U.S. patent application number 13/869413 was filed with the patent office on 2019-10-24 for parametrizable automatic piloting system intended for an aircraft.
The applicant listed for this patent is Thales. Invention is credited to Jerome BIRRE, Arnaud BONNAFOUX, Rodolphe DEVAUREIX.
Application Number | 20190324455 13/869413 |
Document ID | / |
Family ID | 46801572 |
Filed Date | 2019-10-24 |
United States Patent
Application |
20190324455 |
Kind Code |
A1 |
DEVAUREIX; Rodolphe ; et
al. |
October 24, 2019 |
Parametrizable automatic piloting system intended for an
aircraft
Abstract
An automatic piloting system intended for an aircraft comprising
an aircraft signals acquisition module, a module for interfacing
with the crew, and a module for processing the output signals,
comprises: a generic software kernel for automatic piloting aboard
the aircraft, comprising several parametrizable elementary cells, a
parametrization tool for the generic software kernel, able to
transform an operational need of the automatic piloting system,
expressed by means of a configuration file in accordance with a
predetermined configuration domain DC, into a database of binary
parameters DB able to parametrize the generic software kernel; each
cell being parametrized by the database DB, and means for loading
and storage aboard the aircraft of the database DB.
Inventors: |
DEVAUREIX; Rodolphe;
(Valence, FR) ; BONNAFOUX; Arnaud; (Toulouse,
FR) ; BIRRE; Jerome; (Bruguieres, FR) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Thales; |
|
|
US |
|
|
Family ID: |
46801572 |
Appl. No.: |
13/869413 |
Filed: |
April 24, 2013 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
G05D 3/00 20130101; B64C
13/18 20130101; B64C 19/00 20130101; G05D 1/00 20130101; B64D 45/00
20130101; G06F 9/30029 20130101; G06F 16/9035 20190101; G06F 17/11
20130101; G06F 9/44505 20130101; G06F 9/545 20130101; G05D 1/0202
20130101; G05D 1/0088 20130101; G08G 5/00 20130101 |
International
Class: |
G05D 1/00 20060101
G05D001/00; G05D 1/02 20060101 G05D001/02; B64D 45/00 20060101
B64D045/00; G06F 17/11 20060101 G06F017/11; G06F 9/54 20060101
G06F009/54; G06F 9/30 20060101 G06F009/30; G06F 16/9035 20060101
G06F016/9035 |
Foreign Application Data
Date |
Code |
Application Number |
Apr 24, 2012 |
FR |
12 01201 |
Claims
1. An automatic piloting system for an aircraft comprising an
aircraft signals acquisition module, a module for interfacing with
the crew, and a module for processing the output signals,
comprising: a certified generic software kernel for automatic
piloting aboard the aircraft, the certified generic software kernel
comprising several certified parametrizable elementary cells, a
parametrization tool for the certified generic software kernel,
configured to transform an operational need of the automatic
piloting system, expressed by means of a configuration file
comprising a set of parameters structured in accordance with a
predetermined configuration domain (DC), into a database of binary
parameters (DB) for parameterizing the certified generic software
kernel; each certified elementary cell being parametrized by the
database (DB), means for loading and storage aboard the aircraft of
the database (DB).
2. The automatic piloting system according to claim 1, wherein the
configuration file describes an operational need in accordance with
a configuration domain (DC), comprising a definition of the
guidance modes; wherein each guidance mode is described by a list
of parameters comprising at least one type of guidance mode,
activation logic, an activation event, a guidance law, a guidance
directive, or a piloting configuration; and wherein each parameter
is associated with a range of permitted values.
3. The automatic piloting system according to claim 2, wherein the
parametrization tool comprises a first module for verifying the
configuration domain (DC) of a configuration file coded in
marked-up text format, and a second module for converting the
configuration file into the database (DB) configured to parametrize
an automatic piloting system validated for the said configuration
domain (DC).
4. The automatic piloting system according to claim 1, wherein the
means for loading and storage comprise a device for identifying a
user logging on to the automatic piloting system, a database
loading device and a memory device for the storage of the database
(DB).
