CN114427871A - Aviation altimeter application efficiency detection method based on dynamic continuous detection - Google Patents
Aviation altimeter application efficiency detection method based on dynamic continuous detection Download PDFInfo
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Abstract
The invention discloses an aviation altimeter application efficiency detection method based on dynamic continuous detection, which belongs to the technical field of aviation equipment application efficiency detection, and specifically, a transmitted pulse envelope signal is obtained through envelope detection by connecting a radio frequency cable with a radio frequency output port of an aviation altimeter; the transmitting pulse envelope signal is adjusted by a height factor to form a receiving pulse envelope signal, and the receiving pulse envelope signal is output to a radio frequency input port of the aviation altimeter through a radio frequency cable after carrier modulation, up-conversion and power amplification; the method comprises the steps that the height measurement value of the aviation altimeter is extracted to obtain height measurement error data, wherein the height measurement error data are connected with a data port of the aviation altimeter through a data bus; and determining the application efficiency state value of the aviation altimeter according to the maximum membership principle by constructing a height measurement error matrix. The scheme of the invention can implement dynamic continuous detection, can detect the actual application capability of the aviation altimeter under the comprehensive consideration of factors such as terrain, interference and the like, and improves the reliability of the detection result.
Description
Technical Field
The invention relates to an application efficiency detection method of aviation equipment, in particular to an application efficiency detection method of aviation altimeter equipment based on dynamic continuous detection.
Background
The aviation altimeter is a radio device for measuring the height of an aviation platform, and the measured height information is not only used for indicating the height of the aviation platform, but also used for radio navigation positioning, fire control system parameter binding and the like. Therefore, whether the altimeter can provide accurate height measurement data is very important for an aviation platform.
Because the ground static detection mode cannot meet the requirements of altimeter height measurement range and high accuracy measurement, the detection of the aviation altimeter mainly adopts dynamic detection. There are two main approaches. Firstly, flight actual measurement is carried out, but the detection cost of the method is high, and the detection period is long. Secondly, a method for simulating an altimeter to receive pulse signals is adopted, the height change of the aviation platform is simulated by adjusting parameters of the received pulse signals, and the performance of the altimeter is measured. However, the method mainly has the following defects:
first, in the conventional detection method, when the analog altimeter receives the pulse signal, a table lookup method is usually adopted to divide the altitude range of the altimeter into a plurality of intervals, and then sampling points are taken in each interval, and the pulse signal is simulated and received according to the altitude values corresponding to the sampling points, so as to implement performance detection. The method is easy to cause large fluctuation of altimeter height measurement data, low accuracy of height measurement precision, incapability of implementing dynamic continuous detection and only applicable to functional qualitative detection;
secondly, in the existing detection method, when the analog altimeter receives the pulse signal, the analog altimeter is echo signals under the condition of an ideal simulated channel, the influence of factors such as irregular reflection, absorption and multipath of the pulse signal caused by different terrain states is not considered, the detection method is not consistent with the actual use scene of the altimeter of the aviation platform, and the reliability of the detection result is low;
thirdly, in the existing detection method, when the analog altimeter receives the pulse signal, the influence of complex electromagnetic environment factors on the altimeter is not considered, so that the anti-interference capability of the altimeter pulse signal in the transmission process cannot be detected, the detection method is not consistent with the actual application scene of the altimeter of the aviation platform, and the actual application efficiency of the aviation altimeter cannot be detected;
fourthly, in the existing detection method, most detection results adopt a mode of visually observing an altimeter instrument panel to subjectively judge the working state and performance of the altitude, only functional detection can be carried out, quantitative index detection cannot be carried out, and the actual application capability of the altimeter cannot be detected by comprehensively considering the influences of factors such as terrain state, use environment and the like.
Therefore, how to detect the aviation platform altimeter equipment, implement dynamic continuous detection, analyze the practical application efficiency of the altimeter under the condition of comprehensively considering the influence of practical factors such as terrain state, use environment and the like, and improve the reliability of the detection result is a difficult problem to be solved by the conventional aviation platform altimeter equipment detection method.
Disclosure of Invention
The invention aims to disclose an aviation altimeter application efficiency detection method based on dynamic continuous detection, which is used for implementing dynamic continuous detection and detecting the actual application capability of aviation altimeter equipment under the comprehensive consideration of factors such as terrain, interference and the like so as to improve the reliability of a detection result.
