CN104298860A - Method for calculating deviation of GEO satellite forwarded signal codes and carrier phases - Google Patents

Abstract

The invention provides a method for calculating deviation of GEO satellite forwarded signal codes and carrier phases. The method includes the steps that firstly, a carrier large-loop code pseudo-range equation and a carrier phase pseudo-range equation are established, then, ionized layer parameters are calculated through observation results of double-frequency codes and the carrier phases, the offset of the code on the carrier C1 and the carrier phase and the offset of the code on the carrier C2 and the carrier phase are calculated respectively, and finally, the real-time control quantity of the codes on the carrier C1 and the carrier C2 and the carrier phases is acquired through filtering. According to the method, the GEO satellite forwarded signal codes and the carrier phases can be identical.

Description

The computing method of a kind of GEO satellite forward signal code and carrier phase deviation

Technical field

The present invention relates to a kind of control method, the phase place of GEO satellite repeater exit signal code and carrier wave can be made to be consistent.

Background technology

The eighties in 20th century, the U.S. builds up GPS, and USSR (Union of Soviet Socialist Republics) builds up GLONASS (Global Navigation satellite system, GLONASS).Both are placed with high performance satellite atomic clock on star,

Including in the fixer network of GEO satellite in regional positioning system (CAPS), U.S. WAAS system and Europe, is all the mode of operation adopting GEO satellite to forward signal.GEO satellite is the transparent forwarding function utilizing satellite to the mode of operation that signal forwards, and the navigation signal that ground produces is transmitted to user by satellite, a up-link that they are more than general GPS navigation signal.Because the impact of this up-link and satellite repeater causes being destroyed from the code of ground launch navigation signal and the consistance of carrier phase.In order to ensure based on the navigation of GEO satellite, time dissemination system can better service-user, and the correlationship of the code and carrier phase of specifying satellite transmitting antenna phase center is the key problem that these systems must solve.

Summary of the invention

In order to overcome the deficiencies in the prior art, the invention provides the computing method of a kind of GEO satellite signal ground master control station yard and carrier phase deviation, enabling user accurately know the correlationship of satellite exit code and carrier phase.

The technical solution adopted for the present invention to solve the technical problems comprises the following steps:

Step 1. sets up carrier wave large loop code pseudorange and carrier phase pseudorange equation,

Described code phase large ring observation equation P _loop=ρ+I _up+ I _dp+ ε _pi, carrier phase large ring observation equation λ _dΦ _loop=ρ+I _{u φ}+ S _φ+ I _{d φ}+ N λ _d+ ε _φ, wherein, P _loopand Φ _looprepresent that signal is up through radio frequency transmitting channel, space from ground launch base band, satellite forwards, space is descending, the code of radio frequency reception channel and synthetical baseband receiving terminal and carrier phase pseudorange, ρ=ρ _u+ ρ _d+ T _up+ T _dp+ E _u+ E _d+ S _p=ρ _u+ ρ _d+ T _{u φ}+ T _{d φ}+ E _u+ E _d+ S _φ, ρ _urepresent from ground launch antenna phase center to the geometric distance of GEO satellite earth antenna phase center, ρ _dthe geometric distance from GEO satellite transmitting antenna phase center to terrestrial receiving antenna phase center, T _up, to be respectively from ground launch antenna phase center to GEO satellite experience the additional delay that troposphere produces at code phase and carrier phase, T _dp, be respectively the delay experienced troposphere from GEO satellite transmitting antenna phase center to land station and produce at code phase and carrier phase, E _uand E _drepresent the processing delay of the up transmitter of ground master station and downlink reception equipment respectively, S _prepresent satellite repeater equipment delay, S _φrepresent the carrier phase change that satellite repeater causes, I _up, I _{u φ}to be respectively from ground launch antenna phase center to GEO satellite experience the additional delay that ionosphere produces at code phase and carrier phase, I _dp, I _{d φ}be respectively the delay experienced ionosphere from GEO satellite transmitting antenna phase center to land station and produce at code phase and carrier phase, ε _piand ε _{φ i}represent code noise and the carrier phase measurement cumulative noise of receiver, N is the integer ambiguity that in-hole run exists, λ _dfor the wavelength that downstream frequency is corresponding;