5. The automatic piloting system according to claim 1, wherein the
certified software kernel comprises at least five certified
elementary cells: a first certified cell for formulating a set of
external-context variables, a second certified cell for formulating
a set of operational-context variables, a third certified cell for
formulating execution logic for the automatic piloting system, at
least as a function of an operational-context variable, a fourth
certified cell for managing piloting or guidance directives
provided by the pilot or the automatic piloting system, a fifth
certified cell for managing piloting or guidance laws and modes of
the automatic piloting system; each of the certified elementary
cells comprising a software engine parametrizable by the database
(DB).
6. The automatic piloting system according to claim 5, wherein the
certified software kernel further comprises a cell for managing the
MIMI interface, configured to adapt the MMI interface at least as a
function of an external-context or operational-context
variable.
7. A method of automatic piloting aboard an aircraft comprising a
step of acquiring aircraft signals, a step of interacting with the
crew, and a step of processing output signals, further comprising
certified calculation steps parameterized by means of a database of
binary parameters (DB) for: Formulating an external context, by
means of a set of variables representative of conditions exterior
to the automatic piloting system, generated on the basis of the
aircraft signals; Formulating an operational context, by means of a
set of variables representative of operational conditions internal
to the automatic piloting system, generated on the basis of
aircraft signals or of external-context variables; Formulating
execution logic for the automatic piloting system, by associating
with an activation event, at least one external or operational
context and an activation type; Managing piloting or guidance
directives commanded by the pilot or calculated by the automatic
piloting system on the basis of an activation event, for a given
context; Managing piloting or guidance laws and modes, by means of
a set of guidance segments which is associated with at least one
activation logic, a piloting configuration, or a guidance
dynamics.
8. The method of automatic piloting of an aircraft according to
claim 7, wherein the external-context formulating step comprises
the calculation steps including: Identifying external-context
variables to be formulated, such as specified in the database (DB),
For each external-context variable: Identifying a mathematical
operation, specified in the database (DB), making it possible to
formulate the external-context variable, Identifying values of
aircraft signals necessary for the mathematical operation,
Calculating the external-context variable, by means of the
mathematical operation and of the values of aircraft signals.
9. The method of automatic piloting of an aircraft according to
claim 7, wherein the operational-context formulating step comprises
the calculation steps including: Identifying operational-context
variables to be formulated, such as specified in the database (DB),
For each operational-context variable: Identifying a mathematical
operation, specified in the database (DB), making it possible to
formulate the operational-context variable, Identifying values of
external-context variables and of data of the internal state of the
PA, which are necessary for the mathematical operation, Calculating
the operational-context variable, by means of the mathematical
operation and of the values of aircraft signals and
external-context variables.
10. The method of automatic piloting of an aircraft according to
claim 7, wherein the step of formulating execution logic comprises
calculating, for a set of logic associated, in the database (DB),
with an activation event provided by the automatic piloting system,
a boolean condition of satisfaction of the logic, by means of
external-context or operational-context variables; the set of the
execution logic associated with the activation event being
configured to manage the piloting or guidance directives and the
piloting or guidance modes and laws.
11. The method of automatic piloting of an aircraft according to
claim 7, wherein the step of managing the piloting or guidance
directives comprises: calculating a guidance directive value, by:
identifying a mathematical operation, described in the database
(DB), making it possible to calculate the value of the directive,
identifying parameter values of the database (DB) necessary for the
mathematical operation, formulating the value of the directive, by
calculating by means of the mathematical operation, parameters of
the operation and aircraft signals, evaluating guidance directive
parameters as described in the database (DB).
12. The method of automatic piloting of an aircraft according to
claim 7, wherein the step of managing the piloting or guidance laws
and modes comprises: identifying a guidance segment stimulated by
an activation event according to an activation logic, identifying
at least one piloting or guidance directive to be formulated, a
guidance law to be activated, a piloting configuration to be
applied, or an envelope protection to be activated.
13. A method for developing an automatic piloting system for an
aircraft according to claim 1, further comprising a step of
defining a configuration domain (DC), the said configuration domain
(DC) being configured by parametrization to cover a wide spectrum
of operational needs of the automatic piloting system, and a step
of programming and certifying several generic software engines.
14. A method of maintenance of a piloting system for an aircraft
according to claim 1, further comprising a step of identifying a
user logging on to the automatic piloting system, a step of loading
a database of binary parameters (DB) for the parametrization of a
generic software kernel, and a step of storage aboard the aircraft;
the automatic piloting system being operationally configured to
read the binary parameters of the database (DB).
