CN102384755A - High-accuracy method for measuring instant navigational speed of airborne phased array whether radar - Google Patents
High-accuracy method for measuring instant navigational speed of airborne phased array whether radar Download PDFInfo
- Publication number
- CN102384755A CN102384755A CN2010102704218A CN201010270421A CN102384755A CN 102384755 A CN102384755 A CN 102384755A CN 2010102704218 A CN2010102704218 A CN 2010102704218A CN 201010270421 A CN201010270421 A CN 201010270421A CN 102384755 A CN102384755 A CN 102384755A
- Authority
- CN
- China
- Prior art keywords
- speed
- radar
- dprf
- measurement
- airborne
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000005259 measurement Methods 0.000 claims abstract description 46
- 238000005516 engineering process Methods 0.000 claims abstract description 15
- 238000012360 testing method Methods 0.000 claims description 29
- 238000009825 accumulation Methods 0.000 claims description 8
- 238000001514 detection method Methods 0.000 abstract description 8
- 230000002567 autonomic effect Effects 0.000 abstract 1
- 238000004458 analytical method Methods 0.000 description 7
- 230000001133 acceleration Effects 0.000 description 5
- 238000012937 correction Methods 0.000 description 4
- 230000010354 integration Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 241001269238 Data Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
- 238000000827 velocimetry Methods 0.000 description 1
Images
Landscapes
- Radar Systems Or Details Thereof (AREA)
Abstract
A high-accuracy method for measuring instant navigational speed of an airborne phased array weather radar belongs to the field of airborne navigation and is directly applied to measurement of navigational speed parameters in navigation parameters of the airborne phased array radar. In order to acquire motion information of meteorological targets, the airborne phased array weather radar requires high-accuracy instant navigational speed data. Therefore, an autonomic type combined integrated navigation scheme of inertial navigation and Doppler speed measurement is provided, a solution scheme of inertial navigation alignment and overcoming error drifting is provided, and the problem of obscuring of the speed measurement in over-the-ground measurement of the airborne phased array weather radar is resolved. The core content of the high-accuracy method is that double-pulse repeat frequency rate detection (DPRF) technology of the over-the-ground of the airborne radar is provided, and a general formula is given. The high-accuracy method achieves the speed measurement without obscuring of the airborne weather radar on the ground, thereby improving measurement accuracy of the instant navigational speed.
Description
One, technical field
This method belongs to airborne navigation field; Directly be used for the measurement of airborne radar weather radar navigational parameter speed of a ship or plane parameter; For adopting inertial navigation to add the Doppler navigation combination and instantaneous speed of a ship or plane accuracy requirement also being had reference value than higher navigational system.
Two, background technology
The airborne radar weather radar need obtain the information such as scattering strength, translational speed and speed spectrum width of meteorological target.Have only the aircraft speed of a ship or plane to measure accurately, could guarantee that the measurement of meteorological target speed is accurate.Accurately measuring the speed of a ship or plane is the prerequisite of obtaining meteorological target travel information.And when a certain beam direction was surveyed, very little in order to guarantee the aircraft displacement, residence time was very short, we can say that the detection on a certain beam direction was accomplished in moment.Therefore, the airborne radar weather radar is surveyed has than higher accuracy requirement the instantaneous speed of a ship or plane especially.
Airmanship has several big type of inertial navigation, satellite navigation and Doppler navigation.Every type has technical characterstic and measuring accuracy separately.Satellite navigation provides positional information, aspect information is not provided.Speed of a ship or plane information is calculated through two different positions constantly, is the average velocity in a period of time.And the precision of average velocity receives the restriction of bearing accuracy, and bearing accuracy is proportional integration time with satellite-signal again.Through the accumulation of long period, satellite navigation can be obtained the average velocity of degree of precision.But the computational accuracy of instantaneous velocity does not often reach the detection requirement of airborne radar weather radar.In addition, satellite navigation belongs to the navigation of non-autonomous type, receives the restriction of satellite and satellite signal quality deeply.General only when mounting condition allows, can classify it as assisting navigation equipment.
