CN108051865A - Suitable for the intervening atom gradiometry method under spaceborne microgravity environment - Google Patents
Suitable for the intervening atom gradiometry method under spaceborne microgravity environment Download PDFInfo
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Abstract
The present invention provides a kind of intervening atom gradiometry methods suitable under spaceborne microgravity environment, comprise the following steps：Step 1 places Magneto-Optical Trap along three axial symmetry of centroid of satellite；Step 2, laser cooling imprison cold atom；Step 3 closes the field coil electric current of Magneto-Optical Trap；Step 4, laser manipulation atom complete intervening atom measurement；Step 5, the extraction of satellite angular speed.The present invention is in the unique conditions of undamped state of flight using atom free floating under the weightlessness of space, directly using the atomic interaction of laser and free floating in space, so as to which atom be allowed to interfere effect, carries out gradiometry.This method is simple, easy to operate, easily implements in space.
Description
Technical field
The present invention relates to a kind of measuring methods, and in particular, to a kind of atom suitable under spaceborne microgravity environment is done
Relate to gradiometry method.
Background technology
Satellite gradiometry is that high-precision obtains one of most effective means of earth gravitational field, and one high-precision complete
Gravity field model plays an important role in fields such as geodesic survey, geoscience, resource explorations.Satellite gradiometry
Using the measuring principle of difference acceleration, spaceborne gravity gradient is formed by the one or more pairs of gravimeters for being separated by certain baseline length
Instrument carries out difference measurement, to obtain variation of the gravity acceleration g with space, i.e. gravity gradient tensor, such as following formula (1)：
Spaceborne gravity gradiometer currently used for satellite gradiometry is electrostatic gravity gradiometer.Electrostatic gravity
Gradient former has capacitor plate and inspection quality block to form, and the inertia measurement using " capacitive displacement sensing+electrostatic feedback controls " is former
Reason obtains gravity gradient value, simple in structure, and technical maturity is high, has been successfully applied to gradiometry satellite GOCE, but
Its range is small, easily saturation, and is limited by circuit noise, processing technology and Low-Frequency Mechanical thermal noise, and measurement accuracy is promoted empty
Between it is limited；And intervening atom formula gravity gradiometer be by the use of the cold atoms of the movement of falling object as inspection quality come sense weight
The effect of power manipulates cold atom using the raman laser of phase coherence and realizes intervening atom, makes the phase of superposition state residing for atom
Position is related to the acceleration of gravity being subject in motion path, is believed by measuring the phase shift difference of interference fringe to obtain difference acceleration
Breath, and then gravity gradient value in this direction is obtained, there is big stability height, range, measurement bandwidth, low frequency white noise spectrum to put down
Surely, many advantages, such as spaceborne potential high certainty of measurement, one of candidate technologies of next-generation satellite gradiometry task are become.
Stanford University in 1998 has developed ground kept man of a noblewoman's platform intervening atom gravity gradiometer.By the hair of recent two decades
Exhibition, current Duo Jia mechanisms both at home and abroad have developed the ground-based experimental prototype of intervening atom gravity gradiometer, ground survey technology
It is ripe.Ground experiment is mainly imprisoned atom cooling by Magneto-Optical Trap (MOT), passes through the cold original of vertical upthrow different height
Son, under the action of earth's surface 1g acceleration of gravity atom fall and and laser action, interfere, then sense different height
The acceleration of gravity at place obtains the gravity gradient value on vertical direction.
The measurement noise of the gravity gradiometer of the type square is inversely proportional with interference time interval T's, and T is bigger, and noise is got over
Small, measurement accuracy is higher.Since ground is limited be subject to 1g acceleration of gravity and instrument size, atom needs in a short period of time
Whereabouts finishes and completes to interfere, therefore T can be only sustained at ms magnitudes.But under space microgravity environment, satellite is in flight
Process, atom is weightless at this time, in freely float, the state of undamped flight, effectively evaded atom and hurtled down touching appearance
The risk of wall, therefore T is easy to increase to tens of second-times, can significantly promote the measurement accuracy of gravity gradient, has non-
Often high spaceborne application prospect.
In this case, space measurement will there are larger differences with ground survey：
(1) for intervening atom gradiometry, measurement is the opposite acceleration with gradient former apparatus frame of atom
It spends, in ground experiment, apparatus frame is fixed on ground, therefore what is measured is earth's surface 1g acceleration of gravity, belongs to absolute gravity survey
Amount；Under space microgravity environment, apparatus frame is fixed on satellite, and measurement is acceleration of the atom compared with satellite, belongs to phase
To measurement.
