A seat-parallel flip cover ejection laser command system and control method

Abstract

The application belongs to the field of ejection seat design and relates to a laser command system and a control method for a side-by-side ejection cover, which comprises an ejection seat, a cover throwing device and a laser command system; the ejection seat comprises a left ejection seat and a right ejection seat, the cover throwing device comprises a cover throwing device and a pressure relief port cutting device; the laser command system comprises a command system controller, a laser energy-gathering detonation device, an ejection seat igniter and a laser reflection device; the command system controller is electrically connected with the laser energy-gathering detonation device, the ejection seat igniter, the laser reflection device and a fiber microswitch; and the laser energy-gathering detonation device is electrically connected with the cover throwing device. When the cover is thrown, the laser reflection device and the fiber microswitch send signals to the command system controller; after the command system controller judges that the laser reflection device and the fiber microswitch have both sensed that the cabin cover has been thrown away, the right ejection seat and the left ejection seat are controlled to be thrown away in sequence, so that the control stability is ensured.

Description

Technical Field

[0001] This application belongs to the field of ejection seat design, and specifically relates to a side-by-side ejection seat launch laser command system and control method. Background Technology

[0002] In existing technologies, ejection escape control systems are used to control the ejection sequence and time interval between the passenger / chair systems to avoid interference between them after ejection. The ejection escape control systems commonly used in domestic aircraft lack redundancy due to limitations such as weight and cabin space, resulting in low system reliability. A single point of failure can lead to the failure of the entire system, causing serious consequences.

[0003] In the case of a single point of failure, the other seat can be activated to ensure normal ejection. In order to realize the ejection survival control of two-seat side-by-side aircraft occupants, a special ejection control method needs to be designed. The ejection sequence of the ejection seats is that the right seat ejects first, followed by the left seat.

[0004] How to effectively control the ejection of a two-seat side-by-side aircraft is a problem that needs to be solved. Summary of the Invention

[0005] The purpose of this application is to provide a side-by-side ejection laser command system and control method to solve the problem of difficulty in effectively controlling the ejection of two-seat side-by-side aircraft in the prior art.

[0006] The technical solution of this application is: a side-by-side ejection lid-throwing laser command system, comprising an ejection seat, a lid-throwing device, and a laser command system; the ejection seat includes a left ejection seat and a right ejection seat, the lid-throwing device includes a lid-throwing device and a pressure relief port cutting device; the laser command system includes a command system controller, a laser focusing detonation device, an ejection seat igniter, and a laser reflection device; the command system controller is electrically connected to the laser focusing detonation device, the ejection seat igniter, the laser reflection device, and a fiber optic microswitch, and the laser focusing detonation device is electrically connected to the lid-throwing device; the central pull ring is electrically connected to the command system controller, and when the central pull ring is pulled, the command system controller controls the laser focusing detonation device to operate, the laser focusing detonation device drives the lid-throwing device to depressurize and cut the ejection port lid; then the command system controller controls the ejection seat igniter to ignite;

[0007] Both the laser reflector and the fiber optic microswitch are connected to the command system controller via optical fiber. Both the laser reflector and the fiber optic microswitch are mounted on the canopy ejection device. The laser reflector and the fiber optic microswitch send the detected canopy signal to the command system controller. When the command system controller determines that both the laser reflector and the fiber optic microswitch have detected the canopy ejection, the command system controller controls the right ejection seat and the left ejection seat to be ejected in sequence.

[0008] Preferably, the method by which the command system controller judges the laser reflector and the fiber optic micro switch is as follows: when the command system controller senses that the change in the fiber optic micro switch before and after the canopy is: on-off, then it is determined that the fiber optic micro switch has sensed that the canopy has been successfully thrown; when the command system controller senses that the change in the laser reflector before and after the canopy is: off-on-off, then it is determined that the laser reflector has sensed that the canopy has been successfully thrown.

[0009] Preferably, the fiber optic microswitch includes a first fiber optic microswitch and a second fiber optic microswitch, and the laser reflection device includes a first laser reflection device and a second laser reflection device. The first fiber optic microswitch and the first laser reflection device are connected to the left canopy, and the second fiber optic microswitch and the second laser reflection device are connected to the right canopy. When the change in the first fiber optic microswitch after ejection is on-off, and the change in the first laser reflection device after ejection is off-on-off, it is determined that the left canopy has been successfully cut and jettisoned. When the change in the second fiber optic microswitch after ejection is on-off, and the change in the second laser reflection device after ejection is off-on-off, it is determined that the right canopy has been successfully cut and jettisoned.

