A replaceable space imaging test system

Abstract

The present invention provides a replaceable space imaging test system, including a test control system and a replaceable test sub-sample, the test sub-sample is connected to the test control system through a connector; the test sub-sample is a seal encapsulating a test object and a space imaging test instrument, the space imaging test instrument provides a test environment for the test object and collects test data, the test data includes image data and state data of the test object, the state data includes at least temperature signal data and electrical signal data; the test control system receives external instructions to power and control the space imaging test instrument, judges the state of the test object according to the state data, forms an acquisition control strategy to transmit the collected test data to the ground. The present invention can obtain the on-orbit movement and change rules of the test object, adopts strategies to capture and transmit data to key test features in response to downlink resource limitations and transmission link failures, and can stably and reliably implement multi-batch continuous testing.

Description

Technical Field

[0001] The invention relates to the technical field of space experiments, and in particular to a replaceable space imaging experiment system. Background Art

[0002] The construction of my country's space station has provided more and more space experiment resources. Imaging observation is an important and effective means of space experiment observation. At present, there are the following problems in space imaging experiments that need to be solved:

[0003] For different types of test projects, a universal test system is needed to provide standard interfaces and diversified test and detection methods to achieve continuous testing and simple replacement of space test projects and reduce space operations. At the same time, the space science test device is a fully automatic device without human intervention, which needs to independently complete environmental simulation, test state control, test process monitoring, test data transmission and other tasks.

[0004] The test device runs for a long time, and for key test feature moments, the workload of manual interpretation and intervention needs to be reduced, and the data should be automatically captured and transmitted to the ground for analysis by researchers. For limited data transmission resources, reasonable management and blocking management are required to ensure the smooth progress of the test and the reliable transmission of important test data. Summary of the invention

[0005] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and provide a replaceable space imaging test system that can stably and reliably perform on-orbit tests on test objects, capture key features and store and transmit data, and realize multiple batches of continuous tests.

[0006] The technical solution of the present invention is:

[0007] A replaceable space imaging test system comprises a test control system and a replaceable test sub-sample, wherein the test sub-sample is connected to the test control system via a connector, wherein the connector comprises a sub-sample end connector respectively arranged on the test sub-sample and a control end connector arranged on the test control system;

[0008] The test sub-sample is a seal encapsulating a test object and a space imaging test instrument, the space imaging test instrument provides a test environment for the test object and collects test data and sends it to a test control system, the test data includes image data and state data of the test object, and the state data includes at least temperature signal data and electrical signal data;

[0009] The test control system includes a test instrument control module, a test controller and a data transmission module;

[0010] Test instrument control module: receives external instructions sent by the test controller, supplies power to and controls the space test instrument; receives test data collected by the space imaging test instrument, sends the image data to the data transmission module, and sends the status data to the test controller;

[0011] Test controller: receives external instructions and sends them to the test instrument control module; receives status data and sends them to the data transmission module; determines whether the test object has key features based on the status data, forms different acquisition control strategies based on whether the test object has key features and sends them to the data transmission module;

[0012] Data transmission module: receives the test data sent by the test instrument control module and the test controller, obtains the test data to be transmitted from the test data according to the acquisition control strategy, and uses the data transmission strategy to transmit the test data to be transmitted to the ground.

[0013] Preferably, when the test object shows key features, the test controller forms a capture and acquisition control strategy, specifically:

[0014] For image data:

[0015] The t before the test object shows the key characteristics pre Image data at time and t after it appears after All image data collected within a certain period of time are cached and transmitted to the ground in sequence;

[0016] For status data:

[0017] The collected status data is transmitted to the ground in each signal sampling cycle.

[0018] Among them, t pre is the time period before the test subject shows the key characteristics of the state change, t after It is the time period that includes the change in state of the experimental subject after the key characteristics appear.

