CN115331515A - Lightweight online flight simulation system based on enhanced virtual reality - Google Patents
Lightweight online flight simulation system based on enhanced virtual reality Download PDFInfo
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/12—Motion systems for aircraft simulators
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/16—Ambient or aircraft conditions simulated or indicated by instrument or alarm
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention discloses a light online flight simulation system based on enhanced virtual reality, which comprises a simulation platform, an in-cabin operation component, an enhanced virtual reality system, a six-degree-of-freedom motion mechanism, an instrument data interface, an instrument system and a simulation control system, wherein the simulation platform is connected with the instrument data interface; the instrument data interface is connected with the instrument system, and the cabin control assembly, the enhanced virtual reality system, the six-degree-of-freedom motion mechanism, the instrument data interface, the instrument system and the simulation control system are all connected with the simulation platform. The light-weight flight training system based on the immersive display system or the enhanced virtual reality system (AR) can realize orientation tracking, virtual-real fusion and matching of a real control assembly and an instrument system in a cabin by means of an optical projection type helmet display and a head tracking system, and realizes an aviation training system which is complete in function, strong in immersive feeling, low in cost and convenient to install and deploy.
Description
Technical Field
The invention relates to the technical field of flight simulation, in particular to a light-weight online flight simulation system based on enhanced virtual reality.
Background
In the field of navigation, with the low altitude open in China, general aviation rises rapidly, the demands of aviation clubs and aviation schools on light airplane flight trainers are increasing day by day, huge gaps exist in the demands of aviation flight personnel and professionals in the fields related to aviation flight, and the demands of flight simulation equipment, maintenance training equipment and air traffic control training equipment are conservatively estimated to be more than 20 million yuan. On the other hand, with the development of national economy and the improvement of the living standard of people, the demand for experience consumption is increasingly increased, and about 50 million yuan of huge market space in China is preliminarily estimated. Therefore, the product not only meets various requirements of pilot training, but also provides extremely real and reliable flight experience in the consumption field, and has wide market prospect by adding the application of a simulation technology and a virtual reality technology.
The traditional flight simulator is applied to engineering of professional flight training and design institutions, the market is mainly concerned by foreign manufacturers and enterprises in a few countries, most of the market is large-scale projects, the design period is long, the capital occupation is large, and the implementation risk is high. The domestic simulation technology is relatively laggard and the application is concentrated in high-end technical fields such as military, civil aviation and the like.
Disclosure of Invention
The invention aims to provide a light online flight simulation system based on enhanced virtual reality to solve the problems in the prior art.
In order to achieve the purpose, the invention provides the following technical scheme: a light online flight simulation system based on enhanced virtual reality comprises a simulation platform, an in-cabin control assembly, an enhanced virtual reality system, a six-degree-of-freedom motion mechanism, an instrument data interface, an instrument system and a simulation control system;
the instrument data interface is connected with the instrument system, and the cabin control assembly, the enhanced virtual reality system, the six-degree-of-freedom motion mechanism, the instrument data interface, the instrument system and the simulation control system are all connected with the simulation platform.
Preferably, the simulation system comprises a manual control module, an automatic flight system, an operation load system, a flight control system, an aerodynamic model, a ground control force model, an atmospheric environment model, a vision system and a comprehensive system module; the manual control module controls the automatic flight system through an A/P control instruction, the manual control module and the automatic flight system respectively control the flight control system through a flight control instruction, the flight control system is connected with an operation load system, the flight control system is connected with an aerodynamic model and a ground control force model, the aerodynamic model and the ground control force model are connected with the integrated system module, the aerodynamic model and the ground control force model are further connected with the visual system, and the atmospheric environment model is respectively connected with the aerodynamic model, the ground control force model and the visual system.
Preferably, the cabin control assembly is connected with the manual control module through a control signal, and the aerodynamic model and the ground control force model are respectively connected with the enhanced virtual reality system and the six-degree-of-freedom motion mechanism; the enhanced virtual reality system is connected with the manual control module, and the instrument system is connected with the manual control module.
