• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The guide assembly comprises a memory (19) forming part of a flight management system (2), which is configured to store an active flight path and any new flight trajectory, generated by the flight management system; flight (2), and a memory (20) forming part of a guidance system (4), which is configured to also store the flight path and any new flight path, received from said flight management system (2) said guide assembly (1) being configured to periodically transmit from the guidance system (4) to the flight management system (2) flight path identification codes recorded in said guidance system memory (20) ( 4).
    公开号:FR3020478A1
    申请号:FR1453805
    申请日:2014-04-28
    公开日:2015-10-30
    发明作者:Nicolas Albert；Thomas Koebel；Boris Kozlow；Remy Laugero
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a method and a set of guidance of an aircraft during a flight at low height. Usually, a flight phase at low altitude (or low altitude), called LLF phase (for "Low Level Flight" in English), allows an aircraft to fly at low altitude, in particular to follow as closely as possible the terrain overflown , in particular to avoid being identified, while eliminating any risk of collision with a part of said terrain. Such an LLF phase is generally located at a predetermined pitch, for example 500 feet (about 150 meters).
    [0002] In particular, for a military aircraft, including a military transport aircraft, one of the objectives of a low-level flight is to take advantage of the masking vis-à-vis the terrain to protect against threats in hostile geographical areas . To do this, in particular for performing instrument-type instrument flight operations (IMC), a flight management system of the FMS type (Flight Management System) usually calculates a three-dimensional reference trajectory (taking into account the terrain overflown), and the aircraft is guided along this reference trajectory (either automatically using an autopilot system, or manually following instructions presented by a flight director). The flight management system of the aircraft is therefore responsible for calculating the reference trajectory. This reference trajectory is calculated using data relating to the terrain overflown and the climb and descent capabilities of the aircraft, as well as its maneuvering capabilities.
    [0003] In addition, the aircraft comprises a guidance system comprising at least one guidance computer, type FGC ("Flight Guidance Computer" in English), which is responsible for servocontrolling the aircraft on this reference trajectory. Since a flight of the LLF IMC type is subject to safety rules, the flight management and guidance systems must, among other things, ensure that a minimum distance of trajectory (called distance MEMO) is available and validated in front of the aircraft during guidance (or before guidance, to allow guidance). Therefore, the flight path to be followed by the aircraft must be transmitted in advance by the flight management system. The guidance system ensures the storage and validation of this trajectory. In addition, a flight path constructed by the flight management system as defined in a flight plan may be revised or canceled. In the case of such a revision before the flight of an LLF phase, the old trajectory is removed from the flight management system. It is in particular necessary that the guidance system does not enslave the aircraft on a path (previously received and stored) that is unknown to the flight management system. In addition, the architecture and operation of these two systems (flight management system and guidance system) must ensure that the aircraft can only be guided on a valid (safety-relevant) trajectory that the pilot knows ( via the flight management system) and wish to see flying, and that the low-flying capability is not lost in a course change. The present invention aims to meet these needs. It relates to a method for guiding an aircraft during a flight at low altitude, which is intended in particular to allow the aircraft to maintain flight capacity at low height, particularly during a change in the trajectory flight. According to the invention, said method of the type comprising the steps of: a) constructing, using a flight management system, a flight trajectory at low height corresponding to a flight plan, said flight path being transmitted from the flight management system to a guidance system, said flight management system being adapted to construct at least one new low flight path corresponding to a new flight plan; and b) guiding the aircraft using the guidance system, along said so-called active flight path flight path, is remarkable in that it comprises additional steps, consisting of: - memorizing in at least a first memory of the flight management system, the active flight path along which the aircraft is guided, as well as any new flight path; - Store in at least a second memory of the guidance system, the active flight path along which is guided the aircraft, as well as any new flight path; identifying, with the aid of an associated identification code, each flight path transmitted from the flight management system to the guidance system; and - periodically transmitting from the guidance system to the flight management system, the flight path identification codes recorded in said second memory of the guidance system. Thus, thanks to the invention, during a flight of the aircraft at low altitude (in particular of the LLF IMC type), the flight management system and the guidance system memorize the trajectories used, and in particular the current flight trajectory, in order to be able to return to the latter in failure of activation of a new flight path, and thus to avoid losing the flight capacity at low altitude during a change of trajectory. In addition, both systems (the flight management system and the guidance system) synchronize periodically via the transmission of identification codes of the recorded flight paths. This makes it possible in particular to ensure that the aircraft can only be guided on a valid trajectory (meeting safety criteria) that the pilot knows (via the flight management system) and wishes to see flying, as specified below. . Advantageously, the guidance method comprises a step of exchanging activation information between the flight management system and the guidance system, said activation information indicating at least the active flight path along the route. which is guided the aircraft. Furthermore, advantageously, the guiding method further comprises steps consisting, for any new flight path: - to implement in the guidance system, a check consisting in checking whether the new flight path is valid or not; and - to transmit from the guidance system to the flight management system a validity status relating to the new flight path, this validity status indicating whether the new flight path is valid or not.
