CN102540210A - Method and device for generating radio frequency signal of satellite under rotating conditions of carrier - Google Patents
Method and device for generating radio frequency signal of satellite under rotating conditions of carrier Download PDFInfo
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- CN102540210A CN102540210A CN2012100318994A CN201210031899A CN102540210A CN 102540210 A CN102540210 A CN 102540210A CN 2012100318994 A CN2012100318994 A CN 2012100318994A CN 201210031899 A CN201210031899 A CN 201210031899A CN 102540210 A CN102540210 A CN 102540210A
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Abstract
The invention relates to a method and a device for generating a radio frequency signal of a satellite under rotating conditions of a carrier. The method mainly comprises the following steps of: calculating rotating speed of a carrier antenna, and calculating Doppler frequency shift caused by rotation of the carrier according to the rotating speed of the carrier antenna; establishing an antenna coordinate system of the carrier, and calculating gain and receiving signal power of the carrier antenna in a rotating state of the carrier according to the antenna coordinate system; and generating the radio frequency signal of the satellite according to the Doppler frequency shift and the antenna gain and receiving signal power of the carrier antenna. By the method and the device, the rotating speed of the carrier antenna is calculated by establishing the antenna coordinate system of the carrier, the Doppler frequency shift caused by rotation of the carrier is calculated according to the rotating speed of the carrier antenna, a motion attitude of the carrier is modeled in the process of simulating multiple motion tracks of the carrier, the radio frequency signal of the satellite can be generated under the rotating conditions, and a simulation signal source is provided for research, development and test of a missile-borne receiver.
Description
Technical field
The present invention relates to the Computer Applied Technology field, relate in particular to a kind of under carrier rotation condition the generation method and apparatus of the radiofrequency signal of satellite.
Background technology
GPS (Global Positioning System continues; GPS) after, various countries are devoted to develop the satellite navigation system of oneself, and China is on the basis of Big Dipper generation satellite navigation system; Start the new situation of No. two satellite navigation systems of the Big Dipper, and obtained phasic results.Yet the development of Beidou satellite navigation system but is faced with numerous challenges.In order to carry out the research of Big Dipper guidance technology; The equipment of rotation system also carries out high speed rotary motion in high-speed flight; Cause rotating the visible star number order of the equipment of system, amplitude, Doppler, the carrier phase that receives the satellite RF signal changes fast; Therefore, the catching of receiver, tracking performance are had higher requirement.
In the prior art, also do not intend the method for the radiofrequency signal that generates satellite at carrier rotation condition counterdie.
Summary of the invention
Embodiments of the invention provide a kind of under carrier rotation condition the generation method and apparatus of the radiofrequency signal of satellite, to realize generating effectively the satellite RF signal under the rotation condition.
A kind of under carrier rotation condition the generation method of the radiofrequency signal of satellite, comprising:
Calculate the rotational speed of carrier antenna, calculate the Doppler shift that the carrier rotation causes according to the rotational speed of said carrier antenna;
Setting up the antenna coordinate system of carrier, is to calculate gain and the received signal power that the carrier rotation status is downloaded body antenna based on said antenna coordinate;
According to the antenna gain and the received signal power of said Doppler shift and carrier antenna, generate the radiofrequency signal of satellite.
A kind of under carrier rotation condition the generating apparatus of the radiofrequency signal of satellite, comprising:
The Doppler shift computing module is used to calculate the rotational speed of carrier antenna, calculates the Doppler shift that the carrier rotation causes according to the rotational speed of said carrier antenna;
Gaining and power computation module, be used to set up the antenna coordinate system of carrier, is to calculate gain and the received signal power that the carrier rotation status is downloaded body antenna based on said antenna coordinate;
The radiofrequency signal generation module, the antenna gain and the received signal power of the carrier antenna that Doppler shift that is used for being calculated according to said Doppler shift computing module and said gain and power computation module are calculated generate the radiofrequency signal of satellite.
Technical scheme by the embodiment of the invention described above provides can be found out; The embodiment of the invention is through setting up the antenna coordinate system of carrier; Calculate the rotational speed of carrier antenna, calculate the Doppler shift that the carrier rotation causes, in simulation variety carrier movement locus, the carrier movement attitude is carried out modeling according to the rotational speed of said carrier antenna; Can generate the satellite RF signal under the rotation condition, testing for the research and development of missile-borne receiver provides dummy source.