Preferably, the integrated system module comprises an air conditioning system, a power supply system, a fire protection system, a fuel system, a hydraulic system, an anti-icing and rainproof system, an indication recording system, a landing gear system, a navigation system, an air source system, an APU system and an engine system.
Preferably, the aerodynamic mathematical model comprises a pneumatic coefficient model and a mathematical model of aerodynamic force and moment, flight parameters such as height, attack angle, sideslip angle and the angular speed of the airplane around the airplane body axis and a rudder deflection angle are calculated according to other model parameters of the flight simulation model, a pneumatic derivative of the airplane at a certain moment is calculated by adopting a linear interpolation or nonlinear fitting method, and aerodynamic force and aerodynamic moment of the airplane under the airplane body coordinates are calculated for solving a motion equation.
Preferably, the atmospheric environment model comprises a static atmospheric model and a dynamic atmospheric model, the static atmospheric model calculates parameters related to the aircraft altitude according to the international standard atmosphere and the correction, and the dynamic atmospheric model calculates and simulates the atmospheric disturbance condition.
Compared with the prior art, the invention has the beneficial effects that: the light flight training system based on the immersive display system or the enhanced virtual reality system (AR) can realize orientation tracking and virtual-real fusion by depending on an optical projection type helmet display and a head tracking system, and is matched with a real control assembly and an instrument system in a cabin, so that the aviation training system which is complete in function, strong in immersive effect, low in cost and convenient to install and deploy is realized; the AR system adopted in flight simulation is a penetrating helmet-type display based on an optical principle, so that the visual immersion of a user can be greatly enhanced; the system integrates real world information and virtual world information in a seamless manner, entity information which is difficult to experience in a certain time space range of the real world originally is simulated and then superposed through a graph generator (IG), and virtual information is applied to the real world and is perceived by human senses, so that sense experience beyond reality is achieved; real cockpit environment and environment scenes outside the virtual window are superposed to the same picture or space in real time and exist simultaneously, so that not only is real world information displayed, but also virtual information is displayed simultaneously, and the two kinds of information are mutually supplemented and superposed; the system comprises an aerodynamic simulation model, a power device model, an atmospheric environment simulation model, an avionics system model, a flight control system model, an airplane system simulation model and the like; unified resource allocation and scheduling are carried out through a parallel computing and distributed control method, and various requirements of 'identification and use rules of flight simulation equipment (CCAR 60)' of China civil aviation administration are met; the project establishes an aerodynamic model, a ground control force and moment model, a quality characteristic model and a motion equation model which are suitable for a high-grade flight training system through digestion and absorption of foreign mature technologies, and is matched with a flight control system model and related components, so that the real-time feedback data of the whole aircraft meets the QTG test requirement of a specific aircraft model; the aerodynamic mathematical model comprises a pneumatic coefficient model (including pneumatic elasticity correction), a mathematical model of aerodynamic force and moment, flight parameters such as height, an attack angle, a sideslip angle and an angular speed of the airplane around the airplane body axis and a rudder deflection angle are calculated according to other model parameters of the flight simulation model, a pneumatic derivative of the airplane at a certain moment is calculated by adopting a linear interpolation or nonlinear fitting method, and the aerodynamic force and the aerodynamic moment of the airplane under the airplane body coordinates are calculated for solving a motion equation; the method comprises the following steps that the forces and moments of a kinematics mathematical model airplane, such as gravity, aerodynamic force, engine thrust, contact force of an undercarriage and the ground and the like, are solved by adopting a six-degree-of-freedom full-quantity nonlinear motion equation to complete six-degree-of-freedom flight state and motion parameters of the airplane, triaxial acceleration and triaxial angular velocity of the airplane under a body coordinate system are calculated, the speed, displacement and the like of the airplane are obtained through fourth-order Runger-Kutta integration, and the flight parameters of the airplane, such as attitude, position and the like, are obtained according to a geometric space transformation relation; the power plant model realizes the resolving of engine data by establishing a working state control model of an engine system, an engine rotating speed and thrust/tension model, a fuel consumption model, an oil tank flow control model, an engine fault state model and the like; the atmospheric environment model comprises a static atmospheric model and a dynamic atmospheric model, the static atmospheric model calculates parameters related to the height