Step 2. adopts the observed result of dual-frequency code and carrier phase to resolve Ionospheric Parameters;

$P_{\mathrm{loop},c1}=\mathrm{\ρ}+\frac{I}{f_{c1,u}^2}+\frac{I}{f_{c1,d}^2}+{\mathrm{\ϵ}}_{\mathrm{Pi}}$

$P_{\mathrm{loop},c2}=\mathrm{\ρ}+\frac{I}{f_{c2,u}^2}+\frac{I}{f_{c2,d}^2}+{\mathrm{\ϵ}}_{\mathrm{Pi}}$

${\mathrm{\λ}}_{c1,d}{\mathrm{\Φ}}_{\mathrm{loop},c1}=\mathrm{\ρ}-\frac{I}{f_{c1,u}^2}+S_{\mathrm{\φ}}-\frac{I}{f_{c1,d}^2}+N_{c1}\·{\mathrm{\λ}}_{c1,d}+{\mathrm{\ϵ}}_{\mathrm{\φi}}$

${\mathrm{\λ}}_{c2,d}{\mathrm{\Φ}}_{\mathrm{loop},c2}=\mathrm{\ρ}-\frac{I}{f_{c2,u}^2}+S_{\mathrm{\φ}}-\frac{I}{f_{c2,d}^2}+N_{c2}\·{\mathrm{\λ}}_{c2,d}+{\mathrm{\ϵ}}_{\mathrm{\φi}}$

Wherein, the carrier frequency of described dual-frequency code is C1, C2, P _{loop, c1}and P _{loop, c2}represent the large ring code pseudo range observed quantity of C1 and C2 frequency signal respectively; Φ _{loop, c1}and Φ _{loop, c2}represent the carrier phase observed quantity of C1 and C2 frequency signal respectively; f _{c1, u}and f _{c1, d}, f _{c2, u}and f _{c2, d}represent the uplink and downlink carrier frequency of C1 and C2 frequency signal respectively; N _c1and N _c2represent the integer ambiguity of C1 and C2 frequency signal carrier phase observed quantity respectively; λ _{c1, d}and λ _{c2, d}represent C1 and C2 frequency downgoing signal carrier wavelength respectively;

Resolve Ionospheric Parameters $I=\frac{f_{c1,u}^2\·f_{c1,d}^2\·f_{c2,u}^2\·f_{c2,d}^2}{(f_{c1,u}^2+f_{c1,d}^2)\·f_{c2,u}^2\·f_{c2,d}^2-(f_{c2,u}^2+f_{c2,d}^2)\·f_{c1,u}^2\·f_{c1,d}^2}(P_{\mathrm{dc}1}-P_{\mathrm{dc}2})\text{;}$

Step 3. calculates the side-play amount of code on C1 carrier wave and carrier phase

${\mathrm{\Δ}}_{c1}=\frac{2I}{f_{c1,u}^2}-S_{\mathrm{\φ},c1}=P_{\mathrm{loop},c1}-{\mathrm{\λ}}_{c1,d}{\mathrm{\Φ}}_{\mathrm{loop},c1}-\frac{2I}{f_{c1,d}^2};$

Code on calculating C2 carrier wave and the side-play amount of carrier phase

${\mathrm{\Δ}}_{c2}=\frac{2I}{f_{c2,u}^2}-S_{\mathrm{\φ},c2}=P_{\mathrm{loop},c2}-{\mathrm{\λ}}_{c2,d}{\mathrm{\Φ}}_{\mathrm{loop},c2}-\frac{2I}{f_{c2,d}^2};$

