CN115541098A - Intelligent sensing system for transverse aerodynamic moment of aircraft based on aerodynamic load of airfoil - Google Patents
Intelligent sensing system for transverse aerodynamic moment of aircraft based on aerodynamic load of airfoil Download PDFInfo
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- CN115541098A CN115541098A CN202211392979.2A CN202211392979A CN115541098A CN 115541098 A CN115541098 A CN 115541098A CN 202211392979 A CN202211392979 A CN 202211392979A CN 115541098 A CN115541098 A CN 115541098A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L9/00—Measuring steady of quasi-steady pressure of fluid or fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means
- G01L9/02—Measuring steady of quasi-steady pressure of fluid or fluent solid material by electric or magnetic pressure-sensitive elements; Transmitting or indicating the displacement of mechanical pressure-sensitive elements, used to measure the steady or quasi-steady pressure of a fluid or fluent solid material, by electric or magnetic means by making use of variations in ohmic resistance, e.g. of potentiometers, electric circuits therefor, e.g. bridges, amplifiers or signal conditioning
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P13/00—Indicating or recording presence, absence, or direction, of movement
- G01P13/02—Indicating direction only, e.g. by weather vane
- G01P13/025—Indicating direction only, e.g. by weather vane indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
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Abstract
The invention provides an aircraft transverse aerodynamic moment intelligent sensing system based on airfoil aerodynamic loads, and belongs to the field of flight parameter measurement. The device comprises a surface pressure measuring point, an air pressure transmission pipe, a high-precision pressure sensor, a pressure signal transmission cable, a signal transmitter, a signal communication cable, a data processing core module and an upper computer communication cable which are sequentially connected, wherein the current streaming flow condition of the aircraft is distinguished by measuring the aerodynamic load of the airfoil of a typical station aircraft, the action size and the direction of the transverse aerodynamic moment of the aircraft are further sensed, more specific measuring information is provided for the aircraft, and the flight control requirement of the aircraft in the high-dynamic flight process is supported.
Description
Technical Field
The invention relates to the field of flight parameter measurement, in particular to an intelligent sensing system for transverse aerodynamic moment of an aircraft based on airfoil aerodynamic load.
Background
The Air Data (Air Data) of the airplane comprises parameters related to the airflow environment of the airplane during flying, such as an attack angle, a sideslip angle, a vacuum speed, a Mach number, total pressure, static temperature and the like, and is indispensable information of an avionic system, such as fire control, flight management, cockpit instrument display/warning and the like. Atmospheric data for an aircraft reflects the conditions of the airflow that the aircraft is facing during flight. Under different airflow conditions, the aircraft body can be subjected to different airflow acting forces, and the concentrated representation on the aircraft is the change of the motion attitude of the aircraft. Thus, the data parameters provided by conventional aircraft atmospheric data have a greater effect on the fundamental amount of influence of the aircraft on the air flow conditions. As one of the essential avionics systems of modern military and civil aircraft, different performance aircraft have different requirements on the accuracy, dynamic range, resolution, hysteresis characteristics and update rate of the atmospheric data system.
Conventional atmospheric data measurement schemes mainly include two types of invasive sensors and embedded sensors: the traditional atmospheric data system adopts an intrusive measurement mode, the key marks of the system are an airspeed tube and an attack angle/sideslip angle sensor which are externally arranged outside an airplane, the atmospheric sensor is in direct contact with the air around the airplane body and is used for providing information such as the temperature, the air pressure and the direction (namely the attack angle and the sideslip angle) of the external airflow, and other flight control parameters such as the vacuum speed, the indicated airspeed and the Mach number are obtained after the information is subjected to calculation, compensation and correction by an atmospheric data computer.
Under transonic and hypersonic flight conditions, severe friction between the aircraft and the surrounding air brings huge stress to the external atmospheric measurement probe, and a high-heat environment caused by friction can damage the measurement probe of the traditional atmospheric data system, so that effective measurement cannot be carried out. In order to solve the problem of atmospheric data measurement under severe flight conditions such as large angle of attack flight and high supersonic speed, an embedded atmospheric data system measurement method is provided in the 60 th century, and the method adopts a plurality of pressure sensors embedded in different positions on the surface of an airplane, and calculates atmospheric data such as an attack angle, a sideslip angle, total pressure, static pressure and the like by using pressure measurement data of a plurality of positions based on an established airplane surface pressure distribution model. Compared with the traditional atmospheric data measurement means, the embedded measurement method has the following advantages: 1. the sensors arranged by the embedded method can still normally work under extreme flight environments such as large Mach number, large attack angle and the like, and the measurement working range of the traditional test system is expanded; 2. the sensor and the airplane body can be designed in an embedded mode, exposed parts on the surface of the airplane body are reduced, and the airplane is suitable for the stealth design of the appearance of the airplane; 3. more sensors can be arranged in an embedded mode, and the redundancy fault-tolerant capability of the system is improved.
