CN106324593A - Radar altimeter - Google Patents
Radar altimeter Download PDFInfo
- Publication number
- CN106324593A CN106324593A CN201610749657.7A CN201610749657A CN106324593A CN 106324593 A CN106324593 A CN 106324593A CN 201610749657 A CN201610749657 A CN 201610749657A CN 106324593 A CN106324593 A CN 106324593A
- Authority
- CN
- China
- Prior art keywords
- radar
- measurement system
- aircraft
- flight
- radar measurement
- 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.)
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/86—Combinations of radar systems with non-radar systems, e.g. sonar, direction finder
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/882—Radar or analogous systems specially adapted for specific applications for altimeters
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Computer Networks & Wireless Communication (AREA)
- General Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The invention relates to the technical field of radar test systems, and particularly relates to a radar altimeter. The radar altimeter comprises a radar measuring device, a comparison device and an inertial navigation output device, wherein the inertial navigation output device measures the geocentric altitudes of an aircraft at different flight places and obtains a first flight height according to the earth radius, meanwhile, the radar measuring device acquires a second flight height of the aircraft at the same place according to the feedback time of a transmitted signal and a received signal, and the comparison device compares the first flight height with the second flight height to obtain fusion data and provide navigation information, so that an accurate flight locus can be obtained.
Description
Technical field
The present invention relates to Radar Measurement System technical field, particularly relate to a kind of radar altimeter.
Background technology
Radar altimeter is equipped on the flying platform such as aircraft, satellite, can be used to obtain the flight path of aircraft, but
It is, only when radar receives reflected signal, could to obtain, when radar does not receives reflected signal, just cannot determine and fly
The position of machine.
Therefore, prior art cannot obtain flight track accurately the moment in the rebecca altimeter used.
Summary of the invention
Embodiments provide a kind of radar altimeter, solve in prior art at the rebecca height used
Table cannot obtain in the moment flight path accurately.
In order to solve above-mentioned technical problem, embodiments provide a kind of radar altimeter, fill including radar surveying
Put, comparison means, inertial navigation output device, described inertial navigation output device records the aircraft ground at different flight locations
Heart height, the base area radius of a ball, thus obtain the first flying height, meanwhile, the identical place of radar measurement system is according to transmitting
Signal and the feedback time of reception signal, it is thus achieved that the second flying height of aircraft, comparison means is by described first flight height
Degree compares with described second flying height, it is thus achieved that fused data, it is provided that navigation information.
Further, it is correspondingly arranged on object detection device with described radar measurement system, for radar surveying is filled
The signal putting transmitting reflects.
Further, described radar measurement system is provided with multiple antenna, for receiving same mesh in predeterminable range
Mark echo.
The embodiment of the present invention at least has the following technical effect that or advantage:
Owing to using radar measurement system, comparison means, inertial navigation output device, this inertial navigation in this radar altimeter
Output device records the aircraft geocentric altitude at different flight locations, the base area radius of a ball, thus obtains the first flying height,
Meanwhile, the place that radar measurement system is identical is according to launching signal and receiving the feedback time of signal, it is thus achieved that the of aircraft
Two flying heights, this first flying height is compared by comparison means with the second flying height, it is thus achieved that fused data, it is provided that lead
Boat information, solves the skill that cannot obtain flight track accurately in prior art in the flight radar altimeter of user the moment
Art problem, and then can accurately obtain flight track.
Accompanying drawing explanation
Fig. 1 is the module diagram of radar altimeter in the embodiment of the present invention.
Detailed description of the invention
The embodiment of the present invention, by providing a kind of radar altimeter, solves in prior art high at the rebecca used
Degree table cannot obtain in the moment technical problem of flight path accurately.
In order to solve above-mentioned technical problem, below in conjunction with Figure of description and specific embodiment to above-mentioned technology
Scheme is described in detail.
Embodiments provide a kind of radar altimeter, as it is shown in figure 1, include radar measurement system 101, compare dress
Put 102, inertial navigation output device 103, this inertial navigation output device 103 records aircraft the earth's core at different flight locations
Highly, the base area radius of a ball, thus obtain the first flying height, meanwhile, radar measurement system 101 in identical place according to sending out
Penetrating signal and receive the feedback time of signal, it is thus achieved that the second flying height of aircraft, comparison means 102 is by the first flight height
Degree compares with the second flying height, it is thus achieved that fused data, it is provided that navigation information.
In a particular embodiment, it is correspondingly arranged on object detection device with this radar measurement system 103, for right
Radar measurement system 103 is launched signal and is reflected, so that radar measurement system 103 is able to receive that feedback signal, with
Time be obtained in that this radar measurement system launches signal and the feedback time received between signal, this radar measurement system 103 energy
Enough obtain the second flying height of aircraft.This radar measurement system 103 is provided with multiple antenna, at predeterminable range
The same target echo of interior reception, thus the phase contrast relation between the echo-signal received according to multiple antennas calculates target
Arrive the relative distance between this day.
By using this radar measurement system 101 and inertial navigation output device 103 to cooperate, it is possible to obtain accurately
Flight path.
Although preferred embodiments of the present invention have been described, but those skilled in the art once know basic creation
Property concept, then can make other change and amendment to these embodiments.So, claims are intended to be construed to include excellent
Select embodiment and fall into all changes and the amendment of the scope of the invention.
Obviously, those skilled in the art can carry out various change and the modification essence without deviating from the present invention to the present invention
God and scope.So, if these amendments of the present invention and modification belong to the scope of the claims in the present invention and equivalent technologies thereof
Within, then the present invention is also intended to comprise these change and modification.
Claims (3)
1. a radar altimeter, is applied in aircraft, it is characterised in that include radar measurement system, comparison means, inertia
Navigation output device, described inertial navigation output device records the aircraft geocentric altitude at different flight locations, according to the earth
Radius, thus obtain the first flying height, meanwhile, the place that radar measurement system is identical according to transmitting signal and receives signal
Feedback time, it is thus achieved that the second flying height of aircraft, comparison means by described first flying height with described second flight
Highly compare, it is thus achieved that fused data, it is provided that navigation information.
Radar altimeter the most according to claim 1, it is characterised in that be correspondingly arranged on mesh with described radar measurement system
Mark analyte detection device, reflects for the signal launching radar measurement system.
Radar altimeter the most according to claim 1, it is characterised in that be provided with multiple sky on described radar measurement system
Line, for receiving same target echo in predeterminable range.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610749657.7A CN106324593A (en) | 2016-08-29 | 2016-08-29 | Radar altimeter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610749657.7A CN106324593A (en) | 2016-08-29 | 2016-08-29 | Radar altimeter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106324593A true CN106324593A (en) | 2017-01-11 |
Family
ID=57788735
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610749657.7A Withdrawn CN106324593A (en) | 2016-08-29 | 2016-08-29 | Radar altimeter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106324593A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113238231A (en) * | 2021-05-07 | 2021-08-10 | 上海眼控科技股份有限公司 | Echo peak height forecasting method, device, equipment and storage medium |
-
2016
- 2016-08-29 CN CN201610749657.7A patent/CN106324593A/en not_active Withdrawn
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113238231A (en) * | 2021-05-07 | 2021-08-10 | 上海眼控科技股份有限公司 | Echo peak height forecasting method, device, equipment and storage medium |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20170111 |