阅读说明：本技术 基于时间窗口的再入飞行器安全控制方法 (Reentry vehicle safety control method based on time window ) 是由 任昌健 刘欣 高宗 王晓飞 赵利军 华烈 寇宇 谷静 马瑞 王硕 王玥兮 凌咸 于 2019-10-11 设计创作，主要内容包括：基于时间窗口的再入飞行器安全控制方法,控制器能够对外部输入的多源信号进行可靠采集和灵活应用,按照再入飞行器的实际工作需求,结合轴向过载、气压和法向过载三种外部输入环境信号以及其他系统通过通讯接口传送过来的通讯指令,实现不同状态再入飞行器的安全和解保控制。既能适应传统的两道保险的再入飞行器安全控制需求,也能适应扩展后的三道或四道保险的再入飞行器安全控制需求。同时不同状态的再入飞行器通过设计多路状态识别电路实现辨别。根据不同的再入飞行器状态,兼容实现不同的自毁操作。通过上述两方面实际实现了再入飞行器安全控制系统的通用化和兼容性。(According to the reentry aircraft safety control method based on the time window, the controller can reliably collect and flexibly apply externally input multi-source signals, and the reentry aircraft safety and safety protection control in different states is realized by combining three externally input environment signals of axial overload, air pressure and normal overload and other communication instructions transmitted by other systems through communication interfaces according to the actual working requirements of the reentry aircraft. The method can meet the safety control requirement of the traditional reentry aircraft with two insurance lines and can also meet the safety control requirement of the reentry aircraft with three or four insurance lines after expansion. Meanwhile, the reentry vehicles in different states are distinguished by designing a multi-path state identification circuit. Different self-destruction operations can be compatibly realized according to different reentry aircraft states. The generalization and compatibility of the safety control system of the reentry aircraft are actually realized through the two aspects.)

1. The reentry aircraft safety control method based on the time window is characterized by comprising the following steps of:

(1) the controller collects the axial overload information of the reentry aircraft, compares the axial overload information with a preset axial overload threshold value after filtering the axial overload information, and removes the first insurance of the safety control system when the collected axial overload information reaches or exceeds the set axial overload threshold value; meanwhile, the timing starting point of the time window is used at the moment;

(2) after the timing time t is reached, the controller collects the atmospheric pressure environment information of the reentry aircraft, and the second insurance of the safety control system is released when the detected atmospheric pressure environment reaches or exceeds a set atmospheric pressure environment threshold value;

(3) after the timing time t is reached, the controller collects normal overload information of the reentry aircraft, the normal overload information is compared with a preset normal overload threshold value after being filtered, and the third insurance of the safety control system is released when the collected normal overload information reaches or exceeds the set normal overload threshold value;

(4) after the second insurance and the third insurance are both released, the controller receives an insurance releasing communication instruction sent by other systems through the external communication interface, judges whether the insurance releasing communication instruction accords with a preset communication protocol, if so, releases the fourth insurance of the safety control system, the timing of a time window is terminated, and an initiating explosive device circuit of the insurance execution mechanism starts to work.

2. The reentry aircraft safety control method based on the time window is characterized by comprising the following steps of:

(1) the controller collects the axial overload information of the reentry aircraft, filters the axial overload information, compares the filtered axial overload information with a preset axial overload threshold value, and takes the axial overload information as a timing starting point of a time window when the collected axial overload information reaches or exceeds the preset axial overload threshold value;

(2) after the timing time t is reached, the controller collects the atmospheric pressure environment information of the reentry aircraft, and the first insurance of the safety control system is released when the detected atmospheric pressure environment reaches or exceeds a set atmospheric pressure environment threshold value;

(3) after the timing time t is reached, the controller collects normal overload information of the reentry aircraft, the normal overload information is compared with a preset normal overload threshold value after being filtered, and a second insurance of the safety control system is released when the collected normal overload information reaches or exceeds the set normal overload threshold value;

(4) after the first insurance and the second insurance are both released, the controller receives an insurance releasing communication instruction sent by other systems through the external communication interface, judges whether the insurance releasing communication instruction accords with a preset communication protocol, if so, releases the third insurance of the safety control system, the timing of a time window is terminated, and an initiating explosive device circuit of the insurance execution mechanism starts to work.