The existing atmospheric data measurement technology aims at directly or indirectly measuring atmospheric parameters such as an attack angle, a sideslip angle, a vacuum speed, a Mach number, total pressure, static temperature and the like, obtaining airflow parameters required by a flight control system and only meeting the conventional flight requirements. In the flight process under the limit condition (gust, large attack angle maneuver and the like), the airplane cannot master the self streaming condition only by the existing atmospheric data measurement means, cannot effectively sense the stress state of the airplane body, and does not have the capability of predicting the movement trend of the airplane.
In the flight process of the existing aircraft, the aircraft cannot master the self streaming condition, cannot effectively sense the stress state of the aircraft body, does not have the capability of predicting the motion trend of the aircraft, still carries out flight control according to a conventional mode under the working condition of sudden flight, is easy to lose control of the aircraft body and threatens the flight safety.
Disclosure of Invention
The invention aims to provide an aircraft aerodynamic force sensing system which is high in dynamic and sensing capability and based on airfoil aerodynamic loads. The aerodynamic force sensing system is characterized in that pressure information provided by aerodynamic pressure sensors distributed on the surface of an aircraft is utilized, and the information is converted into the stress state of the transverse aerodynamic moment of the aircraft in real time through a preset inversion algorithm.
The technical scheme of the invention is as follows:
the intelligent sensing system for the transverse aerodynamic moment of the aircraft based on the aerodynamic loads of the airfoils comprises a surface pressure measuring point 1, an air pressure transmission pipe 2, a high-precision pressure sensor 3, a pressure signal transmission cable 4, a signal transmitter 5, a signal communication cable 6, a data processing core module 7 and an upper computer communication cable 8 which are sequentially connected. The surface pressure measuring point 1 is arranged on the outer surface of the aircraft and is in direct contact with airflow; the air pressure transmission pipe 2 is a hollow pipeline, one end of the air pressure transmission pipe is connected with the surface pressure measuring point 1, the other end of the air pressure transmission pipe is connected with the high-precision pressure sensor 3, and the two ends of the air pressure transmission pipe are hermetically connected and used for transmitting the air pressure sensed by the surface pressure measuring point 1; the high-precision pressure sensor 3 is used for sensing the airflow pressure in the air pressure transmission pipe 2 and forming an analog electric signal; the pressure signal transmission cable 4 is connected with the high-precision pressure sensor 3 and the signal transmitter 5 and transmits the analog electric signal generated by the high-precision pressure sensor 3; the signal transmitter 5 converts the analog electric signal generated by the high-precision pressure sensor 3 into a digital electric signal through analog-to-digital conversion; the digital electric signals are concentrated into a data processing core module 7 through a signal communication cable 6; pressure data distributed on all positions of the surface of the aircraft are collected to a data processing core module 7 through a signal communication cable 6, aerodynamic load distribution information on the surface of the aircraft is formed through data processing, a rolling torque calculation result under a typical section position is formed according to the pressure distribution information, the distribution information is calculated to form transverse aerodynamic torque data through typical section characteristics obtained through aircraft layout simulation/test, aerodynamic force data information is output to an upper computer system through an upper computer communication cable 8, and the whole transverse aerodynamic force sensing process is completed.
The working principle of the aircraft transverse aerodynamic moment intelligent sensing system is as follows: the method comprises the steps of utilizing surface pressure measuring points symmetrically arranged on the wing surface of the aircraft, corresponding sensors and other devices to measure aerodynamic pressure load on the wing surface of the aircraft in real time in the flight process, calculating pressure data of key points at different positions on the surface to form a preliminary result of the turbulence form of the aircraft, and further judging the size and the direction of the transverse aerodynamic moment of the aircraft in the current state.
Furthermore, the effective working temperature range of the aircraft transverse aerodynamic moment intelligent sensing system is-40 ℃ to 60 ℃, and the measurable pressure range is 0 MPa to 1MPa.
Further, the surface pressure measuring point 1 can be made of metal, alloy and composite materials such as aluminum, steel, alloy and carbon fiber, and is not limited to the above materials, and all materials have air-tight sealing capability, have good extensibility and can be used for embedded installation of the surface of an aircraft, and are all suitable.
Further, the surface pressure measuring points 1 are symmetrically arranged on the wing surfaces of the aircraft along the spanwise position, and the number of the wing surfaces on one side is not less than 8;
further, the positions of the surface pressure measuring points 1 arranged on the aircraft are determined by the positions of the data characteristic points in the built-in algorithm generating process, and the arrangement mode, the number and the spatial positions of the surface pressure measuring points are different for different aircraft.
