A high-reliability telemetry link ignition control method for multi-aircraft space-time interaction

Abstract

A kind of high-reliability telemetry link ignition control method for multi-aircraft space-time interaction, comprising the following steps: step 1: real-time calculation test aircraft remaining flight time and generates ignition control instruction, the ignition control instruction is placed in telemetry frame, is passed to the S-band telemetry detection station set at ground target aircraft by telemetry link of test aircraft;Step 2: S-band telemetry detection station carries out real-time analysis to telemetry data and passes to telemetry ignition control software by network interface according to period after analysis of telemetry frame;Step 3: telemetry ignition control software starts internal timing;Step 4: telemetry ignition control software carries out ignition control.The present application can be applied to the case of information collaborative matching between multiple aircrafts, provides implementation approach for more complex ignition timing control;Meanwhile, multi-level criterion collaborative interaction design is adopted, improve the reliability of ignition control under complex space-time matching.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of measurement and control communication, and particularly relates to a high-reliability telemetry link ignition control method for multi-aircraft space-time interaction. BACKGROUND

[0002] In the field of space measurement and control, wireless ignition mode has been increasingly applied to actual launch tasks. In the scene of complex space-time information interaction and control among multiple aircrafts, reliable ignition is an important condition to ensure success.

[0003] Currently, the key information interaction among aircrafts mainly relies on dedicated data link equipment, which occupies the aircraft load resources and communication channel resources. Once the data link equipment fails, the data link channel will be invalid throughout the whole process, which will have an irreversible impact on the interaction of key information in subsequent tasks. SUMMARY

[0004] To solve the above problems, the application provides a high-reliability telemetry link ignition control method for multi-aircraft space-time interaction. Through multi-level wireless communication link backup and multi-level ignition criterion backup design, high-reliability ignition control under complex space-time matching of multiple aircrafts is realized. Without occupying the limited resources of the aircraft itself, the probability of mis-ignition is reduced, which can meet the needs of different application scenarios.

[0005] A high-reliability telemetry link ignition control method for multi-aircraft space-time interaction includes the following steps:

[0006] Step 1: Real-time calculation of the remaining flight time of the test aircraft and generation of the ignition control instruction, the ignition control instruction is placed in the telemetry frame, and is transmitted to the S-band telemetry detection station set at the target aircraft on the ground through the telemetry link of the test aircraft;

[0007] Step 2: The S-band telemetry detection station analyzes the telemetry data in real time and transmits the analyzed telemetry frame to the telemetry ignition control software through the network interface according to the period;

[0008] Step 3: The telemetry ignition control software starts internal timing;

[0009] Step 4: The telemetry ignition control software performs ignition control.

[0010] In step 1, the ignition control instruction includes the dynamic order, time sequence point 1, time sequence point 2, time sequence point 3, and relative time sequence point time. The dynamic order is the main ignition criterion, and the time sequence point 1, time sequence point 2, time sequence point 3, and relative time sequence point time are the time sequence point backup ignition criterion.

[0011] The period is 25 ms one beat / 50 ms two beats.

[0012] The telemetry ignition control software reads the telemetry frame and puts it into the cache, and then receives the telemetry frame periodically every 1 ms, and analyzes the ignition control instruction data structure.

[0013] Further, in step 3, after the telemetry ignition control software receives the valid time sequence point and the relative time sequence point time for the first time, a timer is started with the value of "current time sequence point binding value-current relative time sequence point time", and before a new time sequence point is received, the telemetry ignition control software will no longer continue to respond to the received relative time sequence point time; if a new time sequence point is received, the original timer is stopped, and the timer is started again with the value of "new time sequence point binding value-new relative time sequence point time";

[0014] If 3 beat command instructions are accumulated in the telemetry data, a "ignition instruction" is sent to the ground target aircraft control system to implement the main criterion ignition; if the internal timer of the telemetry ignition control software is completed, the "ignition instruction" is sent to the ground target aircraft control system to implement the time sequence point backup ignition; wherein any one of the main ignition criterion and the time sequence point backup ignition criterion meets the requirement, that is, the "ignition instruction" is sent; after the ignition instruction is sent, no other ignition criterion is responded.