[0010] Preferably, both the left and right ejection seats are equipped with ejection dispersion modules, which, during ejection, can control the left ejection seat to disperse to the left and the right ejection seat to disperse to the right; the command system controller is equipped with a status handle, which has single-state and dual-state modes.

[0011] Preferably, the cover-throwing device includes a left cover-throwing device, a right cover-throwing device, and a pressure relief port cutting device. The pressure relief port cutting device can cut the top structure of the cockpit to form a pressure relief port. The laser-focused detonation device includes a first laser-focused detonation device, a second laser-focused detonation device, and a third laser-focused detonation device. The first laser-focused detonation device is electrically connected to the pressure relief port cutting device and can drive the pressure relief port cutting device to cut the top structure of the cockpit. The second laser-focused detonation device can drive the left cover-throwing device to throw the cover, and the third laser-focused detonation device can drive the right cover-throwing device to throw the cover.

[0012] As one specific implementation method, a control method for a side-by-side ejection laser command system involves the following steps: When an ejection seat is activated, the command system controller receives the pressure difference signal between the inside and outside of the cockpit and the flight altitude signal, compares them with the set standard values, and determines whether an ejection depressurization delay is required. If so, after a depressurization delay T0, the depressurization port is cut and ejected. After the depressurization delay determination is completed, the command system controller detects the position of the status handle to determine the ejection mode.

[0013] In single-state mode, the command system controller identifies the source of the ejection start signal. If the signal source is the left ejection seat, the laser reflector is activated and the left canopy jettison device is controlled to cut and jettison the left canopy. When jettisoning begins, the laser fiber microswitch disconnects the laser reflector. After receiving the signals from the fiber microswitch and the laser reflector, the command system performs an AND gate check. If the check is successful, an actuation signal is output to the left ejection seat, and the left ejection seat ejects from the cabin. If the signal source is the right ejection seat, the laser reflector is activated and the right canopy jettison device is activated to cut and jettison the right canopy. At the same time, an AND gate check is performed. If the check is successful, an actuation signal is output to the right ejection seat, and the right ejection seat ejects from the cabin.

[0014] In dual-state mode, the ejection start signal is output to the command system for control. After receiving the actuation signal of the right ejection seat, the command system controller activates the laser reflector and outputs the start signal to the right ejection canopy device after a delay of T1. The right ejection canopy device cuts and ejects the left canopy. When ejection begins, the laser fiber micro switch disconnects the laser reflector. After receiving the signals from the fiber micro switch and the laser reflector, the command system performs an AND gate judgment. If the judgment is successful, it outputs the actuation signal to the right ejection seat, and the right ejection seat ejects from the cabin. The command system controller outputs the ejection start signal to the left ejection seat. After the signal from the fiber micro switch and the laser reflector is successfully ANDed, and after a delay of T2 after the right ejection seat ejects, the left ejection seat ejects from the cabin.

[0015] Preferably, T0 = T1 = 2s, and T2 is 0.4s.

[0016] This application discloses a canopy-throwing ejection laser command system and control method, comprising an ejection seat, a canopy-throwing device, and a laser command system. The ejection seat includes a left ejection seat and a right ejection seat; the canopy-throwing device includes a canopy-throwing mechanism and a pressure relief port cutting device; the laser command system includes a command system controller, a laser-guided detonator, an ejection seat igniter, and a laser reflector; the command system controller is electrically connected to the laser-guided detonator, the ejection seat igniter, the laser reflector, and a fiber optic microswitch, and the laser-guided detonator is electrically connected to the canopy-throwing device. During canopy throwing, the laser reflector and the fiber optic microswitch send signals to the command system controller. When the command system controller determines that both the laser reflector and the fiber optic microswitch have sensed canopy throwing, it controls the right and left ejection seats to be thrown sequentially, ensuring control stability. Attached Figure Description

[0017] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0018] Figure 1This is a schematic diagram of the overall operational structure of this application;

[0019] Figure 2 This is the overall control flowchart for this application.

[0020] 1. Command system controller; 2. First laser-focused detonation device; 3. Second laser-focused detonation device; 4. Third laser-focused detonation device; 5. Left ejection seat igniter; 6. Right ejection seat igniter; 7. Central pull ring; 8. First laser reflector; 9. Second laser reflector; 10. Pressure relief port cutting device; 11. Left ejection cover device; 12. Right ejection cover device; 13. First fiber optic micro switch; 14. Second fiber optic micro switch. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] A side-by-side ejection laser command system, such as Figure 1 As shown, it includes an ejection seat, a canopy ejection device, and a laser command system.

