CN112730887B - Mach number acquisition method and system in full-voltage failure - Google Patents

Mach number acquisition method and system in full-voltage failure Download PDF

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CN112730887B
CN112730887B CN202011610399.7A CN202011610399A CN112730887B CN 112730887 B CN112730887 B CN 112730887B CN 202011610399 A CN202011610399 A CN 202011610399A CN 112730887 B CN112730887 B CN 112730887B
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mach number
temperature
static
obtaining
total temperature
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CN112730887A (en
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杜超超
李少雄
孙海玲
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AVIC First Aircraft Institute
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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
    • G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
    • G01P5/14—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid
    • G01P5/16—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes, e.g. Machmeter
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/08—Thermal analysis or thermal optimisation
    • 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

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  • Aviation & Aerospace Engineering (AREA)
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Abstract

The invention provides a Mach number acquisition method and system in full-pressure failure, wherein the method comprises the following steps: acquiring the total temperature acquired at the current moment of a total temperature sensor, and acquiring the static temperature according to the Mach number stored at the last moment of the total temperature; according to the static temperature, acquiring the sound velocity under the static temperature; and obtaining the ground speed of the current moment obtained by the inertial navigation system, and obtaining the Mach number of the current moment according to the ground speed and the sound speed. The invention has simple and reliable algorithm and low modification workload.