15. A program product comprising code instructions to perform the
steps of the automatic piloting method according to claim 7.
16. The automatic piloting system according to claim 1, wherein the
certified generic software kernel is isolated from the
parameterization tool.
17. The automatic piloting system according to claim 1, wherein the
certified generic software is certified by an organization, and
wherein the certified generic software is only permitted, by the
organization, to operate after successfully undergoing a
certification process.
18. The automatic piloting system according to claim 17, wherein
the parameterization tool is permitted, by the organization, to
operate without requiring a certification process.
Description
[0001] The present invention belongs to the field of automatic
piloting systems onboard aircraft. More precisely, it applies to
automatic piloting systems which carry out the guidance of an
aircraft in accordance with the pilot's directives and informs the
crew about the situation of the guidance.
[0002] An automatic piloting system (PA) makes it possible to
automatically accomplish a set of more or less complex activities
that previously used to be carried out manually by the pilot. By
advocating manoeuvres suited to the conditions and to the flight
plan, it helps to lighten the pilot's load. The development and
maintenance of such systems are complex and expensive since they
depend not only on the technical specifications of the aircraft
equipment but also on the operational customs and procedures of
aircraft manufacturers. The maturity of the expression of the
aircraft manufacturer's need, in terms of defining the behaviour of
the PA, progresses during the course of the development of an
aircraft. As long as the expression of the need has not come to an
end, the design of an automatic piloting system is faced with
numerous iterations of software development, sometimes up until
in-flight trials and beyond commissioning into service. Moreover,
the software of an automatic piloting system must be certified. The
certification process consists in providing an organization with
proofs related to the software development activities in order to
obtain certification credits for all or part of the software. As
the behaviour of the automatic piloting system depends on the
specific need of an aircraft manufacturer, interfaced systems and
aerodynamic parameters specific to the carrier, the software of an
automatic piloting system must be modified or redeveloped for each
particular aircraft.
[0003] The automatic piloting systems of the prior art which
exhibit the characteristic of being developed specifically (without
gaining certification credit from the previous developments) as a
monolithic sequential code require iterations which are lengthy,
expensive and uncertain in terms of timescale. Regular software
updates may be necessary during development, and during the phase
of commercial operations when the aircraft manufacturer requests
modification or addition of new automatic piloting functions. Under
the conditions of the prior art, any modification involves
repeating all or part of the software certification process.
[0004] To solve these difficulties, the general idea of the
invention is to structure the automatic piloting system by
isolating on the one hand a generic software kernel which
constitutes an invariant part and which is certified and from which
it will be possible to gain credit, and on the other hand a
configurable variable part making it possible to adapt the
automatic piloting system to alterations in the operational needs
of the aircraft, during development or operations, this
configurable variable part not needing to be certified.
[0005] For this purpose, the subject of the invention is an
automatic piloting system intended for an aircraft comprising an
aircraft signals acquisition module, a module for interfacing with
the crew, and a module for processing the output signals,
characterized in that it furthermore comprises:
[0006] a generic software kernel for automatic piloting aboard the
aircraft, comprising several parametrizable elementary cells,
[0007] a parametrization tool for the generic software kernel, able
to transform an operational need of the automatic piloting system,
expressed by means of a configuration file consisting of a set of
parameters structured in accordance with a predetermined
configuration domain DC, into a database of binary parameters DB
able to parametrize the generic software kernel; each cell being
parametrized by the database DB,
[0008] means for loading and storage aboard the aircraft, of the
database DB.
[0009] The invention also pertains to a method of automatic
piloting aboard an aircraft comprising a step of acquiring aircraft
signals, a step of interacting with the crew, and a step of
processing output signals, characterized in that it furthermore
comprises calculation steps parametrizable by means of a database
of binary parameters DB for: [0010] Formulating an external
context, by means of a set of variables representative of
conditions exterior to the automatic piloting system, generated on
the basis of the aircraft signals; [0011] Formulating an
operational context, by means of a set of variables representative
of operational conditions internal to the automatic piloting
system, generated on the basis of aircraft signals or of
external-context variables; [0012] Formulating execution logic for
the automatic piloting system, at least as a function of an
operational-context variable; [0013] Managing piloting or guidance
directives issued by the pilot or the automatic piloting system;
[0014] Managing piloting or guidance laws and modes. The invention
also pertains to an automatic piloting system intended for an
aircraft having the characteristics defined above, characterized in
that it comprises a step of defining a configuration domain DC, the
said configuration domain DC being able by parametrization to cover
a wide spectrum of operational needs of the automatic piloting
system, and a step of programming and certifying several generic
software engines.