Description of drawings
Fig. 1 provides for the embodiment of the invention one a kind of under carrier rotation condition the processing flow chart of the generation method of the radiofrequency signal of satellite;
The synoptic diagram of the antenna rotating model of a kind of carrier that Fig. 2 provides for the embodiment of the invention one;
The synoptic diagram of the antenna coordinate system of a kind of carrier that Fig. 3 provides for the embodiment of the invention one;
Fig. 4 provides for the embodiment of the invention two a kind of under carrier rotation condition the concrete structure figure of the generating apparatus of the radiofrequency signal of satellite;
The concrete structure figure of a kind of satellite RF signal simulator that Fig. 5 provides for the embodiment of the invention two.
Embodiment
For the purpose, technical scheme and the advantage that make the embodiment of the invention is clearer, will combine accompanying drawing below, clear so that the embodiment of the invention is carried out, intactly describe personnel.
Embodiment one
The high speed rotary motion of the carrier in the space can cause carrier to the blocking of receiving antenna, and causes satellite visibility to change, and in the carrier rotation, the Doppler and the signal power of the reception signal of carrier also change thereupon.
The embodiment of the invention is through setting up carrier coordinate system, and the position of satellite in the horizontal system of coordinates is transformed into carrier coordinate system, thereby calculates the satellite elevation angle, judges satellite visibility according to the satellite elevation angle.Through setting up the antenna rotating model, calculate satellite and user's real-time pseudorange vector and the angular relationship between the antenna rotation rate, thereby calculate Doppler's power of the reception signal of carrier.Received signal by carrier is calculated antenna gain and received signal power to the incident angle of reception antenna, finally sets up signal and generates hardware platform and generate radiofrequency signal.
For ease of understanding, do further below in conjunction with accompanying drawing and specific embodiment and to explain the embodiment of the invention.
Embodiment one
This embodiment provides a kind of under carrier rotation condition the treatment scheme of the generation method of the radiofrequency signal of satellite as shown in Figure 1, comprise following treatment step:
Step 11: the antenna rotating model of setting up carrier.
Under carrier coordinate system, set up the antenna rotating model of carrier, obtain the angular relationship between antenna rotation rate and the pseudorange.Antenna rotating model synoptic diagram such as Fig. 2 of a kind of carrier that this embodiment provides, above-mentioned pseudorange observe the carrier that obtains to the distance between the satellite through GPS.
In Fig. 2, the plane of establishing the carrier coordinate system place is x
uOz
uThe plane, l ' is the air line distance between the true origin of satellite to carrier coordinate system, l is that l ' is at x
uOz
uThe projection on plane, ψ is the angle between l ' and the l, β is l and z
uThe angle of axle, v
zBe the rotational speed of carrier antenna, v
z=ω
zR, ω
z=2 π f
zBe the rotation angle frequency of carrier antenna, r is the carrier radius, f
zBeing frequency, is the inverse of antenna rotation period.Step 12: calculate the speed component of rotational speed on l ' direction of carrier antenna, calculate the Doppler shift that the carrier rotation causes according to this speed component.
If v is the speed component of rotational speed on l ' direction of carrier antenna, its computing method are:
v＝v
zsin(β-ω
zt)cosψ
T in the above-mentioned formula representes a certain moment, and v is the speed in this moment
By Doppler's computing formula f
dThe corresponding Doppler shift of each frequency that the rotation of=vf/c calculating carrier causes does
f
d＝v
zsin(β-ω
zt)cosψ·f
c/c
＝2πrf
zsin(β-2πf
zt)cosψ·f
c/c
Wherein, f
cBe the carrier frequency of certain frequency in the navigational system, c is the light velocity.
In the GPS navigation system, above-mentioned frequency comprises l
1Frequency and l
2Frequency.In Beidou satellite navigation system, above-mentioned frequency comprises B
1Frequency, B
2Frequency and B
3Frequency.
Step 13: calculate gain and received signal power that the carrier rotation status is downloaded body antenna.
Under carrier antenna rotating conditions, the carrier antenna is at the corresponding different yield value of different angles.
The synoptic diagram of the antenna coordinate of a kind of carrier that this embodiment provides system is as shown in Figure 3, and wherein, ε is that the line of satellite and true origin is at X
aOZ
aProjection in the plane and X
aThe angle of axle, X
aOZ
aThe plane is the plane at antenna coordinate system place,
Span is 0～360 °, and η is the line and the Y of satellite and true origin
aAngle between the axle, span is 0～180 °, establishes P
aBe the antenna gain of carrier, P
a=G (ε, η), G is the function of ε and η;
When η=0, antenna gain is maximum, rotates in 180 processes at the antenna of carrier, and gain is reduced to 0 gradually, and this change procedure can be represented by sine function, establish P
aAntenna gain for the carrier antenna.