In order to achieve the aim of the invention, the invention discloses an aviation altimeter application efficiency detection method based on dynamic continuous detection. In the method, a radio frequency cable is connected with a radio frequency output port of an aviation altimeter, a transmitted pulse signal transmitted by the aviation altimeter is periodically received, attenuation control and down-conversion are carried out on the transmitted pulse signal, and then envelope detection is carried out to obtain the second timeiA first detection periodjA transmit pulse envelope signala ij (t) (ii) a The transmitted pulse envelope signala ij (t) Height factor of warpc(h) After adjustment, formIthA first detection periodjA received pulse envelope signaly ij (t) Then, the carrier modulation and the up-conversion are carried out to form the second stepiA first detection periodjA received pulse signals ij (t) The power is amplified and then is output to a radio frequency input port of the aviation altimeter through a radio frequency cable;
the height factorc(h) Comprises the following steps:
in the formula (I), wherein,hin order to simulate the height of the building,
the change quantity of the altitude value of the aviation platform in the altitude measurement process,Cis the transmission speed of the electromagnetic wave;
the received pulse envelope signaly ij (t) The transmit pulse envelope signala ij (t) And height factorc(h) Satisfies the relation:y ij (t)=a ij [t-c(h)]；
the height measurement value of the aviation altimeter is extracted and is connected with the simulation altitude through a data bus and a data port of the aviation altimeterhCompared to obtain the firstiA detection period ofjHeight error of individual pulseq ij (ii) a Constructing a height measurement error matrix Q =of the aviation altimeter
And determining the application efficiency state value of the aviation altimeter according to the maximum membership principle.
Further, in the technical solution disclosed in the present invention, the received pulse envelope signaly ij (t) Terrain factor of first passx(t) Forming a terrain receiving pulse envelope signal after adjustmentm ij (t) Then forms a receiving pulse signal after carrier modulation and up-conversions ij (t)。
Preferably, in the technical solution disclosed in the present invention, the terrain factorx(t) The received pulse envelope signal is a sea factory ij (t) The marine factorx(t) And the terrain receiving pulse envelope signalm ij (t) The three satisfy the relation:m ij (t)=y ij (t)+x(t)；
wherein, the first and the second end of the pipe are connected with each other,x(t) For random signals, the probability density function is:
，
wherein the content of the first and second substances,ain order to be a scale parameter,vin order to be a parameter of the shape,
，vtypical values range from 0.1 to 10, gamma () is a gamma function,
is (a)v-1) order second class modified Bessel function.
Preferably, in the technical solution disclosed in the present invention, the terrain factorx(t) As a land factor, the received pulse envelope signaly ij (t) The land factorx(t) And the terrain receiving pulse envelope signalm ij (t) The three satisfy the relation:
，
represents a convolution;
wherein the content of the first and second substances,
，
wherein, the first and the second end of the pipe are connected with each other,
for the aeronautical altimeteriThe amplitude of the signal received by the strip path,
receiving a pulse signal for the aviation altimeters ij (t) The carrier frequency of (a) is,
for the aeronautical altimeteriPhase of a signal received by a strip path, said
Is a random signal subject to uniform distribution;
wherein, the
For random signals, the probability density function is:
wherein, in the process,
is the standard deviation of the measured data to be measured,
。
further, in the technical solution disclosed in the present invention, the terrain receiving pulse envelope signalm ij (t) First pass interference factorz(t) Forming interference receiving pulse envelope signal after regulationb ij (t) Then forms a receiving pulse signal after carrier modulation and up-conversions ij (t)。
Preferably, in the technical solution disclosed in the present invention, the interference factorz(t) For wideband interference factors, the terrain receives a pulse envelope signalm ij (t) The broadband interference factorz(t) Receiving a pulse envelope signal with said interferenceb ij (t) The three satisfy the relation:b ij (t)=m ij (t)+z(t)；
wherein the content of the first and second substances,
the rect () is a rectangular function,Ain order to be the amplitude of the signal,ω 0receiving a pulse signal for the aviation altimeters ij (t) Is/are as followsThe carrier frequency of the carrier wave,Tthe time period for the broadband interference factor is wide,αis the slope of the frequency change, and
，Bis the bandwidth of the wideband interference factor.
Preferably, in the technical solution disclosed in the present invention, the interference factorz(t) The terrain receives a pulse envelope signal for a narrow-band interference factorm ij (t) The narrow band interference factorz(t) Receiving a pulse envelope signal with said interferenceb ij (t) The three satisfy the relation:b ij (t)=m ij (t)+z(t)；
wherein the content of the first and second substances,
wherein, in the process,g(t) is a raised cosine function,Ain order to be the amplitude of the signal,ω 0receiving a pulse signal for the aviation altimeters ij (t) The carrier frequency of (a).