[0019] Preferably, when the test object does not show the key features, the test controller forms a conventional acquisition control strategy, specifically:

[0020] For image data:

[0021] Sampling period of the current signal and the previous t pre The image data collected during the time is cached and the remaining image data is deleted. DL The most recently acquired image in the cached image data is transmitted to the ground, and the signal sampling period is the acquisition period of the state data; wherein, t DL is a fixed length of time;

[0022] For status data:

[0023] The collected status data is transmitted to the ground in each signal sampling cycle.

[0024] Preferably, the data transmission module adopts a data transmission strategy to transmit the test data to be transmitted to the ground, specifically:

[0025] The test data is transmitted in the form of data frames, which include image data frames and state data frames. The temperature signal data and electrical signal data in each signal sampling period form a state data frame for transmission respectively. Each image is divided into multiple image data frames for transmission. Each image data frame is numbered in sequence and transmitted in turn. After all image data frames of an image are transmitted, the next data frame is transmitted.

[0026] Normal transmission mode: If the data frame is transmitted successfully, a transmission success response mark will be received, and then the next data frame will be transmitted. If the transmission success response mark is not received within t1 time, the transmission waiting mode will be entered; t1 is the first transmission waiting time threshold;

[0027] Transmission waiting mode: continue to try to send the current data frame. If no response mark indicating successful transmission is received within t1 for N consecutive times, enter the fault handling mode; otherwise, resume the normal transmission mode and enter the transmission of the next data frame; N is a positive integer;

[0028] Fault handling mode: continue to try to send the current data frame, and the waiting time is extended to t2. If the response mark of successful transmission is not received for N consecutive times within t2, for image data frames, retry the transmission at the t2 time interval starting from the first data frame of the current image, and for status data frames, continue to retry the transmission at the t2 time interval; until the response mark of successful transmission is received, restore the normal transmission mode, and enter the transmission of the next data frame; t2 is the second transmission waiting time threshold;

[0029] In the transmission waiting mode and the fault handling mode, the data transmission module caches the data to be transmitted and manages the cached data using a cache space management strategy.

[0030] Preferably, the data transmission module caches the data to be transmitted and manages the cached data using a cache space management strategy, specifically:

[0031] Cache the image data into the first cache area, and cache the status data into the second cache area;

[0032] For the first cache area, if the storage space occupancy exceeds 80%, 50% of the image data therein is deleted at a certain time interval according to the cache time sequence;

[0033] For the second cache area, if the number of data items exceeds the data cache threshold, 50% of the data will be deleted at a certain time interval in the order of storage time.

[0034] Preferably, it is characterized in that

[0035] t1=10×t respond

[0036] t2>1000×t respond

[0037] Among them, t respond The average time it takes to successfully receive a response flag for normal data transmission.

[0038] Preferably, 5≤N≤10.

[0039] Preferably, the test controller determines whether the test object has a key feature according to the state data, specifically:

[0040] When the temperature signal of the test object is continuous N r The signal sampling period exceeds the temperature threshold or the electrical signal continues N r When a sampling cycle exceeds the electrical signal threshold, it is determined that the test object has a key feature, otherwise the key feature does not appear.

[0041] Preferably, the N r Satisfies the following expression:

[0042] 10 <N r <t pre / (2×t s )

[0043] Among them, t s is the signal sampling period.

[0044] Preferably, the space imaging test instrument includes a visible light camera, an infrared camera, an LED light source, an electrical signal sensor, and a motor; the visible light camera is used to collect image data of the test object; the infrared camera is used to collect temperature signal data of the test object; the LED light source is used to provide lighting; the electrical signal sensor is used to collect electrical signal data of the test object; and the motor is used to adjust the movement environment of the test object or adjust the observation angle of the visible light camera and the infrared camera.

[0045] The advantages of the present invention compared with the prior art are:

[0046] (1) A replaceable space imaging test system of the present invention is designed with a replaceable test sub-sample encapsulating a test instrument and a test object. The test sub-sample is connected to the test control system through a connector. Different test sub-samples can provide different test environment simulations for the test object and perform state observation. The sample can be conveniently replaced as a whole, and it is easy to implement on-orbit operation, thereby realizing multiple batches of continuous tests.