Inertial navigation (INS, be called for short inertial navigation) be a kind ofly do not rely on external information, also not to the self-aid navigation system of outside emittance; Complete navigation information such as speed, position, crab angle and attitude can be provided.Inertial navigation is passed through to measure acceleration, and it is carried out integration to the time, obtains velocity information.The velocity survey equation can be expressed as:
wherein, a (t) is measured acceleration.Inertial navigation can be obtained high-precision instantaneous speed of a ship or plane information, but prerequisite is: " initial alignment " is very accurate, and the measurement of acceleration also will have very high precision.Initial alignment is a very strict job.The initial alignment error will become the systematic error of inertial navigation.If, do not depend merely on inertial navigation equipment and can't eliminate this error from the correction of other navigation datas.Topmost problem is the diversity of acceleration analysis error.Can find out by its equation that tests the speed: the slight error of acceleration analysis, along with the lengthening of integral time, can cause bigger velocity error, integral time is longer, error is big more.This measuring error is dispersed phenomenon in time and is also referred to as " drift " phenomenon.Therefore, in the occasion that rate accuracy is had relatively high expectations, need revise the inertial navigation measurement result.
Doppler navigation is to utilize aircraft self-contained (having the Doppler range rate measurement function) radar to measure over the ground, obtains speed of a ship or plane information according to the Doppler range rate measurement principle.Though Doppler navigation only provides speed of a ship or plane information, Doppler range rate measurement has that real-time is good, advantage of high precision.And, can also further improve rate accuracy through the increase (being equivalent to increase Measuring Time) that pulse accumulates number of times.
But Doppler range rate measurement generally can run into the fuzzy problem that tests the speed.The Doppler range rate measurement equation can be expressed as:
Wherein, V
DBe actual doppler velocity,
It is the measured value of actual doppler velocity.M is fuzzy number of times (being no fuzzy measurement during m=0).V
NBe the fuzzyyest speed (being also referred to as Nyquist speed).At radar wavelength λ one regularly, V
NSize depend on that (its relation is pulse repetition rate: V
N=± λ * PRF/4, PRF are pulse repetition raties).Work as V
DGreater than V
NThe time, measured value is not equal to actual speed, blooming promptly occurs.
Three, summary of the invention
The technical matters that solves:
Because need to survey the movable information of meteorological target, so the airborne radar weather radar has than higher accuracy requirement instantaneous speed of a ship or plane measurement.Adopting which kind of navigation scheme to require with the detection of satisfying the airborne radar weather radar is the technical matters considered of needs at first.
Because inertial navigation can provide complete navigation informations such as attitude, the speed of a ship or plane, so no matter take which kind of navigation scheme, inertial navigation system all is the indispensable navigational system of airborne radar weather radar.But navigation exists error to disperse phenomenon.So how to revise ins error is the key technical problem that the airborne radar weather radar must solve.
Doppler range rate measurement has the advantages that real-time is good, precision is high, and through the increase that pulse accumulates number of times, can also further improve rate accuracy.These technology satisfy the airborne radar weather radar especially just to speed of a ship or plane Testing requirement.The airborne radar weather radar is expected to obtain the high-precision instantaneous speed of a ship or plane through measuring over the ground.But, because the aircraft speed of a ship or plane is higher, so certainly will have the Doppler range rate measurement blooming when measuring over the ground.Can overcome the fuzzy problem that tests the speed be the key technical problem that can the airborne radar weather radar adopt the Doppler range rate measurement technology, also is core content of the present invention.
The fuzzy problem that tests the speed when measuring over the ground in order to solve aircraft, according to measuring characteristic, perfect dipulse repetition frequency velocity measuring technique (DPRF), and provided general-purpose algorithm.
The technical scheme that the technical solution problem is adopted:
Solve the problems of the technologies described above the main contents that the overall technological scheme of being taked comprises following three aspects:
1. adopt inertial navigation to add the autonomous type integrated navigation system of Doppler range rate measurement
Take all factors into consideration various airmanship characteristics, airborne radar weather radar Detection Techniques condition and aerological sounding requirement, adopt inertial navigation to add the autonomous type integrated navigation scheme of Doppler navigation.Wherein, two problems that inertial navigation system need solve: the one, error drift phenomenon, the 2nd, " aligning "; " aligning " comprises initial alignment and aims in real time.Doppler range rate measurement need solve the fuzzy problem that tests the speed.In addition, when mounting condition allows, can consider to classify satellite navigation as assisting navigation equipment.
