CN1633087A - A method of constellation parameter measurement for low-orbit pole-constellation satellite communication system - Google Patents

Abstract

This invention relates to a constellation parameter measurement method for a low orbit, polar constellation satellite communication system, which carries out single way delay measurement with the satellite system as the relay between two ground stations of a same geographical position on the earth to realize measurement and computation to constellation key parameters including: 1, measuring the single-way delay and computing its time sequence DS, 2, segmenting the sequence DS based on different accessed satellites, 3, segmenting the sequence based on the accessed satellite orbit, 4, computing height and the maximum geo-center angle of the satellite,, 5, computing the minimum elevation of the ground station and included angle between satellites on a same orbit, 6, computing the included angle between adjacent orbits planes, 7, computing the satellite number or orbits in an orbit plane.

Description

A kind of low orbit utmost point constellation satellite communication system constellation parameter method of measurement

Technical field

The present invention relates to the measurement and the monitoring technique field of satellite network system, particularly a kind of low orbit (Low Earth Orbit), utmost point constellation satellite communication system constellation parameter method of measurement.

Background technology

Satellite communication not only has special status as one of main mode of modern communications on military and space science and technology, and since its coverage big, dispose maneuverability and be easy to control and be used to civilian data communication aspect more and more with management advantage.Performance measurement and monitoring to satellite network are that the network behavior characteristic is understood, in time found in depth the phase-split network performance bottleneck, optimizes the important means that Internet resources dispose, strengthen network management.As the important component part of Next Generation Internet (NextGeneration Internet NGI), also be to improve one of important assurance of whole network system operational efficiency to effective measurement of satellite network system and monitoring.

Measurement to constellation parameter is the basis that satellite network system is furtherd investigate.This measurement demand comes from the characteristics that the owner of satellite network system separates with Internet Service Provider (InternetService Provider ISP) on the one hand, and ISP is difficult in time obtain whole satellite network configuration information in service; On the other hand, ISP need pass through promptly and accurately awareness network constellation and topology information, carrying out optimizing configuration on network resource, to promote the overall performance of network, and provide the service of satisfying service level standard (Service Level Agreement SLA) to the user.Simultaneously,, also can in time understand the running status of satellite system, predict its variation tendency, to avoid potential satellite drift or inefficacy by long-term measurement to satellite constellation.

Summary of the invention

The object of the present invention is to provide a kind of low orbit utmost point constellation satellite communication system constellation parameter method of measurement.

The present invention is carrying out measured satellite constellation on the basis of reasonable assumption, is positioned on earth between two ground stations in same place (not comprising high latitude area) or the virtual ground station to utilize satellite relay to carry out the delayed sequence that one-way delay measurements obtains implicit satellite constellation feature.In measuring process, ground station and its access star locationally draw near, more from the close-by examples to those far off variation and ground station and its access star place orbit plane locationally draw near, from the close-by examples to those far off variation all is embodied in the measured one-way latency sequence again.Utilization can realize the accurate measurement to low orbit, the main constellation configuration parameter of utmost point constellation satellite communication system to the delay analysis when the specific relative position of the regularity in the delayed sequence and ground station and access star.The constellation parameter that can survey comprises: phase deviation (angle) etc. between adjacent satellite in number of satellite, satellite maximum communication scope, the interplanar phase difference of adjacent orbit (angle) and the same track in the track number in satellite altitude, the satellite system, every track.

The present invention has designed and has utilized low rail, utmost point constellation satellite communication system to carry out delay measurements for relaying, and then measure the method for communication relay satellite system constellation parameter between a kind of ground station.The ground station that participates in delay measurements can be the physics ground station that is positioned at same geographical position (being same longitude and latitude), also can be the virtual ground station that the different launching beams that dispose in same ground station constitute.Between ground station, initiatively, send unidirectional probe messages periodically, calculate the one-way latency of probe messages.All insert constantly owing to be positioned at the ground station in same geographical position, thereby implied in the measured one-way latency sequence with the ground station of earth rotation and the inherent law on the satellite system relative position in service by same low orbit satellite.This regularity mainly embodies a concentrated reflection of two aspects, that is: ground station and its access star locationally draw near, more from the close-by examples to those far off change procedure and ground station and its access star place orbit plane locationally draw near, from the close-by examples to those far off change procedure again.The present invention utilizes the one-way latency analysis when the specific relative position of the regularity in the delayed sequence and ground station and access star, and realization is to the accurate measurement of low orbit, the main constellation parameter of utmost point constellation satellite communication system.The constellation parameter that can survey comprises: phase deviation (angle) etc. between adjacent satellite in number of satellite, satellite maximum communication scope, the interplanar phase difference of adjacent orbit (angle) and the same track in the track number in satellite altitude, the satellite system, every track.

The present invention hangs down the constellation parameter of rail, utmost point constellation systems and measures based on following rational hypothesis:

(1) tested constellation is that the whole world covers continuously;

(2) the main configuration parameter of every satellite in the constellation is all identical as satellite altitude, satellite maximum communication scope;

(3) the interplanar phase difference of adjacent orbit equates (removing at seam crossing), and phase deviation also equates between the interior star of same track;

(4) the orbit plane inclination angle is 90 ° or near 90 °.

Current low rail, the utmost point constellation systems research back of having disposed and be about to dispose found most constellations all satisfy or approachingly satisfy above-mentioned assumed condition, as famous IRIDIUM and Teledesic system etc.