[0047] (2) The present invention determines the state of the sample object based on the state data and adopts different acquisition control strategies, which can achieve key feature capture and data acquisition of the test object under the condition of limited downlink resources for analysis by researchers;

[0048] (3) The present invention adopts a data transmission strategy to cache and transmit downlink data in response to downlink resource limitations and downlink transmission link failures, and stores and manages accumulated data to ensure data continuity and system operation security;

[0049] (4) The present invention can realize continuous and comprehensive observation of space test objects under on-orbit conditions, and capture and record abnormal conditions, and has strong practicality. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] Figure 1 This is a schematic diagram of the structure of the replaceable space imaging test system of the present invention;

[0051] Figure 2 It is a schematic diagram of the data transmission mode of the present invention. DETAILED DESCRIPTION

[0052] The following detailed description of the present invention will make the features and advantages of the present invention more clear and explicit.

[0053] A replaceable space imaging test system, such as Figure 1 As shown, it includes a test sample and a test control system, wherein the test sample is a replaceable component and the test control system is a fixed part. The test sample includes a sample end connector, and the test control system includes a control end connector, and the two are connected through the connector; after a test sample completes the test, the connector is unplugged after the system is powered off, and the new test sample connector is connected to the control end connector, and the test sample replacement can be completed.

[0054] The test specimen is a sealed structure encapsulating a test object and a space imaging test instrument, and is used to provide a test environment, receive control instructions and signals from a test control system, collect test data and send it to the test control system. The test data includes image data and status data of the test object, and the status data includes at least temperature signal data and electrical signal data.

[0055] Specifically, it includes a visible light camera, an infrared camera, an LED light source, an electrical signal sensor and a motor.

[0056] Visible light camera: collects image data of the test object to observe the change process of the test object;

[0057] Infrared camera: collects temperature signal data of the test object to observe the characteristics of temperature field changes;

[0058] LED light source: provides illumination for the interior of the sample;

[0059] Electrical signal sensor: collects electrical signal data of the test object;

[0060] Motor: Control the motion environment of the test object or adjust the camera observation angle.

[0061] In-orbit tests need to prevent leakage of test objects from polluting the space environment. The above-mentioned components only have electrical signal connections to the outside, which is convenient for the sealing design of test samples, as well as for overall replacement, and easy to implement in-orbit operations.

[0062] The test control system is the fixed part, including the test instrument control module, the test controller and the data transmission module.

[0063] Test instrument control module: receives external instructions sent by the test controller, powers and controls the space test instrument and collects its status information; receives test data collected by the space imaging test instrument, sends the image data to the data transmission module, and sends the status data to the test controller;

[0064] Specifically, the visible light camera is powered, controlled and its status information is collected, image data is sent to the data transmission module, and its status information is sent to the test controller;

[0065] Power the infrared camera, control it and collect its status information, and send the temperature signal data and its status information to the test controller.

[0066] Perform power-on and power-off operations on the LED light source and collect its status information, and send its status information to the test controller;

[0067] Powering, controlling and collecting status information of the electrical signal sensor, and sending the electrical signal data and its status information to the test controller;

[0068] The drive motor rotates and collects its status information, and sends its status information to the test controller.

[0069] Test controller: receives external instructions and sends them to the test instrument control module; determines whether the test object has key features based on the status data. If no key features appear, forms a conventional acquisition control strategy and sends it to the storage data transmission module; if key features appear, forms a capture acquisition control strategy and sends it to the data transmission module; sends the status data to the data transmission module; sends the status data of each spatial imaging test instrument to the data transmission module.

