircraft when the aircraft matches the follow aircraft or identification information for the follow aircraft when the aircraft matches the lead aircraft, based on information received from the follow aircraft and the lead aircraft;

[0014] - the electronic circuitry is further configured to control a disengagement of the aircraft from the formation flight in the event of determination of an inconsistency between the barometric altitude of the following aircraft and the barometric altitude of the lead aircraft.

[0015] The invention also relates to a method for monitoring an aircraft participating in a formation flight in which a follower aircraft flies near a vortex generated by a lead aircraft, the aircraft corresponding to one of the follower aircraft or the lead aircraft, the method comprising the following steps implemented repeatedly by electronic circuitry integrated into at least one avionics computer of the aircraft, during the aircraft's participation in the formation flight:

[0016] - receive barometric altitude information from the lead aircraft;

[0017] - receive barometric altitude information from the following aircraft;

[0018] - calculate a difference between the barometric altitude of the lead aircraft and the altitude barometric of the following aircraft;

[0019] - determine an inconsistency between the barometric altitude of the following aircraft and the barometric altitude of the lead aircraft, in the context of formation flight, if the calculated difference is greater than a vortex height value at a current position of the follow aircraft, plus a height margin; and

[0020] - if such an inconsistency is determined, order the issuance of an alert in the aircraft cockpit.

[0021] In one embodiment, the electronic circuitry comprises a first part integrated into a TCAS-type collision avoidance monitoring system and a second part independent of the TCAS-type collision avoidance monitoring system. The step of calculating the difference between the barometric altitude of the lead aircraft and the barometric altitude of the follow aircraft is implemented in the first part of the electronic circuitry, and the step of determining an inconsistency between the barometric altitude of the follow aircraft and the barometric altitude of the lead aircraft is implemented in the second part of the electronic circuitry.

[0022] In one embodiment, the method further includes a step of receiving identification information for the lead aircraft when the aircraft corresponds to the follower aircraft or a step of receiving identification information for the follower aircraft when the aircraft corresponds to the lead aircraft.

[0023] In another embodiment, the method further includes a step of automatically determining identification information for the lead aircraft when the aircraft matches the follow aircraft or identification information for the follow aircraft when the aircraft matches the lead aircraft, based on information received from the follow aircraft and the lead aircraft.

[0024] The invention also relates to an aircraft comprising such a surveillance system. Description of the implementation methods

[0025] The invention will be better understood upon reading the following description and examining the accompanying figures.

[0026] Fig. 1 is a view of an aircraft comprising a surveillance system according to an embodiment of the invention.

[0027] Figure [Fig.2] schematically illustrates an aircraft surveillance system according to one embodiment of the invention.

[0028] Figure 3 schematically illustrates an aircraft surveillance system according to a particular embodiment of the invention.

[0029] Figure 4 illustrates a situation of a following aircraft relative to a leading aircraft.

[0030] Figure 5 represents a method of monitoring an aircraft, according to an embodiment of the invention.

[0031] The monitoring system 10 shown in [Fig. 2] is installed on board an aircraft such as aircraft 1 shown in [Fig. 1]. When participating in a formation flight, aircraft 1 corresponds to one of a follower aircraft 1S or a lead aircraft IL participating in that formation flight. This monitoring system includes electronic circuitry 14 integrated into at least one avionics computer of the aircraft, for example, an avionics computer installed in an avionics bay 2 of aircraft 1. The electronic circuitry 14 is connected as input to a first information source 12 configured to provide barometric altitude information from aircraft 1. The first information source 12 corresponds, for example, to an altimeter of aircraft 1 or to an avionics system of aircraft 1 receiving barometric altitude information from an altimeter of aircraft 1.The electronic circuitry 14 is also connected as an input to a second information source 13 configured to provide barometric altitude information from the other of the following aircraft 1S and the lead aircraft IL. Thus, when aircraft 1 corresponds to the following aircraft 1S, the second information source 13 is configured to provide barometric altitude information from the lead aircraft IL, and when aircraft 1 corresponds to the lead aircraft IL, the second information source 13 is configured to provide barometric altitude information from the following aircraft 1S. In a particular embodiment, the second information source 13 corresponds to a TCAS system of aircraft 1 that is intended to receive barometric altitude values ​​from aircraft surrounding aircraft 1, these surrounding aircraft including the other of the following aircraft 1S and the lead aircraft IL. This information.The barometric altitude of surrounding aircraft is, for example, transmitted by transponders of said surrounding aircraft. The electronic circuitry 14 is also connected as an input to an information source 15a configured to provide information on aircraft 1's participation in a formation flight when aircraft 1 is participating in a formation flight. According to a first alternative, the information source 15a corresponds to a human-machine interface in the aircraft cockpit configured to allow a crew member to input information on the aircraft's participation in a formation flight. According to a second alternative, the information source 15a corresponds to an avionics computer of aircraft 1, in particular an aircraft guidance computer, configured to provide information on the aircraft's participation in a formation flight when a formation flight type aircraft guidance mode is activated.The electronic circuitry 14 is also connected at the output to a display system 18 in the cockpit of the aircraft 1, for example a CDS type system (“Cockpit Display System” in English).