[0023] The ejection seat includes a left ejection seat and a right ejection seat; the ejection device includes an ejection device and a pressure relief port cutting device 10; the laser command system includes a command system controller 1, a laser focusing detonator, an ejection seat igniter, and a laser reflector; the command system controller 1 is electrically connected to the laser focusing detonator, the ejection seat igniter, the laser reflector, and the fiber optic micro switch; the laser focusing detonator is electrically connected to the ejection device.

[0024] The central pull ring 7 is electrically connected to the command system controller 1. When the central pull ring 7 is pulled, the command system controller 1 outputs an optical signal to the laser reflector. The laser reflector emits and reflects the laser signal and outputs it to the command system controller 1. The command system controller 1 controls the laser focusing detonation device to work. The laser focusing detonation device drives the ejection cover ejection device to depressurize and cut the ejection cover. Then the command system controller 1 controls the ejection seat igniter to ignite.

[0025] Both the laser reflector and the fiber optic microswitch are connected to the command system controller 1 via optical fiber. Both the laser reflector and the fiber optic microswitch are located on the canopy ejection device. The laser reflector and the fiber optic microswitch send the canopy signal they sense to the command system controller 1. When the command system controller 1 determines that both the laser reflector and the fiber optic microswitch have sensed the canopy ejection, the command system controller 1 controls the right ejection seat and the left ejection seat to be ejected in sequence.

[0026] During normal flight, there is no signal in the optical fiber, and the laser reflector has no input or output. When the central pull ring 7 is pulled, the command system controller 1 outputs an optical signal to the laser reflector. The laser reflector emits and reflects the laser signal, and the laser signal is output to the command system controller 1 to realize the release action.

[0027] At the start of the ejection, the command system controller 1 receives signals from the laser reflector and the fiber optic micro switch and performs an AND gate check. Only after both checks pass does the ejection seat corresponding to the ejection seat proceed to prevent signal errors caused by severe aircraft vibration or component damage.

[0028] In this way, through the cooperation of the command system controller 1, the laser-focused detonation device, the ejection seat igniter, and the laser reflection device, the right ejection seat and the left ejection seat can be launched in sequence, ensuring control stability while achieving side-by-side ejection.

[0029] Preferably, the method by which the command system controller 1 judges the laser reflector and the fiber optic micro switch is as follows: when the command system controller 1 senses that the change in the fiber optic micro switch before and after the canopy is: on-off, then it is determined that the fiber optic micro switch has sensed that the canopy has been successfully thrown; when the command system controller 1 senses that the change in the laser reflector before and after the canopy is: off-on-off, then it is determined that the laser reflector has sensed that the canopy has been successfully thrown.

[0030] The fiber optic microswitch is connected to the canopy. When the canopy moves, the T-shaped component in the middle moves upward, disrupting the channel and creating an open circuit. The laser reflection device works on the same principle as the fiber optic microswitch. Under normal conditions, the opening on the T-shaped component corresponds to the laser emission position. Only the laser is emitted, and there is no reflection. After the canopy moves, the T-shaped component moves upward, and the laser hits the reflector, forming a reflected laser signal. The T-shaped component continues to move upward, and the reflection ends.

[0031] Therefore, based on the above judgment, both the fiber optic microswitch and the laser reflection device can accurately determine whether the cockpit canopy has been successfully jettisoned.

[0032] Preferably, the fiber optic microswitch includes a first fiber optic microswitch 13 and a second fiber optic microswitch 14, and the laser reflection device includes a first laser reflection device 8 and a second laser reflection device 9. The first fiber optic microswitch 13 and the first laser reflection device 8 are connected to the left canopy, and the second fiber optic microswitch 14 and the second laser reflection device 9 are connected to the right canopy. When the change in the first fiber optic microswitch 13 after ejection is on-off, and the change in the first laser reflection device 8 after ejection is off-on-off, it is determined that the left canopy has been successfully cut and thrown. When the change in the second fiber optic microswitch 14 after ejection is on-off, and the change in the second laser reflection device 9 after ejection is off-on-off, it is determined that the right canopy has been successfully cut and thrown, thus realizing the separate judgment of the status of the right and left canopies.