3. The reentry aircraft safety control method based on the time window is characterized by comprising the following steps of:

(1) the controller collects the axial overload information of the reentry aircraft, filters the axial overload information, compares the filtered axial overload information with a preset axial overload threshold value, and takes the axial overload information as a timing starting point of a time window when the collected axial overload information reaches or exceeds the preset axial overload threshold value;

(2) after the timing time t is reached, the controller collects normal overload information of the reentry aircraft, the normal overload information is compared with a preset normal overload threshold value after being filtered, and the first insurance of the safety control system is released when the collected normal overload information reaches or exceeds the set normal overload threshold value;

(3) after the first insurance is released, the controller receives an insurance releasing communication instruction sent by other systems through the external communication interface, judges whether the insurance releasing communication instruction accords with a preset communication protocol, if so, releases the second insurance of the safety control system, the timing of a time window is terminated, and an initiating explosive device circuit of the insurance execution mechanism starts to work.

4. The time-window-based reentry vehicle safety control method of claim 1,2 or 3, wherein: t satisfies 70s < t <100 s.

5. The time-window-based reentry vehicle safety control method of claim 1,2 or 3, wherein: the controller is a digital controller of a reentry vehicle safety control system.

6. The time-window-based reentry vehicle safety control method of claim 1,2 or 3, wherein: and in the time window, when the controller receives a self-destruction instruction input from the outside, the controller identifies the state of the reentry vehicle through the state identification circuit, and executes corresponding self-destruction operation according to the state of the reentry vehicle.

7. The time-window-based reentry vehicle safety control method of claim 6, wherein: the self-destruction operation is an aerial disintegration self-destruction operation or a power-off self-destruction operation.

8. The time-window-based reentry vehicle safety control method of claim 7, wherein: the state recognition circuit determines the current state of the reentry vehicle by acquiring the bus voltage of the cable network of the safety control system.

9. The time-window-based reentry vehicle safety control method of claim 8, wherein: the state identification circuit consists of N single-state identification circuits, the N single-state identification circuits have the same structure and respectively comprise a resistor R1, a resistor R2, a resistor R3, a resistor R4, a capacitor C1, a photoelectric coupler D1 and a processor D2 of the controller;

one end of a resistor R1 is connected with the positive end of an input signal Uin, the other end of a resistor R1 is connected with one end of a capacitor C1 and one end of a resistor R2, the other end of a resistor R2 is connected with one end of a resistor R3 and the positive end of an input channel of a photoelectric coupler D1, the other end of a capacitor C1, the other end of a resistor R3 and the negative end of the input channel of a photoelectric coupler D1 are connected with the negative end of the input signal Uin, the positive end of an output channel of a photoelectric coupler D1 is connected with one end of a resistor R4 and the input end of a processor D2 of the controller, the other end of a resistor R4 is connected with the positive end of a safety control system digital circuit power supply, the negative end of an output channel of a photoelectric coupler D1 is connected with the safety control system digital circuit power supply, and the voltage difference between the positive end and the negative end of the output channel of the photoelectric coupler.

10. The time-window-based reentry vehicle safety control method of claim 9, wherein: the positive end of an input signal Uin of the ith single-state identification circuit is connected with the ith positive bus of a safety control system cable network, the negative end of the input signal Uin is connected with the grounding end of the safety control system cable network, and i is 1,2 and … … N.

Technical Field

The invention relates to a reentry vehicle safety control method based on a time window, and belongs to the field of reentry vehicle safety control.

Background

The traditional safety control system of the reentry aircraft is generally based on two fixed external input signals to remove system insurance, the external input signals are converted through a hardware circuit to realize the safety control system insurance removal, and the control mode is relatively simple and solidified. The traditional safety control system of the reentry aircraft is bound with the working state of the reentry aircraft in a way of relieving insurance, different safety control systems need to be designed aiming at the reentry aircraft with different models, and the universalization and the compatibility design of the safety control systems are difficult to achieve.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: in order to overcome the defects of the prior art, the reentry aircraft safety control method based on the time window is provided, the identification and the application of external input signals are flexibly realized, the safety control method is flexible and independent and does not depend on the working state of the reentry aircraft, and the safety control system has generalization and compatibility.

The technical solution of the invention is as follows:

the reentry aircraft safety control method based on the time window comprises the following steps when the safety control system sets four insurance:

(1) the controller collects the axial overload information of the reentry aircraft, compares the axial overload information with a preset axial overload threshold value after filtering the axial overload information, and removes the first insurance of the safety control system when the collected axial overload information reaches or exceeds the set axial overload threshold value; meanwhile, the timing starting point of the time window is used at the moment;

(2) after the timing time t is reached, the controller collects the atmospheric pressure environment information of the reentry aircraft, and the second insurance of the safety control system is released when the detected atmospheric pressure environment reaches or exceeds a set atmospheric pressure environment threshold value;

(3) after the timing time t is reached, the controller collects normal overload information of the reentry aircraft, the normal overload information is compared with a preset normal overload threshold value after being filtered, and the third insurance of the safety control system is released when the collected normal overload information reaches or exceeds the set normal overload threshold value;

(4) after the second insurance and the third insurance are both released, the controller receives an insurance releasing communication instruction sent by other systems through the external communication interface, judges whether the insurance releasing communication instruction accords with a preset communication protocol, if so, releases the fourth insurance of the safety control system, the timing of a time window is terminated, and an initiating explosive device circuit of the insurance execution mechanism starts to work.

