Method for connecting space-based information output position precision identification of aviation platform

Abstract

The invention discloses a method for an aviation platform to receive space-based information and output position precision identification, and relates to the field of reconnaissance satellite broadcast distribution information processing, which comprises the following steps that: firstly, the aviation platform receives information distributed by an electronic reconnaissance satellite broadcast, demodulates the information and recovers data; then extracting a satellite position coordinate sequence and a target sea level projection position coordinate sequence, and querying the actual altitude of the target in a geographic database according to the target sea level projection position coordinate sequence; calculating an elevation angle sequence of the target sea level projection position coordinate sequence pointing to the satellite; and finally, adding positioning precision grade identifiers according to different elevation angle results. According to the method, the problem that the positioning result of the broadcast distribution information of the electronic reconnaissance satellite has no precision grade result element is solved, the application value of the satellite information is further improved, and the requirements of different combat scenes can be met.

Description

Technical Field

[0001] The invention relates to the field of reconnaissance satellite broadcast distribution information processing, and in particular to a method for identifying the position accuracy of an aviation platform receiving space-based information output. Background Art

[0002] The statements in this section merely provide background information related to the present disclosure and may not constitute prior art.

[0003] In modern warfare, the core combat capability is to quickly grasp the global battlefield environment and make accurate and timely action decisions. Judging from the local wars since the Gulf War, the role of space-based reconnaissance and detection systems in quickly obtaining battlefield situation information, assisting decision-making, and supporting troop operations has become increasingly important, and has become an indispensable magic weapon for winning wars.

[0004] Major countries in the world have all recognized that space-based reconnaissance capabilities are the key to winning a war. Electronic reconnaissance satellites have unique advantages such as wide coverage, no national boundaries, and high security. The instantaneous reconnaissance radius can reach thousands of kilometers. They can work all day and all weather. They can conduct large-scale reconnaissance early warning search, discovery, tracking, and monitoring of land / island / sea targets to form a continuous situation, which plays an extremely important role in implementing large-scale threat avoidance and situational awareness for aviation platforms. Electronic reconnaissance satellites are the main force for space-based target reconnaissance. They can detect and locate the radar radiation source signals of surface ships, form space-based intelligence, and broadcast and distribute them to users using broadcast links. The main task of aviation platforms to receive space-based intelligence information technology is to establish satellite-machine transmission links and receive target information broadcast and distributed by electronic reconnaissance satellites in real time.

[0005] However, under normal circumstances, due to limited on-board processing capabilities, the target positioning results output by electronic reconnaissance satellites do not take into account the errors caused by altitude. This positioning result without positioning level accuracy identification is directly distributed to the aviation platform, which will affect the need to adapt to different combat scenarios. Therefore, a method for aviation platforms to receive the position accuracy identification of space-based information output is needed to meet the needs of link back-end information support. Summary of the invention

[0006] The purpose of the present invention is to provide a method for an aviation platform to receive the position accuracy mark of the output of space-based electronic reconnaissance information, which is lacking in the positioning accuracy level part of the target output results of the existing aviation platform receiving the space-based electronic reconnaissance information, so as to make up for the lack of positioning accuracy mark in the current satellite distribution information, and further improve the application value of satellite information. The premise of applying this method is that the aviation platform can receive the data broadcast and distributed by the space-based electronic reconnaissance satellite, and can extract the sequence of satellite position and target position from it; it can solve the problem that the positioning results of the electronic reconnaissance satellite broadcast distribution information do not have the accuracy level result element, and can meet the needs of different combat scenarios.

[0007] The technical solution of the present invention is as follows:

[0008] A method for identifying the position accuracy of an aerospace platform receiving space-based information output, comprising:

[0009] Step S1: The aviation platform receives the information broadcasted by the electronic reconnaissance satellite, demodulates the information, and recovers the data;

[0010] Step S2: extracting a satellite position coordinate sequence and a target sea level projection position coordinate sequence from the data demodulated and restored in step S1;

[0011] Step S3: Calculate the elevation angle sequence of the target sea level projection position coordinate sequence pointing to the satellite;

[0012] Step S4: Add positioning accuracy level identification according to different elevation angle results.

[0013] Furthermore, the step S2 comprises:

[0014] The satellite position coordinate sequence is recorded as (α, β, h);

[0015] The target sea level projection position coordinate sequence is recorded as (a, b).