2. with the Doppler range rate measurement data inertial navigation system is carried out " aligning ", and the inertial navigation data are periodically revised, speed of a ship or plane measuring error is controlled within the accuracy requirement all the time
Speed of a ship or plane data are accurately measured, obtained to the airborne radar weather radar over the ground, is used for the aligning of inertial navigation system and the correction of inertial navigation data.
Before carrying out aerological sounding, can measure the speed of a ship or plane data of obtaining over the ground through radar inertial navigation system is carried out initially " aligning "." aligning " is operated in the aerological sounding process and carries out in real time, looks length and the acquisition environment of detection time and decides.
Airborne radar is measured undoubtedly over the ground can increase Measuring Time.For existing higher rate accuracy, the burden of increase airborne radar within reason again, it is reasonable plan that periodic the correction taked in inertial navigation.So just can range rate error be limited within the accuracy requirement all the time.The correction cycle need according to aerological sounding to the accuracy requirement, aerological sounding cycle and the ins error that test the speed over time rule confirm.
3. overcome the fuzzy problem that tests the speed when surveying over the ground with the DPRF technology
3.1 dipulse repetition frequency velocity measuring technique (DPRF) principle and algorithm
The DPRF technology is to expand the practical technique of the scope that tests the speed in the Doppler range rate measurement.The DPRF technology adopts two different pulse repetition that satisfy the certain proportion relation successively to survey, according to two test the speed result and difference reckoning actual speeds thereof.
Two pulse repetition raties are designated as PRF from high to low respectively
1And PRF
2, their the fuzzyyest corresponding speed is designated as V respectively
N1And V
N2, the scope of testing the speed is respectively ± V
N1With ± V
N2, two measurement results are designated as respectively
With
Both differences are designated as
When adopting the DPRF velocity measuring technique, PRF
1And PRF
2Need to satisfy relation:
PRF
1∶PRF
2＝q∶(q-1) (1)
Wherein, q=3,4,5 ... Positive integer.After adopting the DPRF velocity measuring technique, the range expansion that tests the speed arrives ± qV
N2, the fuzzyyest speed expanded is:
V
N＝qV
N2＝(q-1)V
N1 (2)
The scope of testing the speed like this is equivalent to monopulse repetition frequency PRF=qPRF
2=(q-1) PRF
1Effect on Detecting.
When radar is measured over the ground, velocity reversal have only come to.When the direction of tested speed was two-way, the scope of cannot not testing the speed fuzzyly was ± qV
N2, the fuzzyyest speed is qV
N2When the direction of tested speed was unidirectional, the scope of cannot not testing the speed fuzzyly was 0～2qV
N2, the fuzzyyest speed is 2qV
N2So, when DPRF is used for measuring over the ground, need make some modifications.Following analysis only considers that velocity reversal is unidirectional situation.
When measuring over the ground with the dipulse repetition frequency, according to
With
And difference
Difference, can be with fuzzy velocity range 0～2qV of DPRF
N2Be divided into 2q speed interval.The standard that speed interval is divided is: in each interval, identical difference DELTA V is arranged.2q of so dividing is interval, and its width is not quite similar, but interval width is about qV
N2Point symmetry.
Through analysis to
and Δ V; Which speed interval is judgement measurement result (
and
) fall, and the general calculation method that provides with this method is then calculated actual radial velocity:
Wherein, Int () representes rounding operation, and i representes the speed interval sequence number, i=1, and 2 ..., 2q.
Though
possibly blur; But which interval they fall through correct judgement, still can recover actual speed.
3.2PRF
1: PRF
2=5: 4 DPRF instance
Below with PRF
1: PRF
2=5: 4 DPRF is that example further specifies DPRF expansion test the speed scope principle and speed interval division.Among Fig. 1, solid line is represented PRF
1The measurement result curve, dotted line is represented PRF
2The measurement result curve.
With
Be respectively PRF
1And PRF
2Measurement result.According to
With
Poor, with 0～10V
N2Velocity range be divided into 10 speed intervals.The data of table 1 are obtained by Fig. 1 analysis.Can find out also that by table 1
and Δ V and speed interval are one to one.Therefore; Even if
and
blurs; Through the speed interval that judges rightly, can recover original actual speed.Above example has ubiquity, for the situation of other ratio the similar analysis method is arranged.