The reentry aircraft safety control method based on the time window comprises the following steps when a safety control system sets three insurance:

(1) the controller collects the axial overload information of the reentry aircraft, filters the axial overload information, compares the filtered axial overload information with a preset axial overload threshold value, and takes the axial overload information as a timing starting point of a time window when the collected axial overload information reaches or exceeds the preset axial overload threshold value;

(2) after the timing time t is reached, the controller collects the atmospheric pressure environment information of the reentry aircraft, and the first insurance of the safety control system is released when the detected atmospheric pressure environment reaches or exceeds a set atmospheric pressure environment threshold value;

(3) after the timing time t is reached, the controller collects normal overload information of the reentry aircraft, the normal overload information is compared with a preset normal overload threshold value after being filtered, and a second insurance of the safety control system is released when the collected normal overload information reaches or exceeds the set normal overload threshold value;

(4) after the first insurance and the second insurance are both released, the controller receives an insurance releasing communication instruction sent by other systems through the external communication interface, judges whether the insurance releasing communication instruction accords with a preset communication protocol, if so, releases the third insurance of the safety control system, the timing of a time window is terminated, and an initiating explosive device circuit of the insurance execution mechanism starts to work.

The reentry vehicle safety control method based on the time window comprises the following steps when a safety control system sets two insurance:

(1) the controller collects the axial overload information of the reentry aircraft, filters the axial overload information, compares the filtered axial overload information with a preset axial overload threshold value, and takes the axial overload information as a timing starting point of a time window when the collected axial overload information reaches or exceeds the preset axial overload threshold value;

(2) after the timing time t is reached, the controller collects normal overload information of the reentry aircraft, the normal overload information is compared with a preset normal overload threshold value after being filtered, and the first insurance of the safety control system is released when the collected normal overload information reaches or exceeds the set normal overload threshold value;

(3) after the first insurance is released, the controller receives an insurance releasing communication instruction sent by other systems through the external communication interface, judges whether the insurance releasing communication instruction accords with a preset communication protocol, if so, releases the second insurance of the safety control system, the timing of a time window is terminated, and an initiating explosive device circuit of the insurance execution mechanism starts to work.

t satisfies 70s < t <100 s.

The controller is a digital controller of a reentry vehicle safety control system.

And in the time window, when the controller receives a self-destruction instruction input from the outside, the controller identifies the state of the reentry vehicle through the state identification circuit, and executes corresponding self-destruction operation according to the state of the reentry vehicle.

The self-destruction operation is an aerial disintegration self-destruction operation or a power-off self-destruction operation.

The state recognition circuit determines the current state of the reentry vehicle by acquiring the bus voltage of the cable network of the safety control system.

The state identification circuit consists of N single-state identification circuits, the N single-state identification circuits have the same structure and respectively comprise a resistor R1, a resistor R2, a resistor R3, a resistor R4, a capacitor C1, a photoelectric coupler D1 and a processor D2 of the controller;

one end of a resistor R1 is connected with the positive end of an input signal Uin, the other end of a resistor R1 is connected with one end of a capacitor C1 and one end of a resistor R2, the other end of a resistor R2 is connected with one end of a resistor R3 and the positive end of an input channel of a photoelectric coupler D1, the other end of a capacitor C1, the other end of a resistor R3 and the negative end of the input channel of a photoelectric coupler D1 are connected with the negative end of the input signal Uin, the positive end of an output channel of a photoelectric coupler D1 is connected with one end of a resistor R4 and the input end of a processor D2 of the controller, the other end of a resistor R4 is connected with the positive end of a safety control system digital circuit power supply, the negative end of an output channel of a photoelectric coupler D1 is connected with the safety control system digital circuit power supply, and the voltage difference between the positive end and the negative end of the output channel of the photoelectric coupler.

The positive end of an input signal Uin of the ith single-state identification circuit is connected with the ith positive bus of a safety control system cable network, the negative end of the input signal Uin is connected with the grounding end of the safety control system cable network, and i is 1,2 and … … N.