[0015] In step 4, the telemetry ignition control software periodically sends an ignition instruction and receives the "ignition response" information sent by the ground target aircraft control system; after receiving the "ignition response" information, the sending of the ignition instruction is stopped, and the ignition instruction is correctly sent to the ground target aircraft control system in the form of a log, and the sending and receiving data are saved locally; and the sending time of the "ignition instruction", the criterion triggering ignition and the receiving time of the "ignition response" are recorded in the log.

[0016] A high-reliability telemetry link ignition control system for multi-aircraft space-time interaction includes an S-band telemetry detection station and a telemetry ignition test bench with built-in telemetry ignition control software; a test aircraft synchronously packages real-time calculated ignition control instructions in a central programmer, and the ignition control instructions are sent to the ground target aircraft control system through an S-band transmitter after processing and through a telemetry link backup; the S-band telemetry detection station receives the telemetry data of the test aircraft in real time; the telemetry ignition control software completes data selection from the telemetry frame, performs data analysis and judgment, and sends an ignition instruction to the ground target aircraft control system after judging the ignition instruction in the telemetry frame to implement ignition control.

[0017] The beneficial effects of the present application are as follows:

[0018] The present application has the advantages of high real-time performance, good reliability and strong universality;

[0019] (1) Realize the full release of limited communication link resources, use telemetry data channel idle resources to transfer ignition control information, realize multi-level standby of communication link, ensure that reliable ignition can be completed under the condition of failure of main ignition communication link;

[0020] (2) On the basis of multi-level standby of communication link, realize multi-level standby design of ignition criterion, reduce the probability of misfire, can adapt to more complex ignition timing control scene, can meet the needs of different application scenes;

[0021] (3) Realize the design of long-distance high-speed real-time key information interaction, can expand the information cooperation direction between multiple aircrafts with telemetry requirements, make the aircraft have the ability of "one machine with multiple controls", can balance the universality and real-time performance. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 is the schematic diagram of the telemetry standby ignition control method of the application;

[0023] Figure 2 is the schematic diagram of the ignition control instruction data structure of the application;

[0024] Figure 3 is the schematic diagram of the telemetry frame analysis process of the application;

[0025] Figure 4 is the schematic diagram of the ignition judgment logic of the application. DETAILED DESCRIPTION

[0026] The technical solutions of the application will be further described in detail below in combination with the drawings and specific embodiments. Obviously, the described embodiments are only part of the embodiments of the application, not all the embodiments. Based on the embodiments of the application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the application.

[0027] A high-reliability telemetry link ignition control method for multi-aircraft space-time interaction, comprising the following steps:

[0028] Step 1, after the test aircraft starts to control, according to the distance between the test aircraft and the ground target aircraft minus the ignition distance / the approach speed, the remaining flight time is calculated in real time and the ignition control instruction (including the dynamic order, timing point 1, timing point 2, timing point 3, and relative timing point time) is generated, the ignition control instruction is placed in the telemetry frame, and is transmitted to the S-band telemetry detection station set at the ground target aircraft through the telemetry link of the test aircraft, as shown in Figure 1 .

[0029] Step 2, the S-band telemetry detection station analyzes the telemetry data in real time and transmits the analyzed telemetry frame to the telemetry ignition control software through a network interface according to a period (25 ms for one beat / 50 ms for two beats). The telemetry analysis module of the telemetry ignition control software uses the ReadyRead of UdpSocket to read the telemetry frame and put it into a cache, and then receives the telemetry frame according to a 1 ms period, and analyzes the data frame structure (wherein one packet of telemetry frame contains 5 beat ignition control instruction data) in Figure 2 , and the whole analysis process is shown in Figure 3 .

[0030] Step 3, the telemetry ignition control software itself has an internal timing function, and after receiving the time of the first valid time point and the relative time point, the timing is started with "current time point binding value-current relative time point time". Before receiving a new time point, the received relative time point time is no longer continuously responded; if a new time point is received, the original timer is stopped, and the timing is started again with "new time point binding value-new relative time point time".

