Rocket telemetry data acquisition system
By combining signal acquisition, analog-to-digital conversion, and storage modules, the problems of multi-channel parallel acquisition, storage, and format adaptation in rocket telemetry data acquisition were solved, achieving improvements in channel density and sampling efficiency, increased storage capacity, and flexible format adaptation.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-06-10
- Publication Date
- 2026-04-10
AI Technical Summary
Current rocket telemetry data acquisition presents challenges such as multi-channel parallel acquisition, high-precision analog-to-digital conversion, efficient data caching, and flexible data format adaptation.
By combining a signal acquisition and conditioning module, an analog-to-digital converter module, an FPGA control module, and an SRAM storage module, and using an LMP7721 chip, an AD7606 analog-to-digital converter, and an IS67WVE4M16EBLL-70BLA1 SRAM chip, it achieves simultaneous acquisition of 64 channels of signals, double the storage capacity, and enhanced format compatibility.
It increases channel density by 100%, doubles sampling efficiency, doubles storage capacity, enhances format compatibility, and supports data format adjustments for different rocket models.
Smart Images
Figure CN224109791U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to spaceflight measurement and control technical field, especially relate to a rocket telemetering data acquisition system. BACKGROUND
[0002] Rocket telemetering data acquisition refers to the technical process that in the flight process of rocket (or spacecraft), through various sensors and measuring equipment, real-time acquisition of the key parameters of the internal and external environment of rocket, and transmission to the ground receiving station through radio communication link (telemetering system) for the ground command center monitoring, analysis and control.
[0003] In daily practice, it is found that the existing technical scheme has the following problems:
[0004] The existing rocket telemetering data acquisition mainly faces the challenges of multi-channel parallel acquisition, high-precision analog-digital conversion, high-efficiency data caching and flexible data format adaptation.
[0005] Therefore, it is necessary to provide a new technical scheme to solve the above problems. UTILITY MODEL CONTENT
[0006] To solve the above technical problems, the present application provides a rocket telemetering data acquisition system, which can effectively improve the channel density, sampling efficiency, and effectively increase the storage capacity, and the format adaptation of the collected telemetering data is enhanced.
[0007] A rocket telemetering data acquisition system, comprising: a signal acquisition and conditioning module, an analog-digital conversion module, an FPGA control module and an SRAM storage module;
[0008] The signal acquisition and conditioning module is used for acquiring sensor signals and buffering, amplifying and filtering the acquired signals;
[0009] The analog-digital conversion module receiving end is in communication connection with the signal acquisition and conditioning module, and can receive the data signal sent by the signal acquisition and conditioning module;
[0010] The analog-digital conversion module output end is connected with the FPGA control module through SPI daisy chain;
[0011] The FPGA control module processes the received data through the externally input instruction information;
[0012] The SRAM storage module is in communication connection with the FPGA control module and is used for storing the processed data.
[0013] Preferably, the signal acquisition and conditioning module comprises 16 LMP7721 chips for buffering and amplifying the acquired signals; the input impedance of the signal acquisition and conditioning module is >10GΩ, and the noise voltage is <6.5nV / √Hz.
[0014] Preferably, the signal acquisition and conditioning module can receive 64 sensor signals, and each signal is inhibited by a second-order RC filter to suppress high-frequency interference; the cut-off frequency of the second-order RC filter is 50kHz.
[0015] Preferably, the analog-to-digital conversion module comprises a parallel conversion array of 4 AD7606 analog-to-digital converters; the FPGA control module dynamically switches the acquisition channel through the chip selection signal and the channel register to support continuous channel selection.
[0016] Preferably, the SRAM storage module comprises 1 IS67WVE4M16EBLL-70BLA1 SRAM chip, which is divided into two 4M byte storage areas A and B.
[0017] Preferably, the FPGA control module reads the data output by the analog-to-digital conversion module at a rate of 20MHz through the SPI interface, and uses ping-pong operation to realize continuous data acquisition.
[0018] Preferably, the ping-pong operation for continuous data acquisition comprises:
[0019] When the rising edge of the trigger pulse arrives, the FPGA control module pre-acquires and writes into the SRAM storage module A area 200ms in advance, and continues to write into the SRAM storage module A area 800ms after triggering; when the central module reads the A area data, the FPGA control module switches to the SRAM storage module B area for writing; wherein the pulse rising edge is 200μs high level.
[0020] Preferably, in the ping-pong operation for continuous data acquisition, an external trigger mode or an internal trigger mode is used for triggering;
[0021] The external trigger mode comprises: using an ACPL-M72U-000E coupler to detect an external instruction to generate a 200μs pulse, and the FPGA control module triggers data acquisition after detecting the rising edge of the pulse;
[0022] The internal trigger mode comprises: detecting the voltage change rate, and automatically triggering data acquisition when the voltage change rate reaches a threshold.
[0023] Compared with the prior art, the present application has at least the following beneficial effects:
[0024] 1. The utility model discloses a channel density is promoted 100%: from 32 way promotion to 64 way, single module realizes full arrow multi -part synchronous acquisition, and hardware complexity reduces 50%.