(2) limited on ground by 1g acceleration of gravity, be only capable of gravity gradient component V of the measurement along geocentric verticalzz.Spaceborne ring
Under border, atom is weightless, in the state freely floated, undamped is flown, therefore is no longer limited to the single shaft ladder along geocentric vertical
Spend component (Vzz) measurement, so as to measure V simultaneously for single instrumentxx、Vyy、VzzA kind of possibility is provided etc. multiple gradient components；
If the gradiometry method of atom " upthrow whereabouts " formula still used at this time in space using ground, cannot
The longer interference time is obtained, measurement accuracy can not be promoted.
The content of the invention
For in the prior art the defects of, the object of the present invention is to provide a kind of originals suitable under spaceborne microgravity environment
Son interference gradiometry method, the only of undamped state of flight is in using atom free floating under the weightlessness of space
Special condition directly using the atomic interaction of laser and free floating in space, so as to which atom be allowed to interfere effect, carries out
Gradiometry.This method is simple, easy to operate, easily implements in space.
According to an aspect of the present invention, a kind of intervening atom gravity gradient suitable under spaceborne microgravity environment is provided
Measuring method, which is characterized in that comprise the following steps：
Step 1 places Magneto-Optical Trap along three axial symmetry of centroid of satellite；
Step 2, laser cooling imprison cold atom；
Step 3 closes the field coil electric current of Magneto-Optical Trap；
Step 4, laser manipulation atom complete intervening atom measurement；
Step 5, the extraction of satellite angular speed.
Preferably, the quantity of the Magneto-Optical Trap be six, be specially the first Magneto-Optical Trap, the second Magneto-Optical Trap, the 3rd Magneto-Optical Trap,
4th Magneto-Optical Trap, the 5th Magneto-Optical Trap, the 6th Magneto-Optical Trap, wherein the first Magneto-Optical Trap and the 4th Magneto-Optical Trap are placed on X-axis baseline, second
Magneto-Optical Trap and the 5th Magneto-Optical Trap are placed on Y-axis baseline, and the 3rd Magneto-Optical Trap and the 5th Magneto-Optical Trap are placed on Z axis baseline, each magneto-optic
Trap is fixed on satellite frame.
Preferably, the step 2 selects the alkali metal being commonly used in ground experiment to prepare cold atom.
Preferably, the step 2 uses laser by atom cooling to low-down temperature, on this basis along with two
The opposite coil of a magnetic direction may make up Magneto-Optical Trap to generate magnetic field gradient, by the atom bound of cooling in very little
In scope, cooling imprison cold atom.
Preferably, the step 3 makes Magneto-Optical Trap fail, and the cold atom cloud imprisoned at this time is released in the air, cold atom cloud
Only by gravity, in the air in the state freely floated, undamped is flown, cold atom cloud compared with satellite initial velocity
Close to zero.
Preferably, the intervening atom measurement in tri- directions of X, Y, Z and is not limited on these three directions simultaneously respectively
It carries out.
Preferably, the step 4 is with a distance away two irradiated with a branch of raman laser on the base direction
Cold atom makes atomic wave that division, deflection occur, converge again, so as to fulfill intervening atom, at each cold atom cloud interference
Corresponding interference fringe is obtained, the atomic group measured by each atomic group of phase shift acquisition of interference fringe is compared with satellite
Acceleration；On same base direction two at acceleration measurement do Difference Calculation, obtain the difference on X, Y, Z tri- directions respectively
Component of acceleration information；The intervening atom measurement be after cold atom cloud is released, only by gravity under space microgravity environment,
In freely floating, carried out in the state of undamped flight.
Preferably, the acquisition combination star sensor of the satellite angular speed and the spaceborne gyroscope of high-precision.
Compared with prior art, the present invention has following advantageous effect：
(1) this method maintains the state that atom is zero compared with satellite initial velocity after the release of space, directly using Raman
The atomic interaction of laser and free floating in space can both obtain larger interference time interval T, improve measurement accuracy,
Be conducive to the miniaturization of equipment again；
(2) each direction same raman laser and two atomic interactions, by difference measurement, can obtain very
Good common mode inhibition effect, to satellite platform vibration, Raman light the phase noise at least inhibitory action of 80dB~155dB, this
It is highly beneficial for improving measurement sensitivity；
(3) by 1g gravity effects, the gravity that vertical direction can only be measured by the way of upthrow whereabouts is terraced on ground
Angle value Vzz, and atom is in suspended state under space environment, therefore from the limitation of measurement direction, it can be different using multi beam simultaneously
The raman laser and atomic interaction in direction, measure the relative acceleration of tri- axis of X, Y, Z, therefore can realize Vxx、Vyy、VzzThree
The measurement of a diagonal gradient component.Simulation result shows Vxx、Vyy、VzzThe measurement accuracy of three gradient components is up to 1mE (1E=
10-9/s2), suitable for next-generation high-resolution satellite gradiometry task.