Fig. 1 has shown the result's (for the purpose of clear, only having shown the part measured value among this figure) who IRIDIUM is carried out 24 hours delay measurements in Beijing.From Fig. 1, can clearly reflect ground station and access star and ground station and the interplanar relative position variation relation of access star place satellite orbit in measuring process.Short " trough " of duration is because ground station and the air line distance of its access star in communication process draw near, and from the close-by examples to those far off cycle variation institute causes again; And long-term " trough " is because ground station and the distance of its access star place orbit plane in communication process draw near, and from the close-by examples to those far off cycle variation institute causes again.For ease of elaboration hereinafter, to time of delay sequence do as giving a definition:

The definition 1: transmitting terminal ground station with period tau to length delay measurements message p (i) such as target floor station transmissions, i=1 ..., N, and the transmitting time s (i) of message is sent to the target floor station as the payload of probe messages.Target floor stands in after constantly r (i) receives probe messages p (i), calculates its one-way latency d (i), simultaneously s (i) is parsed from message, then defines DS={ (s (1), d (1)), (s (2), d (2)),, (s (N), d (N)) } and be the one-way latency sequence of probe messages.

Low orbit, utmost point constellation satellite communication system constellation parameter method of measurement, it is characterized in that, by being that relaying carries out one-way delay measurements with the satellite system between two ground stations in same geographical position on earth, can realize measurement and calculating to the constellation key parameter.

Groundwork step of the present invention is as follows:

(1) define as described in 1 as specification, source ground station is to length delay measurements messages such as target floor station cycle transmissions, and target floor stands in to receive and calculates one-way latency time series DS after the probe messages:

DS＝{(s(1)，d(1))，(s(2)，d(2))，…，(s(N)，d(N))}，d(i)＝r(i)-s(i)(1)

Wherein: s (i) and r (i) are respectively i, the transmission and the time of reception of 1≤i≤N probe data packet p (i).

(2) after calculating DS, the target floor station is divided into K segmentation by accompanying drawing 3 methods with DS, makes the k of DS be segmented into sub-time of delay of sequence D S _kAnd be expressed as:

DS _k={ (s (k _s), d (k _s)), (s (k _s+ 1), d (k _s+ 1)) ..., (s (k _e), d (k _e)), 1≤k≤K (2) in formula (2), k _s, k _eBe respectively the subscript of initial and end position in DS of k sub-time of delay of sequence; And make k _oBe DS _kIn have measurement point pairing subscript in DS of minimum delay value.

Sub-delayed sequence DS _kBe expressed as at time period (s (k _s), s (k _e)) in, measured one-way latency when two ground stand in certain same inserting of satellite.Adjacent sub-delayed sequence DS _kAnd DS _K+1Be the measured one-way latencys during of two ground stations with different inserting of satellite.For the purpose of simple and easy, with j the element of DS (j) expression DS.

Description of drawings

Further specify the present invention below in conjunction with the Figure of description table.

Fig. 1 is presented at 24 hours delay measurements are carried out in Beijing to IRIDIUM figure as a result;

Fig. 2 measures main flow chart for constellation parameter;

Fig. 3 is for to carry out the segmentation flow chart to the one-way latency time series;

Fig. 4 is for to carry out the segmentation flow chart to minimum one-way latency time series;

Fig. 5 is for calculating the satellite altitude flow chart;

Fig. 6 is for calculating satellite maximum coverage range (maximum geocentric angle) flow chart;

Fig. 7 is for calculating adjacent satellite angle flow chart in the rail;

Fig. 8 is for calculating angle flow chart between the adjacent satellite orbit plane;

Fig. 9 is for calculating satellite number and constellation track number flow chart in every orbit plane.

Embodiment

Fig. 1 is that (east longitude 116.45 degree, north latitude 39.92 degree) carry out measuring in 24 hours (part) one-way latency sequence and the segmentation signal that is obtained to IRIDIUM in the BeiJing, China in the present invention.The size of probe data packet is 40 bytes in current the measurement, and it is 5 seconds that detection packet sends period tau, and the Uplink/Downlink bandwidth that ground station inserts satellite is 2Mbit/s.

Fig. 2 has briefly concluded the several main flow process in the constellation parameter measurement: its step is as follows:

S1 measures one-way latency and calculates one-way latency time series DS, and in the specification summary of the invention, promptly source ground station is to length delay measurements messages such as target floor station cycle transmissions.Carried the transmitting time of this measured message in the measured message, destination end ground station can calculate the one-way latency time series DS of measured message according to the due in of message thus;

S2, sequence D S comes segmentation according to the difference that inserts satellite to time of delay, in the specification summary of the invention, promptly according to cycle " trough " characteristic (being the concavity feature) that time of delay, sequence was presented, it is divided into K segmentation, and " trough " of an appearance represented in each segmentation.Because each " trough " reflected the variation relation on the relative position between two ground stations and the same access star, by the change procedure that can reflect that to the time series segmentation ground station and different access stars insert;

S3, to time of delay sequence come segmentation according to inserting satellite orbit, in the specification summary of the invention, with after time of delay, sequence D S was divided into K segmentation, can calculate minimum delay time sequence MDS through S2.Because periodicity " trough " characteristic (being the concavity feature) that minimum delay time sequence MDS is presented has reflected the variation relation on the relative position between two ground stations and the same orbit plane, it is carried out the variation relation that the M segmentation can reflect that ground station and different orbit planes insert;

S4 calculates the maximum geocentric angle θ of satellite altitude h and satellite, in the specification summary of the invention;

When calculating satellite altitude h, consider in two kinds of situation:

Situation one: in M the segmentation of MDS, if there is set j={i|d ((i _o) _o)=d ((i _o+ 1) _o), 1≤i≤M then makes m={i|min{d ((i _o) _o), i ∈ j}, mdelay=min{d ((i _o) _o), i ∈ j, and be calculated as follows satellite altitude h, otherwise calculate satellite altitude by situation two;

rad＝sin(90°-Φ)×EARTH；

ab＝2×rad×sin(0.00417×(s((index _o+1) _o)-s((index _o) _o)))；

$\mathrm{theta}=2\×\arcsin \left(\frac{\mathrm{ab}}{2\×\mathrm{EARTH}}\right);$

$d\_\max =0.5\×\mathrm{LIGHT}\×\frac{\mathrm{mdelay}-2\×\mathrm{PACKETSIZE}\×8}{\mathrm{BANDWIDTH}};$

$h=\mathrm{EARTH}\×(\cos \left(\mathrm{theta}\right)-1)+\sqrt{d\_{\max }^2-\mathrm{EART}{H}^2\×{\sin }^2\left(\mathrm{theta}\right)};$

Situation two: make mdelay=min{d ((m _o) _o), 1≤m≤M is calculated as follows satellite altitude h:

$h=0.5\×\mathrm{LIGHT}\×\frac{\mathrm{mdelay}-2\×\mathrm{PACKETSIZE}\×8}{\mathrm{BANDWIDTH}};$

When calculating satellite maximum geocentric angle θ, make mdelay=min{d (k _e), 1≤k≤K is calculated as follows the maximum geocentric angle θ that satellite covers:

$d\_\max =0.5\×\mathrm{LIGHT}\×\frac{\mathrm{mdelay}-2\×\mathrm{PACKETSIZE}\×8}{\mathrm{BANDWIDTH}};$

$\mathrm{\θ}=\arccos \left[\frac{\mathrm{EART}{H}^2+{(\mathrm{EARTH}+h)}^2-d\_{\max }^2}{2\×\mathrm{EARTH}\×(\mathrm{EARTH}+h)}\right]$

S5 calculates the minimum angle of elevation E of ground station and with angle ψ between star in the track, corresponding to specification

In the summary of the invention;

The minimum angle of elevation E of ground station can directly be calculated as follows according to the maximum geocentric angle θ among the S4:

$E=\arctan [\tan \left(\mathrm{\θ}\right)-\frac{\mathrm{EARTH}}{\sin \left(\mathrm{\θ}\right)\×(\mathrm{EARTH}+h)}]$

In calculating track, between star during angle ψ, consider in two kinds of situation:

Situation one: in M the segmentation of MDS, if there is segmentation set j={m|d ((m _o) _o)=d ((m _o+ 1) _o), 1＜i＜M then makes index={i|min{d ((i _o) _o), i ∈ j}, otherwise calculate index by situation two;

Situation two: index={m|min{d ((m _o+ 1) _o), 1＜m＜K};

Angle ψ is calculated as follows between the interior star of track:

Wherein s (i) is an i detection data message delivery time, and T is the orbital period of satellite.

S6 calculates adjacent orbit interplanar angle γ, corresponding to S8 in the specification summary of the invention.Adjacent orbit interplanar angle calculates by the principle of maximum probability of happening;

S7 calculates the interior satellite of orbit plane and counts n and constellation track number P, in the specification summary of the invention.The interior satellite of orbit plane is counted n and is calculated by maximum generate probability, and constellation track number P calculates by following formula after calculating adjacent orbit interplanar angle γ:

In Fig. 3, the detailed implementation of each step is as follows:

S3.1 parameter and initialization comprise following two concrete operations:

k＝1，k _s＝1；

push(DS(1))；push(DS(2))；

The S3.2 method finishes to judge;

S3.3 reads in new one-way delay measurements sample;

S3.4 judges whether the one-way delay measurements sample newly read in is being positioned on the two dimensional surface above the straight line that storehouse top two elements are linked to be, and concrete operations are:

if(isabove(DS(index))＝TRUE)

S3.5 will read in new one-way delay measurements sample and be pressed into storehouse, and concrete operations are:

push(DS(index))；

S3.6 generates a new segmentation, with the expression satellite that ground station was inserted switching has taken place, and simultaneously storehouse is upgraded, and concrete operations comprise:

k _e＝index-1；k++；k _s＝index；

release_stack()；

push(DS(index))；index++；push(DS(index))；

The S3.7 end process generates last segmentation, and concrete operations are:

k _e＝N；K＝k；

release_stack()；

Fig. 3 method is carried out in the mode of storehouse, and wherein push operation is carried out in the push operation, and release_stack then carries out a series of pop of popping operations, is empty up to storehouse.Whether function isabove (DS (index)) judging point DS (index) is being arranged on the two dimensional surface above two straight lines that element was linked to be of current stack top.

Obtain each segmentation of DS by Fig. 3 method after, make k _oBe segmentation DS _kSubscript when minimum value is got in middle delay in DS, that is: k _o={ i|min{d (i) }, (s (i), d (i)) ∈ DS _k.Thus, for each segmentation of DS, minimum point subscript and end point subscript tlv triple (k are got in its starting point subscript, delay _s, k _o, k _e), 1≤k≤K represents.In Fig. 1, use " * ", " X ", "+" to represent the end point of starting point, minimum delay value point and the segmentation of each segmentation respectively.

