CN109927938A - Stationary orbit reality aperture microwave sounding satellite configuration - Google Patents
Stationary orbit reality aperture microwave sounding satellite configuration Download PDFInfo
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- CN109927938A CN109927938A CN201910130676.5A CN201910130676A CN109927938A CN 109927938 A CN109927938 A CN 109927938A CN 201910130676 A CN201910130676 A CN 201910130676A CN 109927938 A CN109927938 A CN 109927938A
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Abstract
The present invention relates to a kind of stationary orbit reality aperture microwave sounding satellite configurations in satellite general technical field, including satellite platform, Microwave sounder, Microwave sounder Quasi optics, locking/release device, solar wing, number biography antenna, light-blocking mechanism；The primary reflection surface and subreflector of Microwave sounder are pressed on satellite platform, and primary reflection surface, subreflector are unlocked and expanded in place after satellite and the rocket separation；Microwave sounder Quasi optics are mounted and embedded into satellite platform by Light deformation frame；Solar wing is mounted on satellite platform radiating surface；Number passes antenna and is mounted at the top of satellite platform by bracket；It is inclined, i.e. earth observation axis and satellite Z axis (i.e.+Z between satellite platform and Microwave sounderGround) between there are certain angles；After in-orbit fixed point, unlock Microwave sounder is connected with the Planar Mechanisms of satellite platform, and light-blocking mechanism is unfolded.The mechanical environment and high accuracy install demand that the present invention makes full use of space resources in delivery radome fairing, adapts to transmitting powered phase realize the high-precision expansion of Microwave sounder primary reflection surface and subreflector.
Description
Technical field
The present invention relates to satellite general technical fields, more particularly to a kind of stationary orbit reality aperture microwave sounding satellite structure
Type.
Background technique
Stationary orbit remote sensing satellite is mainly the Optical remote satellite of representative with wind and cloud four, high score four etc. at present,
Spectral coverage is observed in visible light to infrared band, the size of remote sensing instrument is generally less than satellite platform or suitable with satellite platform.
Such remote sensing instrument is all interface circle being directly installed on to ground (i.e. earth observation axis is parallel with satellite Z axis), with satellite platform
Face is clear (several place's installation points are usually in one plane arranged), is typically thermally isolated, and is not necessarily to remote sensing instrument exhibition
It opens.Its solar wing installed, number pass the expansion sequence of antenna etc. without strict requirements, set because will not spatially block other
Standby deployment paths.
Stationary orbit microwave sounding can realize the continuous observation of minute grade to the internal structure of typhoon, basin-wide precipitation, be
One of stationary orbit optical detection is supplemented well.Stationary orbit reality aperture Microwave sounder is meeting 50GHz with overhead
Between resolution ratio when being better than 50km, antenna aperture reaches 5m, is that the domestic maximum caliber designed at present consolidates surface antenna, under working condition
Full-size reach 6030mm, compared to current stationary orbit optical remote sensing instrument, stationary orbit microwave remote sensing instrument peace
The space requirement of dress be it is huge, the radome fairing envelope of existing carrier rocket can not directly meet.If being in one plane arranged
The installation of Microwave sounder and satellite platform that the mounting means of dry place's installation point is also no longer desirable for this ultra-large type connects, if
It does so, will substantially be lifted satellite altitude, while mechanical environment deteriorates, the envelope of delivery radome fairing certainly will be broken through.Real aperture
Microwave sounder has higher requirements for the position precision between day line style face precision and each parts of antenna-feeder system, finds state
Internal and external pin is to in-orbit thermal deformation measurement and relevant research is inhibited to report, but has no and carry out for large-scale stationary orbit remote sensing instrument
Special light-blocking Study on Measures.The country is more for the research of the expansion of large-scale flexible antenna, but the expansion phase with solid surface antenna
Than there are larger differences, and expansion technique itself is also not laid particular emphasis on herein.
Currently, in the world there are no dedicated stationary orbit microwave sounding satellite or microwave sounding load, various countries are being discussed
In card research, without spaceborne plan.China is loaded with microwave sounding test load on No. four scientific research and testing stars of wind and cloud, is small-sized
The Microwave sounder of change, bore are no more than 200mm, are different from and heavy caliber Microwave sounder described herein.It does not find static
The configuration relevant report or technology of track microwave sounding satellite.