[0025] 2. The utility model discloses sampling efficiency doubles: total sampling rate is promoted from 150kHz to 300kHz, and supports single -way 32kHz independent configuration, and adapts to different signal types.
[0026] 3. The utility model discloses storage capacity and efficiency double promotion: 8M byte capacity is 2 times of traditional scheme 4M byte, and ping -pong operation makes read -write bandwidth utilization from 50% promotion to 100%, and data has no loss.
[0027] 4. The utility model discloses format adaptability enhancement: support multiple version telemetry frame format through register configuration, and the starting pulse wave channel position can be flexibly adjusted, and adapts to the standard of different rocket models. BRIEF DESCRIPTION OF DRAWINGS
[0028] Some specific embodiments of the utility model will be described in detail hereinafter with reference to the accompanying drawings in an exemplary but not restrictive manner. The same reference signs in the drawings indicate the same or similar components or parts. Those skilled in the art should understand that these drawings are not necessarily drawn to scale.
[0029] In the drawings:
[0030] Figure 1 It is the overall function framework drawing of rocket telemetry data acquisition system of the utility model;
[0031] Figure 2 It is the acquisition data flow direction drawing in rocket telemetry data acquisition system of the utility model;
[0032] Figure 3 It is the frame format drawing of impact signal trigger and acquisition data in the utility model.
[0033] Among them, the above drawings include the following reference signs:
[0034] 1, signal acquisition and conditioning module, 2, FPGA control module, 3, SRAM storage module, 4, analog-digital conversion module, 5, inner wire total driver, 6, FLASH storage module. DETAILED DESCRIPTION
[0035] To make the purpose, technical scheme and advantage of the present application more clear, the technical scheme of the present application will be described clearly and completely below in combination with specific embodiments of the present application and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without making creative labor belong to the scope of protection of the present application.
[0036] As shown in Figure 1 and Figure 2 A rocket telemetry data acquisition system, comprising: a signal acquisition and conditioning module 1, an analog-to-digital conversion module 4, an FPGA control module 2 and an SRAM storage module 3.
[0037] The signal acquisition and conditioning module 1 is used to acquire sensor signals and buffer, amplify and filter the acquired signals.
[0038] The receiving end of the analog-to-digital conversion module 4 is in communication connection with the signal acquisition and conditioning module 1, and can receive data signals sent by the signal acquisition and conditioning module 1.
[0039] The output end of the analog-to-digital conversion module 4 is connected with the FPGA control module 2 through SPI daisy chain.
[0040] The FPGA control module 2 processes the received data through externally inputted instruction information.
[0041] The SRAM storage module 3 is in communication connection with the FPGA control module 2, and is used to store the processed data.
[0042] The signal acquisition and conditioning module 1 includes 16 pieces of LMP7721 chips for buffering and amplifying the acquired signals; the input impedance of the signal acquisition and conditioning module 1 is >10GΩ, and the noise voltage is <6.5nV / √Hz, ensuring signal integrity. Each piece of LMP7721 chip has 4 channels.
[0043] The signal acquisition and conditioning module 1 can receive 64-channel sensor signals, each channel of which is inhibited by a second-order RC filter to suppress high-frequency interference, and can meet the anti-aliasing requirements of rapidly changing signals. The cutoff frequency of the second-order RC filter is 50kHz. The input bias current of the LMP7721 chip is <20fA, which cooperates with the second-order RC filter to suppress electromagnetic interference in the rocket-borne environment.
[0044] The analog-to-digital conversion module 4 adopts a parallel conversion array composed of 4 pieces of AD7606 analog-to-digital converters; the FPGA control module 2 dynamically switches the acquisition channel through the chip selection signal and the channel register to support continuous channel selection.
[0045] Through the cascade of LMP7721 chips and AD7606 analog-to-digital converters, synchronous acquisition of 64-channel signals can be realized, and only 8 pieces of AD7606 analog-to-digital converters are needed, effectively reducing the number of cascade chips. In addition, the oversampling rate of the digital filter of the AD7606 analog-to-digital converter is 4 times, and the signal-to-noise ratio (SNR) in the 12-bit mode is improved to 95dB, meeting the accuracy requirements of rapidly changing signals.
[0046] The SRAM storage module 3 comprises an IS67WVE4M16EBLL-70BLA1 SRAM chip, and is divided into two 4M byte storage areas A and B.
[0047] The FPGA control module 2 reads the data output by the analog-digital conversion module 4 through the SPI interface at a rate of 20MHz, and realizes continuous data collection by using ping-pong operation.
[0048] Specifically, as shown in the figure, Figure 3 the continuous data collection by using ping-pong operation comprises the following steps:
[0049] When the rising edge of the trigger pulse arrives, the FPGA control module 2 pre-collects and writes data into the area A of the SRAM storage module 3 for 200ms, and continues to write data into the area A of the SRAM storage module 3 for 800ms after the trigger; when the central module reads the data in the area A, the FPGA control module 2 switches to write data into the area B of the SRAM storage module 3; wherein the pulse rising edge is 200us high.