[0031] Step 4, the telemetry ignition control software discriminates the dynamic instruction, if 3 beat dynamic instruction is accumulated and recognized in the telemetry data, a "ignition instruction" is sent to the ground target spacecraft control system to implement the main criterion ignition; if the internal timing of the software is completed, the "ignition instruction" is sent to the ground target spacecraft control system to implement the time point backup ignition; wherein any one of the software main ignition criterion and the time point backup ignition criterion meets the requirement, and the "ignition instruction" is sent; after the ignition instruction is sent, other ignition criteria are no longer responded, and the ignition judgment logic is shown in Figure 4 .

[0032] Step 5, the telemetry ignition control software uses UDP to periodically (50 ms) send the ignition instruction, and receives the "ignition reply" information sent by the ground target spacecraft control system; after receiving the "ignition reply" information, the sending of the ignition instruction is stopped, and the ignition instruction is correctly sent to the ground target spacecraft control system in the form of a log, and the sending and receiving data ("ignition instruction", "ignition reply" and heartbeat information) are saved locally; and the sending time of the "ignition instruction", the criterion triggering ignition and the receiving time of the "ignition reply" are recorded in the log.

[0033] In the application, in order to ensure reliable ignition in the case of full data link failure caused by ignition data link device failure, the test vehicle synchronously packages the real-time calculated ignition control instruction in the central programmer, and sends the ignition control instruction to the ground target vehicle through the S-band telemetry link. The ground target vehicle is provided with an S-band telemetry detection station for real-time receiving of the telemetry data of the test vehicle. The ground is provided with a telemetry ignition test bench, and the telemetry ignition control software is built in the telemetry ignition test bench. The telemetry ignition control software completes data selection from the telemetry frame, performs data analysis and judgment, and sends the ignition instruction to the ground target vehicle after judging the ignition instruction in the telemetry frame, thereby implementing ignition control. Figure 1

[0034] In order to realize high-reliability telemetry link ignition, the main ignition criterion based on the dynamic order identification code and the time sequence point backup ignition criterion based on time sequence point 1, time sequence point 2, time sequence point 3 and relative time sequence point time are designed to cooperatively complete ignition time sequence control.

[0035] The ignition instruction frame sent by the vehicle central programmer includes the dynamic order, time sequence point 1, time sequence point 2, time sequence point 3 and relative time sequence point time. In the flight process, the time sequence point 1, time sequence point 2, time sequence point 3 and dynamic order are sequentially sent to the ground S-band telemetry detection station through the telemetry link, and when the time sequence point is updated, the relative time sequence point time is also reset.

[0036] The S-band telemetry detection station completes real-time processing of various types of telemetry parameter data, and transmits the analyzed telemetry frame to the telemetry ignition control software through the network. The telemetry ignition control software selects data according to the user-specified sub-frame and sub-frame channel number, analyzes the ignition time sequence control data from the detection station telemetry code stream in real time, and obtains the "flight timing time", "relative time sequence point time" and "ignition time sequence control word (including dynamic order, time sequence point 1, time sequence point 2, time sequence point 3)" information. At the same time, the telemetry ignition control software continuously performs CRC check on the ignition time sequence control data, and the frames that do not pass the check will be discarded.

[0037] After the ignition criterion is met, the telemetry ignition control software sends the "ignition instruction" to the ground target rocket control system. The "ignition instruction" adds software flight timing time and local time stamp information. For the main ignition, the software flight timing time adopts the flight timing time value in the message of the third order in the cumulative three order dynamic order instruction; for the backup ignition, the software flight timing time adopts the flight timing time value in the message corresponding to the current updated effective time sequence point; the "ignition instruction" is periodically sent in the UDP mode, and the sending period is 50 ms.

[0038] ​The application realizes high-reliability matching ignition control of a test aircraft and a ground target aircraft in a time-space interaction background. The application can be applied to information coordination matching among multiple aircrafts, and provides an implementation approach for more complex ignition timing control. Meanwhile, a multi-level criterion coordination interaction design is adopted, and the reliability of the ignition control under complex time-space matching is improved.