Through the retrieval to the prior art, Chinese invention patent CN201810307441.4, entitled one kind is spaceborne more
The microwave radiation detection method in the one-dimensional real aperture in the one-dimensional aperture synthesis of frequency range characterized by comprising detected using cross rail and suitable
The mode of the complex probe of rail detection carries out target acquisition, wherein cross rail electric scanning is realized in array beams synthesis, is transported by satellite
Dynamic to realize straight rail scanning, target scene radiation signal is same by 3 winding displacement feed arrays after the convergence of parabolic-cylinder antenna reflecting surface
When receive, the array layout of the frequency range of each detection meets UV visibility plane space Sampling Theorem, and the received signal is again
By the in-orbit multiple calculation process of alignment processing device, visibility function value is obtained, the last visibility function value is by image weight
After the computer disposal of structure, the distribution of scene radiation brightness is obtained.But the invention is unable to fully provide using space in delivery radome fairing
Source can not well adapt to the mechanical environment and high accuracy install demand of transmitting powered phase, cannot also realize microwave sounding
The expansion of the high-precision of instrument primary reflection surface and subreflector.
Summary of the invention
In view of the drawbacks of the prior art, the object of the present invention is to provide a kind of stationary orbit reality aperture microwave sounding satellite structures
Type.The present invention makes full use of space resources in delivery radome fairing, the mechanical environment of adaptation transmitting powered phase and high accuracy install to need
It asks, realizes the high-precision expansion of Microwave sounder primary reflection surface and subreflector.
The present invention relates to a kind of stationary orbit reality aperture microwave sounding satellite configuration, including satellite platform, Microwave sounder,
Microwave sounder Quasi optics, locking/release device, solar wing, number pass antenna, light-blocking mechanism；
The Microwave sounder includes primary reflection surface and subreflector, and primary reflection surface both sides of the edge portion compresses are being defended
Star platform, the subreflector are pressed on the satellite platform and unlock and expand in place after satellite and the rocket separation；
The Microwave sounder Quasi optics are mounted on the satellite platform by Light deformation frame；
The solar wing is mounted on satellite platform radiating surface, and discharges locking/release device after satellite and the rocket separation；
The number passes antenna and is mounted at the top of satellite platform by bracket；
Be between the satellite platform and the Microwave sounder it is inclined, i.e., deposited between earth observation axis and satellite Z axis
In certain angle.
Preferably, the optical axis+Z over the ground after Microwave sounder inclination installationbWith satellite Z axis+ZGroundAngle α be 24 °.
It preferably, is mutually to be embedded between the satellite platform and the Microwave sounder, to make full use of delivery to rectify
Space resources in covering.
It preferably, is the heating integrated structure of machine between the satellite platform and Microwave sounder.
Preferably, entirely through back bracket inclination and mutually Embedded to be installed to the satellite flat for the primary reflection surface
In platform, and part locking/release device is discharged after stationary orbit reality aperture microwave sounding satellier injection.
Preferably, after stationary orbit reality aperture microwave sounding satellier injection, the Microwave sounder and the sun
The wing and the number pass antenna stepwise development in order.
Preferably, after stationary orbit reality aperture microwave sounding satellier injection, stationary orbit reality aperture microwave is visited
Survey primary reflection surface, the subreflector stepwise development of instrument antenna-feeder system.
Preferably, after the in-orbit expansion of stationary orbit reality aperture microwave sounding satellite, Microwave sounder and satellite are unlocked
The Planar Mechanisms of platform connect.
Preferably, after the in-orbit expansion of stationary orbit reality aperture microwave sounding satellite, using expansion, light-blocking mechanism is hidden
Keep off in stationary orbit sunlight from different directions on direct projection to survey meter.
Preferably, it is tiltedly mounted on satellite platform when the solar wing is in the case where single-blade by driving mechanism.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, when emission state, the heating integrated satellite configuration of machine being embedded in using platform and Microwave sounder tilting, to fill
Divide and utilizes the mechanical environment and high accuracy install demand for delivering space resources in radome fairing, adapting to transmitting powered phase, realization transmitting
Reliable, the effective gathering of state；
2, micro- using the whole star stepwise development of " Microwave sounder, solar wing sum number pass antenna ", real aperture when in-orbit state
The satellite configuration of the primary reflection surface of wave survey meter antenna-feeder system, subreflector stepwise development realizes Microwave sounder primary reflection surface
It is unfolded with the high-precision of subreflector；
3, after in-orbit expansion, in such a way that unlock Microwave sounder is connected with the Planar Mechanisms of satellite platform, connected with discharging
It scoops out power, reduce initial in-orbit deformation, realize the high-profile precision and position precision of antenna reflective face；
4, after in-orbit expansion, using the mechanism and light-locking material of expansion, to block in stationary orbit sunlight from difference
To the direct projection of survey meter on direction, realizes the good temperature uniformity of in-orbit rear survey meter antenna-feeder system and inhibit thermal deformation.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon.