P
a=ksin (ω t), wherein ω is an angular velocity of rotation, k is the antenna gain maximal value.
If P
rFor calculating the received signal power of carrier antenna, its computing formula is following:
P
r=P
s-P
w+ P
a, P wherein
sBe the transmit signal power of satellite, P
wFor spatial transmission postpones, P
aAntenna gain for the carrier antenna.
Received signal power P according to said carrier antenna
rCalculate the signal amplitude A (t) of the radiofrequency signal of the satellite that the receiver front end of carrier antenna receives,
Rotate the Doppler shift f that causes according to said carrier antenna
d=vf/c calculates the angular frequency of Doppler shift
d(t), ω
d(t)=2 π f
d(t).
The radiofrequency signal of the receiver front end satellite of the arrival carrier antenna that the satellite RF signal simulator on the carrier simulates is S (t), and the computing formula of S (t) is following:
S(t)＝A(t)D(t-τ(t))C(t-τ(t))cos
[(ω+ω
d(t))(t-τ(t))+φ(t)]+n(t)
Wherein, the signal amplitude that A (t) receives for receiver front end, D (t) is the navigation message of this satellite, and C (t) is a spreading code, and ω is a radio frequency angular velocity, ω
d(t) for frequency shift (FS), τ (t) for satellite-signal from being transmitted into the time delay of reception, φ (t) is a carrier phase, the thermonoise that n (t) receives for receiver.
Above-mentioned satellite RF signal simulator only generates the radiofrequency signal of visible satellite.
Embodiment two
This embodiment provide a kind of under carrier rotation condition the generating apparatus of the radiofrequency signal of satellite, its concrete structure is as shown in Figure 4, comprises following module:
Doppler shift computing module 41 is used to calculate the rotational speed of carrier antenna, calculates the Doppler shift that the carrier rotation causes according to the rotational speed of said carrier antenna;
Gaining and power computation module 42, be used to set up the antenna coordinate system of carrier, is to calculate gain and the received signal power that the carrier rotation status is downloaded body antenna based on said antenna coordinate;
Radiofrequency signal generation module 43, the antenna gain and the received signal power of the carrier antenna that Doppler shift that is used for being calculated according to said Doppler shift computing module and said gain and power computation module are calculated generate the radiofrequency signal of satellite.
Concrete, described Doppler shift computing module 41, the plane that also is used to establish the carrier coordinate system place is x
uOz
uThe plane, l ' is the air line distance between the true origin of satellite to carrier coordinate system, l is that l ' is at x
uOz
uThe projection on plane, ψ is the angle between l ' and the l, β is l and z
uThe angle of axle, v
zBe the rotational speed of carrier antenna, v
z=ω
zR, ω
z=2 π f
zBe the rotation angle frequency of carrier antenna, r is the carrier radius, f
zBeing frequency, is the inverse of antenna rotation period.
If v is the speed component of rotational speed on l ' direction of carrier antenna, its computing method are:
v＝v
zsin(β-ω
zt)cosψ
Said t representes a certain moment, and v is the speed in this moment
By Doppler's computing formula f
dThe corresponding Doppler shift of each frequency that the rotation of=vf/c calculating carrier causes does
f
d＝v
zsin(β-ω
zt)cosψ·f
c/c
＝2πrf
zsin(β-2πf
zt)cosψ·f
c/c
Wherein, f
cBe the carrier frequency of certain frequency in the navigational system at carrier place, c is the light velocity.
Concrete, described gain and power computation module 42 also are used to set up the antenna coordinate system of carrier, and this antenna coordinate is to comprise: ε is that the line of satellite and true origin is at X
aOZ
aProjection in the plane and X
aThe angle of axle, span is 0～360 °, η is the line and the Y of satellite and true origin
aAngle between the axle, span is 0～180 °, establishes the antenna gain that Pa is a carrier, P
a=G (ε, η), G is the function of ε and η;
If P
rFor calculating the received signal power of carrier antenna, its computing formula is following:
P
r=P
s-P
w+ P
a, P wherein
sBe the transmit signal power of satellite, P
wFor spatial transmission postpones, P
aAntenna gain for the carrier antenna.
