Method for analyzing testability of marine launched rockets by light thunder equipment

Abstract

The invention discloses a method for analyzing the testability of a marine launched rocket by light thunder equipment, which comprehensively considers factors such as radar performance indexes, tracking target characteristics and the like through radar tracking capability calculation, tracking angle calculation, visibility constraint analysis, testability constraint analysis and testability time determination. And a quantitative analysis result is provided for the testability of the sea-based light thunder equipment of the rocket launched on the sea, and the accuracy of a calculation result is high. The application of the method provided by the invention can assist the analysis of measurement and control support conditions during maritime emission, especially the development of maritime optical and radar equipment station distribution design and the verification of the rationality of a maritime station distribution method, and also facilitates the optimization of a scheme which meets the key measurement and control requirements and has a better overall measurement effect through the testability analysis of different station distribution schemes.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace measurement and control data processing, and in particular to a method for analyzing the measurability of a light mine device for a sea-launched rocket. Background Art

[0002] Sea-based rocket launches offer numerous advantages over land-based launches, particularly for geosynchronous orbit satellites. Low-latitude launch sites are readily available, and rockets consume less fuel. This allows for the cost-effective delivery of payloads to low-inclination medium- and high-orbits using sea-based launch platforms. Furthermore, sea-based launches are located away from densely populated areas, allowing for a wider range of control and landing areas for rocket debris, significantly improving launch safety. Consequently, sea-based launches have garnered significant attention from major space-faring nations.

[0003] During a rocket launch, radar, optical instruments, and other equipment are needed to track and measure it, acquiring relevant information to provide real-time flight status and measurement and control. The core of developing a launch vehicle's TT&C plan is to determine the ground station layout, equipment configuration, and information exchange and transmission processes based on the flight trajectory and measurement requirements. Testability analysis is a prerequisite for developing a launch vehicle's TT&C plan.

[0004] Since the launch arrays on land are fixed, their station layout plans are mature. When launching at sea, the station layout needs to take into account economic and safety factors, and cover more measurement and control arcs with as few stations as possible. When designing the testability of the station layout, it is necessary to analyze the visibility constraints and testability constraints of different equipment based on their performance. For example, optical equipment can be measured as long as it is visible; due to its maximum range limitation, single-pulse radar can only obtain measurement signals within its effective range. RCS measurement also needs to be simulated according to factors such as the size, material, and tracking angle of the target, and its measurement effect must be further analyzed. In the present invention, optical equipment and radar equipment are collectively referred to as optical mine equipment. Summary of the Invention

[0005] The purpose of the present invention is to provide a method for analyzing the measurability of sea-launched rockets using optical mine equipment to meet the needs of sea-based measurement. By analyzing the measurability of different station layout schemes, a scheme that meets key measurement and control requirements and has better overall measurement effects can be selected.

[0006] To achieve the above objectives, the present invention designs a method for analyzing the testability of sea-launched rockets using optical radar equipment. The method is applicable to sea-launched rockets and provides technical support for station layout design by analyzing the visibility and testability constraints of sea-based measurement equipment. The analysis method includes at least radar tracking capability calculation, tracking angle calculation, visibility constraint analysis, testability constraint analysis, and testability time determination. The radar tracking capability calculation includes calculating the maximum range of radar electromagnetic scattering based on the tracking target characteristic parameters and radar capability indicators. R max ; The tracking angle calculation includes the following steps: 、 Converted to geocentric radius , launch system radius , respectively calculate the radius vector from the rocket to the station in the launch coordinate system , the radius vector of the rocket body coordinate system , measuring the radius vector of the coordinate system , thereby calculating the tracking angle Theta of the measurement coordinate system 、Phi angle (equivalent to azimuth and elevation angles respectively); The visibility constraint analysis includes calculating the radius vector from the station to the rocket in the launch coordinate system , radius vector in geocentric coordinate system Northeast celestial coordinate system radius vector of the station , determine the visibility constraint condition according to the y direction value; The testability constraint analysis is to calculate the rocket electromagnetic simulation data based on the tracking angle (theta angle, phi angle, also known as the observation angle) and determine the target testability constraint conditions through the radar capability index; The measurable time determination includes comprehensively considering visibility constraints and measurability constraints, determining common valid sections, and thus determining the measurable time.