Fig. 1 is stationary orbit reality of the present invention aperture microwave sounding satellite configuration unfolded state schematic diagram.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the present embodiment is to be based on list too
The satellite configuration of the positive wing without departing from the inventive concept of the premise, can also be done to those skilled in the art
Several modifications and improvements out, the satellite configuration including double solar wings.These are all within the scope of protection of the present invention.
Embodiment
Before being illustrated in connection with specific embodiments, first the coordinate system being related to is explained as follows:
Satellite body coordinate system: coordinate origin ObFor centroid of satellite ,+XbAxis is directed toward satellite flight direction ,+ZbAxis is directed toward star
Lower ,+YbAxis and+Zb、+XbAxis constitutes right hand rectangular coordinate system；
Satellite ground coordinate system: coordinate origin OGroundFor satellite and the rocket geometric separation surface center ,+ZGroundAxis vertical satellite and the rocket parting surface court
On ,+YGroundAxis is backwards to the satellite sun wing ,+XGroundAxis and+YGround、+ZGroundAxis constitutes right hand rectangular coordinate system.
Refering to fig. 1, stationary orbit reality of the present invention aperture microwave sounding satellite configuration, the configuration include: static rail
Road reality aperture Microwave sounder primary reflection surface 1, both sides of the edge portion compresses are unlocked and are opened up after satellite and the rocket separation on satellite platform
Position is reached, primary reflection surface is tiltedly mounted on satellite platform entirely through back bracket, and is mutually embedded into satellite platform, is entered
Part locking/release device 4 is discharged after rail；Microwave sounder subreflector 2, is pressed on satellite platform, solves after satellite and the rocket separation
It locks and expands in place；Microwave sounder Quasi optics 3 are mounted on satellite platform by Light deformation frame, and are mutually embedded into
In satellite platform, part locking/release device 4 is discharged after entering the orbit；It is flat to be tiltedly mounted on satellite by driving mechanism for solar wing 5
On platform (in the case where single-blade)；Number passes antenna 6, is mounted at the top of satellite platform by bracket, unlocks and expand in place after entering the orbit.
Specifically, after Microwave sounder inclination installation, the optical axis+Z over the groundbWith satellite Z axis+ZGroundAngle α be 24 °.
Specifically, the marginal portion of primary reflection surface 1 is pressed on satellite platform by 4 compression points.
Specifically, it is mutually embedded between the satellite platform and Microwave sounder, the principal reflection of Microwave sounder
Face, subreflector and Quasi optics are connected to satellite platform by several locking/release devices respectively, realize preferably transmitting master
The mechanical environment of dynamic section.
" Microwave sounder, solar wing, number pass antenna " is that stepwise development, realization Microwave sounder antenna-feeder system are high in order
Precision expansion, and ensure the highly reliable of whole star expansion.
It is in-orbit unlock between the satellite platform and Microwave sounder, unlock position includes primary reflection surface and satellite
The connection between connection and Quasi optics and satellite platform between platform.
It is in-orbit unlock between the satellite platform and Microwave sounder, retains 3 to 4 tie points, is connected with discharging
It scoops out power, reduce initial in-orbit deformation, provide good condition for the in-orbit thermal deformation suppressing of Microwave sounder, realize antenna-reflected
The high-profile precision and position precision in face.
Particularly, the in-orbit expansion of light-blocking mechanism 7, with block in stationary orbit sunlight from different directions on to survey meter
Direct projection realizes the good temperature uniformity of in-orbit rear survey meter antenna-feeder system and inhibits thermal deformation.