Concrete, described radiofrequency signal generation module 43 also is used for the received signal power P according to said carrier antenna
rCalculate the signal amplitude A (t) of the radiofrequency signal of the satellite that the receiver front end of carrier antenna receives, the Doppler shift f that causes according to said carrier antenna rotation
d=vf/c calculates the angular frequency of Doppler shift
d(t),
The radiofrequency signal that is set to the receiver front end satellite that reaches the carrier antenna is S (t), and the computing formula of S (t) is following:
S(t)＝A(t)D(t-τ(t))C(t-τ(t))cos
[(ω+ω
d(t))(t-τ(t))+φ(t)]+n(t)
Wherein, the signal amplitude that A (t) receives for receiver front end, D (t) is the navigation message of this satellite, and C (t) is a spreading code, and ω is a radio frequency angular velocity, ω
d(t) for frequency shift (FS), τ (t) for satellite-signal from being transmitted into the time delay of reception, φ (t) is a carrier phase, the thermonoise that n (t) receives for receiver.
Wherein, A (t) can be drawn by Pr,
ω d (t) is the angular frequency of Doppler shift, can be by f
dDraw ω
d(t)=2 π f
d(t).
The above-mentioned generating apparatus of the radiofrequency signal of satellite under carrier rotation condition shown in Figure 4 can be arranged in the satellite RF signal simulator on the carrier; The concrete structure of a kind of above-mentioned satellite RF signal simulator that this embodiment provides is as shown in Figure 5, comprises following module:
Main control system; Operation mathematical simulation software and Control Software; Mathematical simulation software has the full constellation copying of No. two satellite navigation systems of the Big Dipper; But simulation space environmental parameter, relativistic effect be to the influence of user's observed quantity, the variation of signal Doppler, carrier phase and the signal power strength of can the rotation of emulation carrier bringing.The workflow of Control Software control whole simulation system.
Interface module provides the interface between main control system and emulated data control module, radiofrequency signal processing module, the radio-frequency module.
The emulated data control module is selected corresponding emulated data according to the control command that main control system sends, and accomplishes the pre-service of emulated data, and is distributed to the radiofrequency signal processing module.The emulated data control module can be upgraded contextual data according to the instruction of main control system scene update.
The radiofrequency signal generation module, the simulation of being responsible for radiofrequency signal produces, and is accomplished the digital baseband of emulated data by numerical portion and handles, and intermediate-frequency section is accomplished modulation and DAC (analog to digital converter) conversion, realizes the radiofrequency signal simulation of No. two satellites of the Big Dipper.The concrete structure of this module such as above-mentioned shown in Figure 4, concrete processing procedure is with reference to the foregoing description one and embodiment two.
The radiofrequency signal sending module is accomplished the control of up-conversion and power, and generates RNSS (satellite navigation system, Radio Navigation Satellite System) needed various clocks of detecting unit and trigger pip.
The signal processing flow of above-mentioned satellite RF signal simulator is: main control system generates the simulating scenes data and sends to the emulated data control module through data interface module according to being provided with by mathematical simulation software.The emulated data control module is with navigation message that receives and observation data; Be distributed to corresponding radiofrequency signal processing module according to the frequency sign; Each radiofrequency signal is handled processing module and is calculated the digital signal processing algorithm parameters needed according to the navigation message and the observation data of this frequency; Generate spreading code, accomplish signal spread-spectrum, produce the baseband digital signal that comprises delay and doppler characterization.The synthetic baseband signal of baseband processing module is delivered to signal synthesizing module and is generated intermediate-freuqncy signal; The intermediate-freuqncy signal of each frequency is delivered in the radio-frequency module; Upconvert on the corresponding RF spot through different up-conversion passages, at last through synthetic one tunnel radiofrequency signal output of combiner.
One of ordinary skill in the art will appreciate that all or part of flow process that realizes in the foregoing description method; Be to instruct relevant hardware to accomplish through computer program; Described program can be stored in the computer read/write memory medium; This program can comprise the flow process like the embodiment of above-mentioned each side method when carrying out.Wherein, described storage medium can be magnetic disc, CD, read-only storage memory body (Read-Only Memory, ROM) or at random store memory body (Random Access Memory, RAM) etc.
In sum; The embodiment of the invention is through setting up the antenna coordinate system of carrier; Calculate the rotational speed of carrier antenna, calculate the Doppler shift that the carrier rotation causes, in simulation variety carrier movement locus, the carrier movement attitude is carried out modeling according to the rotational speed of said carrier antenna; Can generate the satellite navigation signals under the rotation condition, testing for the research and development of missile-borne receiver provides dummy source.