Step 4. adopts wave filter to smoothing, the estimation respectively of the side-play amount of code and carrier phase on C1, C2 carrier wave, obtains the real-time controlled quentity controlled variable on C1 carrier wave $L_{c1}\left(k\right)=\frac{\mathrm{\τ}-T}{\mathrm{\τ}}{L}_{c1}(k-1)+\frac{1}{\mathrm{\τ}}[{\mathrm{\Δ}}_{c1}\left(k\right)-{\mathrm{\Δ}}_{c1}(k-1)]$ With the real-time controlled quentity controlled variable on C2 carrier wave $L_{c2}\left(k\right)=\frac{\mathrm{\τ}-T}{\mathrm{\τ}}{L}_{c2}(k-1)+\frac{1}{\mathrm{\τ}}[{\mathrm{\Δ}}_{c2}\left(k\right)-{\mathrm{\Δ}}_{c2}(k-1)];$ Wherein τ is filter constants, and T is sampling interval, Δ _c1(k), Δ _c2k current pre-adjustment amount that () is C1, C2 carrier wave before filtering, Δ _c1(k-1), L _c1(k-1) be respectively the forward and backward C1 carrier wave of previous moment filtering pre-adjustment amount, Δ _c2(k-1), L _c2(k-1) be respectively the forward and backward C2 carrier wave of previous moment filtering pre-adjustment amount.

The invention has the beneficial effects as follows: the deviation calculating satellite transmitting antenna phase center place's code and carrier phase based on the method, by the control of land station to code and carrier wave, the consistance of GEO satellite forward signal code and carrier phase can be realized, make this system signal be similar to satellite straight hair signal frequently and not interfere with each other, can be used as the enhancing signal of same-frequency satellite straight hair signal; And make this system forwards class signal be similar to gps signal, thus the existing achievement in research of gps system can be used for reference, improve the performance of this system further, shorten the search time that system adopts high precision technology.

Accompanying drawing explanation

Fig. 1 is GEO satellite forward signal navigational system schematic diagram.

Embodiment

Below in conjunction with drawings and Examples, the present invention is further described, the present invention includes but be not limited only to following embodiment.

The code of GEO satellite forward signal and a carrier phase consistance control method, step is as follows:

Step 1: set up code and the large ring observation equation of carrier phase, comprise

The large ring observation equation of code phase:

P _loop＝ρ _u+E _u+I _up+T _up+S _p+ρ _d+I _dp+T _dp+E _d+m _p+ε _p (1)

The large ring observation equation of carrier phase:

Φ _loop＝ρ _u+E _u+I _uφ+T _uφ+S _p+S _φ+ρ _d+I _dφ+T _dφ+E _d+m _φ+ε _φ (2)

Wherein P _loopand Φ _looprepresent that signal is up through radio frequency transmitting channel, space from ground launch base band, satellite forwards, space is descending, the code of radio frequency reception channel and synthetical baseband receiving terminal and carrier phase pseudorange, be called large ring measured value; ρ _urepresent from ground launch antenna phase center to the geometric distance of GEO satellite earth antenna phase center, ρ _dit is the geometric distance from GEO satellite transmitting antenna phase center to terrestrial receiving antenna phase center; I _up, I _{u φ}to be respectively from ground launch antenna phase center to GEO satellite experience the additional delay that ionosphere produces at code phase and carrier phase; T _up, to be respectively from ground launch antenna phase center to GEO satellite experience troposphere (in the additional delay that code phase and carrier phase produce; I _dp, I _{d φ}be respectively the delay experienced ionosphere from GEO satellite transmitting antenna phase center to land station and produce at code phase and carrier phase; T _dp, be respectively the delay experienced troposphere from GEO satellite transmitting antenna phase center to land station and produce at code phase and carrier phase; E _uand E _drepresent the processing delay of the up transmitter of ground master station and downlink reception equipment respectively; D _upand D _dprepresent respectively in signal uplink and downlink transmission process, the pseudo-code time delay that Doppler causes; D _{u φ}and D _{d φ}represent respectively in signal uplink and downlink transmission process, the carrier wave time delay that Doppler causes; m _p, m _φbe respectively the error that multipath produces code phase and carrier phase impact; ε _pand ε _φrepresent code noise and the carrier phase measurement cumulative noise of receiver, N _dfor the integer ambiguity that in-hole run exists, λ _dfor the wavelength that downstream frequency is corresponding.S _prepresent satellite repeater equipment delay, S _φrepresent the carrier phase change that satellite repeater causes.

Step 2: according to the different affecting factors of parameter in step 1, observation equation is simplified.