In conclusion when emission state, using the heating integrated satellite structure of machine of platform and the insertion of Microwave sounder tilting
Type, it is real with the mechanical environment and high accuracy install demand for making full use of space resources in delivery radome fairing, adapting to transmitting powered phase
Reliable, the effective gathering of existing emission state；When in-orbit state, using the whole of " Microwave sounder, solar wing sum number pass antenna "
Star stepwise development, the primary reflection surface of real aperture Microwave sounder antenna-feeder system, subreflector stepwise development satellite configuration, realize
The expansion of the high-precision of Microwave sounder primary reflection surface and subreflector；After in-orbit expansion, using unlock Microwave sounder and satellite
The mode of the Planar Mechanisms connection of platform realizes the high type of antenna reflective face to discharge connection stress, reduce initial in-orbit deformation
Face precision and position precision；After in-orbit expansion, using the mechanism and light-locking material of expansion, to block sunlight in stationary orbit
To the direct projection of survey meter on from different directions, realizes the good temperature uniformity of in-orbit rear survey meter antenna-feeder system and inhibit thermal change
Shape.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of stationary orbit reality aperture microwave sounding satellite configuration, which is characterized in that including satellite platform, Microwave sounder,
Microwave sounder Quasi optics, locking/release device, solar wing, number pass antenna, light-blocking mechanism；
The Microwave sounder includes primary reflection surface and subreflector, and primary reflection surface both sides of the edge portion compresses are flat in satellite
Platform, the subreflector are pressed on the satellite platform and unlock and expand in place after satellite and the rocket separation；
The Microwave sounder Quasi optics are mounted on the satellite platform by Light deformation frame；
The solar wing is mounted on satellite platform radiating surface, and discharges locking/release device after satellite and the rocket separation；
The number passes antenna and is mounted at the top of satellite platform by bracket；
Be between the satellite platform and the Microwave sounder it is inclined, i.e., there are one between earth observation axis and satellite Z axis
Clamp angle.
2. stationary orbit reality according to claim 1 aperture microwave sounding satellite configuration, characterized in that the microwave sounding
The optical axis+Z over the ground after instrument inclination installationbWith satellite Z axis+ZGroundAngle α be 24 °, wherein
Satellite body coordinate system: coordinate origin ObFor centroid of satellite ,+XbAxis is directed toward satellite flight direction ,+ZbAxis is directed toward substar,
+YbAxis and+Zb、+XbAxis constitutes right hand rectangular coordinate system；
Satellite ground coordinate system: coordinate origin OGroundFor satellite and the rocket geometric separation surface center ,+ZGroundThe vertical satellite and the rocket separation of axis is face-up ,+
YGroundAxis is backwards to the satellite sun wing ,+XGroundAxis and+YGround、+ZGroundAxis constitutes right hand rectangular coordinate system.
3. stationary orbit reality according to claim 2 aperture microwave sounding satellite configuration, characterized in that the satellite platform
It is mutually to be embedded between the Microwave sounder, to make full use of space resources in delivery radome fairing.
4. stationary orbit reality according to claim 3 aperture microwave sounding satellite configuration, characterized in that the satellite platform
It is the heating integrated structure of machine between Microwave sounder.
5. stationary orbit reality according to claim 1 aperture microwave sounding satellite configuration, characterized in that the primary reflection surface
It is installed in the satellite platform entirely through back bracket inclination is simultaneously mutually Embedded, and in stationary orbit reality aperture
Part locking/release device is discharged after microwave sounding satellier injection.
6. stationary orbit reality according to claim 1 aperture microwave sounding satellite configuration, characterized in that the stationary orbit
After real aperture microwave sounding satellier injection, the Microwave sounder and the solar wing and the number pass antenna substep in order
Expansion.
7. stationary orbit reality according to claim 1 aperture microwave sounding satellite configuration, characterized in that the stationary orbit
After real aperture microwave sounding satellier injection, the primary reflection surface of stationary orbit reality aperture Microwave sounder antenna-feeder system, pair are anti-
Penetrate face stepwise development.
8. stationary orbit reality according to claim 1 aperture microwave sounding satellite configuration, characterized in that the stationary orbit
After the real in-orbit expansion of aperture microwave sounding satellite, unlock Microwave sounder is connected with the Planar Mechanisms of satellite platform.
9. stationary orbit reality according to claim 1 aperture microwave sounding satellite configuration, characterized in that the stationary orbit
After the real in-orbit expansion of aperture microwave sounding satellite, sunlight is blocked in stationary orbit from different directions using the light-blocking mechanism of expansion
On direct projection to survey meter.
10. stationary orbit reality according to claim 1 aperture microwave sounding satellite configuration, characterized in that the solar wing
It is tiltedly mounted on satellite platform when in the case where single-blade by driving mechanism.
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| CN201910130676.5A CN109927938B (en) | 2019-02-21 | 2019-02-21 | Static orbit real aperture microwave detection satellite configuration |
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Cited By (1)
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| CN110455416A (en) * | 2019-08-21 | 2019-11-15 | 国家卫星气象中心(国家空间天气监测预警中心) | A kind of bright temperature correction method based on microwave radiometer antenna temperature detection |
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| CN104698509A (en) * | 2013-12-10 | 2015-06-10 | 上海卫星工程研究所 | Geostationary orbit meteorological satellite |
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