of the airplane, such as atmospheric pressure, density, temperature and the like according to International Standard Atmospheric (ISA) and correction, and the dynamic atmospheric model calculates and simulates the conditions of atmospheric disturbance, such as disturbance wind field models of clear air turbulence, wind shear table and the like; in the aspect of simulation of an avionics system, the simulation degree of the current domestic flight training system to advanced avionics devices such as an avionics system, particularly a Flight Management System (FMS), an automatic flight control system (DFCS), a stall management yaw damping computer (SMYD) and the like is insufficient, the project utilizes the development experience of foreign mature models and adopts methods such as Re-host, re-engineering and the like to establish an avionics simulation module meeting the unit training requirements; the Re-host is a novel technology at present, an environment meeting the operation of airborne avionics is established by utilizing technologies such as a virtual machine and the like in a standard computer environment, bus connection environments such as ARINC429/ADFX and the like are kept, and the definition and the operation are carried out according to the speed and interface parameters of a standard avionic system, so that the 'Re-host' of the airborne system is realized, and the high-precision avionic system simulation is realized; the Re-engineering adopts an identification modeling technology, utilizes operation feedback and interface data obtained by measurement in the operation or experiment process of the avionics system, and refers to data such as airborne software design documents SRD and FDD to realize simulation and fitting of the avionics system.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic diagram of the present invention;
fig. 2 is a schematic diagram of the data and signal acquisition of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention. Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be obtained by a person skilled in the art without inventive efforts based on the embodiments of the present invention, are within the scope of protection of the present invention.
Referring to fig. 1-2, in an embodiment of the present invention, a lightweight online flight simulation system based on enhanced virtual reality includes a simulation platform, an in-cabin control component, an enhanced virtual reality system, a six-degree-of-freedom motion mechanism, an instrument data interface, an instrument system, and a simulation control system;
the instrument data interface is connected with the instrument system, and the cabin control assembly, the enhanced virtual reality system, the six-degree-of-freedom motion mechanism, the instrument data interface, the instrument system and the simulation control system are all connected with the simulation platform.
Preferably, the simulation system comprises a manual control module, an automatic flight system, an operation load system, a flight control system, an aerodynamic model, a ground control force model, an atmospheric environment model, a vision system and a comprehensive system module; the manual control module controls the automatic flight system through an A/P control instruction, the manual control module and the automatic flight system respectively control the flight control system through a flight control instruction, the flight control system is connected with an operation load system, the flight control system is connected with an aerodynamic model and a ground control force model, the aerodynamic model and the ground control force model are connected with the integrated system module, the aerodynamic model and the ground control force model are further connected with the visual system, and the atmospheric environment model is respectively connected with the aerodynamic model, the ground control force model and the visual system.
Preferably, the cabin control assembly is connected with the manual control module through a control signal, and the aerodynamic model and the ground control force model are respectively connected with the enhanced virtual reality system and the six-degree-of-freedom motion mechanism; the enhanced virtual reality system is connected with the manual control module, and the instrument system is connected with the manual control module.
Preferably, the integrated system module comprises an air conditioning system, a power supply system, a fire protection system, a fuel system, a hydraulic system, an anti-icing and rainproof system, an indication recording system, a landing gear system, a navigation system, an air source system, an APU system and an engine system.
Preferably, the aerodynamic mathematical model comprises a pneumatic coefficient model and a mathematical model of aerodynamic force and moment, flight parameters such as height, attack angle, sideslip angle and angular speed of the airplane around the airplane axis and rudder deflection angle are calculated according to other model parameters of the flight simulation model, the aerodynamic derivative of the airplane at a certain moment is calculated by adopting a linear interpolation or nonlinear fitting method, and the aerodynamic force and the aerodynamic moment of the airplane under the airplane coordinate are calculated for solving a motion equation.
Preferably, the atmospheric environment model comprises a static atmospheric model and a dynamic atmospheric model, the static atmospheric model calculates parameters related to the aircraft altitude according to the international standard atmosphere and the correction, and the dynamic atmospheric model calculates and simulates the atmospheric disturbance condition.