The consistance of the present invention's main research satellite exit code and carrier phase, can ensure in both transmitter exits by transmitting baseband Time synchronization technique consistent, on the transmit path, the phase relation of code and the carrier wave principal element that changes can be made to be ionosphere and transponder, other can make whole signal be delayed, but the phase relation of the two can not be made to change as transmitting and receiving apparatus, transmission geometric path, troposphere, transponder device time delay etc.Therefore, in formula (1) and (2), the error caused by multipath is included into receiver measurement noises, is designated as ε respectively to the noise of pseudo-code and carrier phase _piand ε _{φ i}; By above-mentioned irrelevant with frequency, the factor not affecting pseudo-code and carrier phase relationship is all attributed in geometric distance, is set to ρ, then:

ρ＝ρ _u+ρ _p+T _up+T _dp+E _u+E _d+S _p＝ρ _u+ρ _d+T _uφ+T _dφ+E _u+E _d+S _p (3)

Then formula (1) and (2) can be written as:

P _loop＝ρ+I _up+I _dp+ε _Pi (4)

λ _dΦ _loop＝ρ+I _uφ+S _φ+I _dφ+Nλ _d+ε _φi (5)

Step 3: adopt the observed result of double frequency (setting carrier frequency as C1, C2) code and carrier phase to resolve Ionospheric Parameters.

Because ionosphere makes carrier phase observed quantity in advance, make yard pseudo range observed quantity delayed, and value is equal.Therefore, the first-order lag of ionosphere to carrier phase and code pseudo range observed quantity is and direction is contrary.Wherein I=40.3TEC, TEC are the total electron number of observed ray, and f represents signal frequency.Because the influence amount such as second order, three rank are small, all can disregard.Therefore, formula (5) (6) observed quantity in C1, C2 two frequencies can be written as respectively:

$P_{\mathrm{loop},c1}=\mathrm{\ρ}+\frac{I}{f_{c1,u}^2}+\frac{I}{f_{c1,d}^2}+{\mathrm{\ϵ}}_{\mathrm{Pi}}---\left(6\right)$

$P_{\mathrm{loop},c2}=\mathrm{\ρ}+\frac{I}{f_{c2,u}^2}+\frac{I}{f_{c2,d}^2}+{\mathrm{\ϵ}}_{\mathrm{Pi}}---\left(7\right)$

${\mathrm{\λ}}_{c1,d}{\mathrm{\Φ}}_{\mathrm{loop},c1}=\mathrm{\ρ}-\frac{I}{f_{c1,u}^2}+S_{\mathrm{\φ}}-\frac{I}{f_{c1,d}^2}+N_{c1}\·{\mathrm{\λ}}_{c1,d}+{\mathrm{\ϵ}}_{\mathrm{\φi}}---\left(8\right)$

${\mathrm{\λ}}_{c2,d}{\mathrm{\Φ}}_{\mathrm{loop},c2}=\mathrm{\ρ}-\frac{I}{f_{c2,u}^2}+S_{\mathrm{\φ}}-\frac{I}{f_{c2,d}^2}+N_{c2}\·{\mathrm{\λ}}_{c2,d}+{\mathrm{\ϵ}}_{\mathrm{\φi}}---\left(9\right)$

In formula, P _{loop, cl}and P _{loop, c2}represent the large ring code pseudo range observed quantity of C1 and C2 frequency signal respectively; Φ _{loop, c1}and Φ _{loop, c2}represent the carrier phase observed quantity of C1 and C2 frequency signal respectively; f _{cl, u}and f _{c1, d}, f _{c2, u}and f _{c2, d}represent the uplink and downlink carrier frequency of C1 and C2 frequency signal respectively; N _c1and N _c2represent the integer ambiguity of C1 and C2 frequency signal carrier phase observed quantity respectively; λ _{c1, d}and λ _{c2, d}represent C1 and C2 frequency downgoing signal carrier wavelength respectively.

Obtain according to formula (6), (7):

$I=\frac{f_{c1,u}^2\·f_{c1,d}^2\·f_{c2,u}^2\·f_{c2,d}^2}{(f_{c1,u}^2+f_{c1,d}^2)\·f_{c2,u}^2\·f_{c2,d}^2-(f_{c2,u}^2+f_{c2,d}^2)\·f_{c1,u}^2\·f_{c1,d}^2}(P_{\mathrm{dc}1}-P_{\mathrm{dc}2})---\left(10\right)$

Its result cancellation impact in troposphere and multipath, precision is only with pseudo-code accuracy of observation relevant with observation noise.There is not P code privacy problem in CAPS land station, P code can be utilized to obtain higher accuracy of observation, the method for smoothing the phase of carrier wave also can be adopted simultaneously to improve its precision further.