The embodiment of the invention provides under a kind of carrier rotation condition; The generation method of satellite navigation radiofrequency signal; Effective analog receiver Doppler's in rotary course situation of change, thereby test receiver performance are for the research and development test of rotating carrier receiver provides dummy source.
The above; Be merely the preferable embodiment of the present invention, but protection scope of the present invention is not limited thereto, any technician who is familiar with the present technique field is in the technical scope that the present invention discloses; The variation that can expect easily or replacement all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claim.
Claims (8)
1. the generation method of the radiofrequency signal of satellite under carrier rotation condition is characterized in that, comprising:
Calculate the rotational speed of carrier antenna, calculate the Doppler shift that the carrier rotation causes according to the rotational speed of said carrier antenna;
Setting up the antenna coordinate system of carrier, is to calculate gain and the received signal power that the carrier rotation status is downloaded body antenna based on said antenna coordinate;
According to the antenna gain and the received signal power of said Doppler shift and carrier antenna, generate the radiofrequency signal of satellite.
2. the generation method of satellite RF signal is characterized in that under the carrier rotation condition according to claim 1, and the rotational speed of described calculating carrier antenna is calculated the Doppler shift that the carrier rotation causes according to the rotational speed of said carrier antenna, comprising:
If the plane at carrier coordinate system place is x
uOz
uThe plane, l ' is the air line distance between the true origin of satellite to carrier coordinate system, l is that l ' is at x
uOz
uThe projection on plane, ψ is the angle between l ' and the l, β is l and z
uThe angle of axle, v
zBe the rotational speed of carrier antenna, v
z=ω
zR, ω
z=2 π f
zBe the rotation angle frequency of carrier antenna, r is the carrier radius, f
zBeing frequency, is the inverse of antenna rotation period;
If v is the speed component of rotational speed on l ' direction of carrier antenna, its computing method are:
v＝v
zsin(β-ω
zt)cosψ
Said t representes a certain moment, and v is the speed in this moment
By Doppler's computing formula f
dThe corresponding Doppler shift of each frequency that the rotation of=vf/c calculating carrier causes does
f
d＝v
zsin(β-ω
zt)cosψ·f
c/c
＝2πrf
zsin(β-2πf
zt)cosψ·f
c/c
Wherein, f
cBe the carrier frequency of certain frequency in the navigational system at carrier place, c is the light velocity.
3. the generation method of satellite RF signal under the carrier rotation condition according to claim 1; It is characterized in that; The described antenna coordinate system that sets up carrier is to calculate gain and the received signal power that the carrier rotation status is downloaded body antenna according to said antenna coordinate, comprising:
Set up the antenna coordinate system of carrier, this antenna coordinate system comprises: ε is that the line of satellite and true origin is at X
aOZ
aProjection in the plane and X
aThe angle of axle, span is 0～360 °, η is the line and the Y of satellite and true origin
aAngle between the axle, span is 0～180 °, establishes P
aBe the antenna gain of carrier, P
a=G (ε, η), G is the function of ε and η;
If P
rFor calculating the received signal power of carrier antenna, its computing formula is following:
P
r=P
s-P
w+ P
a, P wherein
sBe the transmit signal power of satellite, P
wFor spatial transmission postpones, P
aAntenna gain for the carrier antenna.
4. according to the generation method of satellite RF signal under claim 1 or the 2 or 3 described carrier rotation conditions, it is characterized in that, described antenna gain and received signal power according to said Doppler shift and carrier antenna, the radiofrequency signal of generation satellite comprises:
Received signal power P according to said carrier antenna
rCalculate the signal amplitude A (t) of the radiofrequency signal of the satellite that the receiver front end of carrier antenna receives, the Doppler shift f that causes according to said carrier antenna rotation
d=vf/c calculates the angular frequency of Doppler shift
d(t),
The radiofrequency signal that is set to the receiver front end satellite that reaches the carrier antenna is S (t), and the computing formula of S (t) is following:
S(t)＝A(t)D(t-τ(t))C(t-τ(t))cos
[(ω+ω
d(t))(t-τ(t))+φ(t)]+n(t)
Wherein, the signal amplitude that A (t) receives for receiver front end,
D (t) is the navigation message of this satellite, and C (t) is a spreading code, and ω is a radio frequency angular velocity, ω
d(t) be frequency shift (FS), ω
d(t)=2 π f
d(t), τ (t) for satellite-signal from being transmitted into the time delay of reception, φ (t) is a carrier phase, the thermonoise that n (t) receives for receiver.
