1 Title of the Invention
Dynamic Simulation of Aircraft Flight Parameters Acquired from Flight
Data Recorders.
2 Field of the Invention
5 The invention relates to the development, in Aerospace domain, facilitates ·
assembler/designer to make the system testing more reliable & to observe
the deviation from realistic range or. user range.
3 Background of the Invention
Functionality test is the primary requirement before fitment of any avionics
10 _system to be installed on aircraft. In today's scenario the traditional
methodology is only available for simulation of parameters. Simulation or
generation of parameters as per the approved Acce"ptance Test "Procedure
(ATP) is th.e only method to ensure the functionality however it does ncit .
cater all possible condition·s during flight. The approved ATP only covers
15 few point to test. The~e was no method earlier to simulate the actual flight
condition through test rig's to test the system at ground. In general air~raft
sensor· related parameters mainly Analog, ARINC-429, Discrete. &
Frequency were being checked as per the test rig predefined inputs rather
than actual values happening during flight operation which results into
20 poor & less accurate testing of system in the defined user range. ·
3.1 Prior Art
Various simulators have been developed for testing the entire aircraft
based on structure, control, response and other sub systems but there is
no system available to test the Flight Data Recorder in loop back kind of
25 continuous manner.
Patent (Application nos. CN113255156A) Loop real-time simulation
system and method for civil aircraft ground dynamic test signals:
. Page 2 of 11
Applicant: Hindustan Aeronautics Limited
The invention discloses a loop real-time simulation system and method for
civil aircraft ground dynamic test signals, and the system comprises: a
human-computer 'interface subsystem which is connected ·with a
simulation subsystem and. is used for editing and compiling an aircraft
5 model, downloading. the compiled aircraft model to the simulation
subsystem, ·obtaining ARINC429 data transmitted by the simulation
· subsystem, and controlling and managing the aircraft model; and the
simulation subsystem that is used for carrying out real-time operation of
the airplane model, carrying out data fusion with al) avionics system real
10 part through an ARINC429 hardware board card, and sending the
received and sent ARINC429 data to the human-computer interface
subsystem. According. to the invention, the test cost of communication
between the aircraft and the avionics device ARINC429 is greatly reduced,
. and the test efficiency is improved.
15 Patent (Application no. CN111158261A) Simulation method and
· system of aircraft control system:
The invention discloses a simulation method and system of an aircraft
control system. !he method comprises the following steps: est1:1blishing a
physical model of an aircraft rudder control system; constructing an
20 · equivalent dynamic mathematical model of the aircraft rudder control
system according ·to the physical model of the aircraft rudder control
system; obtaining a multiple-input-multiple-output linear system state
model according to the equivalent dynamic mathematical model· of the
aircraft rudder control system; according to the multiple-input-multiple-
25 output linear system state model, obtaining a simulation image of a curve
of the deflection angle of the direction rudder changing along with time;
acquiring an actual image of a curve of the deflection angle of. the rudder .
changing withtime; and comparing the simulation image of the curve of
which the deflection angle of the direction rudder changes along with time
· 30 with the actual image of the curve. of which the deflection angle of the
Page 3 of 11
Applicant: Hindustan Aeronautics Limited
direction rudder changes along. with time to obtain simulation accuracy. By .
adopting the method or the system provided by the invention, the dynamic
characteristics of the ·aircraft· can be effectively analyzed·and researched,
and whether the designed control system· meets the specification
5 requirements or not can be checked.
Patent (Application no. CN113392599A) Method for. determining
dynamic re. sponse of elas.t ic. aircraft:
The invention belongs to the technical field of aircraft simulation, and
particularly relates to a method for· determining the dynamic rt;lsponse of
10 an elastic aircraft. The method comprises the following steps: S1,
determining the aerodynamic resistance, lift force and pitching moment of
a rigid body of the aircraft at the current moment; S2, determining modal
coordin.a te dynamic. response o. f elastic· vibration of the aircraft according
to the gust speed; S3, determining rigid body aerodynamic force correction
15 caused by elastic deformation of the aircraft according to the modal
coordinate dynamic response; S4, correcting the aerodynamic resistance,
the lift force and. the pitching moment of the rigid body in the step S1
based on the aerodynamic force correction of the rigid body to obtain.
corrected aerodynamic resistance, lift force and pitching moment of the
20 aircraft; and S5, performing dynamic response solution on the aircraft
according to the corrected aerodynamic resistance, lift force and pitching
moment of the aircraft, updating the aerodynamic attack angle, elevator
skewness and gust speed at the next moment based on a solution result,
and returning to the step S1 for iterative calculation until simulation is
25 finished. According to the invention, the simulation precfsio.n is improved.
Patent (Application no. CN115859592A) 4. CN115859592A
dynamic simulation method for avionics system ground:
Flight
The invention relates to the technical field of flight simulation, in particular
to a flight dynamic simulation method for an avionics system ground join~
Page 4 of 11
Applicant: Hindustan Aeronautics Limited
test, which comprises the following steps: a simulation flight scene is set in
advance, the simulation flight scene comprises navigation stage flight
dynamic· simulation, interception/fighting stage flight dynamic simulation
and approach stage flight dynamic simulation, the flight dynamic
5 simulation in the navigation stage comprises pure inertia simulation and·
combined simulation, and the combined simulation comprises satellite
combined navigation simulation and radio combined navigation simulation;
and .according to the simulation flight scene, equipment which is operated
in cooperation with ·the flight simulation computer is automatically selected ..
10 According to the invention," incorrect test results caused by in coordinated
work among a plurality of systems during testing are effectively avoided;
according to the invention, the dynamic motion· of the avionics system in
multiple scenes in the air is fully simulated in a ground test environment,
the function verification ofthe avionics system is greatly improved, and the
15 flight safety and task completion are ensured.
4 Brief Summary of the Invention
Flight Data Recorder is us. ed to record the. critical parameters of .. flight in
Crash Protected Memory module which is used for post accident analysis.
Erroneous Functionality aspect of Flight Data Recorder (9) is an important
20 factor before actual flight operations. Flight Data Recorders (9) is being
tested as per approved functional test procedure in Lab before actual flight
operations so the scenario cir test points are predefined but to ensure the
entire range of functionality there is need of actual parameters simulation.
When aircraft flies once is known as one sortie (1), that sortie contains the
25 actual value of all parameters as recorded. The values receded in sortie
file may again be . used for simulation. Dynamic Simulation of various
aircraft parameters like Analog (2), Discrete (3), Tache & ARINC-429 (5)
etc in .accordance with downloaded sortie file (1) from Flight Data
Recorders is required to cover the entire functionality check of Flight Data
30 Recorder (9).