The light flight training system based on the immersive display system or the enhanced virtual reality system (AR) can realize orientation tracking, virtual-real fusion and cooperation of a real control assembly and an instrument system in a cabin by means of an optical projection type helmet display and a head tracking system, and is an aviation training system which is complete in function, strong in immersive effect, low in cost and convenient to install and deploy.
The AR system employed in flight simulation is a penetrating head-mounted display based on optical principles, which can greatly enhance the visual immersion of the user. The system integrates real world information and virtual world information in a seamless mode, entity information which is difficult to experience in a certain time space range of the real world originally is overlapped after analog simulation through a graph generator (IG), virtual information is applied to the real world and is perceived by human senses, and therefore sense experience beyond reality is achieved. Real cockpit environment and environment scenes outside a virtual window are overlaid to the same picture or space in real time and exist at the same time, so that not only is real world information displayed, but also virtual information is displayed at the same time, and the two kinds of information are mutually supplemented and overlaid;
the simulation model comprises an aerodynamic simulation model, a power device model, an atmospheric environment simulation model, an avionics system model, a flight control system model, an airplane system simulation model and the like. Unified resource allocation and scheduling are performed through a parallel computing and distributed control method, and various requirements of 'identification and use rules of flight simulation equipment (CCAR 60)' of the China civil aviation administration are met. According to the project, an aerodynamic model, a ground control force and moment model, a quality characteristic model and a motion equation model which are suitable for a high-grade flight training system are established through digestion and absorption of foreign mature technologies, and a flight control system model and related components are matched, so that real-time feedback data of the whole machine meet QTG (quantitative trait locus) testing requirements of specific machine types.
The aerodynamic mathematical model comprises a pneumatic coefficient model (including pneumatic elasticity correction), a mathematical model of aerodynamic force and moment, flight parameters such as height, an attack angle, a sideslip angle and an angular speed of the airplane around the airplane body axis and a rudder deflection angle are calculated according to other model parameters of the flight simulation model, a pneumatic derivative of the airplane at a certain moment is calculated by adopting a linear interpolation or nonlinear fitting method, and the aerodynamic force and the aerodynamic moment of the airplane under the airplane body coordinates are calculated for solving a motion equation. The method comprises the steps of adopting a six-degree-of-freedom full-quantity nonlinear motion equation to solve six-degree-of-freedom flight states and motion parameters of the airplane by force and moment of a kinematics mathematical model airplane, such as gravity, aerodynamic force, engine thrust, contact force of an undercarriage and the ground, calculating three-axis acceleration and three-axis angular velocity under an airplane body coordinate system, obtaining speed, displacement and the like of the airplane through four-order Runger-Kutta integration, and obtaining flight parameters of the airplane, such as attitude, position and the like according to a geometric space transformation relation.
The power plant model realizes the resolving of engine data by establishing a working state control model, an engine rotating speed and thrust/tension model, a fuel consumption model, an oil tank flow control model, an engine fault state model and the like of an engine system.
The atmospheric environment model comprises a static atmospheric model and a dynamic atmospheric model, the static atmospheric model calculates parameters related to the aircraft altitude according to the International Standard Atmosphere (ISA) and correction, such as atmospheric pressure, density, temperature and the like, and the dynamic atmospheric model calculates and simulates the conditions of atmospheric disturbance, such as disturbance wind field models of clear air turbulence, wind shear tables and the like. In the aspect of simulation of an avionics system, the simulation degree of the current domestic flight training system to advanced avionics devices such as an avionics system, particularly a Flight Management System (FMS), an automatic flight control system (DFCS) and a stall management yaw damping computer (SMYD) is insufficient, and the project establishes an avionics simulation module meeting the unit training requirements by using the development experience of foreign mature models and methods such as Re-host and Re-engineering.
The Re-host is a novel technology at present, an environment meeting the operation of airborne avionics is established by utilizing technologies such as a virtual machine and the like in a standard computer environment, bus connection environments such as ARINC429/ADFX and the like are kept, and the definition and the operation are carried out according to the speed and interface parameters of a standard avionic system, so that the 'Re-host' of the airborne system is realized, and the high-precision avionic system simulation is realized; the Re-engineering adopts an identification modeling technology, utilizes operation feedback and interface data obtained by measurement in the operation or experiment process of the avionics system, and refers to data such as airborne software design documents SRD and FDD to realize simulation and fitting of the avionics system.