Description of the drawings
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 the flow chart for the intervening atom gradiometry method that the present invention is suitable under spaceborne microgravity environment.
Specific embodiment
With reference to specific embodiment, the present invention is described in detail.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 ordinary skill to this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
Intervening atom gradiometry method proposed by the present invention be suitable for spaceborne microgravity environment, satellite flight in
The LEO of 200~500km, and it is outer using atmospheric damping, the solar light pressure being subject to without towing control technology elimination satellite etc.
Portion's perturbed force realizes that satellite flies in the undamped of low rail.These designs are the prior art, have obtained in-orbit successful application,
It can directly continue to use, it will not go into details here.Intervening atom gradiometry suitable for spaceborne microgravity environment is added based on difference
The measuring principle of speed by three pairs and is not limited to three pairs of atomic interference gravimeters respectively on space three-dimensional rectangular co-ordinate direction
Constituting atom interference gravity gradiometer carries out difference measurement, to ensure the stability of measurement baseline, each pair atomic interference gravimeter
It is symmetrically mounted on super steady carbon carbon fiber structural and is not limited on the pedestal of carbon carbon fiber structural, each pair atomic interference gravimeter edge
Centroid of satellite is symmetrically placed, and three pairs of gravimeters are mutually orthogonal, and gradient former center is overlapped with centroid of satellite, here using satellite body
Coordinate system, centroid of satellite are coordinate origin, and satellite X, Y and Z axis are respectively satellite flight, vertical track plane and geocentric vertical side
To.
The intervening atom gradiometry method that the present invention is suitable under spaceborne microgravity environment comprises the following steps：
Step 1 places Magneto-Optical Trap along three axial symmetry of centroid of satellite.The quantity of Magneto-Optical Trap is six, is specially the first magneto-optic
Trap, the second Magneto-Optical Trap, the 3rd Magneto-Optical Trap, the 4th Magneto-Optical Trap, the 5th Magneto-Optical Trap, the 6th Magneto-Optical Trap, wherein the first Magneto-Optical Trap and
Four Magneto-Optical Traps are placed on X-axis (heading) baseline, and the second Magneto-Optical Trap and the 5th Magneto-Optical Trap are placed in Y-axis (vertical track plane side
To) on baseline, the 3rd Magneto-Optical Trap and the 5th Magneto-Optical Trap are placed on Z axis (geocentric vertical) baseline.Each Magneto-Optical Trap is fixed on satellite
On frame.
Step 2, laser cooling imprison cold atom.The alkali metal being commonly used in ground experiment is selected to prepare cold atom.
The type of alkali metal, which is selected, commonly uses the atoms such as sodium, rubidium, caesium in ground experiment.Using laser by atom cooling to low-down temperature
Degree, on this basis along with the opposite coil of two magnetic directions may make up Magneto-Optical Trap to generate magnetic field gradient, will cool down
Atom bound in the scope of a very little, i.e., cooling imprison cold atom.The method of this laser cooling Trapping of Atoms is existing
There is mature technology, can directly continue to use, it will not go into details here.During measurement, the field coil electric current of Magneto-Optical Trap is closed, loses Magneto-Optical Trap
Effect, allows the cold atom cloud of imprison to be released in the air, and the initial velocity of cold atom cloud release is zero.
Step 3 closes the field coil electric current of Magneto-Optical Trap, Magneto-Optical Trap is made to fail, and the cold atom cloud imprisoned at this time is released
To aerial, cold atom cloud is only by gravity, and in the air in the state freely floated, undamped is flown, cold atom cloud is opposite
In satellite initial velocity close to zero.
Step 4, laser manipulation atom complete intervening atom measurement.Intervening atom measurement respectively in tri- directions of X, Y, Z and
It is not limited to be carried out at the same time on these three directions.With with a branch of raman laser irradiate on the base direction a distance away
Two cold atoms make atomic wave that division, deflection occur, converge again, so as to fulfill intervening atom, are done in each cold atom cloud
It relates to place and obtains corresponding interference fringe, atomic group that each atomic group measures is obtained compared with defending by the phase shift of interference fringe
The acceleration of star；On same base direction two at acceleration measurement do Difference Calculation, obtain respectively on X, Y, Z tri- directions
Difference acceleration information；The intervening atom measurement be after cold atom cloud is released, under space microgravity environment only by
Gravity, in freely floating, carried out in the state of undamped flight.It is manipulated simultaneously with a branch of raman laser in each direction
A distance away two cold atoms on the base direction realize intervening atom measurement, can obtain good common mode suppression
Effect processed.