[0015] The invention also pertains to a method of maintenance of a
piloting system intended for an aircraft having the characteristics
defined above, characterized in that it comprises a step of
identifying a user logging on to the automatic piloting system, a
step of loading a database of binary parameters DB for the
parametrization of a generic software kernel, and a step of storage
aboard the aircraft; the automatic piloting system being able in
operational configuration to read the binary parameters of the
database DB.
[0016] The invention finally pertains to a program product
comprising code instructions making it possible to perform the
steps of the automatic piloting method having the characteristics
defined above.
[0017] The invention will be better understood and other advantages
will become apparent on reading the detailed description of the
embodiments given by way of example in the following figures:
[0018] FIG. 1 represents the simplified functional architecture of
a parametrization tool for an automatic piloting system according
to the invention,
[0019] FIG. 2 represents the simplified functional architecture of
means for loading and storage of a database of parameters for an
automatic piloting system aboard an aircraft,
[0020] FIG. 3 represents the simplified functional architecture and
the relationships of an automatic piloting system comprising a
generic software kernel according to the invention,
[0021] FIG. 4 describes the steps of a method for formulating a set
of external-context variables according to the invention,
[0022] FIG. 5 describes the steps of a method for formulating a set
of operational-context variables according to the invention,
[0023] FIG. 6 illustrates the principle of a method for calculating
execution logic for the automatic piloting system.
[0024] For the sake of clarity, the same elements will bear the
same labels in the various figures.
[0025] FIG. 1 represents the simplified functional architecture of
a parametrization tool for an automatic piloting system. According
to the invention, a qualified parametrization tool 10 allows an
operator 11 to generate a database DB in the machine format. The
operator 11 provides as input to the parametrization tool 10 a
configuration file 12 containing the variable parameters of the
automatic piloting system, or PA system, which are peculiar to the
characteristics of the aircraft, to the specific need of the
aircraft manufacturer, to technical constraints of the PA system,
to constraints of interaction and display destined for the crew, or
to input and output constraints of the PA system. The content of
the configuration file 12 is humanly comprehensible; several
formats are possible for the configuration file 12, and notably
XML, HTML, XHTML, LaTeX or any other structured text format. The
structure of the content of the configuration file 12 is
constrained by a configuration domain DC. The parametrization tool
10 comprises a first module 13 for verifying the configuration
domain DC of the configuration file 12, and a second module 14 for
converting the configuration file 12 into a database of binary
parameters DB. Stated otherwise, the parametrization tool 10 is
designed to make it possible to verify the conformity of the
parameters contained in the configuration file 12 with respect to
the configuration domain DC, before converting the said
configuration file into a database of binary parameters DB. The
fact that the parametrization tool 10 is qualified implies that the
machine code generated for the database DB is not subjected to
obtaining of certification credits.
[0026] According to the invention, the configuration file describes
an operational need by means of a set of parameters structured in
accordance with a configuration domain DC, the said configuration
domain DC consisting at least of the definition of the guidance
modes. Each guidance mode is described by a list of parameters
comprising at least one type of guidance mode, activation logic, an
activation event, a guidance law, a guidance directive, or a
piloting configuration. With each parameter is associated a range
of permitted values.
[0027] FIG. 2 represents the simplified functional architecture of
means for loading and storage of a database of parameters for an
onboard automatic piloting system aboard an aircraft. According to
the invention, the storage and loading means 20 comprise a device
21 for identifying a user 22 logging on to the automatic piloting
system, a database DB loading device 23 and a memory device 24 for
the storage of the database DB.
[0028] The identification device 21 allows a user 22, for example a
maintenance operator, to identify himself with the aid of an
identification medium 25 in order to open a database DB loading
session. Several types of identification media 25 are envisaged
according to the invention, for example a chip card, a contactless
card, a USB peripheral or any other removable storage peripheral.
Likewise, media for biometric identification, associated with
physiological information characteristic of the user 22, such as,
for example, fingerprints, a facial recognition, a DNA recognition,
a geometry of the hand, a palmar recognition, a retinal recognition
or a recognition of the iris are envisaged.