Further, the air pressure transmission pipe 2 can be made of metal, alloy and composite materials such as copper, aluminum alloy and rubber, is not limited to the above materials, has air sealing capability and good extensibility, and is suitable for use;
further, the air pressure transfer pipe 2 is not more than 5cm in length and not more than 2mm in diameter.
Further, the high-precision pressure sensor 3 can be a pressure sensor with a piezoelectric structure, a silicon chip structure and the like, is not limited to the above forms, and is suitable for all the pressure sensors with air pressure measurement capability and accuracy and dynamic characteristics meeting measurement requirements;
further, the air pressure measurement resolution of the high-precision pressure sensor 3 is not lower than 10Pa, and the effective working temperature range covers-40 ℃ to 60 ℃;
further, the measuring range of the high-precision pressure sensor 3 can be selected according to the actual flight condition of the aircraft;
further, the surface pressure measuring point 1, the air pressure transmission pipe 2 and the high-precision pressure sensor 3 can be integrally designed and embedded and flush mounted on a skin structure on the outer surface of the aircraft.
Further, the data processing core module 7 has data processing, storage, communication and distribution functions, and can convert pressure information into pneumatic power data through a built-in algorithm;
further, the data processing core module 7, the built-in algorithm of which needs to establish a calculation model through data obtained by carrying out pre-simulation and test on the aerodynamic shape of the aircraft, forms a roll moment calculation result at a typical section position according to pressure distribution information, and obtains roll moment data through typical section characteristics obtained by aircraft layout simulation/test and modeling calculation of the distribution information through typical point data.
The invention has the beneficial effects that: the invention provides an aircraft transverse aerodynamic moment intelligent sensing system based on airfoil aerodynamic loads, which is used for distinguishing the current streaming flow condition of an aircraft by measuring the airfoil aerodynamic loads of a typical station aircraft, further sensing the action size and direction of the transverse aerodynamic moment, providing more specific measurement information for the aircraft and supporting the flight control requirement of the aircraft in a high-dynamic flight process.
Drawings
FIG. 1 is a schematic diagram of an intelligent sensing system for the lateral aerodynamic moment of an aircraft based on the aerodynamic loading of an airfoil.
Fig. 2 is a schematic diagram of the working principle and the flow of the present invention.
Fig. 3 is a result of an experimental test of the working principle of the present invention, in which (a) is a pressure information feedback diagram for a left roll moment and (b) is a pressure information feedback diagram for a right roll moment.
Fig. 4 is a schematic view of embodiment 1 of the present invention.
FIG. 5 is a schematic diagram of the integrated design structure of the surface pressure measuring point, the air pressure transmitting tube and the high-precision pressure sensor in embodiment 1 of the invention.
Fig. 6 is a measurement schematic diagram of a first generation air data machine.
In the figure: 1 surface pressure measurement point, 2 atmospheric pressure transfer tubes, 3 high accuracy pressure sensor, 4 pressure signal transmission cables, 5 signal transmitter, 6-signal communication cable, 7 data processing core module, 8 in the host computer communication cable picture: 1-1 aircraft skin.
Detailed Description
The invention is further described below with reference to examples and figures.
Example 1
As shown in fig. 5: the surface pressure measuring point 1, the air pressure transfer pipe 2 and the high-precision pressure sensor 2 are in integrated design, and are embedded and flush mounted on an aircraft skin 1-1.
As shown in fig. 4: the integrated design structure (shown in figure 5) of the surface pressure measuring point 1, the air pressure transmission pipe 2 and the high-precision pressure sensor 3 is used for sensing the air flow pressure in the air pressure transmission pipe 2 and forming an analog electric signal; the pressure signal transmission cable 4 is connected with the surface pressure measuring point 1, the air pressure transmission pipe 2, the high-precision pressure sensor 3 integrated design structure and the signal transmitter 5, and transmits the analog electric signal generated by the high-precision pressure sensor 3; the signal transmitter 5 generates a digital electric signal by performing analog-to-digital conversion on the analog electric signal; the digital electric signals are concentrated into a data processing core module 7 through a signal communication cable 6; pressure data distributed on all positions of the surface of the aircraft are collected to a data processing core module 7 through a signal communication cable 6, aerodynamic load distribution information on the surface of the aircraft is formed through data processing, aerodynamic force data are formed through calculation of the distribution information according to a built-in inversion algorithm, and the aerodynamic force data information is output to an upper computer system through an upper computer communication cable 8, so that the whole aerodynamic moment sensing process is completed.
Particularly, the surface pressure measuring point 1 and the air pressure transmission pipe 2 are made of aluminum alloy, and the high-precision pressure sensor 3 is a silicon chip resistance type pressure sensor.
It should be noted that: the above embodiments are only used to illustrate the present invention and do not limit the technical solutions described in the present invention; thus, although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted; all such modifications and variations that do not depart from the spirit and scope of the invention are intended to be included within the scope of the appended claims.