[0007] Furthermore, the maximum range of the radar electromagnetic scattering is R max Methods for determining include:

[0008] in, P t is the peak power of the transmitted signal, G is the antenna gain, σ is the radar cross section, λ is the radar operating wavelength, n p is the number of coherently accumulated pulses, T p is the pulse duration, k is the Boltzmann constant, Ts is the receiver system noise temperature, S / N is the output signal-to-noise ratio, L S is the system loss, R max The superscript 4 indicates the fourth power.

[0009] Furthermore, the tracking angle Theta of the rocket in the measurement coordinate system 、Phi angle Calculation methods include:

[0010] .

[0011] Furthermore, according to the geocentric longitude and latitude of the sea-based optical mine equipment 、 , station geocentric diameter The scalar size of is:

[0012] The Earth's equatorial radius , the Earth's polar radius ; Its vector component form is:

[0013] in, is the longitude of the launch point on the Earth's surface.

[0014] Furthermore, the geocentric radius of the station in the launch coordinate system Expressed as:

[0015] in, is the geographical latitude of the launch point on the Earth’s surface, is the launch azimuth.

[0016] Furthermore, the radius vector from the rocket to the station in the launch coordinate system is expressed as:

[0017] in, are the three components of the radius vector from the launch point to any point on the trajectory in the launch coordinate system, the radius vector from the launch point to the center of the earth Three components in the emission coordinate system: , in, is the difference between the geographical latitude of the launch point and the latitude of the center of the Earth, that is, , is the geocentric latitude.

[0018]

[0019] The radius vector of the rocket to the measuring station in the rocket body coordinate system is expressed as:

[0020] in, is the rocket body pitch angle, is the rocket body yaw angle, is the rocket body roll angle; The radius vector of the rocket to the measuring station in the measurement coordinate system is expressed as: .

[0021] Furthermore, the radius vector from the observation station to the rocket in the launch coordinate system is expressed as:

[0022] The radius vector from the measuring station to the rocket in the geocentric coordinate system is expressed as:

[0023] The radius vector from the observation station to the rocket in the northeast celestial coordinate system of the observation station is expressed as:

[0024] When time t satisfies When the rocket is visible to radar and optical equipment, the optical equipment can detect it.

[0025] Furthermore, the tracking angle Theta of the rocket in the measurement coordinate system 、Phi angle , target radar cross-sectional area and radar operating frequency as parameters, build target RCS simulation model according to rocket physical size and material properties, calculate rocket RCS simulation data .

[0026] Furthermore, the target testability constraint is: and ,in, .

[0027] Furthermore, the determination of the measurable time includes: when the time t satisfies and ,and When t is set, the RCS of the sea-based radar can be measured, and the range determined by t is the measurable time.

[0028] The advantages and beneficial effects of the present invention are as follows: The method designed by the present invention for analyzing the measurability of sea-based optical mine equipment for sea-launched rockets comprehensively considers factors such as radar performance indicators and target tracking characteristics, providing quantitative analysis results for the measurability of rockets during sea launches, with high accuracy. Application of the present method can assist in analyzing measurement and control support conditions for sea launches, particularly in designing the deployment of marine optical and radar equipment, verifying the rationality of marine deployment methods, and facilitating the selection of a solution that meets key measurement and control requirements and provides better overall measurement results through measurability analysis of different deployment schemes. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This is a flow chart of a method for analyzing the testability of a light mine device for a sea-launched rocket; Figure 2 is the target RCS variation curve; Figure 3 It is the rocket-radar straight-line distance and the RCS detectable range; Figure 4 It is the time mark when RCS can be measured. DETAILED DESCRIPTION