[0029] After identification of the user 22, the loading of a
database DB can be carried out by wire-based connection by means of
transfer protocols such as FTP, TFTP or any other data transfer
protocol, or else by wireless connection for example of Wifi type,
or else again by physical connection via a removable support of USB
or CD-ROM medium type or any other memory support.
[0030] Finally, the database DB is stored aboard the aircraft by
means for example of a physical medium such as hard disk, USB key
or CD-ROM, or else by means of a memory device of RAM or FLASH
memory type.
[0031] FIG. 3 represents the simplified functional architecture and
the relationships of an automatic piloting system comprising a
generic software kernel. The onboard automatic piloting system
aboard an aircraft ensures the guidance of an aircraft as a
function of directives of the crew 31; on the basis of a set of
aircraft signals 32, the PA system defines a set of piloting
directives 33 transmitted to components 34 or sub-systems 35 of the
aircraft. According to the invention, the PA system comprises an
aircraft signals acquisition module 36, a module 37 for interfacing
with the crew, a module for processing the output signals 38 and a
generic software kernel 39.
[0032] According to the invention, the generic software kernel 39
is designed so as to be able to be parametrized by means of the
database of binary parameters DB, defined for a predetermined
configuration domain DC, such as described hereinabove. A new
operational need, described by a configuration file 12 in
accordance with the configuration domain DC for which the generic
software kernel 39 was initially developed, can be taken into
account in the course of the development or operation of the
aircraft, by performing an update of the database DB stored in the
PA system.
[0033] The software kernel 39 comprises several parametrizable
elementary cells, and notably:
[0034] a first cell 40 for formulating a set of external-context
variables,
[0035] a second cell 41 for formulating a set of
operational-context variables,
[0036] a third cell 42 for formulating execution logic for the
automatic piloting system, at least as a function of an
operational-context variable,
[0037] a fourth cell 43 for managing guidance directives provided
by the pilot or the automatic piloting system,
[0038] a fifth cell 44 for managing guidance laws and modes of the
automatic piloting system.
[0039] Advantageously, each of the cells comprises a software
engine parametrizable by the database of binary parameters DB. The
structuring of a configuration domain DC, and the slicing into
parametrizable elementary cells driven by generic software engines
makes it possible advantageously to isolate the invariant parts of
the PA system. It becomes possible to factorize the set of code
lines of the software. The invariant parts which depend for example
on hardware configurations of components common to a set of
aircraft or which depend on regulatory execution logic are isolated
from the parametrizable variable parts. The operational conditions
of employment peculiar to an aircraft manufacturer, such as for
example the content of guidance procedures, are processed as
bundled parameters in a configuration file 12.
[0040] Advantageously, the software kernel 39 furthermore comprises
a cell 45 for managing the MMI interface, able to adapt the MMI
interface at least as a function of an external-context or
operational-context variable. Typically, the cell 45 for managing
the MMI interface makes it possible to manage several types of
media for interaction, for example control panel or touchscreen,
and for display, for example PFD, FMA or LCD screen. During working
operations, the information to be displayed to the operational user
31 are known and can be characterized by qualitative properties
such as the default colour, the colour in a particular context, the
frequency of information updating, or the visibility of the
information as a function of a particular context. The PA system is
designed to retrieve these characteristics from the database DB in
order to adapt the display as a function of the parameters
retrieved or of the context. For example, when the context
associated with an item of information changes, the MMI management
cell 45 retrieves from the database DB the parameters corresponding
to the item of information and to the new context, and then updates
the properties of the item of information accordingly. The set of
information constantly updated by the MMI constitutes the guidance
situation displayed to the operational user 31. Likewise, certain
information originating from the user 31 such as commands and
directive, transmitted to the generic kernel 39, can have
parametrizable variant properties such as a priority or a
precision. The PA is designed to retrieve the set of these
properties from the database DB so as to adapt the behaviour of the
PA as a function of the parameters contained in the database
DB.