Claims (8)
1. The aircraft transverse aerodynamic moment intelligent sensing system based on wing surface aerodynamic loads is characterized by comprising a surface pressure measuring point (1), an air pressure transmission pipe (2), a high-precision pressure sensor (3), a pressure signal transmission cable (4), a signal transmitter (5), a signal communication cable (6), a data processing core module (7) and an upper computer communication cable (8) which are sequentially connected; the surface pressure measuring point (1) is arranged on the outer surface of the aircraft and is in direct contact with airflow; the air pressure transmission pipe (2) is a hollow pipeline, one end of the air pressure transmission pipe is connected with the surface pressure measuring point (1), the other end of the air pressure transmission pipe is connected with the high-precision pressure sensor (3), and the two ends of the air pressure transmission pipe are hermetically connected and used for transmitting the air pressure sensed by the surface pressure measuring point (1); the high-precision pressure sensor (3) is used for sensing the airflow pressure in the air pressure transmission pipe (2) and forming an analog electric signal; the pressure signal transmission cable (4) is connected with the high-precision pressure sensor (3) and the signal transmitter (5) and transmits the analog electric signal generated by the high-precision pressure sensor (3); the signal transmitter (5) converts the analog electric signal generated by the high-precision pressure sensor (3) into a digital electric signal through analog-to-digital conversion; the digital electric signals are collected into a data processing core module (7) through a signal communication cable (6); pressure data distributed on all positions of the surface of the aircraft are collected to a data processing core module (7) through a signal communication cable (6), aerodynamic load distribution information on the surface of the aircraft is formed through data processing, a rolling torque resolving result under a typical section position is formed according to the pressure distribution information, the distribution information is calculated to form transverse aerodynamic torque data through typical section characteristics obtained through aircraft layout simulation/tests, aerodynamic force data information is output to an upper computer system through an upper computer communication cable (8), and the whole transverse aerodynamic torque sensing process is completed.
2. The intelligent sensing system for the transverse aerodynamic moment of the aircraft based on the aerodynamic loads of the airfoils as claimed in claim 1, wherein the effective working temperature range of the intelligent sensing system for the transverse aerodynamic moment of the aircraft is-40 ℃ to 60 ℃, and the measurable pressure range is 0 to 1Mpa.
3. The system for intelligently sensing the transverse aerodynamic moment of the aircraft based on the aerodynamic loads of the airfoils as claimed in claim 1, wherein the surface pressure measuring points (1) are symmetrically arranged on the airfoils of the aircraft along a spanwise position, and the number of the airfoils on one side is not less than 8.
4. The system for intelligently sensing the transverse aerodynamic moment of the aircraft based on the aerodynamic loads of the airfoils as claimed in claim 1, wherein the air pressure transfer pipe (2) is not more than 5cm in length and not more than 2mm in diameter.
5. The system for intelligently sensing the transverse aerodynamic moment of the aircraft based on the aerodynamic loads of the airfoils as claimed in claim 1, wherein the high-precision pressure sensor (3) has an air pressure measurement resolution of not less than 10Pa and an effective working temperature range covering-40 ℃ to 60 ℃.
6. The intelligent sensing system for the transverse aerodynamic moment of the aircraft based on the aerodynamic loads of the airfoils as claimed in claim 1, wherein the surface pressure measuring points (1), the air pressure transmission pipes (2) and the high-precision pressure sensors (3) can be designed integrally and are integrally embedded and flush mounted on a skin structure on the outer surface of the aircraft.
7. The system for intelligently sensing the transverse aerodynamic moment of the aircraft based on the aerodynamic loads of the airfoils as claimed in claim 1, wherein the data processing core module (7) has data processing, storing, communicating and distributing functions, and can convert pressure information into aerodynamic data through a built-in algorithm.
8. The intelligent sensing system for the transverse aerodynamic moment of the aircraft based on the aerodynamic loads of the airfoils as claimed in claim 1, wherein the built-in algorithm of the data processing core module (7) requires a calculation model to be established through data obtained by carrying out pre-simulation and test on the aerodynamic shape of the aircraft, a roll moment calculation result in a typical section position is formed according to pressure distribution information, typical section characteristics obtained through aircraft layout simulation/test are obtained, and the distribution information is subjected to modeling calculation through typical point data to obtain roll moment data.
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| CN202211392979.2A CN115541098A (en) | 2022-11-08 | 2022-11-08 | Intelligent sensing system for transverse aerodynamic moment of aircraft based on aerodynamic load of airfoil |
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| CN202211392979.2A CN115541098A (en) | 2022-11-08 | 2022-11-08 | Intelligent sensing system for transverse aerodynamic moment of aircraft based on aerodynamic load of airfoil |
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