[0030] Because land-based launch arrays are fixed in position, their deployment plans are established and mature. For sea-based launches, deployment must comprehensively consider factors such as cost-effectiveness, safety, and testability, aiming to cover as many tracking and control arcs as possible with as few deployments as possible. When designing a testability deployment, visibility and testability constraints must be considered based on the performance of different devices. For example, optical devices can be measured only if they are visible, while monopulse radars, due to their maximum range, can only acquire measurement signals within their effective range. RCS measurements also require simulation and further analysis of the measurement results based on factors such as target size, material, and tracking angle.

[0031] The following embodiments are further described in conjunction with the accompanying drawings and examples. The following embodiments are only used to more clearly illustrate the technical solutions of the present invention and are not intended to limit the scope of protection of the present invention.

[0032] like Figures 1-3 As shown, the present invention designs a method for analyzing the testability of optical mine equipment for sea-launched rockets. The method is applicable to sea-launched rockets. By analyzing the visibility constraints and testability constraints of sea-based measurement equipment, technical support is provided for station layout design. The analysis method at least includes radar tracking capability calculation, tracking angle calculation, visibility constraint analysis, testability constraint analysis, and testability time determination. The radar tracking capability calculation includes calculating the maximum range of radar electromagnetic scattering based on the tracking target characteristic parameters and radar capability indicators. R max ; The tracking angle calculation includes the following steps: 、 Converted to geocentric radius , launch system radius , respectively calculate the radius vector from the rocket to the station in the launch coordinate system , the radius vector of the rocket body coordinate system , measuring the radius vector of the coordinate system , thereby calculating the tracking angle Theta of the measurement coordinate system 、Phi angle (equivalent to azimuth and elevation angles respectively); The visibility constraint analysis includes calculating the radius vector from the station to the rocket in the launch coordinate system , radius vector in geocentric coordinate system Northeast celestial coordinate system radius vector of the station , determine the visibility constraint condition according to the y direction value; The testability constraint analysis is to calculate the rocket electromagnetic simulation data based on the tracking angle (theta angle, phi angle, also known as the observation angle) and determine the target testability constraint conditions through the radar capability index; The measurable time determination includes comprehensively considering visibility constraints and measurability constraints, determining common valid sections, and thus determining the measurable time.

[0033] like Figure 1 As shown, the specific method steps of this embodiment include: S1. Calculate radar tracking capability; S2. Calculate the geocentric diameter of the offshore station; S3. Calculate the coordinate components of the geocentric radial vector of the measuring station; S4. Calculate the Earth's center vector of the launch system station; S5. Calculate the radius vector from the launch system rocket to the measuring station; S6. Calculate the radius vector of the rocket system from the rocket to the measuring station; S7. Calculate the radius vector from the rocket to the measuring station; S8. Calculate the tracking angle of the rocket in the measurement coordinate system; S9. Calculate the launch system's radius from the station to the rocket. S10, calculate the radius vector from the Earth-centered station to the rocket; S11. Calculate the vector radius from the measuring station to the rocket in the northeast celestial coordinate system of the measuring station and determine whether it is optically measurable. S12. Construct an RCS simulation model based on rocket properties; S13. Determine radar testability constraints based on simulation results; S14. Determine the radar measurable time.

[0034] Preferably, the maximum range of the radar electromagnetic scattering is R max Methods for determining include:

[0035] in, P t is the peak power of the transmitted signal, G is the antenna gain, σ is the radar cross section, λ is the radar operating wavelength, n p is the number of coherently accumulated pulses, T p is the pulse duration, k is the Boltzmann constant, Ts is the receiver system noise temperature, S / N is the output signal-to-noise ratio, L S is the system loss, R max The superscript 4 indicates the fourth power.