[0070] Specifically, key features capture:

[0071] The temperature signal acquisition value of the infrared camera and the acquisition value of the electrical signal sensor are used to determine whether the test has key features. The method is threshold judgment, and the temperature threshold is set to T threshold , the electrical signal threshold is U threshold The threshold is determined by the characteristics of the test object. When the test temperature acquisition value or the electrical signal acquisition value continues for N r When the number of beats exceeds the threshold, the system enters the capture processing mode. Generally, there should be:

[0072] 10 <N r <t pre / (2×t s )

[0073] Among them, t s is the signal sampling period.

[0074] This setting prevents the system from malfunctioning due to an error in the one-shot acquisition signal, while ensuring that image data before and after the key features appear can be acquired.

[0075] Conventional acquisition control strategy:

[0076] For image data: collect images at the highest acquisition frequency of the visible light camera, and perform the current signal sampling period and the previous t pre The image data collected within the time is cached and the remaining image data is deleted; the timer is used to count the time every t DL Transmitting the most recently acquired image in the cached image data to the ground, wherein the signal sampling period is the acquisition period of the state data;

[0077] For status data:

[0078] The collected status data is transmitted to the ground in each signal sampling cycle.

[0079] This method meets the needs for long-term observation of slowly varying processes and adapts to the limited data downlink capabilities on orbit.

[0080] Capture acquisition control strategy:

[0081] For image data:

[0082] The t before the test subject shows the key feature pre The image data within the time is stored in the storage area, and continues to store t after After the image data of the duration is stored, t pre +t after This operation can obtain the data before the key features of the test occur. pre and after occurrence after The image data of the duration can be used to study the changes in the state of the test object.

[0083] For status data:

[0084] The collected status data is transmitted to the ground in each signal sampling cycle.

[0085] Among them, t pre is the time period before the test subject shows the key characteristics of the state change, t after The time period that includes the state change after the test subject shows key characteristics. pre and t after The start and duration of the key features of the test object obtained by prior prediction or ground comparison test are determined and are related to the characteristics of the test object. In order to ensure that the test data of the key features of the test object and the state changes before and after the key features appear can be collected, the t before the key features appear in the test object according to the state judgment is pre The data within the time period is collected to obtain the status data before the key features appear, and the status data after the key features of the test occur. after Collect data within a certain period of time and obtain the status data after the key features appear.

[0086] t DL It is determined by the time interval between the state changes of the test object, and also takes into account the allowable conditions of the on-orbit downlink resources.

[0087] Specifically, t DL It can generally be determined by the maximum amount of data transmitted on orbit per day, t DL >M limit / (M pc ×60×24), M limit M is the maximum daily data transmission volume. pc is the amount of image data transmitted each time, at this time t DL The unit is minutes.

[0088] Data transmission module: receives the test data sent by the test instrument control module and the test controller, obtains the test data to be transmitted from the test data according to the conventional acquisition control strategy or the capture acquisition control strategy, and uses the data transmission strategy to transmit the test data to be transmitted to the ground.

[0089] During the operation of the space test device, a large amount of data will be continuously generated. In order to ensure the long-term stable and reliable operation of the system, a data transmission and fault management method is designed. While ensuring reliable and stable data transmission, this method has the function of processing image data transmission congestion. When there is no response to the image transmission response, the transmission mode can be intelligently converted to reduce data pressure, and the normal transmission function can be restored after the response is normal.

[0090] Data transmission is divided into 3 modes: Figure 2 shown.

[0091] The test data is transmitted in the form of data frames, which include image data frames and status data frames. The temperature signal data and electrical signal data in each signal sampling period form a status data frame for transmission respectively. The amount of data in an image is large, and the length of data transmitted on track is limited. The image is divided into multiple data frames for transmission. Each frame is numbered in sequence and transmitted in turn. The image data must be guaranteed to be transmitted reliably in sequence. Any sequence error and frame loss will result in decoding failure. After all image data frames of an image are transmitted, the next data frame will be transmitted.

[0092] Normal transmission mode: If the data frame is transmitted successfully, a successful transmission response mark will be received, and then the next data frame will be transmitted. Each image starts to be transmitted from the first frame of data. The response method is used to ensure that the data is received reliably and in order.