Speed interval and the corresponding speed (PRF of table 1:DPRF
1: PRF
2=5: 4)
3.3 guarantee effective two problems of DPRF
The field angle problem
When measuring over the ground, ground is relevant with the speed of a ship or plane and field angle with respect to the radial velocity of aircraft.Field angle be meant beam direction and antenna method between angle.In order to guarantee that DPRF is in no fuzzy measurement, should adopt big as far as possible field angle.
PRF
1And PRF
2The selection problem
Because when measuring over the ground with DPRF, the fuzzyyest speed is 2qV
N2=2 (q-1) V
N1DPRF is to the extended capability and the PRF of the scope of testing the speed
1With PRF
2Relative value and absolute value relation is all arranged.The difference of two pulse repetition raties is more little, and the effect of expanding the scope that tests the speed is good more.PRF
1With PRF
2Select high, corresponding more V
N1And V
N2Big more, the scope that tests the speed of expansion is big more.
But when practical application DPRF technology, the size of pulse repetition rate and the ratio of two pulse repetition raties all are restricted.Pulse repetition rate receives the restriction of transmitter, can not unrestrictedly increase.Because the existence of measuring error, two pulse repetition raties can not be unrestrictedly approaching.Because the existence of measuring error; Two pulse repetition raties are approaching more; Judge by accident easily when judging the corresponding speed interval of
and
, cause the DPRF technical failure with Δ V.In fact, along with two pulse repetition raties are more and more approaching, DPRF surveys and will change in quality into the detection of monopulse repetition frequency.
When measuring over the ground with Doppler's principle, range rate error is relevant with the flat characteristic of underlying surface.Underlying surface is smooth more, and range rate error is more little.In addition, range rate error is relevant with pulse accumulation number of times.Integration time is long more, and this part error is more little.This part error
can be expressed as:
Wherein, N
pBe pulse accumulation number of times, λ is a radar wavelength.The smooth degree of underlying surface is the main source of measuring error over the ground.With the relevant range rate error
of pulse accumulation number of times be can analyze, controllable, very little usually.
So, PRF
1With PRF
2Selection will from expansion test the speed scope with guarantee that DPRF effective two aspects compromise considers.On the one hand, PRF
1With PRF
2Ratio will to make DPRF be no fuzzy measurement.On the other hand, PRF
1With PRF
2Difference corresponding speed be greater than 2 times
Could guarantee that DPRF is effective.
For example: (get radar wavelength λ=3cm) measure over the ground with 45 ° of field angles with X-band radar.Two pulse repetition rate PRF
1With PRF
2Get 1500Hz and 1200Hz respectively.The fuzzyyest speed that 1200Hz is corresponding is 9m/s, uses PRF
1: PRF
2After=5: 4 the DPRF technology, the fuzzyyest speed can expand to 90m/s, and the corresponding speed of a ship or plane can satisfy the detection requirement up to 127m/s.In addition, the corresponding speed of two pulse repetition rate differences is δ V=λ δ F/2=0.03 * (1500-1200)/2=4.5 (m/s).
If adopt N
p=64 pulse accumulation, then
Can guarantee DPRF effectively.
Beneficial effect
The present technique scheme is a kind of navigation scheme of autonomous type, need not to increase other navigator, such as satellite navigation, can simplify the navigational system of airborne weather radar.
Adopt the present technique scheme can realize airborne radar no fuzzy measurement over the ground, and can improve the measuring accuracy of the instantaneous speed of a ship or plane to greatest extent.Speed of a ship or plane precision is main relevant with factors such as attitude angle error, Doppler range rate measurement errors.After adopting technical scheme, speed of a ship or plane error will depend primarily on the measuring accuracy of attitude angle.If cooperate high-precision inertial navigation system, obtain the high-accuracy posture angular data, can improve speed of a ship or plane precision greatly, to satisfy the requirement of airborne weather radar to velocity survey.