Step 5, the extraction of satellite angular speed.Measurement satellite angular speed is realized by surveying appearance instrument on high precision star.Satellite
The acquisition combination star sensor of angular speed and the spaceborne gyroscope of high-precision.Using star sensor measurement attitude of satellite angle, pair when
Between first derivative can obtain satellite angular velocity information；Gyroscope selects high-precision lasergyro or atomic gyroscope, should
The gyroscope of type does not generate satellite any mechanical oscillation, it is ensured that high-precision measurement.Gyroscope is responsible for mainly measuring,
The data of star sensor are used to be corrected.Satellite angular velocity omega x, ω y, the ω z being derived from tri- directions of X, Y, Z,
It is deducted in the difference acceleration output that 4th pacing obtains, to obtain gravity gradient value Vxx, Vyy, Vzz.
The method provided by the invention is mainly characterized in that using the unique conditions of atom free floating under satellite weightlessness, after discharging atom,
By the way of atom not being dished out using ground, but the state for being zero compared with satellite initial velocity after maintaining atom release, respectively edge
X, three directions of Y, Z (space three-dimensional direct orthonormal coordinate system) directly use the atom phase of raman laser and free floating in space
Interaction so as to which atom be allowed to interfere effect, is realized to Vxx、Vyy、VzzThe measurement of three diagonal gradient components.
Specifically, intervening atom gradiometry is mainly based upon the atomic interference gravimeter of difference form and realizes
's.For single atomic interference gravimeter, operation principle is that the atomic group of cooling is allowed with laser interacted
Into interference, by the phase shift for measuring interference fringeObtain the relative acceleration a between atomic group and satellite, be represented by as
Following formula (2)：
Wherein keffIt is effective wave vector of raman laser pulse, T is laser pulse interval.
Two atomic interference gravimeters on same base direction form difference measurement.Under spaceborne microgravity environment, atom
Weightlessness, close to free floating condition, under conditions of low rail gradiometry satellite is used and controlled without towing, each interferometer
Relative acceleration between the atomic group and satellite that measure is represented by such as following formula (3)：
Wherein, ai,pWith ai,pWhat the two interferometer p and q on expression i base directions (i=x, y, z) was measured respectively adds
Speed, ViiIt represents along the diagonal gradient component V on i directionsii, liRepresent the baseline length on i directions.ω2=ωx 2+ωy 2+
ωz 2Represent satellite angular speed, ωiFor the angular speed of satellite i axis.aingRepresent the non-gravitational acceleration that satellite is subject to along i directions
(such as atmospheric damping, solar light pressure).ai,pWith ai,pValue it is very small, in the LEO of below 500km, no more than 10-6m/
s2Magnitude, this shows between atom and satellite almost remains stationary.Thus effectively prevent the atom occurred in ground experiment
The problem of being hurtled down by earth's surface acceleration of gravity, therefore longer interference time interval T can be obtained, greatly improve measurement essence
Degree.
At this point, the difference acceleration Δ a of two interferometer measurements on i base directionsiIt is represented by such as following formula (4)：
Above-mentioned difference acceleration is by the interference fringe phase shift difference on i base directionsIt obtains, is represented by such as following formula
(5)：
It is such as following formula (6) this makes it possible to obtain the gradiometry expression formula under spaceborne environment：
It follows that intervening atom gravity gradiometer obtains gravity gradient value, space microgravity ring by measuring phase difference
Under border, phase differenceIn both contained gravity gradient value V at orbit altitudeii, and satellite angular velocity information is carried, wherein
Satellite angular speed can be obtained by surveying appearance system on the stars such as star sensor, gyroscope in high precision, and in gravity gradient extraction process
Middle deduction.