[0093] After the data frame is sent, if no transmission success response mark is received within t1 time, the transmission wait mode is entered; where t1 is the first transmission wait time threshold;

[0094] Transmission waiting mode: Continue to try to send the current data frame. If the response mark of successful transmission is not received for N consecutive times within t1 time, enter the fault handling mode;

[0095] If a successful transmission response is received during this process, the normal transmission mode is restored and the next data frame transmission begins;

[0096] Generally, t1 can be set to 10×t respond .

[0097] Among them, t respond The average time it takes to successfully receive a response flag for normal data transmission.

[0098] Fault handling mode: continue to try to send the current data frame, and the waiting time is extended to t2. If the response mark of successful transmission is not received for N consecutive times within t2, for image data frames, retry the transmission at the t2 time interval starting from the first data frame of the current image, and for status data frames, continue to retry the transmission at the t2 time interval; until the response mark of successful transmission is received, restore the normal transmission mode, and enter the transmission of the next data frame; t2 is the second transmission waiting time threshold;

[0099] Generally, t2>1000×t respond .

[0100] In the transmission waiting mode and the fault handling mode, the data transmission module caches the data to be transmitted and manages the cached data using a cache space management strategy.

[0101] Setting the fault handling mode and increasing the transmission interval can alleviate transmission failures caused by data congestion. Continuing to transmit can effectively utilize limited data downlink resources. After trying N times, restart the transmission from the first frame. Considering that long-term transmission failures may be due to a fault at the data receiving end, the previously transmitted data may be unreliable and need to be retransmitted.

[0102] Among them, 5≤N≤10, and N is a positive integer.

[0103] In fault handling mode, data cannot be transmitted to the ground. At this time, data is stored inside the system. If too much storage space is occupied or there are too many data files, the system operation speed will be affected. Storage space management operations are required:

[0104] Cache the image data into the first cache area, and cache the status data into the second cache area;

[0105] For the first cache area, query the storage space, if the storage space occupancy exceeds 80%, delete 50% of the image data at a certain time interval according to the cache time sequence;

[0106] For the second cache area, the status data storage space is small but the number of files is large, so it is managed by quantity; if the number of data exceeds the threshold, 50% of the data will be deleted at a certain time interval in the order of storage time. The threshold is determined by the system's ability to handle the number of files.

[0107] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A replaceable space imaging test system, characterized in that: It includes a test control system and a replaceable test sub-sample, wherein the test sub-sample is connected to the test control system via a connector, and the connector includes a sub-sample end connector respectively arranged on the test sub-sample and a control end connector arranged on the test control system; The test sub-sample is a seal encapsulating a test object and a space imaging test instrument, the space imaging test instrument provides a test environment for the test object and collects test data and sends it to a test control system, the test data includes image data and state data of the test object, and the state data includes at least temperature signal data and electrical signal data; The test control system includes a test instrument control module, a test controller and a data transmission module; Test instrument control module: receives external instructions sent by the test controller, supplies power to and controls the space test instrument; receives test data collected by the space imaging test instrument, sends the image data to the data transmission module, and sends the status data to the test controller; Test controller: receives external instructions and sends them to the test instrument control module; receives status data and sends them to the data transmission module; determines whether the test object has key features based on the status data, forms different acquisition control strategies based on whether the test object has key features and sends them to the data transmission module; Data transmission module: receiving the test data sent by the test instrument control module and the test controller, obtaining the test data to be transmitted from the test data according to the acquisition control strategy, and transmitting the test data to be transmitted to the ground using the data transmission strategy; When the test object shows key features, the test controller forms a capture and acquisition control strategy, specifically: For image data: The t before the test subject shows the key feature pre Image data at time and t after it appears after All image data collected within a certain period of time are cached and transmitted to the ground in sequence; For status data: The collected status data is transmitted to the ground in each signal sampling cycle. Among them, t pre is the time period before the test subject shows the key characteristics of the state change, t after It is the time period that includes the change in status of the test subject after the onset of key characteristics; When the test object does not show key features, the test controller forms a conventional acquisition control strategy, specifically: For image data: Sampling period of the current signal and the previous t pre The image data collected during the time is cached and the remaining image data is deleted. DL The most recently acquired image in the cached image data is transmitted to the ground, and the signal sampling period is the acquisition period of the state data; wherein, t DL is a fixed length of time; For status data: The collected status data is transmitted to the ground in each signal sampling cycle; The test controller determines whether the test object has key features based on the status data, specifically: When the temperature signal of the test object is continuous N r The signal sampling period exceeds the temperature threshold or the electrical signal continues N r When a sampling cycle exceeds the electrical signal threshold, it is determined that the test object has a key feature, otherwise the key feature does not appear.