[0050] In the continuous data collection by using ping-pong operation, the external trigger mode or the internal trigger mode is used for triggering;
[0051] The external trigger mode comprises the following steps:
[0052] The internal trigger mode comprises the following steps:
[0053] As another embodiment of the utility model, in a rocket telemetry data acquisition system, when the FPGA control module 2 reads the data output by the analog-digital conversion module 4 through the SPI interface at a rate of 20MHz, and realizes continuous data collection by using ping-pong operation, a configurable telemetry frame structure is used.
[0054] The configurable telemetry frame structure is set as follows:
[0055] The frame structure comprises a 4-byte synchronization header (0xAAAA5555), a 128-bit / channel data area (containing sample values, channel status, and time stamp), and a 32-bit CRC check code.
[0056] As another embodiment of the utility model, a rocket telemetry data acquisition system further comprises an inner line total driver 5 for providing power driving.
[0057] As another embodiment of the utility model, a rocket telemetry data acquisition system further comprises a FLASH storage module 6 in communication connection with the FPGA control module 2. The FLASH storage module 6 is a non-volatile memory module, which can still retain data even after power failure. The FLASH storage module 6 is used for storing programs, data or configuration information.
[0058] For the convenience of description, spatial relative terms such as "above", "upper", "on", "top", etc. can be used herein to describe the spatial positional relationship of one device or feature with other devices or features as shown in the drawings. It should be understood that the spatial relative terms are intended to include different orientations in use or operation in addition to the orientation of the device described in the drawings. For example, if the device in the drawing is inverted, the device described as "above" or "on" other devices or structures will be positioned "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below" orientations. The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein are interpreted accordingly.
[0059] It should be noted that the terms used herein are only for the purpose of describing specific embodiments, and are not intended to limit the exemplary embodiments according to the present application. As used herein, the singular form is intended to include the plural form unless the context clearly indicates otherwise, and it should be understood that when the terms "comprise" and / or "include" are used in the specification, there is a feature, step, work, device, component and / or combination thereof.
[0060] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-described drawings are used to distinguish similar objects, and do not necessarily describe a specific order or sequence. It should be understood that the data used in this way can be interchanged under appropriate circumstances, so that the embodiments of the application described herein can be implemented in an order other than those illustrated or described herein.
[0061] The above merely describes preferred embodiments of the present application and is not intended to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims
1. A rocket telemetry data acquisition system, characterized by, The application relates to a signal acquisition and processing system. The signal acquisition and processing module is used for acquiring sensor signals and buffering, amplifying and filtering the acquired signals. The input end of the analog-digital conversion module is in communication connection with the signal acquisition and processing module and can receive the data signal sent by the signal acquisition and processing module. The output end of the analog-digital conversion module is connected with the FPGA control module through SPI daisy chain. The FPGA control module processes the received data according to the externally input instruction information. The SRAM storage module is in communication connection with the FPGA control module and is used for storing the processed data. The signal acquisition and processing module comprises 16 LMP7721 chips used for buffering and amplifying the acquired signals.
2. The rocket telemetry data collection system of claim 1 wherein, The input impedance of the signal acquisition and processing module is greater than 10 GΩ, and the noise voltage is less than 6.5 nV / sqrt(Hz).
3. The rocket telemetry data collection system of claim 2 wherein, The signal acquisition and processing module can receive 64 sensor signals, and each signal is inhibited by a second-order RC filter to suppress high-frequency interference.
4. The rocket telemetry data collection system of claim 1 wherein, The cut-off frequency of the second-order RC filter is 50 kHz.
5. The rocket telemetry data collection system of claim 1 wherein, The analog-digital conversion module adopts a parallel conversion array composed of four AD7606 analog-digital converters.
6. The rocket telemetry data collection system of claim 5 wherein, The FPGA control module dynamically switches the acquisition channel through the chip selection signal and the channel register to support continuous channel selection.
7. The rocket telemetry data collection system of claim 6 wherein, The SRAM storage module comprises one IS67WVE4M16EBLL-70BLA1 SRAM chip and is divided into two 4M-byte storage areas A and B. The FPGA control module reads the data output by the analog-digital conversion module at a speed of 20 MHz through the SPI interface and realizes continuous data acquisition through ping-pong operation.
8. The rocket telemetry data collection system of claim 7 wherein, The ping-pong operation for realizing continuous data acquisition comprises the following steps. When the rising edge of the trigger pulse arrives, the FPGA control module pre-acquires data 200 ms in advance and writes the data into the A area of the SRAM storage module, and continues to write the data into the A area of the SRAM storage module 800 ms after the trigger. When the central module reads the data in the A area, the FPGA control module is switched to write data into the B area of the SRAM storage module. The external trigger mode comprises the following steps. The ACPL-M72U-000E coupler is used to detect the external instruction to generate a 200-microsecond pulse. The FPGA control module detects the rising edge of the pulse and triggers data acquisition. The internal trigger mode comprises the following steps. The voltage change rate is detected. When the voltage change rate reaches the threshold, the data acquisition is automatically triggered.