Description

Mach number acquisition method and system in full-voltage failure
Technical Field
The invention belongs to the technical field of atmospheric data acquisition, and particularly relates to a Mach number acquisition method and system in full-pressure failure.
Background
Mach number is the ratio of the aircraft's vacuum velocity to the sonic velocity at the altitude of the flight, and characterizes the air compressibility effect. Mach numbers are important atmospheric parameters in the flight of aircraft, and are often used to correct atmospheric pressure altitude parameters, which have a large impact on flight performance and safety. Thus, obtaining the Mach number of the aircraft is of great importance for the performance and safety of the aircraft.
The existing Mach number is obtained according to atmospheric static pressure and dynamic pressure calculation, and the static pressure and dynamic pressure are obtained by means of measurement of a total static pressure system.
However, when the full-pressure system is frozen or blocked, dynamic pressure failure is caused, so that Mach number failure is caused, data such as static pressure, air pressure height, static temperature and the like output by the atmospheric data system are further influenced, the data seriously deviate from real numerical values, and flight safety is endangered.
Disclosure of Invention
The purpose of the invention is that:
the Mach number acquisition method and system for the full-pressure failure are provided, and the problem that the Mach number cannot be acquired when the full-pressure system fails is solved.
The technical scheme of the invention is as follows:
the invention provides a Mach number acquisition method in full-pressure failure, which comprises the following steps:
acquiring the total temperature acquired at the current moment of a total temperature sensor, and acquiring the static temperature according to the Mach number stored at the last moment of the total temperature;
according to the static temperature, acquiring the sound velocity under the static temperature;
and obtaining the ground speed of the current moment obtained by the inertial navigation system, and obtaining the Mach number of the current moment according to the ground speed and the sound speed.
Optionally, the obtaining the static temperature includes:
according to the total temperature T t And Mach number M stored at the previous time, calculating static temperature T by adopting the following formula S ；
Wherein k is the adiabatic index of air; and N is the total temperature recovery rate of the total temperature sensor.
Optionally, the acquiring the sound velocity under the static temperature includes:
according to the static temperature T S The static temperature T is obtained by adopting the following formula S Lower sonic velocity c;
wherein R is the gas constant of air.
Optionally, the obtaining the mach number at the current moment according to the ground speed and the sound speed includes:
setting the ground speed V Ground (floor) The ratio to the sonic velocity c is taken as the Mach number.
A second aspect of the present invention provides a system for obtaining mach number at full-voltage failure, including: the system comprises a total temperature sensor, an inertial navigation system and an atmosphere data computer; wherein the atmosphere data computer is for:
acquiring the total temperature acquired at the current moment of a total temperature sensor, and acquiring the static temperature according to the Mach number stored at the last moment of the total temperature;
according to the static temperature, acquiring the sound velocity under the static temperature;
and obtaining the ground speed of the current moment obtained by the inertial navigation system, and obtaining the Mach number of the current moment according to the ground speed and the sound speed.
Optionally, the air data computer is specifically configured to:
according to the total temperature T t And Mach number M stored at the previous time, calculating static temperature T by adopting the following formula S ；
Wherein k is the adiabatic index of air; and N is the total temperature recovery rate of the total temperature sensor.
Optionally, the air data computer is specifically configured to:
according to the static temperature T S The static temperature T is obtained by adopting the following formula S Lower sonic velocity c;
wherein R is the gas constant of air.
Optionally, the air data computer is specifically configured to:
setting the ground speed V Ground (floor) The ratio to the sonic velocity c is taken as the Mach number.
The invention has the advantages that:
a Mach number acquisition method and system in full pressure failure are provided, wherein the system comprises an atmosphere data computer, a full static pressure system, a total temperature sensor, an attack angle sensor and an inertial navigation system. All the required equipment is the existing equipment of the aircraft, no new equipment is needed, and the system is simple to realize. Using Mach number M in combination with the collected total temperature T t Calculating the static temperature T S The method comprises the steps of carrying out a first treatment on the surface of the According to the static temperature T S Obtaining the static temperatureT S Under the sound speed c, the atmospheric data computer introduces the inertial navigation ground speed V by utilizing the principle that the vacuum speed is equal to the inertial navigation ground speed under the condition of no wind in the air and the condition of small wind speed is close to the inertial navigation ground speed Ground (floor) According to the ground speed V Ground (floor) The Mach number M is estimated by the ratio of the sound velocity c, and the dynamic pressure q is used for c Static pressure P S Relation with Mach number M to obtain dynamic pressure q c The method is simple and reliable in algorithm and low in modification workload.
Drawings
FIG. 1 is a schematic diagram of an architecture of a Mach number acquisition system for full-voltage failure according to the present invention;
fig. 2 is a flow chart of a method for obtaining mach number in full-voltage failure provided by the invention.
Detailed Description
The present invention will be explained in detail with reference to the drawings.
Fig. 1 is a schematic diagram of an architecture of a mach number acquisition system in a full-voltage failure provided by the present invention, and fig. 2 is a flow diagram of a mach number acquisition method in a full-voltage failure provided by the present invention; as shown in fig. 1 and 2, the mach number acquisition system for full-voltage failure provided by the present invention includes: an atmosphere data computer, a total temperature sensor and an inertial navigation system. Optionally, the system further comprises: a total static pressure system; the total static pressure system comprises a total pressure system and a static pressure system.
Under normal condition of full pressure system, the atmosphere data computer receives full pressure P of the full static pressure system t Static pressure P S Receiving total temperature T of total temperature sensor t The pre-correction angle of attack α of the angle of attack sensor is received. Obtaining dynamic pressure q according to the difference between total pressure and static pressure c I.e. q c ＝P t -P S And further calculate the indicated airspeed V i The method comprises the steps of carrying out a first treatment on the surface of the According to dynamic pressure q c Static pressure P S Obtaining Mach number M; according to the total temperature T t Obtaining static temperature T by Mach number M S The method comprises the steps of carrying out a first treatment on the surface of the And further correcting the static pressure P using the obtained Mach number M S Data such as angle of attack alpha and the like according to the corrected static pressure P S The gas pressure height Hb is calculated.
In the event of a failure of the full pressure system,the atmospheric data computer can only receive and normally calculate the static pressure P of the total static pressure system S Receiving total temperature T of total temperature sensor t The pre-correction angle of attack α of the angle of attack sensor is received. At this time, the atmospheric data computer cannot obtain an effective full pressure P due to the full pressure system failure t Will result in dynamic pressure q c Mach number M, indicated airspeed V i Static temperature T S Etc. are not effective. For this case, the calculation method of the present invention is specifically as follows:
step one:
the first calculation of the atmospheric data computer utilizes the Mach number M with valid upper period and the Mach number M obtained by the invention in the process of re-iteration, and the static temperature T is calculated by combining the collected total temperature Tt S Wherein the static temperature T S The calculation method comprises the following steps:
wherein: t (T) t -total temperature (K); k-adiabatic index (air 1.4); M-Mach number; n—total temperature recovery rate (obtained from the total temperature sensor characteristics employed).
Step two:
according to the static temperature T S Obtaining the static temperature T S The following sound velocity c is obtained by the following method:
wherein k-the adiabatic index (air is 1.4); R-Special gas constant 287.05287 (unit: m) 3 /K·s 2 )；T S -resting temperature (unit: K).
Step three:
the atmospheric data computer receives the ground speed V calculated by the inertial navigation system Ground (floor) Obtained by using the ground speed V Ground (floor) The ratio to the speed of sound c estimates the mach number M. The mach number M is defined as follows:
wherein V is Ground (floor) -inertial navigation ground speed; c is the speed of sound. And ground speed V of inertial navigation system Ground (floor) The ground speed of other similar principle equipment can be used for replacing the ground speed.
Using the obtained Mach number M versus static pressure P S And correcting data such as attack angle alpha and the like to obtain more accurate parameters.
Step four:
according to Mach number M already obtained, according to dynamic pressure q c Static pressure P S Relation with Mach number M to obtain dynamic pressure q c The definition is as follows:
when M is less than or equal to 1:
when M > 1:
wherein P is S Atmospheric static pressure (unit: kPa); M-Mach number; k-adiabatic index (air 1.4).
Then according to the dynamic pressure q c Can calculate the indicated airspeed V i 。
And repeating the first, second, third and fourth steps to obtain all atmospheric parameters under the condition of full-pressure system faults.