The working principle of the invention is as follows: the light flight training system based on the immersive display system or the enhanced virtual reality system (AR) can realize orientation tracking and virtual-real fusion by depending on an optical projection type helmet display and a head tracking system, and is matched with a real control assembly and an instrument system in a cabin, so that the aviation training system which is complete in function, strong in immersive effect, low in cost and convenient to install and deploy is realized; the AR system adopted in flight simulation is a penetrating helmet-type display based on an optical principle, so that the visual immersion of a user can be greatly enhanced; the system integrates real world information and virtual world information in a seamless manner, entity information which is difficult to experience in a certain time space range of the real world originally is simulated and then superposed through a graph generator (IG), and virtual information is applied to the real world and is perceived by human senses, so that sense experience beyond reality is achieved; real cockpit environment and environment scenes outside the virtual window are superposed to the same picture or space in real time and exist simultaneously, so that not only is real world information displayed, but also virtual information is displayed simultaneously, and the two kinds of information are mutually supplemented and superposed; the system comprises an aerodynamic simulation model, a power device model, an atmospheric environment simulation model, an avionics system model, a flight control system model, an airplane system simulation model and the like; unified resource allocation and scheduling are carried out through a parallel computing and distributed control method, and various requirements of 'identification and use rules of flight simulation equipment (CCAR 60)' of the China civil aviation administration are met; the project establishes an aerodynamic model, a ground control force and moment model, a quality characteristic model and a motion equation model which are suitable for a high-grade flight training system through digestion and absorption of foreign mature technologies, and is matched with a flight control system model and related components, so that real-time feedback data of the whole machine meets the QTG test requirement of a specific machine type; the method comprises the following steps that an aerodynamic mathematical model comprises an aerodynamic coefficient model (including pneumatic elasticity correction), an aerodynamic force and moment mathematical model, flight parameters such as height, an attack angle, a sideslip angle and an angular speed of the airplane around the airplane axis and a rudder deflection angle are calculated according to other model parameters of a flight simulation model, an aerodynamic derivative of the airplane at a certain moment is calculated by adopting a linear interpolation or nonlinear fitting method, and aerodynamic force and aerodynamic moment of the airplane under the airplane coordinate are calculated and used for solving a motion equation; the method comprises the following steps that the forces and moments of a kinematics mathematical model airplane, such as gravity, aerodynamic force, engine thrust, contact force of an undercarriage and the ground and the like, are solved by adopting a six-degree-of-freedom full-quantity nonlinear motion equation to complete six-degree-of-freedom flight state and motion parameters of the airplane, triaxial acceleration and triaxial angular velocity of the airplane under a body coordinate system are calculated, the speed, displacement and the like of the airplane are obtained through fourth-order Runger-Kutta integration, and the flight parameters of the airplane, such as attitude, position and the like, are obtained according to a geometric space transformation relation; the power plant model realizes the resolving of engine data by establishing a working state control model of an engine system, an engine rotating speed and thrust/tension model, a fuel consumption model, an oil tank flow control model, an engine fault state model and the like; the atmospheric environment model comprises a static atmospheric model and a dynamic atmospheric model, the static atmospheric model calculates parameters related to the aircraft altitude, such as atmospheric pressure, density, temperature and the like according to the International Standard Atmosphere (ISA) and correction, and the dynamic atmospheric model calculates and simulates the atmospheric disturbance condition, such as disturbance wind field models of clear air turbulence, wind shear tables and the like; in the aspect of simulation of an avionics system, the simulation degree of the current domestic flight training system to advanced avionics devices such as an avionics system, particularly a Flight Management System (FMS), an automatic flight control system (DFCS), a stall management yaw damping computer (SMYD) and the like is insufficient, the project utilizes the development experience of foreign mature models and adopts methods such as Re-host, re-engineering and the like to establish an avionics simulation module meeting the unit training requirements; the Re-host is a novel technology at present, an environment meeting the operation of airborne avionics is established by utilizing technologies such as a virtual machine and the like in a standard computer environment, bus connection environments such as ARINC429/ADFX and the like are kept, and the definition and the operation are carried out according to the speed and interface parameters of a standard avionic system, so that the 'Re-host' of the airborne system is realized, and the high-precision avionic system simulation is realized; the Re-engineering adopts an identification modeling technology, utilizes operation feedback and interface data obtained by measurement in the operation or experiment process of the avionics system, and refers to data such as airborne software design documents SRD and FDD to realize simulation and fitting of the avionics system.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described above, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. The utility model provides an online flight analog system of lightweight based on enhancement mode virtual reality which characterized in that: the system comprises a simulation platform, an in-cabin control component, an enhanced virtual reality system, a six-degree-of-freedom motion mechanism, an instrument data interface, an instrument system and a simulation control system;
the instrument data interface is connected with the instrument system, and the cabin control assembly, the enhanced virtual reality system, the six-degree-of-freedom motion mechanism, the instrument data interface, the instrument system and the simulation control system are all connected with the simulation platform.