[0036] Preferably, the tracking angle Theta of the rocket in the measurement coordinate system is 、Phi angle Calculation methods include:

[0037] .

[0038] Preferably, according to the geocentric longitude and latitude of the sea-based optical mine equipment 、 , station geocentric diameter The scalar size of is:

[0039] The Earth's equatorial radius , the Earth's polar radius ; Its vector component form is:

[0040] in, is the longitude of the launch point on the Earth's surface.

[0041] Preferably, the geocentric radius of the station in the launch coordinate system Expressed as:

[0042] in, is the geographical latitude of the launch point on the Earth’s surface, is the launch azimuth.

[0043] Preferably, the radius vector from the rocket to the station in the launch coordinate system is expressed as:

[0044] in, are the three components of the radius vector from the launch point to any point on the trajectory in the launch coordinate system, the radius vector from the launch point to the center of the earth Three components in the emission coordinate system: , in, is the difference between the geographical latitude of the launch point and the latitude of the center of the Earth, that is, , is the geocentric latitude.

[0045]

[0046] The radius vector of the rocket to the measuring station in the rocket body coordinate system is expressed as:

[0047] in, is the rocket body pitch angle, is the rocket body yaw angle, is the rocket body roll angle; The radius vector of the rocket to the measuring station in the measurement coordinate system is expressed as: .

[0048] Preferably, the radius vector from the observation station to the rocket in the launch coordinate system is expressed as:

[0049] The radius vector from the measuring station to the rocket in the geocentric coordinate system is expressed as:

[0050] The radius vector from the observation station to the rocket in the northeast celestial coordinate system of the observation station is expressed as:

[0051] When time t satisfies When the rocket is visible to radar and optical equipment, the optical equipment can detect it.

[0052] Preferably, the tracking angle Theta of the rocket in the measurement coordinate system is 、Phi angle , target radar cross-sectional area and radar operating frequency are used as parameters, and a target RCS simulation model is constructed according to the physical size and material properties of the rocket. In this embodiment, the FEKO tool is used for simulation to calculate the rocket's RCS simulation data. .

[0053] Preferably, the target testability constraint is: and ,in, .

[0054] Preferably, the determination of the measurable time includes: when the time t satisfies the above and ,and When t is set, the RCS of the sea-based radar can be measured, and the range determined by t is the measurable time.

[0055] Figures 2 to 4 Shown are the geocentric longitude and latitude of the optical mine equipment in the hypothetical sea-based station scheme 、 , the geographical longitude of the emission point on the Earth's surface , geographical latitude , launch azimuth , set the peak power of the transmitted signal P t The antenna transmission gain is 640000W. G The receiving gain is 52.49dB, and the radar cross-section σ is 1m. 2 , radar operating wavelength λ The square of is 0.001 m 2 , the number of coherently accumulated pulses n p is 512, the pulse duration T p For 20us, the receiver system noise temperature Ts The output signal-to-noise ratio is 448.9K S / N 13.2 dB, system loss L S The simulation analysis shows the target RCS variation curve, rocket-radar straight-line distance and RCS detectable distance, and RCS measurable time range when the target is 8dB. It can be seen that the method proposed in this paper can accurately and efficiently analyze the detectability of different sea-based dynamic deployment schemes of optical mine equipment to rocket launches, providing a basis for reasonable and effective decision-making.

[0056] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as within the scope of protection of the present invention.