[0033] Preferably, both the left and right ejection seats are equipped with ejection dispersion modules. During ejection, the ejection dispersion modules can control the left ejection seat to disperse to the left and the right ejection seat to disperse to the right. Each ejection seat has a built-in central pull ring 7 and a laser igniter. The central pull ring 7 is used to initiate ejection, and the laser igniter initiates seat ejection.

[0034] The ejection port ejection device is installed on the top of the cockpit. It is used to cut the top structure of the cockpit to form a pressure relief port and an ejection port cover. The pressure relief port cutting device 10 is fired by a laser-guided detonator, the left ejection port ejection device 11 is fired by a laser-guided detonator, and the right ejection port ejection device 12 is fired by a laser-guided detonator. After being fired by the laser-guided detonator, the ejection port ejection device completes the pressure relief and cutting / ejection of the ejection port cover.

[0035] The laser command system is installed in the cockpit to control the timing of the cockpit canopy depressurization and ejection and the ejection seat deployment.

[0036] The instruction system controller 1 is equipped with a status handle, which has two modes: single-state and dual-state.

[0037] The pilot manually selects the command system controller 1. The controller is connected to the electromechanical system via a bus to acquire the pressure difference signal between the inside and outside of the cockpit and the flight altitude signal.

[0038] Preferably, the ejection device includes a left ejection device 11, a right ejection device 12, and a pressure relief port cutting device 10. The pressure relief port cutting device 10 can cut the top structure of the cockpit to form a pressure relief port. The laser-focused detonation device includes a first laser-focused detonation device 2, a second laser-focused detonation device 3, and a third laser-focused detonation device 4. The first laser-focused detonation device 2 is electrically connected to the pressure relief port cutting device 10 and can drive the pressure relief port cutting device 10 to cut the top structure of the cockpit. The second laser-focused detonation device 3 can drive the left ejection device 11 to eject, and the third laser-focused detonation device 4 can drive the right ejection device 12 to eject. The ejection seat igniter includes a left ejection seat igniter 5 connected to the left ejection seat and a right ejection seat igniter 6 connected to the right ejection seat.

[0039] The first fiber optic micro switch 13 is fixed to the left cover throwing device 11. Under normal conditions, it is in the open circuit state. When the left cover throwing device 11 works and cuts and throws the cockpit cover, the first fiber optic micro switch 13 turns into an open circuit state.

[0040] The second fiber optic micro switch 14 is fixed to the right cover throwing device 12. Under normal conditions, it is in the open circuit state. When the right cover throwing device 12 works and cuts and throws the cockpit cover, the second fiber optic micro switch 14 turns into an open circuit state.

[0041] As one specific implementation, it also includes a control method for a side-by-side ejection laser command system, combined with... Figure 2 When an ejection seat is activated, the command system controller 1 receives the pressure difference signal inside and outside the cockpit and the flight altitude signal, compares them with the set standard value, and determines whether an ejection depressurization delay is required. If so, after a 2-second depressurization delay, the depressurization port is cut and ejected. After the depressurization delay determination is completed, the command system controller 1 detects the position of the status handle and determines the ejection mode.

[0042] In single-state operation, the left seat activates and ejects the left seat. The right seat activates and ejects the right seat. In dual-state operation, if either seat activates, the ejection order is right seat ejection first, followed by left seat ejection. When the aircraft is flying at a certain altitude, the specific operation is as follows:

[0043] After the single-state left ejection seat is activated, an ejection start signal is output to the command system controller 1. The command system controller 1 outputs an optical signal to the laser reflector and an actuation signal to the pressure relief port laser focusing detonation device. The pressure relief port cutting device 10 is activated by the laser focusing detonation device, cutting the canopy to form a pressure relief port. After 2 seconds, the command system controller 1 outputs an actuation signal to the left canopy laser focusing detonation device. The laser focusing detonation device activates the left canopy ejection device 11, and the left canopy cuts and ejects the canopy. When ejection begins, the fiber optic micro switch is activated. When the canopy is ejected to a certain angle, the laser reflector is disconnected. After receiving the signals from the fiber optic micro switch and the laser reflector, the command system controller 1 performs an AND gate judgment. After successful judgment, the command system controller 1 outputs a signal to the left ejection seat laser igniter, and the left ejection seat is ejected from the cabin.