Further, in the technical solution disclosed in the present invention, the method for determining the application effectiveness state value of the aviation altimeter according to the maximum membership principle includes:
build up ofnA normalized height measurement error mean matrix composed of the normalized height measurement error data of each period: GY =
Wherein, in the process,
，
，Edsolving the normalized altimetry error mean matrix GY for the rated altimetry accuracy value of the aviation altimeter for S = [ S ] in the application performance space1,s2,s3,...,sn]Membership matrix of (d): h =
Wherein
Is that
The corresponding membership degree; performing matrix multiplication operation E = GYTObtaining state value of normalized height measurement error by multiplying by H
And determining the application efficiency state value of the aviation altimeter according to the maximum membership principle.
Further, in the technical solution disclosed in the present invention, the application performance space is S = [ S ]1,s2,s3,s4,s5]Said
Is that
The membership degree of the corresponding application performance space S satisfies the relation:
wherein the content of the first and second substances,a 1,a 2,a 3,a 4is the application effectiveness space S = [ S ] of the aviation altimeter1,s2,s3,s4,s5]Typical values of (a).
Further, in the technical scheme disclosed by the invention, an application effectiveness curve of the aviation altimeter equipment is formed by using the application effectiveness state values of the aviation altimeter equipment in each detection period through a data fitting method; and correspondingly displaying the application efficacy state value of the aviation altimeter equipment by adopting different colors, wherein the lighter the color is, the weaker the representative application efficacy state value is, and the darker the color is, the stronger the representative application efficacy state is.
Compared with the prior art, the invention has the following beneficial effects:
(1) in the technical scheme disclosed by the invention, the transmitting pulse signal is converted into the receiving pulse signal through the height factor, the height factor can generate the corresponding receiving pulse signal in real time according to the change of the analog height value, and the continuous change of the height can be realized, so that the dynamic continuous detection of the height measurement error of the altimeter is realized. In the prior art, a table look-up mode is adopted to simulate a height measurement value, the height data fluctuation is large, the height measurement precision is low, and the method can only be used for functional qualitative detection. Therefore, compared with the prior art, the method improves the detection precision and can realize the dynamic and continuous detection of the aviation altimeter.
(2) In the technical scheme disclosed by the invention, the topographic factors are set and used for simulating the transmission influence of different topographic features on the altimeter pulse signals, so that the electromagnetic wave transmission process of the altimeter height measurement pulse signals is better reproduced and is consistent with the actual application scene. In the existing detection method, when the analog altimeter receives the pulse signal, the pulse signal transmission is under the analog ideal channel condition, and the influence of factors such as irregular reflection, absorption, multipath and the like of the pulse signal caused by different terrain states is not considered. Therefore, compared with the prior art, the environment measured by the method is consistent with the actual use scene, and the reliability of the detection result is high.
(3) According to the technical scheme disclosed by the invention, the interference factor is set, and the interference type of the aviation altimeter in the complex electromagnetic environment is simulated, so that the height measurement capability of the aviation altimeter under the interference condition can be detected. In the existing detection method, when the analog altimeter receives the pulse signal, the influence of complex electromagnetic environment factors on the altimeter is not considered, the influence is not consistent with the actual scene of the aviation platform altimeter, and the actual application efficiency of the aviation altimeter cannot be detected. Therefore, compared with the prior art, the method can reflect the real and complex electromagnetic environment of the aviation altimeter and can detect the practical application efficiency of the aviation altimeter.
(4) According to the technical scheme, the height measurement error data of the aviation altimeter is obtained in a periodic detection mode, the application efficiency state value of the aviation altimeter is determined according to the maximum membership principle, the real application efficiency of the aviation altimeter can be comprehensively given under the influence of factors such as terrain state, interference modes and the like, and the detection data can be fitted to construct an application efficiency curve through a data fitting method, so that related personnel can macroscopically grasp the operation interval and the development trend of the application efficiency of the current equipment. In the prior art, most detection results adopt a mode of visually observing an instrument panel of the altimeter to subjectively judge the working state and the performance of the altimeter, only functional detection can be carried out, quantitative index detection cannot be carried out, and the actual environment application capability of the altimeter cannot be detected by comprehensively considering the influences of factors such as terrain state, specific environment and the like. Therefore, compared with the prior art, the method can detect the real application efficiency of the aviation altimeter, and can grasp the future operation state and the development trend of the equipment on the whole according to the detection data.
Additional advantages and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Detailed Description
The present invention is further described in detail below with reference to examples so that those skilled in the art can practice the invention with reference to the description.