2. The replaceable space imaging test system according to claim 1, characterized in that: The data transmission module transmits the test data to be transmitted to the ground using a data transmission strategy, specifically: The test data is transmitted in the form of data frames, which include image data frames and state data frames. The temperature signal data and electrical signal data in each signal sampling period are respectively formed into a state data frame for transmission; Each image is divided into multiple image data frames for transmission. Each image data frame is numbered in sequence and transmitted in turn. After all image data frames of an image are transmitted, the next data frame is transmitted. Normal transmission mode: If the data frame is transmitted successfully, a transmission success response mark will be received, and then the next data frame will be transmitted. If the transmission success response mark is not received within t1 time, the transmission waiting mode will be entered; t1 is the first transmission waiting time threshold; Transmission waiting mode: Continue to try to send the current data frame. If the response mark of successful transmission is not received for N consecutive times within t1 time, enter the fault handling mode; Otherwise, the normal transmission mode is restored and the transmission of the next data frame is started; N is a positive integer; Fault handling mode: continue to try to send the current data frame, and the waiting time is extended to t2. If the response mark of successful transmission is not received for N consecutive times within t2, for image data frames, retry the transmission at the t2 time interval starting from the first data frame of the current image, and for status data frames, continue to retry the transmission at the t2 time interval; until the response mark of successful transmission is received, restore the normal transmission mode, and enter the transmission of the next data frame; t2 is the second transmission waiting time threshold; In the transmission waiting mode and the fault handling mode, the data transmission module caches the data to be transmitted and manages the cached data using a cache space management strategy.

3. The replaceable space imaging test system according to claim 2, characterized in that: The data transmission module caches the data to be transmitted and manages the cached data using a cache space management strategy, specifically: Cache the image data into the first cache area, and cache the status data into the second cache area; For the first cache area, if the storage space occupancy exceeds 80%, 50% of the image data therein is deleted at a certain time interval according to the cache time sequence; For the second cache area, if the number of data items exceeds the data cache threshold, 50% of the data will be deleted at a certain time interval in the order of storage time.

4. The replaceable space imaging test system according to claim 2, characterized in that: t1=10×t respond t2>1000×t respond Among them, t respond The average time it takes to successfully receive a response flag for normal data transmission.

5. The replaceable space imaging test system according to claim 2, characterized in that: 5≤N≤10。 6. The replaceable space imaging test system according to claim 1, characterized in that: The N r Satisfies the following expression: 10<N r <t pre / (2×t s ) Among them, t s is the signal sampling period.

7. The replaceable space imaging test system according to claim 6, characterized in that: The space imaging test instrument includes a visible light camera, an infrared camera, an LED light source, an electrical signal sensor, and a motor; the visible light camera is used to collect image data of the test object; the infrared camera is used to collect temperature signal data of the test object; the LED light source is used to provide illumination; the electrical signal sensor is used to collect electrical signal data of the test object; and the motor is used to adjust the movement environment of the test object or adjust the observation angle of the visible light camera and the infrared camera.

Images