(3) after DS is divided into the K section, receiving terminal ground station postpones smallest point with per minute section among the DS and constitutes minimum delay time sequence MDS, that is:

MDS＝{(s(1 _o)，d(1 _o))，…，(s(k _o)，d(k _o))，…，(s(K _o)，d(K _o))}????(3)

Owing to implied in the measuring process change information of relative distance between ground station and access star place orbit plane among the minimum delay time sequence MDS, receiving terminal ground station is divided into MDS M segmentation once more by Fig. 4 method, makes the m of MDS be segmented into sub-time of delay of sequence MDS _mAnd be expressed as:

MDS _m＝{(s(m _s)，d(m _s))，(s(m _s+1)，d(m _s+1))，…，(s(m _e)，d(m _e))}，1≤m≤M(4)

Wherein: m _s, m _eBe respectively m the initial and subscript of end position in MDS of sub-sequence time of delay; And make m _oBe segmentation MDS _mIn when postponing to get minimum value in MDS pairing subscript.

Sequence MDS _mMeaning is the minimum delay sequence during the different inserting of satellite in two ground stations and the same orbit plane in the measuring process.Adjacent delay subsequence MDS _mAnd MDS _M+1Measured minimum one-way latency sequence when being two ground stations with different orbit plane inserting of satellite.For the purpose of simple and easy, with j element among MDS (j) the expression MDS.

Similar with Fig. 3, the detailed implementation of each step is as follows among Fig. 4:

S4.1 parameter and initialization comprise following two concrete operations:

m＝1，m _s＝1；

push(MDS(1))；push(MDS(2))；

The S4.2 method finishes to judge;

S4.3 reads in new minimum one-way delay measurements sample;

S4.4 judges whether the minimum one-way delay measurements sample newly read in is being positioned on the two dimensional surface above the straight line that storehouse top two elements are linked to be, and concrete operations are:

if(isabove(MDS(index))＝TRUE)

S4.5 will read in new minimum one-way delay measurements sample and be pressed into storehouse, and concrete operations are:

push(MDS(index))；

S4.6 generates a new segmentation, with the expression satellite that ground station was inserted switching has taken place, and simultaneously storehouse is upgraded, and concrete operations comprise:

m _e＝index-1；m++；m _s＝index；

release_stack()；

push(MDS(index))；index++；push(MDS(index))；

The S4.7 end process generates last segmentation, and concrete operations are:

m _e＝K；M＝m；

release_stack()；

The implementation of the executive mode of Fig. 4 method and Fig. 3 method is similar, stack operation push, release_stack, and respective operations or function meaning are identical in function isabove (MDS (index)) and the algorithm 1.

Obtain each segmentation of MDS by Fig. 4 method after, make m _oBe segmentation MDS _mIn when postponing to get minimum value in MDS pairing subscript, that is: m _o={ i|min{d (i) }, (s (i), d (i)) ∈ MDS _m.Thus, for each segmentation of MDS, minimum point subscript and the also available tlv triple (m of end point subscript are got in its starting point subscript, delay _s, m _o, m _e), 1≤m≤M represents.Element M DS (m among the MDS _s), MDS (m _o) and MDS (m _e) point of correspondence is DS ((m in DS _s) _o), DS ((m _o) _o) and DS ((m _e) _o).

(4) measurement of satellite altitude h.In the above-mentioned steps (3) minimum delay time sequence MDS is divided into M segmentation MDS _m, behind 1≤m≤M, the height h of satellite is calculated by drawing method 5 in the target floor station, wherein make ground station's place longitude and latitude for (Θ, Φ):

The detailed implementation of each step is as follows among Fig. 5:

S5.1 parameter initialization, i.e. executable operations:

mdelay＝∞；

S5.2 is from each sub-time sequence MDS of minimum delay time sequence MDS _mIn search the point that whether exists length of delay to equate, if exist, then get the length of delay reckling, its manner of execution is as follows:

The sub-minimum delay time sequence of foreach MDS _mDo

if(d((m _o) _o)＝d((m _o+1) _o)and?mdelay＞d((m _o) _o))

mdelay＝d((m _o) _o)；index＝m；

end?if

end?foreach

S5.3 is in S5.2, if the situation that exists length of delay to equate is then calculated satellite altitude h accurately by following method:

rad＝sin(90°-Φ)×EARTH；

ab＝2×rad×sin(0.00417×(s((index _o+1) _o)-s((index _o) _o)))；

$\mathrm{theta}=2\×\arcsin \left(\frac{\mathrm{ab}}{2\×\mathrm{EARTH}}\right);$

$d\_\max =0.5\×\mathrm{LIGHT}\×\frac{\mathrm{mdelay}-2\×\mathrm{PACKETSIZE}\×8}{\mathrm{BANDWIDTH}};$

$h=\mathrm{EARTH}\×(\cos \left(\mathrm{theta}\right)-1)+\sqrt{d\_{\max }^2-\mathrm{EART}{H}^2\×{\sin }^2\left(\mathrm{theta}\right)};$

S5.4 in S5.2, if there is no length of delay situation about equating, then by following method estimation satellite altitude h:

mdelay＝min{d((m _o) _o)}，1≤m≤M；

$h=0.5\×\mathrm{LIGHT}\×\frac{\mathrm{mdelay}-2\×\mathrm{PACKETSIZE}\×8}{\mathrm{BANDWIDTH}};$

S5.5 finishes.

At two kinds of different situations, Fig. 5 method utilizes step S5.3 and S5.4 to calculate satellite altitude h respectively.Wherein the meaning of part constant is:

EARTH-earth radius; PACKETSIZE-delay probe data packet size (byte);

LIGHT-light wave is propagation velocity aloft; BANDWIDTH-measure link bandwidth (bps).