Step 4: the departure calculating code and carrier phase.

Computation process and the C2 frequency of C1 frequency code and carrier phase departure are similar, are described here for C1 frequency.

Adopt formula (6)-(8), the deviation of C1 frequency code and carrier phase can be obtained:

$P_{\mathrm{loop},c1}-{\mathrm{\λ}}_{c1,d}{\mathrm{\Φ}}_{\mathrm{loop},c1}=\frac{2I}{f_{c1,u}^2}+\frac{2I}{f_{c1,d}^2}-S_{\mathrm{\φ}}-N_{c1}\·{\mathrm{\λ}}_{c1,d}+{\mathrm{\ϵ}}_{\mathrm{Pi}}-{\mathrm{\ϵ}}_{\mathrm{\φi}}---\left(11\right)$

The object of this method is to ensure the consistent of satellite outlet code and carrier phase, therefore, need up-link, the code that namely before satellite transmitting antenna phase center, link causes and carrier phase depart from, the i.e. bias that causes of up ionosphere and satellite repeater, is calculated as:

$\frac{2I}{f_{c1,u}^2}-S_{\mathrm{\φ}}=P_{\mathrm{loop},c1}-{\mathrm{\λ}}_{c1,d}{\mathrm{\Φ}}_{\mathrm{loop},c1}-\frac{2I}{f_{c1,d}^2}+N_{c1}\·{\mathrm{\λ}}_{c1,d}-({\mathrm{\ϵ}}_{\mathrm{Pi}}-{\mathrm{\ϵ}}_{\mathrm{\φi}})---\left(12\right)$

In satellite repeater system, the time-frequency of ground master station transmitting and receiving apparatus is with reference to homology, by to transmit and the code of Received signal strength and carrier phase variable quantity accurately obtain the code and carrier phase deviation that large ring closed-loop causes, namely there is not integer ambiguity problem in the code of large ring closed-loop and carrier phase deviation.Ignore the difference of observation noise, the bias of the code that up-link causes and carrier phase can be expressed as:

$\mathrm{\Δ}=\frac{2I}{f_{c1,u}^2}-S_{\mathrm{\φ}}=P_{\mathrm{loop},c1}-{\mathrm{\λ}}_{c1,d}{\mathrm{\Φ}}_{\mathrm{loop},c1}-\frac{2I}{f_{c1,d}^2}---\left(13\right)$

Step 5: adopt wave filter to smoothing, the estimation respectively of the side-play amount of code and carrier phase on C1, C2 carrier wave, obtain the pre-in real time deviator on each carrier wave, thus keep the code on two carrier waves and carrier phase to be consistent in GEO satellite exit.

The result of (13) is input with the formula, carrier wave NCO and code NCO is launched to land station and carries out pre-adjustment, satellite outlet code and carrier phase can be made to be consistent, in order to improve the transient response of circuit to input adjustment amount, we adopt the pre-adjustment amount of second order LTI (Linear Time Invariant) wave filter to input smoothing, to reduce the response time of circuit, and eliminate the impact of high frequency interference.Thus obtain code and carrier phase offset adjustment amount (being called for short " pre-adjustment amount ") estimator and export (Laplace conversion) and be:

$L\left(s\right)=\frac{s}{({\mathrm{\τ}}_{1}s+1)({\mathrm{\τ}}_{2}s+1)}\mathrm{\Δ}\left(s\right)---\left(19\right)$

With the difference between pre-adjustment amount state for input, carrying out pre-estimation to NextState can obtain:

$L\left(k\right)=\frac{{\mathrm{\τ}}_1-T}{{\mathrm{\τ}}_1}L(k-1)+\frac{1}{{\mathrm{\τ}}_1}[\mathrm{\Δ}\left(k\right)-\mathrm{\Δ}(k-1)]---\left(20\right)$

Wherein τ ₁, τ ₂for filter constants, T is sampling interval, and Δ (k), L (k) are respectively the current pre-adjustment amount before and after filtering, and Δ (k-1), L (k-1) are respectively the forward and backward pre-adjustment amount of previous moment filtering.