Compared with the prior art, the invention has the advantages that:

(1) the controller can flexibly process and apply external input environmental signals and communication signals, realizes the fusion of various information sources, can meet the safety control requirement of the reentry vehicle of the traditional two-way insurance, and can also meet the safety control requirement of the reentry vehicle of the expanded three-way or four-way insurance.

(2) According to the invention, by setting the time window, the safety control capability of the reentry vehicle is improved, and the safety problem possibly occurring in ground test reentry flight is effectively avoided.

(3) The controller can identify the current state of the reentry vehicle according to the state identification circuit in the time window and execute a corresponding self-destruction instruction according to the state. The controller can identify various aircraft states and can meet the self-destruction operation requirements of the aircraft in various states.

(4) The invention ensures that the safety control system has generalization and compatibility and is not bound with a specific reentry vehicle any more by the solution method and the self-destruction method.

Drawings

FIG. 1 is a schematic diagram of an implementation of the present invention;

FIG. 2 is a schematic diagram of a single state identification circuit.

Detailed Description

The method can meet the safety control requirement of the traditional reentry vehicle with two insurance lines and can also meet the safety control requirement of the reentry vehicle with three or four insurance lines after expansion.

The implementation of the invention is schematically shown in fig. 1.

Specifically, when the safety control system sets four insurance, the method comprises the following steps:

(1) the controller collects the axial overload information of the reentry aircraft, compares the axial overload information with a preset axial overload threshold value after filtering the axial overload information, and removes the first insurance of the safety control system when the collected axial overload information reaches or exceeds the set axial overload threshold value; meanwhile, the timing starting point of the time window is used at the moment;

(2) after the timing time t is reached, the controller collects the atmospheric pressure environment information of the reentry aircraft, and the second insurance of the safety control system is released when the detected atmospheric pressure environment reaches or exceeds a set atmospheric pressure environment threshold value; 70s < t <100 s;

(3) after the timing time t is reached, the controller collects normal overload information of the reentry aircraft, the normal overload information is compared with a preset normal overload threshold value after being filtered, and the third insurance of the safety control system is released when the collected normal overload information reaches or exceeds the set normal overload threshold value;

(4) after the second insurance and the third insurance are both released, the controller receives an insurance releasing communication instruction sent by other systems through the external communication interface, judges whether the insurance releasing communication instruction accords with a preset communication protocol, if so, releases the fourth insurance of the safety control system, the timing of a time window is terminated, and an initiating explosive device circuit of the insurance execution mechanism starts to work.

When the safety control system sets three insurance, the method comprises the following steps:

(1) the controller collects the axial overload information of the reentry aircraft, filters the axial overload information, compares the filtered axial overload information with a preset axial overload threshold value, and takes the axial overload information as a timing starting point of a time window when the collected axial overload information reaches or exceeds the preset axial overload threshold value;

(2) after the timing time t is reached, the controller collects the atmospheric pressure environment information of the reentry aircraft, and the first insurance of the safety control system is released when the detected atmospheric pressure environment reaches or exceeds a set atmospheric pressure environment threshold value; 70s < t <100 s;

(3) after the timing time t is reached, the controller collects normal overload information of the reentry aircraft, the normal overload information is compared with a preset normal overload threshold value after being filtered, and a second insurance of the safety control system is released when the collected normal overload information reaches or exceeds the set normal overload threshold value;

(4) after the first insurance and the second insurance are both released, the controller receives an insurance releasing communication instruction sent by other systems through the external communication interface, judges whether the insurance releasing communication instruction accords with a preset communication protocol, if so, releases the third insurance of the safety control system, the timing of a time window is terminated, and an initiating explosive device circuit of the insurance execution mechanism starts to work.

When the safety control system sets two insurance, the method comprises the following steps:

(1) the controller collects the axial overload information of the reentry aircraft, filters the axial overload information, compares the filtered axial overload information with a preset axial overload threshold value, and takes the axial overload information as a timing starting point of a time window when the collected axial overload information reaches or exceeds the preset axial overload threshold value;

(2) after the timing time t is reached, the controller collects normal overload information of the reentry aircraft, the normal overload information is compared with a preset normal overload threshold value after being filtered, and the first insurance of the safety control system is released when the collected normal overload information reaches or exceeds the set normal overload threshold value; 70s < t <100 s;

(3) after the first insurance is released, the controller receives an insurance releasing communication instruction sent by other systems through the external communication interface, judges whether the insurance releasing communication instruction accords with a preset communication protocol, if so, releases the second insurance of the safety control system, the timing of a time window is terminated, and an initiating explosive device circuit of the insurance execution mechanism starts to work.