In the prior art, the method for simulating the echo signal of the altimeter is mainly adopted to detect the height measurement precision of the aviation altimeter, generally, a table look-up method is adopted to simulate the change of the altitude value, but the method has large fluctuation range of the simulated altitude value and low measurement precision, and cannot realize dynamic continuous detection.
In order to solve the problems in the prior art, the embodiment of the invention discloses an aviation altimeter application efficiency detection method based on dynamic continuous detection. In the method, a radio frequency cable is connected with a radio frequency output port of an aviation altimeter, a transmitted pulse signal transmitted by the aviation altimeter is periodically received, attenuation control and down-conversion are carried out on the transmitted pulse signal, and then envelope detection is carried out to obtain the second timeiA first detection periodjA transmit pulse envelope signala ij (t) (ii) a The transmitted pulse envelope signala ij (t) Height factor of warpc(h) After adjustment, form the firstiA first detection periodjA received pulse envelope signaly ij (t) Then, the carrier modulation and the up-conversion are carried out to form the second stepiA first detection periodjA received pulse signals ij (t) The power is amplified and then is output to a radio frequency input port of the aviation altimeter through a radio frequency cable;
the height factorc(h) Comprises the following steps:
in the formula (I), wherein,hin order to simulate the height of the building,
the change quantity of the altitude value of the aviation platform in the altitude measurement process,Cis the transmission speed of the electromagnetic wave;
the received pulse envelope signaly ij (t) The said emission pulseEnvelope signala ij (t) And height factorc(h) Satisfies the relation:y ij (t)=a ij [t-c(h)]；
the height measurement value of the aviation altimeter is extracted (the height measurement value is output to the data port after the aviation altimeter finishes height measurement), and is connected with the simulation altitude through a data bushCompared to obtain the firstiA detection period ofjHeight error of individual pulseq ij (ii) a Constructing a height measurement error matrix Q =of the aviation altimeter
And determining the application efficiency state value of the aviation altimeter according to the maximum membership principle.
In the technical solution disclosed in the embodiment of the present invention, the height factor
Can be based on the simulated height valuehAnd the amount of aerial platform altitude change
The time delay between the transmitting pulse and the receiving pulse of the altimeter is generated in real time by the change of the altimeter, so that a receiving pulse signal for measuring the height is simulated and formed. When implemented by engineering, the method can be implemented by N = round (r) ((r))c(h) The XClock _ refresh (the Clock _ refresh is the FPGA Clock frequency) converts the height factor into the number of FPGA Clock cycles, thereby establishing the relationship between the number of the FPGA Clock cycles and the simulated height value.
Further, in the prior art, the simulated echo signals are all echo signals under ideal channel conditions, and the influence of factors such as irregular reflection, absorption, multipath and the like of the echo signals caused by different terrains is not considered. The influence of terrain factors on an echo signal of the altimeter is large, so that the received pulse signal generates amplitude fading, phase nonlinear change and the like, and a noise signal is superposed in a channel, so that the signal-to-noise ratio is reduced, and the difficulty in measuring the height of the altimeter is greatly improved. Therefore, in the process of detecting the height measurement precision of the altimeter, the influence of the terrain state on the electromagnetic wave transmission of the altimeter pulse signal needs to be considered, so that the transmission environment of the aviation altimeter pulse signal can be really reflected and is consistent with the application scene of the aviation altimeter, and the detection result is accurate and reliable.
In order to solve the problems in the prior art, in the technical solution disclosed in the embodiment of the present invention, the received pulse envelope signal isy ij (t) Terrain factor of first passx(t) Forming a terrain receiving pulse envelope signal after adjustmentm ij (t) Then forms a receiving pulse signal after carrier modulation and up-conversions ij (t). In consideration of the difference of the terrain states of the aviation altimeters, the terrain can be macroscopically divided into two terrain states of sea and land. The inventor sets an ocean factor and a land factor by analyzing the transmission influence of the two terrains on the altimeter altimetry pulse signal so as to truly reflect the use environment of the altimeter.
When the aviation altimeter works in the marine environment, the transmitted pulse signal is reflected by the sea level and then received by the altimeter, so that the altitude measurement is completed. However, when the pulse signal transmitted by the aviation altimeter meets sea surface reflection, the pulse signal of the altimeter is reflected, and a backscattering signal from the sea surface is generated, and the backscattering signal enters the altimeter receiving channel along with the reflected pulse signal of the altimeter, so that the altimeter measurement is influenced. Therefore, when the altimeter is subjected to high-precision detection, the influence of marine environment on pulse signal transmission must be considered, the using environment of the altimeter is truly restored, and the detected result can be truly and credibly.