[0016] Furthermore, the step S3 comprises:

[0017] Step S31: Calculate the ground distance d = [d1, d2, d3, ..., d n ];

[0018] Step S32: Calculate the cosine value sequence of the geocentric angle ∠θ;

[0019] Step S33: Calculate the distance sequence R between the satellite position and the target sea level projection position = [R1, R2, R3, ..., R n ];

[0020] Step S34: Calculate the elevation angle sequence.

[0021] Furthermore, the step S31 includes:

[0022] d=r+arccos(sinβsinb+cosβcosbcos(α-a))

[0023] in:

[0024] r is the radius of the Earth;

[0025] β is the satellite position latitude sequence, β=[β1,β2,β3,...,β n ];

[0026] b is the latitude sequence of the target sea level projection position, b=[b1,b2,b3,...,b n ];

[0027] α is the satellite position longitude sequence, α=[1,α2,α3,...,α n ];

[0028] a is the longitude sequence of the target sea level projection position, a=[a1,a2,a3,...,a n ].

[0029] Furthermore, the step S32 includes:

[0030]

[0031] in:

[0032] cosθ is the cosine value sequence of the geocentric angle ∠θ, cosθ=[cosθ1,cosθ2,cosθ3,...,cosθ n ].

[0033] Furthermore, the step S33 includes:

[0034]

[0035] in:

[0036] h is the satellite position height sequence, h=[h1,h2,h3,...,h n ].

[0037] Furthermore, the step S34 includes:

[0038]

[0039] in:

[0040] is the elevation angle sequence, Furthermore, the step S4 comprises:

[0041] Step S41: Statistically analyze a large amount of measured data to determine the positioning accuracy level judgment rule; Step S42: Output the positioning accuracy level based on the positioning accuracy level judgment rule and the elevation angle sequence. Further, the positioning accuracy level judgment rule includes:

[0042] The elevation angle range is [0°, 20°), and the positioning accuracy level is low;

[0043] The elevation angle range is [20°, 30°], and the positioning accuracy level is medium;

[0044] The elevation angle range is (30°, 90°], and the positioning accuracy level is high.

[0045] Furthermore, the step S42 includes:

[0046] According to the range of each elevation angle in the elevation angle sequence falling within the positioning accuracy level judgment rule, the corresponding positioning accuracy level is output.

[0047] Compared with the prior art, the present invention has the following beneficial effects:

[0048] Compared with the existing method for outputting the location of space-based electronic reconnaissance information, the invention has the advantage of adding a positioning level accuracy mark to the target positioning result output by the electronic reconnaissance satellite, reflecting the error impact caused by different elevation angles in the positioning result, more intuitively reflecting it in the intelligence product, adapting to the needs of different combat scenarios, and meeting the demand for link back-end information support. The method of the invention is suitable for aviation platforms with the function of receiving space-based electronic reconnaissance information. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] Figure 1 Flowchart of a method for outputting position accuracy identification for an aviation platform receiving space-based information

[0050] Figure 2 The present invention is a schematic diagram of the principle of the elevation angle calculation process. DETAILED DESCRIPTION

[0051] It should be noted that relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0052] The features and performance of the present invention are further described in detail below in conjunction with the embodiments.

[0053] Embodiment 1

[0054] See also Figure 1-2 A method for identifying the position accuracy of an aerospace platform receiving space-based information output comprises:

[0055] Step S1: The aviation platform receives the information broadcasted by the electronic reconnaissance satellite, demodulates the information, and recovers the data;

[0056] Step S2: extracting a satellite position coordinate sequence and a target sea level projection position coordinate sequence from the data demodulated and restored in step S1;

[0057] Step S3: Calculate the elevation angle sequence of the target sea level projection position coordinate sequence pointing to the satellite;

[0058] Step S4: Add positioning accuracy level identification according to different elevation angle results.

[0059] It should be noted that the above four steps are all completed on the aviation platform.