5. the generating apparatus of the radiofrequency signal of satellite under carrier rotation condition is characterized in that, comprising:
The Doppler shift computing module is used to calculate the rotational speed of carrier antenna, calculates the Doppler shift that the carrier rotation causes according to the rotational speed of said carrier antenna;
Gaining and power computation module, be used to set up the antenna coordinate system of carrier, is to calculate gain and the received signal power that the carrier rotation status is downloaded body antenna based on said antenna coordinate;
The radiofrequency signal generation module, the antenna gain and the received signal power of the carrier antenna that Doppler shift that is used for being calculated according to said Doppler shift computing module and said gain and power computation module are calculated generate the radiofrequency signal of satellite.
6. the generating apparatus of satellite RF signal under the carrier rotation condition according to claim 5 is characterized in that:
Described Doppler shift computing module, the plane that also is used to establish the carrier coordinate system place is x
uOz
uThe plane, l ' is the air line distance between the true origin of satellite to carrier coordinate system, l is that l ' is at x
uOz
uThe projection on plane, ψ is the angle between l ' and the l, β is l and z
uThe angle of axle, v
zBe the rotational speed of carrier antenna, v
z=ω
zR, ω
z=2 π f
zBe the rotation angle frequency of carrier antenna, r is the carrier radius, f
zBeing frequency, is the inverse of antenna rotation period;
If v is the speed component of rotational speed on l ' direction of carrier antenna, its computing method are:
v＝v
zsin(β-ω
zt)cosψ
Said t representes a certain moment, and v is the speed in this moment
By Doppler's computing formula f
dThe corresponding Doppler shift of each frequency that the rotation of=vf/c calculating carrier causes does
f
d＝v
zsin(β-ω
zt)cosψ·f
c/c
＝2πrf
zsin(β-2πf
zt)cosψ·f
c/c
Wherein, f
cBe the carrier frequency of certain frequency in the navigational system at carrier place, c is the light velocity.
7. the generating apparatus of satellite RF signal under the carrier rotation condition according to claim 5 is characterized in that:
Described gain and power computation module also are used to set up the antenna coordinate system of carrier, and this antenna coordinate system comprises: ε is that the line of satellite and true origin is at X
aOZ
aProjection in the plane and X
aThe angle of axle, span is 0～360 °, η is the line and the Y of satellite and true origin
aAngle between the axle, span is 0～180 °, establishes P
aBe the antenna gain of carrier, P
a=G (ε, η), G is the function of ε and η;
If P
rFor calculating the received signal power of carrier antenna, its computing formula is following:
P
r=P
s-P
w+ P
a, P wherein
sBe the transmit signal power of satellite, P
wFor spatial transmission postpones, P
aAntenna gain for the carrier antenna.
8. according to the generating apparatus of satellite RF signal under claim 5 or the 6 or 7 described carrier rotation conditions, it is characterized in that:
Described radiofrequency signal generation module also is used for the received signal power P according to said carrier antenna
rCalculate the signal amplitude A (t) of the radiofrequency signal of the satellite that the receiver front end of carrier antenna receives, the Doppler shift f that causes according to said carrier antenna rotation
d=vf/c calculates the angular frequency of Doppler shift
d(t),
The radiofrequency signal that is set to the receiver front end satellite that reaches the carrier antenna is S (t), and the computing formula of S (t) is following:
S(t)＝A(t)D(t-τ(t))C(t-τ(t))cos
[(ω+ω
d(t))(t-τ(t))+φ(t)]+n(t)
Wherein, the signal amplitude that A (t) receives for receiver front end,
D (t) is the navigation message of this satellite, and C (t) is a spreading code, and ω is a radio frequency angular velocity, ω
d(t) be frequency shift (FS), ω
d(t)=2 π f
d(t), τ (t) for satellite-signal from being transmitted into the time delay of reception, φ (t) is a carrier phase, the thermonoise that n (t) receives for receiver.
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| CN109725170A (en) * | 2018-12-25 | 2019-05-07 | 中国科学院西安光学精密机械研究所 | A kind of doppler shift effect simulator |
| CN109474353A (en) * | 2018-12-29 | 2019-03-15 | 中科院计算技术研究所南京移动通信与计算创新研究院 | A kind of arbitrary waveform generator and method based on modelling, storage medium |
| CN109474353B (en) * | 2018-12-29 | 2023-09-12 | 中科南京移动通信与计算创新研究院 | Random waveform generator based on model design, random waveform generation method based on model design and storage medium |
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