    [0004] Furthermore, advantageously, said guidance method further comprises the steps of: - implementing in the flight management system, a check consisting of checking whether the following two conditions are met for a new flight path: this new flight path is considered valid by the guidance system; and - this new flight path corresponds to a flight plan approved by a pilot of the aircraft; and for the flight management system, to authorize the guidance by the guidance system of the aircraft along this new flight path, if said two conditions are simultaneously fulfilled. Furthermore, in a particular embodiment, the guidance method comprises: an additional step consisting, when activating a new flight path (consisting in making this new flight path active, ie ie to guide the aircraft along the latter), to erase the previously active flight path in said first and second memories and / or the previous flight plan in said first memory; and / or - an additional step consisting, in the event of failure of activation of a new flight path, to reactivate at the level of the flight management system the previous flight plan and the associated flight path (or corresponding flight path). ).
    [0005] The present invention also relates to a guide assembly for guiding an aircraft at least during a flight at low height. According to the invention, said guide assembly of the type comprising: a flight management system configured to construct a flight path at low height corresponding to a flight plan, said flight management system being able to build at least a new flight path at low altitude corresponding to a new flight plan; a data transmission unit configured to transmit said flight path of the flight management system to a guidance system; and 10 - said guidance system which is configured to guide the aircraft along said low flight path, said active flight path, is remarkable in that: - said guide assembly further comprises: - at least a first memory forming part of the flight management system, said first memory being configured to store the active flight path along which the aircraft is guided and any new flight path; and at least one second memory forming part of the guidance system, said second memory being configured to store the active flight path along which the aircraft is guided and any new flight path received from said flight management system. ; and - said guidance set is configured to periodically transmit from the guidance system to the flight management system the flight path identification codes recorded in said second memory of the guidance system, each flight path transmitted from the management system. flight to the guidance system being identified using an associated identification code. Furthermore, advantageously, the guide assembly is configured to implement an operation consisting, when activating a new flight path, in erasing the previously active flight path in said first and second memories.
    [0006] In addition, in a particular embodiment, the flight management system is configured to implement an operation consisting, in case of failure of activation of a new flight path, to reactivate the current flight plan and the corresponding (or associated) flight path.
    [0007] The present invention further relates to an aircraft, particularly a transport aircraft including military, which is provided with a guide assembly such as that specified above. The figures of the appended drawing will make it clear how the invention can be realized. In these figures, identical references i.o designate similar elements. Figure 1 is a block diagram of a guide assembly that illustrates an embodiment of the invention. Figures 2 to 4 show different successive steps when activating a new flight path at low altitude. FIG. 5 illustrates a failure situation of the activation of a new flight trajectory at low altitude. The guide assembly 1 shown diagrammatically in FIG. 1 and making it possible to illustrate the invention, is intended to automatically guide an aircraft AC (FIGS. 2 to 5), in particular a military transport aircraft, at least when a low flight (in particular of the LLF IMC type), along a flight path at low altitude. To do this, this guidance assembly 1 which is embedded on the aircraft AC, comprises: a Flight Management System (FMS) 2, which includes a calculation unit (or unit 3) to build a low flight path corresponding to a flight plan. The flight management system 2 is capable of constructing a new flight path corresponding to a new flight plan; a guidance system 4 configured to guide the aircraft AC along a flight path at low altitude, called the active flight path; and a data transmission unit (double link 5) configured to transmit information between the flight management system 2 and the guidance system 4. The flight trajectory at low altitude is customarily constructed by the calculation unit 3 according to the relief of the terrain overflown and a safety lane which defines limits on either side of the flight path at least in the lateral (or horizontal) plane. The guidance assembly 1 furthermore comprises a man / machine interface 16 enabling a crew member (via a link 17) to enter the data management system 2 and, in particular, a flight plan. , and modify a flight plan. In a particular embodiment, the guide assembly 1 also comprises a set 6 of usual information sources, which is connected via a link 7 to the flight management system 2 and 15 which provides information to the flight management system 2, including the current values of flight parameters of the AC aircraft, as well as field information. In addition, the guidance system 4 comprises a calculation unit (or central unit) 8 which preferably corresponds to a guidance computer 20 of the FGC ("Flight Guidance Computer") type. This calculation unit 8 is formed so as to calculate guidance instructions, as a function of the flight path (in particular at low altitude) received from the flight management system 2 via the link 5 and a current position