Claims

1. A method for analyzing the testability of a light mine device for a sea-launched rocket, characterized in that: The analysis method at least includes radar tracking capability calculation, tracking angle calculation, visibility constraint analysis, testability constraint analysis and testability time determination; The radar tracking capability calculation includes calculating the maximum range of radar electromagnetic scattering based on the tracking target characteristic parameters and radar capability indicators. R max ; The tracking angle calculation includes the following steps: 、 Converted to geocentric radius , launch system radius , respectively calculate the radius vector from the rocket to the station in the launch coordinate system , the radius vector of the rocket body coordinate system , measuring the radius vector of the coordinate system , thereby calculating the tracking angle Theta of the measurement coordinate system 、Phi angle ; The visibility constraint analysis includes calculating the radius vector from the station to the rocket in the launch coordinate system , radius vector in geocentric coordinate system Northeast celestial coordinate system radius vector of the station , determine the visibility constraint condition according to the y direction value; The testability constraint analysis is to calculate the rocket electromagnetic simulation data based on the tracking angle and determine the target testability constraint conditions through the radar capability index; The measurable time determination includes comprehensively considering visibility constraints and measurability constraints, determining common valid sections, and thus determining the measurable time.

2. The method for analyzing the measurability of a light mine device for launching a rocket at sea according to claim 1, characterized in that: The maximum effective range of radar electromagnetic scattering R max Methods for determining include: ； in, P t is the peak power of the transmitted signal, G is the antenna gain, σ is the radar cross section, λ is the radar operating wavelength, n p is the number of coherently accumulated pulses, T p is the pulse duration, k is the Boltzmann constant, Ts is the receiver system noise temperature, S / N is the output signal-to-noise ratio, L S For system loss.

3. The method for analyzing the measurability of a light mine device for launching a rocket at sea according to claim 1, characterized in that: Theta angle of the rocket's tracking angle in the measurement coordinate system 、Phi angle Calculation methods include: ； 。 4. The method for analyzing the measurability of a light mine device for launching a rocket at sea according to claim 1, characterized in that: Station geocentric diameter The size is: ； The Earth's equatorial radius , the Earth's polar radius ; Its component form is: ； in, is the longitude of the launch point on the Earth's surface.

5. The method for analyzing the measurability of a light mine device for launching a rocket at sea according to claim 1, characterized in that: Geocentric radius of the station in the launch coordinate system Expressed as: ； in, is the geographical latitude of the launch point on the Earth’s surface, is the launch azimuth.

6. The method for analyzing the measurability of a light mine device for launching a rocket at sea according to claim 1, characterized in that: The radius vector of the rocket to the measuring station in the launch coordinate system is expressed as: ； in, are the three components of the radius vector from the launch point to any point on the trajectory in the launch coordinate system, the radius vector from the launch point to the center of the earth Three components in the emission coordinate system: ， in, is the difference between the geographical latitude of the launch point and the latitude of the center of the Earth, that is, ; ； The radius vector of the rocket to the measuring station in the rocket body coordinate system is expressed as: ； in, is the rocket body pitch angle, is the rocket body yaw angle, is the rocket body roll angle; The radius vector of the rocket to the measuring station in the measurement coordinate system is expressed as: 。 7. The method for analyzing the testability of a light mine device for launching a rocket at sea according to claim 1, wherein the test The rocket's radius vector in the launch coordinate system is expressed as: ； The radius vector from the measuring station to the rocket in the geocentric coordinate system is expressed as: ； The radius vector from the observation station to the rocket in the northeast celestial coordinate system of the observation station is expressed as: ； When time t satisfies When the rocket is visible to radar and optical equipment, the optical equipment can detect it.

8. The method for analyzing the measurability of a light mine device for launching a rocket at sea according to claim 7, characterized in that: Theta angle of the rocket in the measurement coordinate system 、Phi angle , target radar cross-sectional area and radar operating frequency as parameters, build target RCS simulation model according to the physical size and material properties of the rocket, and calculate the rocket's RCS simulation data .

9. The method for analyzing the measurability of a light mine device for launching a rocket at sea according to claim 8, characterized in that: The target testability constraints are: and ,in, .

10. The method for analyzing the measurability of a light mine device for launching a rocket at sea according to claim 9, characterized in that: The determination of the measurable time includes: when the time t satisfies and ,and When t is set, the RCS of the sea-based radar can be measured, and the range determined by t is the measurable time.

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