Here adopt the effect of DPRF technology with the instance explanation.Two pulse repetition rate PRF
1And PRF
2Get 1500Hz and 1200Hz respectively, two pulse repetition raties constitute PRF
1: PRF
2=5: 4 DPRF surveys.Two pulse repetition rate the fuzzyyest corresponding speed are respectively V
N1=11.25m/s and V
N2=9m/s.
(get radar wavelength λ=3cm), the fuzzyyest speed that 900Hz is corresponding is 9m/s, adopts PRF for X-band radar
1: PRF
2After=5: 4 the DPRF technology, the fuzzyyest speed expanded is 90m/s.The scope that tests the speed like this can satisfy airborne weather radar Testing requirement over the ground fully.
Suppose; Aircraft is put down when flying; Measure over the ground for 45 ° with field angle; Two measurement results be respectively
and
so; Interval i=8; Calculate by
; Ground is 70.71m/s with respect to the wave beam speed radially of aircraft, and amounting to speed over ground is 100m/s.
Four, description of drawings
Fig. 1: DPRF measuring principle figure (PRF
1: PRF
2=5: 4)
Figure is to the test the speed explanation of scope principle of DPRF technological expansion.The DPRF technology successively adopts two pulse repetition raties to test the speed, and reaches the purpose of expanding the scope that tests the speed through the analysis to two results that test the speed with calculating.Wherein, PRF
1And PRF
2Represent two pulse repetition raties respectively, V
N1And V
N2Be respectively their the fuzzyyest corresponding speed, ± V
N1With ± V
N2Be respectively their corresponding scopes of cannot not testing the speed fuzzyly.Solid line is represented PRF among the figure
1Corresponding measurement curve, dotted line is represented PRF
2Corresponding measurement curve.Two measurements were recorded as?
and?
difference between the two is denoted by?
PRF
1And PRF
2Represent two pulse repetition raties respectively, V
N1And V
N2Be respectively their the fuzzyyest corresponding speed, ± V
N1With ± V
N2Be respectively their corresponding scopes of cannot not testing the speed fuzzyly.Solid line is represented PRF among the figure
1Corresponding measurement curve, dotted line is represented PRF
2Corresponding measurement curve.Two measurement results are designated as respectively
Or
Both differences are designated as
Can be according to Δ V with 10V
N2Be divided into 10 speed intervals, Δ V and speed interval are corresponding one by one.According to the speed range and measurement results (?
and?
) can recover the actual speed.
Five, embodiment
1. confirm two pulse repetition rate ratios of DPRF
According to speed of a ship or plane V roughly
a, technical indicators such as scope that field angle θ can change, scope that transmitter pulse repetition frequency PRF can change, range rate error, confirm two pulse repetition raties ratio: PRF of DPRF
1: PRF
2=q: (q-1).In two pulse repetition raties ratios, q is worth confirming to need to satisfy two conditions:
qV
N2＞V
acosθ (5)
Wherein, V
N2Be PRF
2The fuzzyyest corresponding speed, δ V is two pulse repetition rate difference PRF
1-PRF
2Corresponding doppler velocity.
is associated with the accumulation of the number of pulses corresponding Doppler velocimetry error (by the formula?
OK).
2. confirm speed interval number and the velocity contrast of DPRF
According to above-mentioned definite q value, confirm the speed interval number, interval number is 2q.Then, be similar to table 1, confirm the velocity contrast that each speed interval is corresponding, Δ V
i, i=1,2 ..., 2q.
3 for DPRF measured?
and?
4 discriminant?
and?
where the speed range
Ask the poor of
and
, and be designated as
and calculate
and be and the corresponding Doppler range rate measurement error of pulse accumulation number of times.Will
With according to the 2 velocity contrast Δ V that confirm
iCompare one by one and Δ V
iImmediate speed interval i does
With
The place speed interval.
5. the calculating of actual speed
According to top definite speed interval i, calculate the actual radial velocity of ground with respect to radar with following formula.
V wherein
rBe the radial velocity of ground with respect to radar, the meaning of other each symbol with above identical.
6. the calculating of speed over ground
According to field angle θ, ground radial velocity V with respect to radar
r, calculate the instantaneous speed of a ship or plane.
7. inertial navigation is aimed at and is revised
According to the instantaneous speed of a ship or plane data that said method obtains, the inertial navigation data are aimed at and correcting process.