[0039] The above description of disclosed embodiments enables one of ordinary skill in the art to make or use the application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein can be applied to other embodiments without departing from the scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A high-reliability telemetry link ignition control method for multi-aircraft space-time interaction, characterized in that, The method comprises the following steps: Step 1: Real-time calculation of the remaining flight time of the test aircraft and generation of ignition control instructions, placement of the ignition control instructions in a telemetry frame, and transmission of the ignition control instructions to the S-band telemetry detection station arranged at the target aircraft on the ground through the telemetry link of the test aircraft; Step 2: Real-time analysis of the telemetry data by the S-band telemetry detection station and transmission of the analyzed telemetry frame to the telemetry ignition control software through the network interface according to a period; Step 3: Start of internal timing of the telemetry ignition control software; Step 4: Ignition control by the telemetry ignition control software.

2. The high-reliability telemetry link ignition control method for multi-UAV space-time interaction according to claim 1, characterized in that, In step 1, the ignition control instructions include a dynamic order, a time sequence point 1, a time sequence point 2, a time sequence point 3, and a relative time sequence point time; the dynamic order serves as a main ignition criterion, and the time sequence points 1, 2, and 3 and the relative time sequence point time serve as time sequence point backup ignition criteria.

3. The high-reliability telemetry link ignition control method for multi-UAV space-time interaction according to claim 1, characterized in that, The period is 25 ms for one beat / 50 ms for two beats.

4. The high-reliability telemetry link ignition control method for multi-UAV space-time interaction according to claim 1, characterized in that, The telemetry ignition control software reads the telemetry frame and places it in a cache, and then receives the telemetry frame periodically at a period of 1 ms, and analyzes the ignition control instruction data structure.

5. The high-reliability telemetry link ignition control method for multi-UAV space-time interaction according to claim 2, characterized in that, In step 3, after the telemetry ignition control software receives a valid time sequence point and a relative time sequence point time for the first time, the software starts timing with the "current time sequence point value-current relative time sequence point time", and before receiving a new time sequence point, the software no longer continues to respond to the received relative time sequence point time; If a new time sequence point is received, the original timer is stopped, and the timer is restarted with the "new time sequence point value-new relative time sequence point time"; If three beat dynamic order instructions are accumulated and identified in the telemetry data, a "ignition instruction" is sent to the ground target aircraft control system, and main criterion ignition is implemented; if the internal timing of the telemetry ignition control software is completed, the "ignition instruction" is sent to the ground target aircraft control system, and time sequence point backup ignition is implemented; any of the main ignition criterion and the time sequence point backup ignition criterion meets the requirements, and the "ignition instruction" is sent; after the ignition instruction is sent, no response is given to subsequent other ignition criteria.

6. The high-reliability telemetry link ignition control method for multi-UAV space-time interaction according to claim 2, characterized in that, In step 4, the telemetry ignition control software periodically sends an ignition instruction, and receives the "ignition response" information sent by the ground target aircraft control system; after receiving the "ignition response" information, the sending of the ignition instruction is stopped, and the correct sending of the ignition instruction to the ground target aircraft control system is prompted in the form of a log, and the data sent and received are saved locally; and the sending time of the "ignition instruction", the criterion triggering ignition, and the receiving time of the "ignition response" are recorded in the log.

7. A high-reliability telemetry link ignition control system for multi-aircraft spatio-temporal interaction, characterized in that, The method comprises an S-band telemetry detection station, a telemetry ignition test bench with built-in telemetry ignition control software; the test aircraft synchronously packages the ignition control instructions calculated in real time in a central programmer, and the ignition control instructions are sent after being processed by an S-band transmitter through a telemetry link; the S-band telemetry detection station receives the telemetry data of the test aircraft in real time; the telemetry ignition control software completes data selection from the telemetry frame, performs data analysis and judgment, and sends an ignition instruction to the ground target aircraft control system after judging the ignition instruction in the telemetry frame, and implements ignition control.

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