(5) measurement of satellite maximum coverage range-maximum geocentric angle θ.After measuring satellite altitude by step (4), the maximum geocentric angle θ of satellite calculates in receiving terminal ground station by accompanying drawing 6 methods:

The detailed implementation of each step is as follows among Fig. 6:

S6.1 calculates in measuring period the satellite minimum one-way latency value constantly that switches, and computational methods are as follows:

mdelay＝min{d(k _e)}，1≤k≤K；

S6.2 calculate the minimum one-way latency value of switching instant constantly ground station and intersatellite spacing from, the calculating concrete grammar is as follows:

$d\_\max =0.5\×\mathrm{LIGHT}\×\frac{\mathrm{mdelay}-2\×\mathrm{PACKETSIZE}\×8}{\mathrm{BANDWIDTH}};$

The maximum geocentric angle θ of S6.3 calculating satellite is as follows:

$\mathrm{\θ}=\arccos \left[\frac{\mathrm{EART}{H}^2+{(\mathrm{EARTH}+h)}^2-d\_{\max }^2}{2\×\mathrm{EARTH}\×(\mathrm{EARTH}+h)}\right]$

In the S6.1 of Fig. 6 went on foot, mdelay was a ground station and the end-to-end one-way latency value that inserts satellite switching instant minimum in the measuring process; Corresponding constant same meaning in the accompanying drawing method 5 of the meaning of constant and step (4) among S6.2 and the S6.3.

(6) measuring and calculating of ground station minimum angle of elevation E.Ground station is calculated as follows the minimum angle of elevation E that ground station and satellite communicate after (5) measure satellite maximum coverage range θ set by step:

$E=\arctan [\tan \left(\mathrm{\θ}\right)-\frac{\mathrm{EARTH}}{\sin \left(\mathrm{\θ}\right)\×(\mathrm{EARTH}+h)}]$

(7) measurement of angle between adjacent satellite in the same orbit plane.Destination end ground station calculates in the orbital period T of satellite and the same orbit plane angle ψ between adjacent satellite by Fig. 7 method after step (4) algorithm 3 calculates satellite altitude:

The detailed implementation of each step is as follows among Fig. 7:

S7.1 method initial phase is comprising calculating satellite orbit cycle of operation T, that is:

$T=2\mathrm{\π}\×{(\mathrm{EARTH}+h)}^{3/2}/\sqrt{\mathrm{\μ}};$

mdelay＝∞；

S7.2, S7.3 is from each sub-time sequence MDS of minimum delay time sequence MDS _mIn search the point that whether exists length of delay to equate, if exist, then write down this delay point position:

The sub-minimum delay time sequence of foreach MDS _m, 1＜m＜Kdo

if(d((m _o) _o)＝d((m _o+1) _o)and?mdelay＞d((m _o) _o))

mdelay＝d((m _o) _o)；index＝m；

end?if

end?foreach

It is as follows that S7.4 calculates a new some position that postpones:

index＝{m|min{d((m _o+1) _o)}，1＜m＜K}；

Angle ψ between adjacent satellite in the same orbit plane of S7.5:

μ ≈ 3.986013 * 10 in S7.1 ⁵Km ³/ s ²Be the Kai Bule constant.

(8) measurement of adjacent satellite orbit plane angle γ.The target floor station is pressed Fig. 8 method and is calculated adjacent satellite orbit plane angle γ:

The detailed implementation of each step is as follows among Fig. 8:

The S8.1 initial phase:

nsum[360]＝{0}；asum[360]＝{0.0}；

S8.2 is according to every pair of adjacent minimum delay sequence is calculated plane included angle angle:

The sub-minimum delay time sequence of foreach is to (MDS _m, MDS _M+1), 1＜m＜K-1 do

angle＝0.00417×(s(((m+1) _o) _o)-s((m _o) _o))；

end?foreach

S8.3 determines adjacent orbit plane included angle γ by maximum probability of happening, and computational methods are as follows:

index＝{i|max{nsum[i]}，0≤i＜360}；

γ＝asum[index]/nsum[index]；

Among Fig. 8

Be operating as and be not more than the angle maximum integer.

(9) calculating and the satellite constellation track number of satellite number in every track.Therefore step (8) calculates adjacent satellite orbit plane angle γ, can easily calculate satellite in each orbit plane by method among Fig. 9 and count track number P in n and the constellation:

The detailed implementation of each step is as follows among Fig. 9:

The S9.1 initial phase:

snum[MAXSAT]＝{0}；

S9.2 is to satellite number in rail of each sub-minimum delay sequence calculating, and computational methods are as follows:

The sub-minimum delay time sequence of foreach MDS _m, 1＜m＜K do

$i=\frac{T}{(s\left({\left(m_o\right)}_e\right)-s\left({\left(m_o\right)}_s\right))};$

end?foreach

S9.3 determines that by maximum probability of happening satellite is counted n in the orbit plane:

n＝{i|max{snum[i]}，0≤i＜MAXSAT}；

S9.4 calculates constellation track number P:

Operation Still for getting the maximum integer that is not more than x.

Table 1 shown China and world's major cities to the measurement result of the main constellation parameter of IRIDIUM and with the comparison of actual parameter.As can be known, the method for measurement measured result of patent design of the present invention is accurately, reliably from table.

Table 2 shown China and world's major cities to the measurement result of the main constellation parameter of certain 6 * 8 low orbit, utmost point constellation satellite network and with the comparison of actual parameter.As can be known, the method for measurement measured result of patent design of the present invention also is very accurately, reliably from table.

In the measuring process of subordinate list 1, subordinate list 2, all the measurement parameter with shown in Figure 1 is identical to measure used key parameter.