[0041] The invention also pertains to a method of automatic
piloting aboard an aircraft comprising a step of acquiring aircraft
signals, a step of interacting with the crew, and a step of
processing output signals, characterized in that it furthermore
comprises parametrizable calculation steps for: [0042] Formulating
an external context, by means of a set of variables representative
of conditions exterior to the automatic piloting system, generated
on the basis of the aircraft signals; [0043] Formulating an
operational context, by means of a set of variables representative
of operational conditions internal to the automatic piloting
system, generated on the basis of aircraft signals or of
external-context variables; [0044] Formulating execution logic for
the automatic piloting system, by associating with an activation
event, at least one external or operational context and with an
activation type; [0045] Managing piloting or guidance directives
commanded by the pilot or calculated by the automatic piloting
system on the basis of an activation event, for a given context;
[0046] Managing piloting or guidance laws and modes, by means of a
set of guidance segments which is associated with at least one
activation logic, a piloting configuration, or a guidance
dynamics.
[0047] FIG. 4 describes the steps of a method for formulating a set
of external-context variables according to the invention. These
external-context variables, which can be of various types, for
example integer, decimal, or boolean, are established on the basis
of input data 46 consolidated by the acquisition module 36 on the
basis of aircraft signals 32.
[0048] The nature and the number of external-context variables
formulated in this step is variable and depends on the aircraft and
the aircraft manufacturer's need. The PA system is therefore
designed so that the number and the nature of these
external-context variables is parametrized in the database DB. The
database DB also contains the parametrization information defining,
for each external-context variable, the mathematical operation
which makes it possible to formulate it, that is to say the
operands and the operators. For each external-context variable, the
PA system accesses the database DB to extract the information which
makes it possible to formulate this variable, i.e. the mathematical
operation consisting of the various operands and operators. The
structure of the possible mathematical operations for the
formulation of the external context is constrained by the
configuration domain.
[0049] Moreover: [0050] The operands are input data 46 arising from
the aircraft signals 32 acquisition module 36. The PA system offers
a mechanism making it possible to identify, from among the input
data 46, those which may be operands for constructing the external
context. For example, the input data 46 concerned may be associated
with a single identifier making it possible to reference them as
operand in the database DB; [0051] The mathematical operations may
be of various types, constraining the type of the operators and
operands: [0052] Boolean equations: the operands are boolean data
and the operators are logical AND and logical OR, [0053] Numerical
equation: the operands are numerical values, for example integers
or decimals, and the operators may be mathematical comparators such
as >, <, or threshold operators such as MIN, which determines
the smaller of two values, and MAX, which determines the larger of
two values.
[0054] Thus, as described in FIG. 4, the external-context
formulating step comprises the calculation steps consisting in:
[0055] Identifying in a step 51 external-context variables to be
formulated, such as specified in a database of binary parameters
DB, [0056] For each external-context variable: [0057] Identifying
in a step 52 a mathematical operation, specified in the database
DB, making it possible to formulate the external-context variable,
[0058] Identifying in a step 53 values of aircraft signals
necessary for the mathematical operation, [0059] Calculating in a
step 54 the external-context variable, by means of the mathematical
operation and of the values of aircraft signals.
[0060] FIG. 5 describes the steps of a method for formulating a set
of operational-context variables according to the invention. These
operational-context variables are boolean variables established on
the basis of the input data 46 arising from the acquisition module
36, external-context variables, and data of the internal state of
the PA.
[0061] The nature and the number of operational-context variables
depend on the aircraft and the aircraft manufacturer's need. The PA
system is therefore designed so that the number and the nature of
these operational-context variables are parametrized in the
database DB. The database DB also contains the parametrization
information defining, for each operational-context variable, the
mathematical operation which makes it possible to formulate it,
that is to say the operands and the operators.
[0062] The PA is designed to periodically formulate the operational
context. The structure of the possible operations for the
formulation of the operational context is constrained by the
configuration domain: [0063] the operands are external-context
variables and data of the internal state of the PA. The PA system
offers a mechanism making it possible to identify, from among the
data of the internal state of the PA, those which may be operands
for constructing the operational context. For example, the relevant
data of the internal state of the PA may be associated with a
single identifier making it possible to reference them as operand;
[0064] The mathematical operations may be of various types,
constraining the type of the operators and operands: [0065] Boolean
equations: the operands are boolean data and the operators are
logical AND and logical OR, [0066] Numerical equation: the operands
are numerical values, for example integers or decimals, and the
operators may be mathematical comparators such as >, <, or
threshold operators such as MIN, which determines the smaller of
two values, and MAX, which determines the larger of two values.