The present invention can not only obtain higher measurement accuracy, but also can realize multiple diagonal gradient components while surveys
Amount can be applied to next-generation high-resolution satellite gradiometry task.The present invention utilizes atom under spaceborne weightlessness
Freely float the unique conditions in undamped state of flight, the shape for being zero compared with satellite initial velocity after maintenance atom release
State directly completes intervening atom using the atomic interaction of raman laser and free floating in space, realizes that gravity gradient is surveyed
Amount.This method is simple, easy to operate, easily implements in space.Spaceborne measuring method proposed by the present invention can obtain higher measurement
Precision is realized to Vxx、Vyy、VzzIt is measured while three diagonal gradient components, can be applied to next-generation high-resolution satellite weight
Power gradiometry task.The present invention is suitable for spaceborne microgravity environment, and satellite flight is adopted in the LEO of 200~500km
With external disturbances power such as atmospheric damping, the solar light pressures being subject to without towing control technology elimination satellite, realize satellite in low rail
Undamped is flown.The present invention is based on the measuring principle of difference acceleration, respectively by three pairs on space three-dimensional rectangular co-ordinate direction
And it is not limited to three pairs of atomic interference gravimeter constituting atom interference gravity gradiometers and carries out difference measurement, each pair intervening atom weight
Power instrument is symmetrically mounted on super steady construction pedestals, and each pair atomic interference gravimeter is symmetrically placed along centroid of satellite, three pairs of gravimeters
Mutually orthogonal, gradient former center is overlapped with centroid of satellite.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (8)
- A kind of 1. intervening atom gradiometry method suitable under spaceborne microgravity environment, which is characterized in that including with Lower step：Step 1 places Magneto-Optical Trap along three axial symmetry of centroid of satellite；Step 2, laser cooling imprison cold atom；Step 3 closes the field coil electric current of Magneto-Optical Trap；Step 4, laser manipulation atom complete intervening atom measurement；Step 5, the extraction of satellite angular speed.
- 2. the intervening atom gradiometry method according to claim 1 suitable under spaceborne microgravity environment, It is characterized in that, the quantity of the Magneto-Optical Trap is six, is specially the first Magneto-Optical Trap, the second Magneto-Optical Trap, the 3rd Magneto-Optical Trap, the 4th magnetic Ligh trap, the 5th Magneto-Optical Trap, the 6th Magneto-Optical Trap, wherein the first Magneto-Optical Trap and the 4th Magneto-Optical Trap are placed on X-axis baseline, the second Magneto-Optical Trap It is placed in the 5th Magneto-Optical Trap on Y-axis baseline, the 3rd Magneto-Optical Trap and the 5th Magneto-Optical Trap are placed on Z axis baseline, and each Magneto-Optical Trap is connected In on satellite frame.
- 3. the intervening atom gradiometry method according to claim 1 suitable under spaceborne microgravity environment, It is characterized in that, the step 2 selects the alkali metal being commonly used in ground experiment to prepare cold atom.
- 4. the intervening atom gradiometry method according to claim 1 suitable under spaceborne microgravity environment, Be characterized in that, the step 2 using laser by atom cooling to low-down temperature, on this basis along with two magnetic fields The opposite coil in direction may make up Magneto-Optical Trap to generate magnetic field gradient, by the atom bound of cooling a very little scope In, cooling imprison cold atom.
- 5. the intervening atom gradiometry method according to claim 1 suitable under spaceborne microgravity environment, It is characterized in that, the step 3 makes Magneto-Optical Trap fail, and the cold atom cloud imprisoned at this time is released in the air, and cold atom cloud is only by weight Power act on, in the air in freely float, undamped fly state, cold atom cloud compared with satellite initial velocity close to Zero.
- 6. the intervening atom gradiometry method according to claim 1 suitable under spaceborne microgravity environment, It is characterized in that, the intervening atom measurement in tri- directions of X, Y, Z and is not limited to be carried out at the same time on these three directions respectively.
- 7. the intervening atom gradiometry method according to claim 1 suitable under spaceborne microgravity environment, It is characterized in that, the step 4 is with a distance away the two cold originals irradiated with a branch of raman laser on the base direction Son makes atomic wave that division, deflection occur, converge again, so as to fulfill intervening atom, is obtained at each cold atom cloud interference Corresponding interference fringe, by the atomic group that each atomic group of phase shift acquisition of interference fringe measures compared with the acceleration of satellite Degree；On same base direction two at acceleration measurement do Difference Calculation, the difference obtained respectively on X, Y, Z tri- directions adds Velocity information；The intervening atom measurement is after cold atom cloud is released, and only by gravity under space microgravity environment, is in It freely floats, undamped carries out in the state of flying.
- 8. the intervening atom gradiometry method according to claim 1 suitable under spaceborne microgravity environment, It is characterized in that, acquisition combination star sensor and the spaceborne gyroscope of high-precision of the satellite angular speed.
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Application publication date: 20180518 |