In specific implementation process, adopt double frequency (setting carrier frequency as C1, C2) with the regional navigational system CAPS built up national time service center (NTSC) (Chinese area positioning system) for experiment porch.As shown in Figure 1, the system composition of the present embodiment comprise that upward signal is launched, GEO satellite forwards, the reception of satellite forward signal and measurement, code and carrier phase deviation pre-estimation algorithm four part.

The reception of satellite forward signal and measure portion mainly complete the reception of satellite converting downlink signal, and the code of docking receipts downgoing signal and large ring signal and carrier phase pseudorange are measured, and obtain code and carrier phase Pseudo-range Observations.

The code that code and carrier phase deviation pre-estimation algorithm obtain with the reception of satellite forward signal and measure portion and carrier phase Pseudo-range Observations are for inputting, calculate the pre-deviator of code and carrier phase, and adopt wave filter to smoothing, the estimation respectively of the side-play amount of code and carrier phase on C1, C2 carrier wave, obtain the pre-in real time deviator on each carrier wave.

The pre-in real time deviator that the control section of code and carrier wave NCO obtains with code and carrier phase deviation pre-estimation algorithm, for input, realizes the control to code and carrier wave NCO, and that passes through that this control ensures in satellite exit code and carrier phase is consistent.

Signal is transmitted to satellite through antenna by the up-conversion of upward signal radiating portion settling signal, through satellite repeater, signal is transmitted to downlink reception equipment, forms the closed loop of signal.

Implement this method for this system, concrete implementation step is as follows:

Step 1: set up C1, C2 carrier wave large ring loop code pseudorange and carrier phase observation equation:

$P_{\mathrm{loop},c1}=\mathrm{\ρ}+\frac{I}{f_{c1,u}^2}+\frac{I}{f_{c1,d}^2}{\mathrm{\ϵ}}_{\mathrm{Pi}}---\left(21\right)$

$P_{\mathrm{loop},c2}=\mathrm{\ρ}+\frac{I}{f_{c2,u}^2}+\frac{I}{f_{c2,d}^2}+{\mathrm{\ϵ}}_{\mathrm{Pi}}---\left(22\right)$

${\mathrm{\λ}}_{\mathrm{cl},d}{\mathrm{\Φ}}_{\mathrm{loop},c1}=\mathrm{\ρ}-\frac{I}{f_{c1,u}^2}+S_{\mathrm{\φ},c1}-\frac{I}{f_{c1,d}^2}+N_{c1}\·{\mathrm{\λ}}_{c1,d}+{\mathrm{\ϵ}}_{\mathrm{\φi}}---\left(23\right)$

${\mathrm{\λ}}_{c2,d}{\mathrm{\Φ}}_{\mathrm{loop},c2}=\mathrm{\ρ}-\frac{I}{f_{c2,u}^2}+S_{\mathrm{\φ},c2}-\frac{I}{f_{c2,d}^2}+N_{c2}\·{\mathrm{\λ}}_{c2,d}+{\mathrm{\ϵ}}_{\mathrm{\φi}}---\left(24\right)$

Step 2: resolve Ionospheric Parameters.

$I=\frac{f_{c1,u}^2\·f_{c1,d}^2\·f_{c2,u}^2\·f_{c2,d}^2}{(f_{c1,u}^2+f_{c1,d}^2)\·f_{c2,u}^2\·f_{c2,d}^2-(f_{c2,u}^2+f_{c2,d}^2)\·f_{c1,u}^2\·f_{c1,d}^2}(P_{\mathrm{dc}1}-P_{\mathrm{dc}2})---\left(25\right)$

Step 3: the code on calculating C1, C2 carrier wave and the side-play amount of carrier phase.