When the aviation altimeter works in the terrestrial environment, the transmitted pulse signals are transmitted through the terrestrial environment, the aviation altimeter can receive a plurality of reflected pulses through different transmission paths due to the influence of terrestrial environment buildings, and the plurality of reflected pulse signals are superposed together, so that the height measurement accuracy is influenced. Therefore, when the aviation altimeter works in a land environment, the influence of the environmental factors on the measurement accuracy is also considered.
In the prior art, the influence of the terrain state is not considered, the altimeter is simulated according to the reflection principle of the altimeter pulse signal to finish the altimeter precision detection, namely the simulated altimeter transmits the pulse signal under the condition of an ideal channel when receiving the pulse signal, and the influence of different terrain states on factors such as irregular reflection, absorption, multipath and the like of the pulse signal is not considered, so that the reliability of a measured result is low, and the application efficiency of the aviation altimeter in a real terrain environment cannot be detected.
In order to solve the problems in the prior art, the inventor theoretically deduces and simulates the electromagnetic wave transmission influence of marine environment and land environment on pulse signals of the aviation altimeter, and constructs a relationship between marine factors, land factors and transmitted pulses and received pulses of the altimeter, so that the detection result can truly reflect the height measurement capability of the aviation altimeter in different terrain environments.
Preferably, in the technical solution disclosed in the embodiment of the present invention, the terrain factorx(t) The received pulse envelope signal is a sea factory ij (t) The marine factorx(t) And the terrain receiving pulse envelope signalm ij (t) The three satisfy the relation:m ij (t)=y ij (t)+x(t)；
wherein the content of the first and second substances,x(t) For random signals, the probability density function is:
，
wherein the content of the first and second substances,ain order to be a scale parameter,vin order to be a parameter of the shape,
，vtypical values range from 0.1 to 10, gamma () is a gamma function,
is (a)v-1) order second class modified Bessel function.
Preferably, in the technical solution disclosed in the embodiment of the present invention, the terrain factorx(t) The received pulse envelope signal being a land factory ij (t) The land factorx(t) And the terrain receiving pulse envelope signalm ij (t) The three satisfy the relation:
，
represents a convolution;
wherein the content of the first and second substances,
，
for the aeronautical altimeteriThe amplitude of the signal received by the strip path,
receiving a pulse signal for the aviation altimeters ij (t) The carrier frequency of (a) is set,
for the aeronautical altimeteriThe phase of the signal received by the strip path. Wherein, the
Is a random signal subject to uniform distribution; the above-mentioned
For random signals, the probability density function is:
wherein, in the step (A),
is the standard deviation of the measured data to be measured,
. Typically, the appropriate number of paths can be selected according to the actual working environmentN，NTypical values range from 2 to 5.
In the technical scheme disclosed by the embodiment of the invention, the topographic factors are arranged and used for simulating the electromagnetic wave transmission influence of different topographic features on the altimeter pulse signals, so that the transmission process of the altimeter height measuring pulse signals is better reproduced and is consistent with the actual application scene. Therefore, compared with the prior art, the environment measured by the method is consistent with the actual use scene, and the reliability of the detection result is high.
Further, when the aviation platform is used in a specific environment, the aviation platform is inevitably subjected to electromagnetic interference released by the electronic interference platform, so as to reduce the application efficiency of the aviation platform. The electromagnetic interference inevitably influences the height measurement precision of the aviation altimeter. Therefore, when detecting the height measurement capability of the altimeter of the aviation platform, the influence of interference factors of a specific environment is considered.
In the prior art, the influence of electromagnetic interference factors on the altimeter height measurement capability is not considered, the influence is seriously inconsistent with the actual use scene of the altimeter of the aviation platform, and the real application efficiency of the aviation altimeter under the electromagnetic interference cannot be detected.
Generally, from the viewpoint of interference bandwidth, the electromagnetic interference types can be classified into broadband interference and narrowband interference. In order to solve the problems in the prior art, the inventor analyzes the electromagnetic interference type and the interference model and the principle of releasing interference on the altimeter pulse for measuring the altitude of the aviation altimeter, respectively establishes a broadband interference model and a narrowband interference model from the aspects of broadband interference and narrowband interference, and establishes the transmission relation between an interference signal and an altimeter pulse signal.