[0032] During operation, when a formation flight is initiated, the various aircraft, including aircraft 1, participating in this formation flight position themselves relative to each other according to a specific geometry such that a follow aircraft flies close to a vortex generated by a lead aircraft, the various aircraft being sufficiently spaced to avoid any risk of collision. When the aircraft participating in the formation flight are positioned in a stabilized manner according to this specific geometry, a formation flight guidance mode for aircraft 1 is engaged. The information source 15a then transmits information to the electronic circuitry 14 indicating that aircraft 1 is participating in a formation flight. Advantageously, this information also indicates whether aircraft 1 is participating in the formation flight as a follow aircraft 1S or as a lead aircraft IL.Receiving information about aircraft 1's participation in the formation flight corresponds to step 30 of the process illustrated in [Fig. 5]. This step is labeled a in the figure.

[0033] From the moment it is thus informed of the participation of aircraft 1 in the formation flight, the electronic circuitry 14 implements the following steps repeatedly during the participation of aircraft 1 in the formation flight. These steps are, for example, repeated at a predetermined frequency, for example 1 Hz.

[0034] In a step 31, labeled A in [Fig. 5], the electronic circuitry 14 receives barometric altitude information from the lead aircraft IL. When aircraft 1 corresponds to the follow aircraft 1S, this barometric altitude information from the lead aircraft is received from the second information source 13. When aircraft 1 corresponds to the lead aircraft IL, this barometric altitude information from the lead aircraft is received from the first information source 12.

[0035] In a step 32, labeled B in [Fig. 5], the electronic circuitry 14 receives barometric altitude information from the follower aircraft 1S. When aircraft 1 corresponds to the follower aircraft 1S, this barometric altitude information from the lead aircraft is received from the first information source 12. When aircraft 1 corresponds to the lead aircraft IL, this barometric altitude information from the lead aircraft is received from the second information source 13.

[0036] Although step 31 is shown in [Fig.5] as prior to step 32, the chronological order of steps 31 and 32 is not limiting of the invention.

[0037] In a step 33, labeled C in [Fig.5], the electronic circuitry 14 calculates a difference between the barometric altitude of the lead aircraft IL and the barometric altitude of the follow aircraft 1S. In a particular embodiment, this difference is calculated in absolute value.

[0038] In a step 34, labeled D in [Fig. 5], the electronic circuitry 14 determines an inconsistency between the barometric altitude of the follow aircraft 1S and the barometric altitude of the lead aircraft IL, in the context of formation flight, if the difference calculated in step 32 is greater than a vortex height value at a current position of the follow aircraft, plus a height margin. As illustrated in [Fig. 4], a current position of the follow aircraft 1S relative to the lead aircraft IL, corresponding in particular to a horizontal distance L between the lead aircraft IL and the follow aircraft 1S, corresponds to a vortex height H. Advantageously, the height H takes into account a slope 0 between a longitudinal axis of the vortex and a horizontal line corresponding to the altitude of the lead aircraft, as illustrated in [Fig. 4].The slope 0 chosen to determine the height H is, for example, a maximum value for the slope of the longitudinal axis of the vortex determined from a model. The height margin is chosen so as not to introduce such an inconsistency unexpectedly due to small variations in altitude of the lead aircraft IL and / or the follow aircraft 1S, or due to uncertainties in the barometric altitude information of the lead and follow aircraft. Given that, during their participation in the formation flight, the lead aircraft IL and the follow aircraft 1S are supposed to fly according to the aforementioned specific geometry, the difference between their barometric altitudes is expected to correspond approximately to the vortex height H. Consequently, there is an inconsistency with the participation of these aircraft in the formation flight if this difference is greater than the vortex height H plus the height margin.Therefore, the monitoring system 10 helps to monitor compliance with said particular geometry by the lead aircraft IL and by the follow aircraft 1S. Since this particular geometry is intended to avoid any risk of collision between the aircraft participating in the formation flight, the system monitors compliance with said geometry. This particular system is therefore complementary to the collision avoidance monitoring performed by the TCAS system. The monitoring system 10 is thus redundant with the TCAS system.