Table 1 is in measurement result and the comparison to the iridium satellite constellation parameter of China and world's major cities

Major area and longitude and latitude	Star height (kilometer)	Maximum geocentric angle (degree)	Minimum angle of elevation (degree)	Track number X satellite number	Orbit plane angle (degree)	Angle (degree) between star in the rail
							Actual parameter	??780.0	??19.92	??8.20	??6×11	??31.60	??32.73
Beijing (116.45,39.92)	??778.83	??19.97	??8.11	??6×11	??31.96	??32.56
							Urumchi (87.57,43.77)	??781.44	??19.96	??8.18	??6×11	??31.96	??32.84
Harbin (126.63,45.75)	??783.46	??19.95	??8.23	??6×11	??31.96	??32.53
							Lhasa (91.08,28.67)	??785.40	??19.94	??8.28	??6×11	??31.95	??32.82
Haikou (110.35,20.02)	??780.16	??19.97	??8.15	??6×11	??31.95	??32.85
							Shanghai (121.43,31.18)	??787.15	??19.94	??8.33	??6×11	??31.96	??32.80
Wuhan (114.31,30.52)	??787.30	??19.94	??8.33	??6×11	??31.96	??32.50
							Tokyo (139.75,35.67)	??774.40	??19.99	??7.99	??6×11	??31.96	??33.19
Singapore (103.83,1.33)	??773.86	??19.99	??7.98	??6×11	??31.96	??33.19
							Paris (2.33,48.87)	??785.20	??19.95	??8.28	??6×11	??31.96	??33.11
London (0.17,51.50)	??787.33	??19.94	??8.28	??6×11	??31.95	??33.10
							New York (74.00,40.72)	??779.46	??19.97	??8.13	??6×11	??31.96	??32.56
Los Angeles (118.25,34.07)	??789.84	??19.93	??8.40	??6×11	??31.96	??32.49
							Sydney (151.22 ,-33.87)	??789.12	??19.93	??8.38	??6×11	??31.96	??32.79
Rio de Janeiro (43.28 ,-22.88)	??781.73	??19.96	??8.19	??6×11	??31.95	??32.84
							Hong Kong (114.20,22.27)	??781.38	??19.96	??8.18	??6×11	??31.96	??32.84
Cape Town (18.37 ,-35.92)	??791.19	??19.92	??8.44	??6×11	??31.96	??32.48
							Cairo (31.25,30.05)	??786.35	??19.94	??8.31	??6×11	??31.97	??32.81

Table 2 is in measurement result and the comparison to certain 6 * 8 constellation parameter of China and world's major cities

Major area and longitude and latitude	Star height (kilometer)	Maximum geocentric angle (degree)	Minimum angle of elevation (degree)	Track number * satellite number	Orbit plane angle (degree)	Angle (degree) between star in the rail
							Actual parameter	??1450.0	????26.64	????10.0	????6×8	????30.0	????45.0
Beijing (116.45,39.92)	??1442.08	????26.81	????9.67	????6×8	????30.50	????44.20
							Urumchi (87.57,43.77)	??1445.20	????26.80	????9.73	????6×8	????30.51	????44.96
Harbin (126.63,45.75)	??1447.52	????26.65	????0.96	????6×8	????30.50	????44.94
							Lhasa (91.08,28.67)	??1444.47	????26.80	????9.72	????6×8	????30.51	????44.70
Haikou (110.35,20.02)	??1435.58	????26.71	????9.72	????6×8	????30.53	????45.30
							Shanghai (121.43,31.18)	??1479.98	????26.61	????10.43	????6×8	????30.50	????44.70
Wuhan (114.31,30.52)	??1479.98	????26.61	????10.43	????6×8	????30.50	????44.88
							Tokyo (139.75,35.67)	??1479.79	????26.47	????10.61	????6×8	????30.50	????43.36
Singapore (103.83,1.33)	??1427.62	????26.76	????9.56	????6×8	????30.51	????45.37
							Paris (2.33.48.87)	??1450.48	????26.63	????10.02	????6×8	????30.50	????45.44
London (0.17,51.50)	??1453.27	????26.62	????10.07	????6×8	????30.51	????45.67
							New York (74.00,40.72)	??1441.19	????26.82	????9.65	????6×8	????30.50	????45.25
Los Angeles (118.25,34.07)	??1479.98	????26.47	????10.61	????6×8	????30.51	????43.88
							Sydney (151.22 ,-33.87)	??1479.98	????26.47	????10.61	????6×8	????30.51	????45.70
Rio de Janeiro (43.28 ,-22.88)	??1439.22	????26.69	????9.79	????6×8	????30.51	????44.75
							Hong Kong (114.20,22.27)	??1437.38	????26.84	????9.58	????6×8	????30.52	????45.29
Cape Town (18.37 ,-35.92)	??1479.98	????26.61	????10.43	????6×8	????30.51	????45.40
							Cairo (31.25,30.05)	??1445.25	????26.80	????9.73	????6×8	????30.52	????44.96

Claims (11)

1. a low orbit, utmost point constellation satellite communication system constellation parameter method of measurement, it is characterized in that, by being that relaying carries out one-way delay measurements with the satellite system between two ground stations in same geographical position on earth, can realize measurement and calculating to the constellation key parameter.

2. low orbit according to claim 1, utmost point constellation satellite communication system constellation parameter method of measurement is characterized in that, comprise step:

S1 measures one-way latency and calculates one-way latency time series DS, and source ground station is to length delay measurements messages such as target floor station cycle transmissions;

S2, sequence D S comes segmentation according to the difference that inserts satellite to time of delay, and cycle " trough " characteristic (being the concavity feature) according to time of delay, sequence was presented is divided into K segmentation with it, and " trough " of an appearance represented in each segmentation;

S3, to time of delay sequence come segmentation according to inserting satellite orbit, with after time of delay, sequence D S was divided into K segmentation, can calculate minimum delay time sequence MDS through S2;

S4 calculates the maximum geocentric angle θ of satellite altitude h and satellite;

S5 calculates the minimum angle of elevation E of ground station and with angle Ψ between star in the track;

S6 calculates adjacent orbit interplanar angle γ;

S7 calculates the interior satellite of orbit plane and counts n and constellation track number P.