Preferably, in the technical solution disclosed in the embodiment of the present invention, the interference factorz(t) For wideband interference factors, the terrain receives a pulse envelope signalm ij (t) The broadband interference factorz(t) Receiving a pulse envelope signal with said interferenceb ij (t) The three satisfy the relation:b ij (t)=m ij (t)+z(t)；
wherein the content of the first and second substances,
the rect () is a rectangular function,Ain order to be the amplitude of the signal,ω 0receiving a pulse signal for the aviation altimeters ij (t) The carrier frequency of (a) is,Tthe time period for the broadband interference factor is wide,αis the slope of the frequency change, and
，Bis the bandwidth of the wideband interference factor. Typically, the bandwidth of the interfering signalBAnd the bandwidth of the pulse signal of the altimeter is more than or equal to the bandwidth of the pulse signal of the altimeter.
Preferably, in the technical solution disclosed in the embodiment of the present invention, the interference factorz(t) The terrain receives a pulse envelope signal for a narrow-band interference factorm ij (t) The narrow band interference factorz(t) Receiving a pulse envelope signal with said interferenceb ij (t) The three satisfy the relation:b ij (t)=m ij (t)+z(t)；
wherein the content of the first and second substances,
wherein, in the step (A),g(t) In the form of a raised cosine function,Ain order to be the amplitude of the signal,ω 0receiving pulse signals for the aviation altimeters ij (t) The carrier frequency of (a).
In the prior art, the working state of the altitude is subjectively judged by adopting a mode of visually observing an indication result of an instrument panel of the altimeter for judging the detection result of the aviation altimeter. Therefore, only functional detection can be performed, that is, only whether the altimeter can work normally can be judged, and the detection index quantification cannot be performed. Because the existing detection method also has no data analysis function, the working interval of the altimeter equipment in operation cannot be macroscopically grasped, the future development excess of the equipment operation cannot be predicted, and the reliability of the equipment operation cannot be improved by adopting corresponding preventive measures through predicting the development trend.
In order to solve the problems in the prior art, in the technical scheme disclosed by the embodiment of the invention, the height measurement error of the aviation altimeter is obtained through periodic detectionq ij And normalizing the current height measurement error to obtain a normalized height measurement errorgy ij I.e. by
Wherein, in the step (A),Edand the value is the rated altimetry precision value of the aviation altimeter. When the normalization result is negative value, namely better than rated height measurement precision, the normalization value is obtainedgy ij Is considered to be 0, i.e.gy ij =0, when the normalization result is greater than 1, which means that the altimetry precision of the aviation altimeter is drastically deteriorated, the normalization valuegy ij Is regarded as 1, i.e.gy ij And = 1. After normalization, the data is obtainednThe normalized height measurement error mean matrix constructed by the normalized height measurement error data of each detection period is GY =
Wherein, in the step (A),
denotes the firstiThe normalized mean height error of the individual detection periods,E() Which represents averaging the altimetric error data for one detection cycle, wherein,
is shown asiObtaining normalized height measurement error data in each detection period, and solving the normalized height measurement error average matrix GY about application performance space S = [ S ]1,s2,s3,...,sn]Membership matrix of (d): h =
In which
Is that
The corresponding membership degree; performing matrix multiplication operation E = GYTObtaining state value of normalized height measurement error by multiplying by H
And determining the application efficiency state value of the aviation altimeter according to the maximum membership principle.
Preferably, in the technical solution disclosed in the embodiment of the present invention, the method for determining the application effectiveness state value of the aviation altimeter according to the maximum membership principle includes: taking a normalized altimetry error mean value matrix GY = constructed by altimetry error data of 5 detection cycles (each detection cycle comprises a plurality of altimetry cycles, an altimetry cycle is time for completing one altimetry of the altimeter, and typically, one detection cycle comprises 10 altimetry cycles)
Solving the normalized altimetry error mean matrix GY for application Performance space S = [ S ]1,s2,s3,s4,s5]Membership matrix H:
H=
wherein
Is that
（i= 1-5) corresponding membership; performing matrix multiplication operation E = GYTObtaining state value of normalized height measurement error by multiplying by H
And determining the application efficiency state value of the aviation altimeter according to the maximum membership principle.
In the technical solution disclosed in the embodiment of the present invention, the altimeter application performance space is S = [ S ]1,s2,s3,s4,s5]I.e. the application performance of the altimeter device is divided into 5 state subspaces. The above-mentioned
Is that
（i= 1-5) corresponding to the membership of the link establishment capability space S, the two satisfy the following relation:
wherein the content of the first and second substances,μas a parameter of the mean value, the average value,σas variance parameter, typicallyμ=0，σ=1；a 1,a 2,a 3,a 4The application efficiency space of the aviation altimeter is S = [ S ]1,s2,s3,s4,s5]Typical values of (2), typicala 1=0.2，a 2=0.4，a 3=0.6，a 4= 0.8; s is a typical subspace into which the application performance space S of the aviation altimeter is divided, wherein 0,a 1]、[a 1,a 2]、[a 2,a 3]、[a 3,a 4]、[a 4,1]respectively, the typical value range of each element subspace in the application performance space S is calculated by solving the membership matrix of the normalized height measurement error mean matrix relative to the application performance space S, and then matrix multiplication operation is carried out, wherein E = GYTAnd multiplying by the multiplied by the factor, and determining which subspace of the application effectiveness state of the aviation altimeter equipment in the S is located according to the maximum membership principle so as to determine the application effectiveness state value of the aviation altimeter equipment.