${\mathrm{\Δ}}_{c1}=\frac{2I}{f_{c1,u}^2}-S_{\mathrm{\φ},c1}=P_{\mathrm{loop},c1}-{\mathrm{\λ}}_{c1,d}{\mathrm{\Φ}}_{\mathrm{loop},c1}-\frac{2I}{f_{c1,d}^2}---\left(26\right)$

${\mathrm{\Δ}}_{c2}=\frac{2I}{f_{c2,u}^2}-S_{\mathrm{\φ},c2}=P_{\mathrm{loop},c2}-{\mathrm{\λ}}_{c2,d}{\mathrm{\Φ}}_{\mathrm{loop},c2}-\frac{2I}{f_{c2,d}^2}---\left(27\right)$

Step 4: the real-time controlled quentity controlled variable obtaining code on C1, C2 carrier wave and carrier phase after filtering.

$L_{c1}\left(k\right)=\frac{\mathrm{\τ}-T}{\mathrm{\τ}}{L}_{c1}(k-1)+\frac{1}{\mathrm{\τ}}[{\mathrm{\Δ}}_{c1}\left(k\right)-{\mathrm{\Δ}}_{c1}(k-1)]---\left(28\right)$

$L_{c2}\left(k\right)=\frac{\mathrm{\τ}-T}{\mathrm{\τ}}{L}_{c2}(k-1)+\frac{1}{\mathrm{\τ}}[{\mathrm{\Δ}}_{c2}\left(k\right)-{\mathrm{\Δ}}_{c2}(k-1)]---\left(29\right)$

Control code or carrier phase with this controlled quentity controlled variable, making to transmit produces deviation at the code of transmitter outlet and carrier phase, and after up-link and satellite repeater, what ensure in satellite repeater exit code and carrier phase is consistent.

Claims (1)

1. computing method for GEO satellite forward signal code and carrier phase deviation, is characterized in that comprising the steps:

Step 1. sets up carrier wave large loop code pseudorange and carrier phase pseudorange equation,

Described code phase large ring observation equation P _loop=ρ+I _up+ I _dp+ ε _pi, carrier phase large ring observation equation λ _dΦ _loop=ρ+I _{u φ}+ S _φ+ I _{d φ}+ N λ _d+ ε _φ, wherein, P _loopand Φ _looprepresent that signal is up through radio frequency transmitting channel, space from ground launch base band, satellite forwards, space is descending, the code of radio frequency reception channel and synthetical baseband receiving terminal and carrier phase pseudorange, ρ=ρ _u+ ρ _d+ T _up+ T _dp+ E _u+ E _d+ S _p=ρ _u+ ρ _d+ T _{u φ}+ T _{d φ}+ E _u+ E _d+ S _φ, ρ _urepresent from ground launch antenna phase center to the geometric distance of GEO satellite earth antenna phase center, ρ _dthe geometric distance from GEO satellite transmitting antenna phase center to terrestrial receiving antenna phase center, T _up, to be respectively from ground launch antenna phase center to GEO satellite experience the additional delay that troposphere produces at code phase and carrier phase, T _dp, be respectively the delay experienced troposphere from GEO satellite transmitting antenna phase center to land station and produce at code phase and carrier phase, E _uand E _drepresent the processing delay of the up transmitter of ground master station and downlink reception equipment respectively, S _prepresent satellite repeater equipment delay, S _φrepresent the carrier phase change that satellite repeater causes, I _up, I _{u φ}to be respectively from ground launch antenna phase center to GEO satellite experience the additional delay that ionosphere produces at code phase and carrier phase, I _dp, I _{d φ}be respectively the delay experienced ionosphere from GEO satellite transmitting antenna phase center to land station and produce at code phase and carrier phase, ε _piand ε _{φ i}represent code noise and the carrier phase measurement cumulative noise of receiver, N is the integer ambiguity that in-hole run exists, λ _dfor the wavelength that downstream frequency is corresponding;

Step 2. adopts the observed result of dual-frequency code and carrier phase to resolve Ionospheric Parameters;

$P_{\mathrm{loop},c1}=\mathrm{\ρ}+\frac{I}{f_{c1,u}^2}+\frac{I}{f_{c1,d}^2}+{\mathrm{\ϵ}}_{\mathrm{Pi}}$

$P_{\mathrm{loop},c2}=\mathrm{\ρ}+\frac{I}{f_{c2,u}^2}+\frac{I}{f_{c2,d}^2}+{\mathrm{\ϵ}}_{\mathrm{Pi}}$