3. constellation parameter method of measurement according to claim 2 is characterized in that, source ground station is to length delay measurements messages such as target floor station cycle transmissions, and target floor stands in to receive and calculates one-way latency time series DS after the probe messages:

DS＝{(s(1)，d(1))，(s(2)，d(2))，…，(s(N)，d(N))}，d(i)＝r(i)-s(i)??(1)

Wherein: s (i) and r (i) are respectively i, the transmission and the time of reception of 1≤i≤N probe data packet p (i).

4. according to claim 2 or 3 described low orbits, utmost point constellation satellite communication system constellation parameter method of measurement, it is characterized in that, after calculating DS, DS is divided into K segmentation, make the k of DS be segmented into sub-time of delay of sequence D S _kAnd be expressed as:

DS _k＝{(s(k _s)，d(k _s))，(s(k _s+1)，d(k _s+1))，…，(s(k _e)，d(k _e))}，1≤k≤K(2)

Wherein: k _s, k _eBe respectively k the initial and subscript of end position in DS of sub-sequence time of delay; And make k _oBe DS _kIn have measurement point pairing subscript in DS of minimum delay value;

The detailed implementation of each step is as follows:

S3.1 parameter and initialization comprise following two concrete operations:

k＝1，k _s＝1；

push(DS(1))；push(DS(2))；

The S3.2 method finishes to judge;

S3.3 reads in new one-way delay measurements sample;

S3.4 judges whether the one-way delay measurements sample that newly reads in is positioned at storehouse on two dimensional surface

The straight line top that top two elements are linked to be, concrete operations are:

if(isabove(DS(index))＝TRUE)

S3.5 will read in new one-way delay measurements sample and be pressed into storehouse, and concrete operations are:

push(DS(index))；

S3.6 generates a new segmentation, has taken place to cut with the expression satellite that ground station was inserted

Change, simultaneously storehouse is upgraded, concrete operations comprise:

k _e＝index-1；k++；k _s＝index；

release_stack()；

push(DS(index))；index++；push(DS(index))；

The S3.7 end process generates last segmentation, and concrete operations are:

k _e＝N；K＝k；

release_stack()；

5. according to claim 2 or 3 or 4 described low orbits, utmost point constellation satellite communication system constellation parameter method of measurement, it is characterized in that after DS was divided into the K section, receiving terminal ground station postponed smallest point with per minute section among the DS and constitutes minimum delay time sequence MDS, that is:

MDS＝{(s(1 _o)，d(1 _o))，…，(s(k _o)，d(k _o))，…，(s(K _o)，d(K _o))}????????????(3)

6. low orbit according to claim 5, utmost point constellation satellite communication system constellation parameter method of measurement is characterized in that, the target floor station is divided into M sub-time of delay of sequence MDS with minimum delay time sequence MDS _m:

MDS _m＝{(s(m _s)，d(m _s))，(s(m _s+1)，d(m _s+1))，…，(s(m _e)，d(m _e))}，1≤m≤M??(4)

Wherein: m _s, m _eBe respectively m the initial and subscript of end position in MDS of sub-sequence time of delay; And make m _oBe segmentation MDS _mIn when postponing to get minimum value in MDS pairing subscript;

Its concrete steps are as follows:

S4.1 parameter and initialization comprise following two concrete operations:

m＝1，m _s＝1；

push(MDS(1))；push(MDS(2))；

The S4.2 method finishes to judge;

S4.3 reads in new minimum one-way delay measurements sample;

S4.4 judges whether the minimum one-way delay measurements sample that newly reads in is positioned on two dimensional surface

The straight line top that storehouse top two elements are linked to be, concrete operations are:

if(isabove(MDS(index))＝TRUE)

S4.5 will read in new minimum one-way delay measurements sample and be pressed into storehouse, and concrete operations are:

push(MDS(index))；

S4.6 generates a new segmentation, has taken place to cut with the expression satellite that ground station was inserted

Change, simultaneously storehouse is upgraded, concrete operations comprise:

m _e＝index-1；m++；m _s＝index；

release_stack()；

push(MDS(index))；index++；push(MDS(index))；

The S4.7 end process generates last segmentation, and concrete operations are:

m _e＝K；M＝m；

release_stack()；

Wherein, with j element among MDS (j) the expression MDS.

7. low orbit according to claim 2, utmost point constellation satellite communication system constellation parameter method of measurement is characterized in that, in known ground station longitude and latitude be (Θ, in the time of Φ), the target floor station is pressed algorithm 3 and is calculated satellite altitude h:

The detailed implementation of each step is as follows:

S5.1 parameter initialization, i.e. executable operations:

mdelay＝∞；

S5.2 is from each sub-time sequence MDS of minimum delay time sequence MDS _mIn search and be

The point that does not exist length of delay to equate if exist, is then got the length of delay reckling, its

Manner of execution is as follows:

The sub-minimum delay time sequence of foreach MDS _mDo

if(d((m _o) _o)＝d((m _o+1) _o)and?mdelay＞d((m _o) _o))

mdelay＝d((m _o) _o)；index＝m；

end?if

end?foreach

S5.3 is in S5.2, if the situation that exists length of delay to equate is then calculated by following method