2. The enhanced virtual reality based lightweight online flight simulation system according to claim 1, wherein: the simulation system comprises a manual control module, an automatic flight system, an operation load system, a flight control system, an aerodynamic model, a ground control force model, an atmospheric environment model, a visual system and a comprehensive system module; the manual control module controls the automatic flight system through an A/P control instruction, the manual control module and the automatic flight system respectively control the flight control system through a flight control instruction, the flight control system is connected with an operation load system, the flight control system is connected with an aerodynamic model and a ground control force model, the aerodynamic model and the ground control force model are connected with the integrated system module, the aerodynamic model and the ground control force model are further connected with the visual system, and the atmospheric environment model is respectively connected with the aerodynamic model, the ground control force model and the visual system.
3. The enhanced virtual reality based lightweight online flight simulation system according to claim 2, wherein: the cabin control assembly is connected with the manual control module through a control signal, and the aerodynamic model and the ground control force model are respectively connected with the enhanced virtual reality system and the six-degree-of-freedom motion mechanism; the enhanced virtual reality system is connected with the manual control module, and the instrument system is connected with the manual control module.
4. An enhanced virtual reality based lightweight online flight simulation system according to claim 2 or 3, wherein: the integrated system module comprises an air conditioning system, a power supply system, a fire prevention system, a fuel oil system, a hydraulic system, an anti-icing and rainproof system, an indication recording system, an undercarriage system, a navigation system, an air source system, an APU system and an engine system.
5. The enhanced virtual reality based lightweight online flight simulation system according to claim 2, wherein: the aerodynamic mathematical model comprises a pneumatic coefficient model and mathematical models of aerodynamic force and moment, flight parameters such as height, attack angle, sideslip angle and the angular speed of the airplane around the airplane axis and rudder deflection angle are calculated according to other model parameters of the flight simulation model, the aerodynamic derivative of the airplane at a certain moment is calculated by adopting a linear interpolation or nonlinear fitting method, the aerodynamic force and the aerodynamic moment of the airplane under the airplane coordinate are calculated, and the aerodynamic force and the aerodynamic moment are used for solving a motion equation.
6. The enhanced virtual reality based lightweight online flight simulation system according to claim 2, wherein: the atmospheric environment model comprises a static atmospheric model and a dynamic atmospheric model, the static atmospheric model calculates parameters related to the aircraft altitude according to the international standard atmosphere and correction, and the dynamic atmospheric model calculates and simulates the atmospheric disturbance condition.
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| CN103473966A (en) * | 2013-08-29 | 2013-12-25 | 南京航空航天大学 | Semi-physical digital simulation control platform of aircraft cockpit |
| CN112037606A (en) * | 2020-08-28 | 2020-12-04 | 南京轩世琪源软件科技有限公司 | Interactive virtual simulation teaching training system |
| CN112542070A (en) * | 2020-11-30 | 2021-03-23 | 中国人民解放军海军航空大学青岛校区 | Light-weight dynamic flight simulation trainer based on high-definition head display |
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