Claims (2)
1. the instantaneous speed of a ship or plane method of airborne radar weather radar high-acruracy survey; It is characterized in that; With dipulse repetition frequency (DPRF) the technological expansion scope that tests the speed; No fuzzy measurement when with realization airborne radar weather radar velocity survey is carried out on ground is aimed at and is revised inertial navigation system with the instantaneous speed of a ship or plane data of high precision that the DPRF technology is obtained.
2. method according to claim 1, expansion Doppler range rate measurement scope adopts dipulse repetition frequency (DPRF) technology, and adopts
Judge speed interval, usefulness that two measurement results are corresponding
Calculate the method for ground with respect to the radial velocity of radar, wherein i representes DPRF speed interval sequence number, Δ V
iBe that DPRF is theoretical poor,
Be that the DPRF measurement is poor,
Be and the relevant range rate error of pulse accumulation number of times, V
rBe the radial velocity of ground with respect to radar, V
N2Be the fuzzyyest speed of a correspondence lower in two pulse repetition raties,
Be one measured value lower in two pulse repetition raties, Int () representes rounding operation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010270421.8A CN102384755B (en) | 2010-09-02 | 2010-09-02 | High-accuracy method for measuring instant navigational speed of airborne phased array whether radar |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010270421.8A CN102384755B (en) | 2010-09-02 | 2010-09-02 | High-accuracy method for measuring instant navigational speed of airborne phased array whether radar |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102384755A true CN102384755A (en) | 2012-03-21 |
| CN102384755B CN102384755B (en) | 2016-01-06 |
Family
ID=45824396
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201010270421.8A Expired - Fee Related CN102384755B (en) | 2010-09-02 | 2010-09-02 | High-accuracy method for measuring instant navigational speed of airborne phased array whether radar |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102384755B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013041027A1 (en) * | 2011-09-22 | 2013-03-28 | 艾欧史密斯(中国)热水器有限公司 | Dirt-proof water level sensing device and solar water heater using same |
| CN108121003A (en) * | 2017-12-26 | 2018-06-05 | 湖南迈克森伟电子科技有限公司 | Integrated navigation precise positioning system |
| CN108351420A (en) * | 2015-11-10 | 2018-07-31 | 赛峰电子与防务公司 | For detecting parasitic mobile method and relevant detection device during the static alignment of Inertial Measurement Unit |
| CN109932700A (en) * | 2019-03-28 | 2019-06-25 | 北京润科通用技术有限公司 | A kind of ambiguity solution method and device of doppler velocity |
| WO2021035395A1 (en) * | 2019-08-23 | 2021-03-04 | 深圳市大疆创新科技有限公司 | Speed determining method and device, and storage medium |
| CN113534066A (en) * | 2021-06-23 | 2021-10-22 | 北京遥感设备研究所 | Method and system for rejecting multi-reflection wild values of landing measurement radar in height direction |
| US11630203B2 (en) | 2019-06-25 | 2023-04-18 | Raytheon Company | Ground station sensing of weather around an aircraft |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5109230A (en) * | 1987-11-17 | 1992-04-28 | Litef Gmbh | Method for aircraft velocity error detection with a Doppler radar |
| JP3749486B2 (en) * | 2002-01-17 | 2006-03-01 | 三菱電機株式会社 | Radar signal processing method |
-
2010
- 2010-09-02 CN CN201010270421.8A patent/CN102384755B/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5109230A (en) * | 1987-11-17 | 1992-04-28 | Litef Gmbh | Method for aircraft velocity error detection with a Doppler radar |
| JP3749486B2 (en) * | 2002-01-17 | 2006-03-01 | 三菱電機株式会社 | Radar signal processing method |
Non-Patent Citations (4)
| Title |
|---|
| A.FERRARI: ""Doppler Ambiguity Resolution Using Multiple PRF"", 《IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS》 * |
| S.KOTESWARA RAO: ""Doppler Ambiguity Resolution Using Optimal Multiple Pulse Repetition Frequencies"", 《IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS》 * |
| 张弢: ""脉冲多普勒天气雷达解模糊处理"", 《现代雷达》 * |