[0060] In this embodiment, specifically, refer to Figure 2 The radius of the earth and the altitude of the satellite orbit (i.e., the satellite position altitude sequence) are known and are constants, denoted as r and h respectively, where h = [h1,h2,h3,...,h n ],h n Indicates t n The satellite orbit height at the moment; the aviation platform receives the information broadcast by the electronic reconnaissance satellite, from which it extracts the satellite position and the target sea level projection position coordinate sequence, where the satellite position coordinate sequence is recorded as (α, β, h), t n The satellite position coordinates at this moment are marked as (α n ,β n ,h n ), the satellite sub-satellite position coordinate sequence is recorded as (α, β), t n The satellite subsatellite position coordinates at this moment are marked as (α n ,β n ); the target sea level projection position coordinate sequence is recorded as (a,b), where:

[0061] α=[1,α2,α3,...,α n ], is the satellite position longitude sequence;

[0062] β=[β1,β2,β3,...,β n ], is the satellite position latitude sequence;

[0063] h=[h1,h2,h3,...,h n ], is the satellite position height sequence;

[0064] a=[a1,a2,a3,...,a n ], is the extracted target sea level projection position longitude sequence;

[0065] b=[b1,b2,b3,...,bn ], which is the extracted target sea level projection position latitude sequence.

[0066] In this embodiment, specifically, step S2 includes:

[0067] The satellite position coordinate sequence is recorded as (α, β, h);

[0068] The target sea level projection position coordinate sequence is recorded as (a, b).

[0069] In this embodiment, specifically, Figure 2 As shown, the step S3 includes:

[0070] Step S31: Calculate the ground distance d = [d1, d2, d3, ..., d n ]; where d n Indicates t n The ground distance between the satellite sub-satellite position and the target sea level projection at the moment;

[0071] Step S32: Calculate the cosine value sequence of the geocentric angle ∠θ;

[0072] Step S33: Calculate the distance sequence R between the satellite position and the target sea level projection position = [R1, R2, R3, ..., R n ]; where R n Indicates t n The distance between the satellite position and the target sea level projection position at the moment;

[0073] Step S34: Calculate the elevation angle sequence.

[0074] In this embodiment, specifically, step S31 includes:

[0075] d=r+arccos(sinβsinb+cosβcosbcos(α-a))

[0076] in:

[0077] r is the radius of the Earth;

[0078] β is the satellite position latitude sequence, β=[β1,β2,β3,...,β n ];

[0079] b is the latitude sequence of the target sea level projection position, b=[b1,b2,b3,...,b n ];

[0080] α is the satellite position longitude sequence, α=[1,α2,α3,...,α n ];

[0081] a is the longitude sequence of the target sea level projection position, a=[a1,a2,a3,...,a n ];

[0082] That is, given the satellite sub-satellite point position coordinate sequence and the target sea level projection position coordinate sequence, the ground distance between the satellite sub-satellite point position and the target sea level projection can be calculated according to the formula, taking time t1 as an example:

[0083] d1=r+arccos(sinβ1sinb1+cosβ1cosb1cos(α1-a1))

[0084] In this embodiment, specifically, step S32 includes:

[0085]

[0086] in:

[0087] cosθ is the cosine value sequence of the geocentric angle ∠θ, cosθ=[cosθ1,cosθ2,cosθ3,...,cosθ n ];

[0088] That is, after obtaining the ground distance between the satellite sub-satellite point position and the target sea level projection position, the cosine value sequence of the geocentric angle ∠θ is calculated according to the cosine theorem within ΔOPQ. Taking time t1 as an example:

[0089]

[0090] In this embodiment, specifically, step S33 includes:

[0091]

[0092] in:

[0093] h is the satellite position height sequence, h=[h1,h2,h3,...,h n ];

[0094] That is, within ΔOPQ, the distance sequence between the satellite position and the target sea level projection position is calculated according to the cosine theorem. Take time t1 as an example:

[0095]

[0096] In this embodiment, specifically, step S34 includes:

[0097]

[0098] in:

[0099] is the elevation angle sequence,

[0100] That is, within ΔOPQ, the elevation angle sequence is calculated according to the cosine theorem, taking time t1 as an example:

[0101]

[0102] In this embodiment, specifically, step S4 includes:

[0103] Step S41: Statistically analyze a large amount of measured data to determine the positioning accuracy level judgment rule;

[0104] Step S42: outputting the positioning accuracy level based on the positioning accuracy level judgment rule and the elevation angle sequence;

[0105] That is, taking into account the different error effects of elevation angles in different ranges on target positioning, statistical analysis is performed based on a large amount of measured data, and the positioning accuracy level is given by the elevation angle range, which can determine the position accuracy identifier of the output position of the aviation platform receiving space-based electronic reconnaissance information.