[0039] When an inconsistency between the barometric altitude of the follow aircraft 1S and the barometric altitude of the lead aircraft IL is determined in step 34, in a step 35, labeled E on the [Fig.5], the electronic circuitry 14 commands the emission of an alert in the cockpit of the aircraft 1 by sending an appropriate command to the display system 18.

[0040] Advantageously, the electronic circuitry 14 is further connected at its output to a guidance system 16 of the aircraft 1, for example, a Flight Guidance System (FGS) type guidance computer. When an inconsistency between the barometric altitude of the follow aircraft 1S and the barometric altitude of the lead aircraft IL is determined in step 34, the electronic circuitry 14 further commands, in step 35, the disengagement of aircraft 1 from the formation flight. For example, the electronic circuitry 14 sends an appropriate command to the aircraft's guidance system 16 for this purpose.

[0041] Advantageously, the electronic circuitry 14 is further connected as an input to an information source 15b configured to provide identification information for the other aircraft, specifically the lead aircraft IL and the follow aircraft 1S: when aircraft 1 corresponds to the follow aircraft 1S, the other aircraft corresponds to the lead aircraft IL, and when aircraft 1 corresponds to the lead aircraft IL, the other aircraft corresponds to the follow aircraft 1S. In one embodiment, the information source 15b is a human-machine interface in the aircraft cockpit configured to allow a crew member of the aircraft to enter identification information for the other aircraft. In another variant, the identification information for the other aircraft is determined automatically based on information relating to the flight of the lead aircraft IL and the flight of the follow aircraft 1S.Specifically, this information includes at least one of the following: a heading of the lead aircraft or the follow aircraft, position information of the lead aircraft and the follow aircraft allowing the calculation of a distance between the lead aircraft and the follow aircraft, etc. In particular, the electronic circuitry 14 receives or determines the identification information of the other aircraft in step 30 of the process.

[0042] When aircraft 1 corresponds to the follow aircraft 1S, the electronic circuitry 14 uses the identification information of the other aircraft in step 31 to select the barometric altitude received from the lead aircraft IL, which then corresponds to the other aircraft. When aircraft 1 corresponds to the lead aircraft IL, the electronic circuitry 14 uses the identification information of the other aircraft in step 32. to select the barometric altitude received from the follow aircraft 1S which then corresponds to the other aircraft.

[0043] In the particular embodiment illustrated in [Fig. 3], the electronic circuitry 14 comprises a first part 14a integrated into a TCAS-type collision avoidance monitoring system and a second part 14b independent of the TCAS-type collision avoidance monitoring system. Specifically, the TCAS-type collision avoidance monitoring system is installed on board the aircraft 1. The TCAS-type collision avoidance monitoring system is configured, in a typical manner, to receive barometric altitude information from the lead aircraft IL and the follow aircraft 1S, and then to calculate the difference between the barometric altitude of the lead aircraft and the barometric altitude of the follow aircraft. Steps 31, 32, and 33 of the method are thus implemented in the first part 14a of the electronic circuitry.The first part 14a of the electronic circuitry transmits the difference in barometric altitudes calculated in step 33 to the second part 14b of the electronic circuitry. Step 34, for determining an inconsistency, and if necessary, step 35, are implemented in the second part 14b of the electronic circuitry.

[0044] In practice, the TCAS-type collision avoidance monitoring system receives barometric altitude information from aircraft 1, as well as barometric altitude information corresponding to each aircraft in a group of aircraft surrounding aircraft 1 (for example, aircraft whose distance to aircraft 1 is less than a distance threshold). On this basis, the TCAS system calculates differences between the barometric altitude of aircraft 1 and the barometric altitudes of each of the aircraft in the group of aircraft surrounding aircraft 1. In the particular embodiment illustrated in [Fig. 3], these barometric altitude differences are transmitted from the first part 14a of the electronic circuitry, integrated into the TCAS system, to the second part 14b of the electronic circuitry.The second part 14b of the electronic circuitry uses the identification information of the other aircraft among the leader aircraft IL and the follower aircraft 1S (received from the information source 15b or determined automatically by the electronic circuitry 14) to select, among these differences in barometric altitudes, the one that corresponds to the difference in altitude between the barometric altitude of the leader aircraft IL and the barometric altitude of the follower aircraft 1S.