| 梁华: ""脉冲多普勒天气雷达数据质量控制之解速度模糊处理"", 《气象水文海洋仪器》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013041027A1 (en) * | 2011-09-22 | 2013-03-28 | 艾欧史密斯(中国)热水器有限公司 | Dirt-proof water level sensing device and solar water heater using same |
| CN108351420A (en) * | 2015-11-10 | 2018-07-31 | 赛峰电子与防务公司 | For detecting parasitic mobile method and relevant detection device during the static alignment of Inertial Measurement Unit |
| CN108351420B (en) * | 2015-11-10 | 2021-12-10 | 赛峰电子与防务公司 | Method for detecting parasitic movements during static alignment of an inertial measurement unit, and associated detection device |
| CN108121003A (en) * | 2017-12-26 | 2018-06-05 | 湖南迈克森伟电子科技有限公司 | Integrated navigation precise positioning system |
| CN109932700A (en) * | 2019-03-28 | 2019-06-25 | 北京润科通用技术有限公司 | A kind of ambiguity solution method and device of doppler velocity |
| US11630203B2 (en) | 2019-06-25 | 2023-04-18 | Raytheon Company | Ground station sensing of weather around an aircraft |
| WO2021035395A1 (en) * | 2019-08-23 | 2021-03-04 | 深圳市大疆创新科技有限公司 | Speed determining method and device, and storage medium |
| CN113534066A (en) * | 2021-06-23 | 2021-10-22 | 北京遥感设备研究所 | Method and system for rejecting multi-reflection wild values of landing measurement radar in height direction |
| CN113534066B (en) * | 2021-06-23 | 2023-06-20 | 北京遥感设备研究所 | Method and system for eliminating landing measurement radar altitude multi-reflection wild value |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102384755B (en) | 2016-01-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3056922B1 (en) | Velocity and attitude estimation using an interferometric radar altimeter | |
| CN102384755A (en) | High-accuracy method for measuring instant navigational speed of airborne phased array whether radar | |
| US9007570B1 (en) | Airborne wind profiling algorithm for Doppler Wind LIDAR | |
| DK168342B1 (en) | Method and apparatus for passive distance measurement | |
| US9304198B1 (en) | Navigator alignment using radar scan | |
| Henke et al. | Moving target tracking in single-and multichannel SAR | |
| US8816896B2 (en) | On-board INS quadratic correction method using maximum likelihood motion estimation of ground scatterers from radar data | |
| CN102004244B (en) | Doppler direct distance measurement method | |
| CN105403887A (en) | INS-based onboard SAR real-time motion compensation method | |
| RU2411538C2 (en) | Method of determining error in measuring aircraft velocity with inertial navigation system and onboard navigation system for realising said method | |
| CN103487798A (en) | Method for measuring height of phase array radar | |
| CN101937080A (en) | Method for rapidly measuring speed of flying target by fixed single station | |
| CN102141611A (en) | Method for rapidly determining Doppler fuzzy number of squint synthetic aperture radar | |
| CN103823209B (en) | For low cost kinematic error measurement mechanism in small-sized polarization sensitive synthetic aperture radar system | |
| CN103792519B (en) | A kind of spaceborne radar clock drift bearing calibration in-orbit based on source scaler | |
| RU2569843C1 (en) | Method of forming three-dimensional image of earth's surface in on-board doppler radar station with linear antenna array | |
| US8933836B1 (en) | High speed angle-to-target estimation for a multiple antenna system and method | |
| CN109471102B (en) | Inertial measurement unit error correction method | |
| RU2572357C1 (en) | Method of forming three-dimensional image of earth's surface in on-board four-channel doppler radar set | |
| US11150334B2 (en) | Bistatic interferometric terrestrial radar with transponder | |
| RU2483324C1 (en) | Method for aircraft navigation on radar images of earth's surface | |
| CN110146050B (en) | Communication base station antenna monitoring method | |
| Chicarella et al. | Improvement of GPR tracking by using inertial and GPS combined data | |
| RU2564552C1 (en) | Navigation method of airborne vehicle as per radar images of earth surface | |
| RU2550299C2 (en) | Method of determining true velocity of ship from measurements of travel distance on tack from fixed constellation of spacecraft of mid-orbit satellite radio navigation system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160106 |