Further, in the technical scheme disclosed by the embodiment of the invention, on the basis of historical detection data, the application effectiveness state value of the aviation altimeter equipment is displayed by constructing an application effectiveness curve in a data fitting mode, so that a detector can macroscopically grasp the operating interval of the aviation altimeter equipment and predict the development trend of the application effectiveness of the aviation altimeter equipment according to the change situation of the fitting curve; when the operation trend develops towards the deterioration direction, a countermeasure can be taken in advance, for example, the altimeter equipment is detected and maintained in advance or spare parts are replaced in time, so that the altimeter equipment can smoothly complete a task, and the reliability of task completion is improved.
In the prior art, most detection results adopt a mode of visually observing an instrument panel of the altimeter to subjectively judge the working state and the performance of the altimeter, only functional detection can be carried out, quantitative index detection cannot be carried out, and the actual environment application capability of the altimeter cannot be detected by comprehensively considering the influences of factors such as terrain state, use environment and the like. Therefore, compared with the prior art, the detection result of the invention can truly reflect the practical application efficiency of the aviation altimeter, and the future operation state development trend of the equipment can be integrally grasped according to the detection data.
Further, in the technical solution disclosed in the embodiment of the present invention, when displaying the application effectiveness curve of the aviation altimeter, different colors are used to correspondingly display the subspace status of the application effectiveness space of the aviation altimeter, and the lighter the color is, the weaker the value of the application effectiveness status is represented, and the darker the color is, the stronger the application effectiveness status is represented. And detecting or using personnel can more intuitively and quickly master the current state and the development trend of the application efficiency of the aviation altimeter according to the color depth and the color change trend of the application efficiency curve.
Preferably, in the technical solution disclosed in the embodiment of the present invention, the application performance curve of the aviation altimeter device is formed by a data fitting method, and typically, the data fitting method is a least square method.
While embodiments of the invention have been disclosed above, it is not intended to be limited to the uses set forth in the specification and examples. It can be applied to all kinds of fields suitable for the present invention. Additional modifications will readily occur to those skilled in the art.
Claims (10)
1. The method for detecting the application efficiency of the aviation altimeter based on dynamic continuous detection is characterized in that a radio frequency cable is connected with a radio frequency output port of the aviation altimeter, a transmission pulse signal transmitted by the aviation altimeter is periodically received, attenuation control and attenuation control are carried out on the transmission pulse signalDown conversion, and envelope detection to obtainiA first detection periodjA transmit pulse envelope signala ij (t) (ii) a The transmitted pulse envelope signala ij (t) Height factor of warpc(h) After adjustment, form the firstiA first detection periodjA received pulse envelope signaly ij (t) Then, the carrier modulation and the up-conversion are carried out to form the second stepiA first detection periodjA received pulse signals ij (t) The power is amplified and then is output to a radio frequency input port of the aviation altimeter through a radio frequency cable;
the height factorc(h) Comprises the following steps:
in the formula (I), wherein,hin order to simulate the height of the building,
the change quantity of the altitude value of the aviation platform in the altitude measurement process,Cis the transmission speed of the electromagnetic wave;
the received pulse envelope signaly ij (t) The transmit pulse envelope signala ij (t) And height factorc(h) The three satisfy the relation:y ij (t)=a ij [t-c(h)]；
the height measurement value of the aviation altimeter is extracted and is connected with the simulation altitude through a data bus and a data port of the aviation altimeterhCompared to obtain the firstiA detection period ofjHeight error of individual pulseq ij (ii) a Constructing a height measurement error matrix Q =of the aviation altimeter
And determining the application effectiveness state value of the aviation altimeter according to the maximum membership principle.