Claims

Demands

1. 1) A monitoring system (10) for an aircraft (1) participating in a formation flight in which a follower aircraft (1S) flies near a vortex (V) generated by a lead aircraft (IL), the aircraft (1) being either the follower aircraft or the lead aircraft, the monitoring system comprising electronic circuitry (14) integrated into at least one avionics computer of the aircraft, wherein the electronic circuitry is configured to repeatedly perform the following steps during the aircraft's participation in the formation flight: - receive (31) barometric altitude information from the lead aircraft; - receive (32) barometric altitude information from the follower aircraft; - calculate (33) a difference between the barometric altitude of the lead aircraft and the barometric altitude of the follower aircraft;- determine (34) an inconsistency between the barometric altitude of the follow aircraft (1S) and the barometric altitude of the lead aircraft (IL), in the context of formation flight, if the calculated difference is greater than a vortex height (H) value (V) at a current position of the follow aircraft, plus a height margin; and - if such an inconsistency is determined, order (35) the issuance of an alert in the aircraft cockpit.

2. 2) System according to claim 1, characterized in that the electronic circuitry (14) comprises a first part (14a) integrated into a TCAS type anti-collision monitoring system and a second part (14b) independent of the TCAS type anti-collision monitoring system, in which the step (33) of calculating the difference between the barometric altitude of the lead aircraft (IL) and the barometric altitude of the follow aircraft (1S) is implemented in the first part (14a) of the electronic circuitry and the step (34) of determining an inconsistency between the barometric altitude of the follow aircraft and the barometric altitude of the lead aircraft is implemented in the second part (14b) of the electronic circuitry.

3. 3) System according to any one of claims 1 or 2, characterized in that the electronic circuitry (14) is further configured to implement a step (30) of receiving identification information for the lead aircraft (IL) when the aircraft (1) matches the follow aircraft (1S) or a step (30) of receiving identification information for the follow aircraft (1S) when the aircraft (1) matches the lead aircraft (IL).

4. 4) System according to any one of claims 1 or 2, characterized in that the electronic circuitry (14) is further configured to automatically determine identification information for the lead aircraft (IL) when the aircraft (1) matches the follow aircraft (1S) or identification information for the follow aircraft (1S) when the aircraft (1) matches the lead aircraft (IL), based on information received from the follow aircraft and the lead aircraft.

5. 5) System according to any one of the preceding claims, characterized in that the electronic circuitry (14) is further configured to command a disengagement of the aircraft's participation in the formation flight in the event of a determination of an inconsistency between the barometric altitude of the following aircraft and the barometric altitude of the leading aircraft.

6. 6) Method of monitoring an aircraft (1) participating in a formation flight in which a follow aircraft (1S) flies near a vortex (V) generated by a lead aircraft (IL), the aircraft (1) corresponding to either the follow aircraft (1S) or the lead aircraft (IL), the method comprising the following steps implemented repeatedly by electronic circuitry (14) integrated into at least one avionics computer of the aircraft, during the participation of the aircraft (1) in the formation flight: - receive (31) barometric altitude information from the lead aircraft; - receive (32) barometric altitude information from the follow aircraft; - calculate (33) a difference between the barometric altitude of the lead aircraft (IL) and the barometric altitude of the follow aircraft (1S); - determine (34) an inconsistency between the barometric altitude of the following aircraft and the barometric altitude of the leading aircraft, in the context of formation flying, if the calculated difference is greater than a height value (H) of the vortex (V) at a current position of the following aircraft, plus a height margin; and - in the event of determination of such an inconsistency, command (35) the issuance of an alert in the cockpit of the aircraft.

7. 7) Method according to claim 6, characterized in that the electronic circuitry (14) comprising a first part (14a) integrated into a TCAS type anti-collision monitoring system and a second part (14b) independent of the TCAS type anti-collision monitoring system, the step (33) of calculating the difference between the barometric altitude of the lead aircraft and the barometric altitude of the follow aircraft is implemented in the first part (14a) of the electronic circuitry (14) and the step (34) of determining an inconsistency between the barometric altitude of the follow aircraft and the barometric altitude of the lead aircraft is implemented in the second part (14b) of the electronic circuitry.

8. 8) A method according to any one of claims 6 or 7, characterized in that it further comprises a step (30) of receiving identification information for the lead aircraft (IL) when the aircraft (1) corresponds to the follow aircraft (1S) or a step (30) of receiving identification information for the follow aircraft (1S) when the aircraft (1) corresponds to the lead aircraft (IL).

9. 9) A method according to any one of claims 6 or 7, characterized in that it further comprises a step (30) of automatically determining identification information for the lead aircraft (IL) when the aircraft (1) matches the follow aircraft (1S) or identification information for the follow aircraft (1S) when the aircraft (1) matches the lead aircraft (IL), based on information received from the follow aircraft and the lead aircraft.

10. 10) Aircraft (1), characterized in that it comprises a surveillance system (10) according to any one of claims 1 to 5.

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