indication, received via a link 9 of a system 10 for determining the current position of the aircraft AC. This system 10 of the usual type may comprise, in particular, a position calculator that prepares the current position of the aircraft from information received from position sensors, and in particular information received from GPS receivers and / or one or more air and inertial data generation units. The guidance system 4 comprises, in addition to the calculation unit 8: a usual automatic control system 11 which is able to automatically control the aircraft AC, according to guidance commands received from the control unit. calculation 8 via a link 12; and / or - a flight director 13 which presents piloting indications to the pilot on a dedicated screen, according to guidance commands received from the calculation unit 8 via a link 14. According to the invention, said set of guidance 1 further comprises: - at least one memory 19 forming part of the flight management system 2 and for example of the calculation unit 3. This memory 19 is configured to store at least the active flight path along which is guided the aircraft AC and any new flight path determined by the calculation unit 3; and at least one memory 20 forming part of the guidance system 4 and for example the calculation unit 8. This memory 20 is configured to store at least the flight path along which the aircraft AC is guided and any new flight path, received from the flight management system 2 via the link 5. In addition, according to the invention, each flight path transmitted from the flight management system 2 to the guidance system 3 is identified using a code (or name or number) associated identification, for example TRAJi or Ti for a trajectory index "i". In addition, according to the invention, the guide assembly 1 is configured to transmit periodically (for example every 120 ms), from the guidance system 4 to the flight management system 2, the identification codes of the flight paths. flight recorded in said memory 20 of the guidance system 4. Therefore: the flight management system 2 is thus able to store (in the memory 19) a new trajectory LLF defined in the active flight plan 30 (that which the pilot wishes to fly), as well as the active LLF trajectory (according to which the aircraft AC is currently guided by the guidance system 4); and the guidance system 4 is capable of storing (in the memory 20) the new revised or defined trajectory LLF of the active flight plan (called passive trajectory during validation or activation) and the validated trajectory for the guidance ( so-called active trajectory).
    [0008] The guidance assembly 1 provides for exchange of activation information between the flight management system 2 and the guidance system 4. This activation information indicates at least the active flight path along which the flight path is guided. AC aircraft. In particular, as indicated above, the guidance system 4 periodically informs the flight management system 2 of the stored flight trajectories by transmitting the trajectory numbers (or identification codes). The flight management system 2 and the guidance system 4 thus synchronize continuously, which ensures that the aircraft AC can only be guided on a valid flight trajectory (meeting the security criteria) that the pilot knows (via the flight management system 2) and he wishes it to be followed by the aircraft AC. During a flight of an LLF phase, the flight path Ti (Figure 2) defined in the flight plan can be revised (for example to avoid a hostile zone). The process leading to the slaving of the guidance system 4 on the revised trajectory T2 lasts several seconds (typically 30 seconds), during which it is necessary to maintain the flight conditions LLF. In the example of FIG. 2, the current trajectory Ti followed by the aircraft AC passes through successive waypoints ("waypoints" in English) P1, P2, P3 and P4 forming part of the initial flight plan. In addition, in this example, as shown in FIG. 3, the new flight trajectory (or auxiliary trajectory) T2 deviates from the flight path Ti downstream from the passage point P2 (in the direction of flight E) for join a waypoint P4 via a new waypoint P5 (eg entered by the pilot using a data entry unit of the man / machine interface 16), instead of passing through the waypoint P3 . FIGS. 2 to 5 also show a point PO downstream from the current position of the aircraft AC, to which a revision triggered at the current instant will be effective at the earliest. The new trajectory T2 can be judged non-malleable at any moment of the revision process, thus imposing to re-enslave the two systems 2 and 4 on the initial trajectory Ti (current). For this purpose, the current trajectory Ti is maintained by the flight management system 2 and by the guidance system 4, at least until the servo-control of the guidance system 4 on the new trajectory T2. For these reasons, during the LLF flight, the flight management system 2 and the guidance system 4 memorize the current trajectory Ti in order to be able to return to the latter in the event of activation failure on the new T2 trajectory of the LLF type. , and thus avoid losing LLF flight capability. Furthermore, the guidance system 3 comprises a verification unit 21 (which may for example be part of the calculation unit 8). This verification unit 21 implements, for any new flight trajectory T2, a check consisting in checking the validity of this new flight trajectory T2, in particular to check that there has been no error or error. failure during the transmission of the flight path T2. In a preferred embodiment, the flight management system 2 comprises two flight management computers that each send the same trajectory, and the verification unit 21 checks whether the two trajectories received are identical for the valid declarations. A validity status of the new flight path T2 (indicating whether the latter is valid or invalid) is then transmitted from the guidance system 4 to the flight management system 2 (via the link 5).