The controller is a digital controller of the reentry aircraft safety control system, all external input signals are filtered and collected through software, and reliable processing and flexible application of the input signals are achieved.

In the time window, when the controller receives a self-destruction instruction input from the outside, the controller identifies the state of the reentry aircraft through the state identification circuit, and runs software programs of different branches according to the state of the reentry aircraft to execute corresponding self-destruction operation (air disintegration self-destruction operation or power-off self-destruction operation).

The state recognition circuit determines the current state of the reentry vehicle by acquiring the bus voltage of the cable network of the safety control system. The state identification circuit consists of N single-state identification circuits, the N single-state identification circuits are identical in structure and respectively comprise a resistor R1, a resistor R2, a resistor R3, a resistor R4, a capacitor C1, a photoelectric coupler D1 and a processor D2 of the controller. FIG. 2 is a schematic diagram of a single-pass state identification circuit.

One end of a resistor R1 is connected with the positive end of an input signal Uin, the other end of a resistor R1 is connected with one end of a capacitor C1 and one end of a resistor R2, the other end of a resistor R2 is connected with one end of a resistor R3 and the positive end of an input channel of a photoelectric coupler D1, the other end of a capacitor C1, the other end of a resistor R3 and the negative end of the input channel of a photoelectric coupler D1 are connected with the negative end of the input signal Uin, the positive end of an output channel of a photoelectric coupler D1 is connected with one end of a resistor R4 and the input end of a processor D2 of the controller, the other end of a resistor R4 is connected with the positive end of a safety control system digital circuit power supply, the negative end of an output channel of a photoelectric coupler D1 is connected with the safety control system digital circuit power supply, and the voltage difference between the positive end and the negative end of the output channel of the photoelectric coupler.

The positive end of an input signal Uin of the ith single-state identification circuit is connected with the ith positive bus of a safety control system cable network, the negative end of the input signal Uin is connected with the grounding end of the safety control system cable network, and i is 1,2 and … … N.

When the direct current transmission ratio of the photoelectric coupler D1 is within the range of 100% -500%, the resistance value of R1 is 1.2k, the resistance value of R2 is 1k, the resistance value of R3 is 240 omega, and the resistance value of R4 is 1.9k, the single-state identification circuit can reliably output a low-level signal under the condition that the input signal Uin is greater than 20V, and can reliably output a high-level signal under the condition that the input signal Uin is lower than 10V. The working reliability and the anti-interference capability of the single-state identification circuit are effectively ensured through the design.

And if N is equal to 4, the controller of the invention has four single-state identification circuits in common, and the four states of the aircraft are distinguished and reentered through the high and low level combination of the four single-state identification circuits.

If the 1 st positive bus, the 2 nd positive bus and the 3 rd positive bus of the cable network of the safety control system are all connected with 28V for power supply, and the 4 th positive bus is connected with 0V for power supply, the state of the reentry vehicle identified by the four-way single-state identification circuit is 0001, and the controller executes self-destruction operation corresponding to the state 0001 according to the written program.

If the 2 nd positive bus, the 3 rd positive bus and the 4 th positive bus of the cable network of the safety control system are all connected with 28V power supply, and the 1 st positive bus is connected with 0V power supply, the state of the reentry vehicle identified by the four-way single-state identification circuit is 1000, and the controller executes the self-destruction operation corresponding to the state 1000 according to the written program.

If the 1 st positive bus, the 3 rd positive bus and the 4 th positive bus of the cable network of the safety control system are all connected with 28V for power supply, and the 2 nd positive bus is connected with 0V for power supply, the state of the reentry vehicle identified by the four-way single-state identification circuit is 0100, and the controller executes the self-destruction operation corresponding to the state 0100 according to the written program.

According to different combinations, the four-path single-state identification circuit can identify 16 reentry aircraft states in total. And executing different self-destruction operations according to different states.

The controller of the invention can reliably collect and flexibly apply externally input multi-source signals, and realizes the safety and insurance control of the reentry vehicle in different states by combining three external input environment signals of axial overload, air pressure and normal overload and other communication instructions transmitted by other systems through the communication interface according to the actual working requirements of the reentry vehicle.

And the reentry aircrafts in different states are distinguished by designing a multi-path state identification circuit. Different self-destruction operations can be compatibly realized according to different reentry aircraft states.

The safety control system of the reentry aircraft is generalized through the two aspects.

Those skilled in the art will appreciate that the invention has not been described in detail in this specification.