Satellite altitude h accurately:

rad＝sin(90°-Φ)×EARTH；

ab＝2×rad×sin(0.00417×(s((index _o+1) _o)-s((index _o) _o)))；

$\mathrm{theta}=2\×\arcsin \left(\frac{\mathrm{ab}}{2\×\mathrm{EARTH}}\right);$

$d\_\max =0.5\×\mathrm{LIGHT}\×\frac{\mathrm{mdelay}-2\×\mathrm{PACKETSIZE}\×8}{\mathrm{BANDWIDTH}};$

$h=\mathrm{EARTH}\×(\cos \left(\mathrm{theta}\right)-1)+\sqrt{d\_{\max }^2-{\mathrm{EARTH}}^2\×{\sin }^2\left(\mathrm{theta}\right)};$

S5.4 is in S5.2, and if there is no the equal situation of length of delay is then estimated by following method

Calculate satellite altitude h:

mdelay＝min{d((m _o) _o)}，1≤m≤M；

$h=0.5\×\mathrm{LIGHT}\×\frac{\mathrm{mdelay}-2\×\mathrm{PACKETSIZE}\×8}{\mathrm{BANDWIDTH}};$

S5.5 finishes;

Wherein:

The EARTH-earth radius; PACKETSIZE-postpones probe data packet size (byte);

The LIGHT-light wave is propagation velocity aloft; BANDWIDTH-measure link bandwidth (bps).

8. low orbit according to claim 2, utmost point constellation satellite communication system constellation parameter method of measurement is characterized in that, the maximum geocentric angle θ of satellite is calculated at the target floor station:

The detailed implementation of each step is as follows:

S6.1 calculates in measuring period the satellite minimum one-way latency value constantly that switches, calculating side

Method is as follows:

mdelay＝min{d(k _e)}，1≤k≤K；

S6.2 calculate the minimum one-way latency value of switching instant constantly ground station and intersatellite spacing from, count

The calculation concrete grammar is as follows:

$d\_\max =0.5\×\mathrm{LIGHT}\×\frac{\mathrm{mdelay}-2\×\mathrm{PACKETSIZE}\×8}{\mathrm{BANDWIDTH}};$

The maximum geocentric angle θ of S6.3 calculating satellite is as follows:

$\mathrm{\θ}=\arccos \left[\frac{{\mathrm{EARTH}}^2+{(\mathrm{EARTH}+h)}^2-d\_{\max }^2}{2\×\mathrm{EARTH}\×(\mathrm{EARTH}+h)}\right]$

9. low orbit according to claim 2, utmost point constellation satellite communication system constellation parameter method of measurement is characterized in that, angle Ψ between the interior adjacent satellite of same orbit plane is calculated at the target floor station:

The detailed implementation of each step is as follows:

S7.1 method initial phase is comprising calculating satellite orbit cycle of operation T, that is:

$T=2\mathrm{\π}\×{(\mathrm{EARTH}+h)}^{3/2}/\sqrt{\mathrm{\μ}};$

mdelay＝∞；

S7.2, S7.3 is from each sub-time sequence MDS of minimum delay time sequence MDS _mIn

Search the point that whether exists length of delay to equate,, then write down this delay point if exist

The position:

The sub-minimum delay time sequence of foreach MDS _m, 1＜m＜K do

if(d((m _o) _o)＝d((m _o+1) _o)and?mdelay＞d((m _o) _o))

mdelay＝d((m _o) _o)；index＝m；

end?if

end?foreach

It is as follows that S7.4 calculates a new some position that postpones:

index＝{m|min{d((m _o+1) _o)}，1＜m＜K}；

Angle Ψ between adjacent satellite in the same orbit plane of S7.5:

μ ≈ 3.986013 * 10 in S7.1 ⁵Km ³/ s ²Be the Kai Bule constant.

10. low orbit according to claim 2, utmost point constellation satellite communication system constellation parameter method of measurement is characterized in that, adjacent satellite orbit plane angle γ is calculated at the target floor station:

The detailed implementation of each step is as follows:

The S8.1 initial phase:

nsum[360]＝{0}；asum[360]＝{0.0}；

S8.2 is according to every pair of adjacent minimum delay sequence is calculated plane included angle angle:

The sub-minimum delay time sequence of foreach is to (MDS _m, MDS _M+1), 1＜m＜K-1 do

angle＝0.00417×(s(((m+1) _o) _o)-s((m _o) _o))；

end?foreach

S8.3 determines adjacent orbit plane included angle γ by maximum probability of happening, and computational methods are as follows:

index＝{i|max{nsum[i]}，0≤i＜360}；

γ＝asum[index]/nsum[index]；

Wherein Be operating as and be not more than the angle maximum integer.

11. low orbit according to claim 2, utmost point constellation satellite communication system constellation parameter method of measurement is characterized in that, the track number P that satellite in each orbit plane is counted n and constellation is calculated by algorithm 7 in the target floor station:

The detailed implementation of each step is as follows:

The S9.1 initial phase:

snum[MAXSAT]＝{0}；

S9.2 calculates satellite number in rail to each sub-minimum delay sequence, computational methods as

Down:

The sub-minimum delay time sequence of foreach MDS _m, 1＜m＜K do

$i=\frac{T}{(s\left({\left(m_o\right)}_e\right)-s\left({\left(m_o\right)}_e\right))};$

end?foreach

S9.3 determines that by maximum probability of happening satellite is counted n in the orbit plane:

n＝{i|max{snum[i]}，0≤i＜MAXSAT}；

S9.4 calculates constellation track number P:

Operation

Still for getting the maximum integer that is not more than x.

Images