    [0009] Moreover, the flight management system 2 comprises a verification unit 22 (which may for example be part of the calculation unit 3). This verification unit 22 implements a check consisting of checking whether the two following conditions are simultaneously fulfilled, for any new flight trajectory T2: the flight trajectory T2 is considered valid by the guidance system 3; and the flight trajectory T2 corresponds to a flight plan approved by a pilot of the aircraft (and entered via the man / machine interface 16). If the flight management system 2 concludes that the two preceding conditions are simultaneously fulfilled, it authorizes guidance by the guidance system 4 of the aircraft AC along this flight path T2. Consequently, after verifying the trajectory T2 transmitted, the guidance system 4 informs the flight management system 2 of the validity status of the new stored trajectory (passive trajectory). The flight management system 2 authorizes the guidance of an LLF trajectory if and only if this trajectory has been validated by the guidance system 4 and is well defined in the flight plan (known by the pilot). For the implementation of this authorization, the flight management system 2 provides the guidance system 4, the number or identification code of the trajectory T2 to follow (for example "TRAJ2" or "T2").
    [0010] The guidance system 4 then automatically activates the T2 trajectory of type LLF (thus allowing guidance along this trajectory T2), as shown in FIG. 4 for the aforementioned example. This activation therefore takes place if and only if the flight management system 2 authorizes it, by supplying the number (or identification code) of the trajectory to be followed. Furthermore, the guide assembly 1 further comprises erase units 23 and 24 arranged for example, respectively, in the calculation units 3 and 8. These erasing units 23 and 24 are configured for, when of the activation of a new flight path T2, erase the previously active flight trajectory 25 Ti in said memories 19 and 20, as well as the previous flight plan (relative to the trajectory Ti) in said memory 19. during a revision during the flight LLF, the current flight plan and the corresponding current trajectory Ti are stored by the current flight management system 2. The guidance assembly 1 then enters a waiting state ( "LLF Pending State"). When activating the new trajectory T2, the current flight plan and the current trajectory Ti are erased from the erasure unit 23. Furthermore, the flight management system 2 is configured to, in case of failure of the activation of the new flight path T2, reactivate the current flight plan and the current flight path Ti (a so-called "roll back" operation in English), as represented for the example considered in FIG. to be seen in parallel with Figure 4 for which the revision was successful). An activation failure can occur in many cases, for example when the process of revising the trajectory takes too long a time to achieve the change of trajectory at the point of separation of the two trajectories.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A method of guiding an aircraft during a low flight, said method comprising the steps of: a) constructing with a flight management system (2) a corresponding low-flying flight path to a flight plan, said flight path being transmitted from the flight management system (2) to a guidance system (4), said flight management system (2) being able to construct at least one new flight path at low altitude corresponding to a new flight plan; and Io b) guiding the aircraft using the guidance system (4), along said so-called active flight path flight path, characterized in that it comprises additional steps, consisting of: storing in at least a first memory (19) of the flight management system (2), the active flight path along which the aircraft (AC) is guided, as well as any new flight trajectory; - Store in at least a second memory (20) of the guidance system (4), the active flight path along which is guided the aircraft (AC), as well as any new flight path; identifying, with the aid of an associated identification code, each flight trajectory transmitted from the flight management system (2) to the guidance system (4); and - periodically transmitting from the guidance system (4) to the flight management system (2), the identification codes of the flight paths recorded in said second memory (20) of the guidance system (4).