[0067] Thus, as described in FIG. 5, the operational-context
formulating step comprises the calculation steps consisting in:
[0068] Identifying in a step 61 operational-context variables to be
formulated, such as specified in a database of binary parameters
DB, [0069] For each operational-context variable: [0070]
Identifying in a step 62 a mathematical operation, specified in the
database DB, making it possible to formulate the
operational-context variable, [0071] Identifying in steps 63 and 64
values of external-context variables and of data of the internal
state of the PA, which are necessary for the mathematical
operation, [0072] Calculating in a step 65 the operational-context
variable, by means of the mathematical operation and of the values
of aircraft signals and external-context variables.
[0073] FIG. 6 illustrates the principle of a method for calculating
execution logic for the automatic piloting system. According to the
invention, an execution logic can be the association of an event
and of a boolean operation the operands of which may be variables
of the operational context and the operators of which may be
operators such as logical AND and logical OR. The various execution
logic depends on the aircraft and on the aircraft manufacturer's
need. The PA system is designed so that the execution logic is
parametrized in the database DB, that is to say the database DB can
reference events of the PA system and variables of the operational
context, in the guise of operands of boolean operations. The PA
system offers a mechanism making it possible to identify the events
and a mechanism making it possible to reference the variables of
the operational context. These mechanisms can be carried out by a
unique identifier associated with the events, with the variables of
the operational context or with any other item of data that can
help to define an execution logic. The form of the execution logic
is constrained by the configuration domain DC. When an event is
received by the PA system, such as a command of the operational
user 31, the PA system is designed so that the step of formulating
the execution logic accesses the database DB to search for all the
various logic associated with this event. For each logic found, the
boolean operation of the logic is evaluated.
[0074] As represented in FIG. 6, the calculation of execution logic
comprises: [0075] A step 71 of receiving an activation event [0076]
A step 72 of identifying a set of execution logic associated with
this activation event, specified in the database DB, [0077] For
each execution logic associated with the activation event: [0078] A
step 73 of identifying the values of operational-context variables
necessary for the evaluation of the logic, [0079] A step 74 of
formulating the execution logic for the operational-context
variables.
[0080] Thus, on completion of the calculation, with an activation
event received is associated a set of execution logic which may or
may not be satisfied, as a function of the operational context of
the PA. This result is subsequently implemented for the management
of the piloting directives, or the management of the PA modes and
laws, by means of the elementary cells 43 and 44 described
previously.
[0081] Stated otherwise, the step of formulating execution logic
consists in calculating, for a set of logic associated, in a
database of binary parameters DB, with an activation event provided
by the automatic piloting system, a boolean condition of
satisfaction of the logic, by means of external-context or
operational-context variables; the set of the execution logic
associated with the activation event being able to be implemented
for the management of the guidance directives and the management of
the automatic guidance or piloting modes and law.
[0082] Advantageously, the step of managing the guidance directives
consists in: [0083] calculating a piloting or guidance directive
value, by: [0084] identifying a mathematical operation, described
in the database DB, making it possible to calculate the value of
the directive, [0085] identifying parameter values of the database
DB necessary for the mathematical operation, [0086] formulating the
value of the directive, by calculating by means of the mathematical
operation, parameters of the operation and aircraft signals, [0087]
evaluating piloting or guidance directive parameters as described
in the database DB.
[0088] Advantageously, the step of managing the piloting or
guidance laws and modes consists in: [0089] identifying a guidance
segment stimulated by an activation event according to an
activation logic, [0090] identifying at least one piloting or
guidance directive to be formulated, a guidance law to be
activated, a piloting configuration to be applied, or an envelope
protection to be activated.
[0091] The invention also pertains to a method for developing an
automatic piloting system having the characteristics described
above, and comprising in particular a step of defining a
configuration domain DC, the said configuration domain DC being
able by parametrization to cover a wide spectrum of operational
needs of the automatic piloting system, and a step of programming
and certifying several generic software engines.
[0092] The invention finally pertains to a method of maintenance of
a system having the characteristics described above, and comprising
a step of identifying a user logging on to the automatic piloting
system, a step of loading a database of binary parameters DB for
the parametrization of a generic software kernel, and a step of
storage aboard the aircraft; the automatic piloting system being
able in operational configuration to read the binary parameters of
the database DB.
* * * * *