[0106] In this embodiment, specifically, as shown in Table 1, the positioning accuracy level judgment rule includes:

[0107] The elevation angle range is [0°, 20°), and the positioning accuracy level is low;

[0108] The elevation angle range is [20°, 30°], and the positioning accuracy level is medium;

[0109] The elevation angle range is (30°, 90°], and the positioning accuracy level is high;

[0110] Table 1 Positioning accuracy level judgment rules

[0111]

[0112]

[0113] In this embodiment, specifically, step S42 includes:

[0114] According to the range of each elevation angle in the elevation angle sequence falling within the positioning accuracy level judgment rule, the corresponding positioning accuracy level is output.

[0115] The above-mentioned embodiments only express the specific implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the protection scope of the present application. It should be pointed out that, for ordinary technicians in this field, several variations and improvements can be made without departing from the technical solution concept of the present application, and these all belong to the protection scope of the present application.

[0116] This background section is provided to generally present the context of the invention, and the work of the presently named inventors, the work to the extent described in this background section, and aspects of this section that did not constitute prior art at the time of application are neither explicitly nor implicitly admitted to be prior art to the present invention.

Claims

1. A method for identifying the position accuracy of an aviation platform receiving space-based information output, characterized in that: include: Step S1: The aviation platform receives the information broadcasted by the electronic reconnaissance satellite, demodulates the information, and recovers the data; Step S2: extracting a satellite position coordinate sequence and a target sea level projection position coordinate sequence from the data demodulated and restored in step S1; Step S3: Calculate the elevation angle sequence of the target sea level projection position coordinate sequence pointing to the satellite; Step S4: Add positioning accuracy level identification according to different elevation angle results.

2. The method for identifying the position accuracy of an aviation platform receiving space-based information output according to claim 1, characterized in that: The step S2 comprises: The satellite position coordinate sequence is recorded as (α, β, h); The target sea level projection position coordinate sequence is recorded as (a, b).

3. The method for identifying the position accuracy of the output of space-based information from an aviation platform according to claim 2, characterized in that: The step S3 comprises: Step S31: Calculate the ground distance d = [d1, d2, d3, ..., d n ]; Step S32: Calculate the cosine value sequence of the geocentric angle ∠θ; Step S33: Calculate the distance sequence R between the satellite position and the target sea level projection position = [R1, R2, R3, ..., R n ]; Step S34: Calculate the elevation angle sequence.

4. The method for identifying the position accuracy of an aviation platform receiving space-based information output according to claim 3, characterized in that: The step S31 comprises: d=r+arccos(sinβsinb+cosβcosbcos(α-a)) in: r is the radius of the Earth; β is the satellite position latitude sequence, β=[β1,β2,β3,...,β n ]; b is the latitude sequence of the target sea level projection position, b=[b1,b2,b3,...,b n ]; α is the satellite position longitude sequence, α=[1,α2,α3,...,α n ]; a is the longitude sequence of the target sea level projection position, a=[a1,a2,a3,...,a n ].

5. The method for identifying the position accuracy of an aviation platform receiving space-based information output according to claim 3, characterized in that: The step S32 comprises: in: cosθ is the cosine value sequence of the geocentric angle ∠θ, cosθ=[cosθ1,cosθ2,cosθ3,...,cosθ n ].

6. The method for identifying the position accuracy of an aviation platform receiving space-based information output according to claim 3, characterized in that: The step S33 comprises: in: h is the satellite position height sequence, h=[h1,h2,h3,...,h n ].

7. The method for identifying the position accuracy of an aviation platform receiving space-based information output according to claim 3, characterized in that: The step S34 comprises: in: is the elevation angle sequence, 8. The method for identifying the position accuracy of an aviation platform receiving space-based information output according to claim 3, characterized in that: The step S4 comprises: Step S41: Statistically analyze a large amount of measured data to determine the positioning accuracy level judgment rule; Step S42: Based on the positioning accuracy level judgment rule and the elevation angle sequence, output the positioning accuracy level.

9. A method for identifying the position accuracy of an aviation platform receiving space-based information output according to claim 8, characterized in that: The positioning accuracy level judgment rule includes: The elevation angle range is [0°, 20°), and the positioning accuracy level is low; The elevation angle range is [20°, 30°], and the positioning accuracy level is medium; The elevation angle range is (30°, 90°], and the positioning accuracy level is high.

10. A method for identifying the position accuracy of an aviation platform receiving space-based information output according to claim 9, characterized in that: The step S42 comprises: According to the range of each elevation angle in the elevation angle sequence falling within the positioning accuracy level judgment rule, the corresponding positioning accuracy level is output.

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