Claims (4)

1. The Mach number acquisition method during full-pressure failure is characterized by comprising the following steps:
acquiring the total temperature acquired at the current moment of a total temperature sensor, and acquiring the static temperature according to the Mach number stored at the last moment of the total temperature;
according to the static temperature, acquiring the sound velocity under the static temperature;
obtaining the ground speed of the current moment obtained by the inertial navigation system, and obtaining the Mach number of the current moment according to the ground speed and the sound speed;
the obtaining the static temperature comprises the following steps:
according to the total temperature T t And Mach number M stored at the previous time, calculating static temperature T by adopting the following formula S ；
Wherein k is the adiabatic index of air; n is the total temperature recovery rate of the total temperature sensor;
the obtaining the sound velocity under the static temperature comprises the following steps:
according to the static temperature T S The static temperature T is obtained by adopting the following formula S Lower sonic velocity c;
wherein R is the gas constant of air.
2. The method of claim 1, wherein said obtaining the mach number at the current time based on the ground speed and the sonic speed comprises:
setting the ground speed V Ground (floor) The ratio to the sonic velocity c is taken as the Mach number.
3. A system for obtaining mach numbers at full-pressure failure, comprising: the system comprises a total temperature sensor, an inertial navigation system and an atmosphere data computer; wherein the atmosphere data computer is for:
acquiring the total temperature acquired at the current moment of a total temperature sensor, and acquiring the static temperature according to the Mach number stored at the last moment of the total temperature;
according to the static temperature, acquiring the sound velocity under the static temperature;
obtaining the ground speed of the current moment obtained by the inertial navigation system, and obtaining the Mach number of the current moment according to the ground speed and the sound speed;
the atmospheric data computer is specifically configured to:
according to the total temperature T t And Mach number M stored at the previous time, calculating static temperature T by adopting the following formula S ；
Wherein k is the adiabatic index of air; n is the total temperature recovery rate of the total temperature sensor;
the atmospheric data computer is specifically configured to:
according to the static temperature T S The static temperature T is obtained by adopting the following formula S Lower sonic velocity c;
wherein R is the gas constant of air.
4. A system according to claim 3, wherein the atmospheric data computer is specifically configured to:
setting the ground speed V Ground (floor) The ratio to the sonic velocity c is taken as the Mach number.
CN202011610399.7A 2020-12-29 2020-12-29 Mach number acquisition method and system in full-voltage failure Active CN112730887B (en)

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CN114580219B (en) * 2022-05-07 2022-09-09 成都凯天电子股份有限公司 Method for calibrating parameters of distributed atmospheric data system

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105301275A (en) * 2014-07-23 2016-02-03 空中客车运营简化股份公司 Method and device for estimating the mach number of an aircraft
CN110346605A (en) * 2019-08-01 2019-10-18 中国商用飞机有限责任公司 For correcting the method and system that carry out aircraft airspeed calibration based on static pressure error

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7031871B2 (en) * 2004-06-04 2006-04-18 Rosemount Aerospace, Inc. Sensor assembly for determining total temperature, static temperature and Mach number
US7334469B2 (en) * 2005-07-29 2008-02-26 Honeyweill International Inc. Methods and systems using ratiometric characterizations to improve air data accuracy
CN102360088B (en) * 2011-09-09 2013-05-15 陕西长岭电子科技有限责任公司 Air data computer and realization method thereof
CN104866703B (en) * 2015-03-09 2018-04-13 中国航空工业集团公司沈阳飞机设计研究所 A kind of unmanned plane true air speed reconstructing method
CN111122106A (en) * 2019-12-19 2020-05-08 中国航空工业集团公司西安飞机设计研究所 Correction method for measurement error of full-pressure sensor and computer equipment

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105301275A (en) * 2014-07-23 2016-02-03 空中客车运营简化股份公司 Method and device for estimating the mach number of an aircraft
CN110346605A (en) * 2019-08-01 2019-10-18 中国商用飞机有限责任公司 For correcting the method and system that carry out aircraft airspeed calibration based on static pressure error

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Non-intrusive acoustic measurement of flow velocity and temperature in a high subsonic Mach number jet;R Otero Jr, et al;《Measurement Science and Technology》;第29卷(第1期);第1-8页 *

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