    [0002]
    2. Method according to claim 1, characterized in that it comprises a step of exchanging activation information between the flight management system (2) and the guidance system (4), said information activation indicating at least the active flight path along which is guided the aircraft (AC).
    [0003]
    3. Method according to one of claims 1 and 2, characterized in that it further comprises steps consisting, for any new flight path: - to implement in the guidance system (4), a verification checking whether the new flight path is valid or not; and - to transmit from the guidance system (4) to the flight management system (2) a validity status relating to the new flight path, this validity status indicating whether the new flight path is valid or not.
    [0004]
    The method as claimed in claim 1, further comprising steps of: two following conditions are fulfilled for a new flight path: - this new flight path is considered valid by the guidance system (4); and - this new flight path corresponds to a flight plan approved by a pilot of the aircraft; and - for the flight management system (2), to allow guidance by the guidance system (4) of the aircraft (AC) along this new flight path, if these two conditions are simultaneously met.
    [0005]
    5. Method according to any one of the preceding claims, characterized in that it comprises an additional step consisting, when an activation of a new flight path, to erase the previously active flight path, in said first and second memories (19, 20).
    [0006]
    6. Method according to any one of the preceding claims, characterized in that it comprises an additional step consisting, in the event of failure of activation of a new flight path, to reactivate at the level of the management system. flight (2) a previous flight plan and associated flight path.
    [0007]
    7. A guide assembly of an aircraft during a flight at low height, said guide assembly (1) comprising: a flight management system (2) configured to construct a trajectory of 30 v01 at low height corresponding to a flight plan, said flight management system (2) being capable of constructing at least one new low flight path corresponding to a new flight plan; a data transmission unit (5) configured to transmit said flight plan; flight path of the flight management system (2) to a guidance system (4); and - said guidance system (4) which is configured to guide the aircraft (AC) along said low flight path, said active flight path, characterized in that: - said guide assembly (1) further comprises: - at least a first memory (19) forming part of the flight management system (2), said first memory (19) being configured to store the active flight path Io along which the aircraft is guided (AC) and any new flight path; and - at least a second memory (20) forming part of the guidance system (4), said second memory (20) being configured to store the active flight path along which the aircraft (AC) is guided and any new Flight path, received from said flight management system (2); and - said guide assembly (1) is configured to periodically transmit from the guidance system (4) to the flight management system (2) identification codes of the flight paths recorded in said second memory (20) of the flight system. guidance (4), each flight path transmitted zo the flight management system (2) to the guidance system (4) being identified using an associated identification code.
    [0008]
    8. An assembly according to claim 7, characterized in that it is configured to implement an operation consisting, when activating a new flight trajectory, to erase the previously active flight path in said first flight path. and second memories (19, 20).
    [0009]
    9. An assembly according to one of claims 7 and 8, characterized in that the flight management system (2) is configured to implement an operation consisting, in case of failure of activation of a new flight path, to reactivate the current flight plan and the associated flight path.
    [0010]
    10. Aircraft, characterized in that it comprises a guide assembly (1) according to any one of claims 7 to 9.
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    引用文献:
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    FR3020478B1|2014-04-28|2016-05-20|Airbus Operations Sas|METHOD AND ASSEMBLY FOR GUIDING AN AIRCRAFT AT LOW HEIGHT.|
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    法律状态:
    2015-04-21| PLFP| Fee payment|Year of fee payment: 2 |
    2015-10-30| PLSC| Publication of the preliminary search report|Effective date: 20151030 |
    2016-04-21| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-19| PLFP| Fee payment|Year of fee payment: 4 |
    2018-04-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-04-18| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-04-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1453805A|FR3020478B1|2014-04-28|2014-04-28|METHOD AND ASSEMBLY FOR GUIDING AN AIRCRAFT AT LOW HEIGHT.|FR1453805A| FR3020478B1|2014-04-28|2014-04-28|METHOD AND ASSEMBLY FOR GUIDING AN AIRCRAFT AT LOW HEIGHT.|
    US14/694,690| US9569974B2|2014-04-28|2015-04-23|Method and assembly for guidance of an aircraft during a low-altitude flight|
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