2. The method of claim 1, wherein the received pulse envelope signal is a pulse envelope signaly ij (t) Terrain factor of first passx(t) Forming a terrain receiving pulse envelope signal after adjustmentm ij (t) Then forms a receiving pulse signal after carrier modulation and up-conversions ij (t)。
3. The method of claim 2, wherein the terrain reception pulse envelope signal is a pulse envelope signalm ij (t) First pass interference factorz(t) Forming interference receiving pulse envelope signal after regulationb ij (t) Then forms a receiving pulse signal after carrier modulation and up-conversions ij (t)。
4. The method of claim 2, wherein the terrain factor is a factor of terrainx(t) The received pulse envelope signal is a sea factory ij (t) The marine factorx(t) And the terrain receiving pulse envelope signalm ij (t) The three satisfy the relation:m ij (t)=y ij (t)+x(t)；
wherein the content of the first and second substances,x(t) For random signals, the probability density function is:
，
wherein the content of the first and second substances,ain order to be a scale parameter,vin order to be a parameter of the shape,
and Γ () is a gamma function,
is (a)v-1) order second class modified Bessel function.
5. The method of claim 2, wherein the terrain factor is a factor of terrainx(t) The received pulse envelope signal being a land factory ij (t) The land factorx(t) And the terrain receiving pulse envelope signalm ij (t) The three satisfy the relation:
；
wherein the content of the first and second substances,
，
wherein the content of the first and second substances,
for the aeronautical altimeteriThe amplitude of the signal received by the strip path,
receiving a pulse signal for the aviation altimeters ij (t) The carrier frequency of (a) is,
for the aeronautical altimeteriPhase of a signal received by a strip path, said
Is a random signal subject to uniform distribution;
wherein, the
For random signals, the probability density function is:
wherein, in the step (A),
is the standard deviation of the measured data to be measured,
。
6. the method of claim 3, wherein the interference factor is a factor related to performance of the aviation altimeter application based on dynamic continuous detectionz(t) For wideband interference factors, the terrain receives a pulse envelope signalm ij (t) The broadband interference factorz(t) Receiving a pulse envelope signal with said interferenceb ij (t) The three satisfy the relation:b ij (t)=m ij (t)+z(t)；
wherein the content of the first and second substances,
and rect () is a rectangular function,Ain order to be the amplitude of the signal,ω 0receiving a pulse signal for the aerial altimeters ij (t) The carrier frequency of (a) is,Tthe time period for the broadband interference factor is wide,αis the slope of the frequency change, and
，Bis the bandwidth of the wideband interference factor.
7. The method of claim 3, wherein the interference factor is a factor related to performance of the aviation altimeter application based on dynamic continuous detectionz(t) Is a narrow-band interference factorThe terrain receiving pulse envelope signalm ij (t) The narrowband interference factorz(t) Receiving a pulse envelope signal with said interferenceb ij (t) The three satisfy the relation:b ij (t)=m ij (t)+z(t)；
wherein the content of the first and second substances,
wherein, in the step (A),g(t) In the form of a raised cosine function,Ain order to be the amplitude of the signal,ω 0receiving pulse signals for the aviation altimeters ij (t) The carrier frequency of (a).
8. The method for detecting the application effectiveness of the aviation altimeter based on the dynamic continuous detection as claimed in claim 6 or 7, wherein the method for determining the application effectiveness state value of the aviation altimeter according to the maximum membership principle comprises the following steps:
build up ofnA normalized height measurement error mean matrix formed by the normalized height measurement error data of each detection period: GY =
Wherein, in the step (A),
，
，Edsolving the normalized altimetry error mean matrix GY for the rated altimetry accuracy value of the aviation altimeter for S = [ S ] in the application performance space1,s2,s3,...,sn]Membership matrix of (d): h =
In which
Is that
The corresponding membership degree; performing matrix multiplication operation E = GYTObtaining state value of normalized height measurement error by multiplying by H
And determining the application efficiency state value of the aviation altimeter according to the maximum membership principle.
9. The method as claimed in claim 8, wherein the application performance space is S = [ S ]1,s2,s3,s4,s5]Said
Is that
The membership degree of the corresponding application performance space S satisfies the relation:
wherein, the first and the second end of the pipe are connected with each other,a 1,a 2,a 3,a 4is the application effectiveness space S = [ S ] of the aviation altimeter1,s2,s3,s4,s5]Typical values of (a).
10. The method for detecting the application effectiveness of the aviation altimeter based on the dynamic continuous detection as claimed in claim 9, wherein the application effectiveness state values of each detection period of the aviation altimeter device are used for forming an application effectiveness curve of the aviation altimeter device by a data fitting method; and correspondingly displaying the application efficacy state value of the aviation altimeter equipment by adopting different colors, wherein the lighter the color is, the weaker the representative application efficacy state value is, and the darker the color is, the stronger the representative application efficacy state is.
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