${\mathrm{\λ}}_{c1,d}{\mathrm{\Φ}}_{\mathrm{loop},c1}=\mathrm{\ρ}-\frac{I}{f_{c1,u}^2}+S_{\mathrm{\φ}}-\frac{I}{f_{c1,d}^2}+N_{c1}\·{\mathrm{\λ}}_{c1,d}+{\mathrm{\ϵ}}_{\mathrm{\φi}}$

${\mathrm{\λ}}_{c2,d}{\mathrm{\Φ}}_{\mathrm{loop},c2}=\mathrm{\ρ}-\frac{I}{f_{c2,u}^2}+S_{\mathrm{\φ}}-\frac{I}{f_{c2,d}^2}+N_{c2}\·{\mathrm{\λ}}_{c2,d}+{\mathrm{\ϵ}}_{\mathrm{\φi}}$

Wherein, the carrier frequency of described dual-frequency code is C1, C2, P _{loop, c1}and P _{loop, c2}represent the large ring code pseudo range observed quantity of C1 and C2 frequency signal respectively; Φ _{loop, c1}and Φ _{loop, c2}represent the carrier phase observed quantity of C1 and C2 frequency signal respectively; f _{c1, u}and f _{c1, d}, f _{c2, u}and f _{c2, d}represent the uplink and downlink carrier frequency of C1 and C2 frequency signal respectively; N _c1and N _c2represent the integer ambiguity of C1 and C2 frequency signal carrier phase observed quantity respectively; λ _{c1, d}and λ _{c2, d}represent C1 and C2 frequency downgoing signal carrier wavelength respectively;

Resolve Ionospheric Parameters $I=\frac{f_{c1,u}^2\·f_{c1,d}^2\·f_{c2,u}^2\·f_{c2,d}^2}{(f_{c1,u}^2+f_{c1,d}^2)\·f_{c2,u}^2\·f_{c2,d}^2-(f_{c2,u}^2+f_{c2,d}^2)\·f_{c1,u}^2\·f_{c1,d}^2}(P_{\mathrm{dc}1}-P_{\mathrm{dc}2});$

Step 3. calculates the side-play amount of code on C1 carrier wave and carrier phase

${\mathrm{\Δ}}_{c1}=\frac{2I}{f_{c1,u}^2}-S_{\mathrm{\φ},c1}=P_{\mathrm{loop},c1}-{\mathrm{\λ}}_{c1,d}{\mathrm{\Φ}}_{\mathrm{loop},c1}-\frac{2I}{f_{c1,d}^2};$

Code on calculating C2 carrier wave and the side-play amount of carrier phase

${\mathrm{\Δ}}_{c2}=\frac{2I}{f_{c2,u}^2}-S_{\mathrm{\φ},c2}=P_{\mathrm{loop},c2}-{\mathrm{\λ}}_{c2,d}{\mathrm{\Φ}}_{\mathrm{loop},c2}-\frac{2I}{f_{c2,d}^2};$

Step 4. adopts wave filter to smoothing, the estimation respectively of the side-play amount of code and carrier phase on C1, C2 carrier wave, obtains the real-time controlled quentity controlled variable on C1 carrier wave $L_{c1}\left(k\right)=\frac{\mathrm{\τ}-T}{\mathrm{\τ}}{L}_{c1}(k-1)+\frac{1}{\mathrm{\τ}}[{\mathrm{\Δ}}_{c1}\left(k\right)-{\mathrm{\Δ}}_{c1}(k-1)]$ With the real-time controlled quentity controlled variable on C2 carrier wave $L_{c2}\left(k\right)=\frac{\mathrm{\τ}-T}{\mathrm{\τ}}{L}_{c2}(k-1)+\frac{1}{\mathrm{\τ}}[{\mathrm{\Δ}}_{c2}\left(k\right)-{\mathrm{\Δ}}_{c2}(k-1)];$ Wherein τ is filter constants, and T is sampling interval, Δ _c1(k), Δ _c2k current pre-adjustment amount that () is C1, C2 carrier wave before filtering, Δ _c1(k-1), L _c1(k-1) be respectively the forward and backward C1 carrier wave of previous moment filtering pre-adjustment amount, Δ _c2(k-1), L _c2(k-1) be respectively the forward and backward C2 carrier wave of previous moment filtering pre-adjustment amount.