[0044] After the dual-state left ejection seat is activated, it outputs an ejection start signal to the command system controller 1. The command system controller 1 outputs an optical signal to the laser reflector and an actuation signal to the pressure relief port laser focusing detonation device. The laser focusing detonation device detonates the pressure relief port cutting device 10, cutting the canopy to form a pressure relief port. After 2 seconds, the command system controller 1 outputs an actuation signal to the right canopy laser focusing detonation device. The laser focusing detonation device activates the right canopy ejection device 12, and the right canopy cuts and ejects the canopy. When ejection begins, the fiber optic micro switch is activated. When the canopy is ejected to a certain angle, the laser reflector is disconnected. After receiving the signals from the fiber optic micro switch and the laser reflector, the command system controller 1 performs an AND gate judgment. If the judgment is successful, the command system controller 1 outputs a signal to the right ejection seat, and the right ejection seat ejects from the cabin. 0.15 seconds after the right hatch cutting device starts working, the command system controller 1 outputs an actuation signal to the left hatch laser focusing detonation device. The laser focusing detonation device activates the left hatch ejection device 11, and the left hatch cuts and ejects the canopy. When ejection begins, the fiber optic micro switch is activated. When the canopy is ejected to a certain angle, the laser reflector is disconnected. After receiving the signals from the fiber optic micro switch and the laser reflector, the command system controller 1 performs an AND gate judgment. After the judgment is successful, the command system controller 1 outputs an ejection signal to the right ejection seat 0.4 seconds later, and then outputs an ejection signal to the left ejection seat laser igniter. The left ejection seat ejects from the cabin.

[0045] Finally, it should be noted that the accompanying drawings of the embodiments disclosed in this invention only involve the structures involved in the embodiments disclosed in this invention. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this invention can be combined with each other.

[0046] In conclusion, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A laser command system for launching a canister from a launcher, characterized in that: The system includes an ejection seat, a cover ejection device, and a laser command system. The ejection seat includes a left ejection seat and a right ejection seat. The cover ejection device includes a cover ejection device and a pressure relief port cutting device (10). The laser command system includes a command system controller (1), a laser focusing detonation device, an ejection seat igniter, and a laser reflection device. The command system controller (1) is electrically connected to the laser focusing detonation device, the ejection seat igniter, the laser reflection device, and the fiber optic micro switch. The laser focusing detonation device is electrically connected to the cover ejection device. The central pull ring (7) is electrically connected to the command system controller (1). When the central pull ring (7) is pulled, the command system controller (1) controls the laser focusing detonation device to work. The laser focusing detonation device drives the cover ejection device to depressurize and cut the ejection port cover. Then, the command system controller (1) controls the ejection seat igniter to ignite. The laser reflection device and the fiber optic micro switch are both connected to the command system controller (1) via optical fiber. The laser reflection device and the fiber optic micro switch are both located on the canopy ejection device. The laser reflection device and the fiber optic micro switch send the canopy signal they sense to the command system controller (1). When the command system controller (1) determines that the laser reflection device and the fiber optic micro switch have sensed the canopy ejection, the command system controller (1) controls the right ejection seat and the left ejection seat to be ejected in sequence.

2. The laser command system for launching a cover as described in claim 1, characterized in that, The method by which the command system controller (1) judges the laser reflector and the fiber optic micro switch is as follows: when the command system controller (1) senses that the change in the fiber optic micro switch before and after the canopy is: on-off, it is determined that the fiber optic micro switch senses that the canopy has been successfully thrown; when the command system controller (1) senses that the change in the laser reflector before and after the canopy is: off-on-off, it is determined that the laser reflector senses that the canopy has been successfully thrown.

3. The side-mounted ejector laser command system as described in claim 2, characterized in that: The fiber optic microswitch includes a first fiber optic microswitch (13) and a second fiber optic microswitch (14). The laser reflection device includes a first laser reflection device (8) and a second laser reflection device (9). The first fiber optic microswitch (13) and the first laser reflection device (8) are connected to the left cockpit canopy, and the second fiber optic microswitch (14) and the second laser reflection device (9) are connected to the right cockpit canopy. When the change of the first fiber optic microswitch (13) after ejection is on-off, and the change of the first laser reflection device (8) after ejection is off-on-off, it is determined that the left cockpit canopy has been successfully cut and thrown. When the change of the second fiber optic microswitch (14) after ejection is on-off, and the change of the second laser reflection device (9) after ejection is off-on-off, it is determined that the right cockpit canopy has been successfully cut and thrown.

4. The laser command system for launching a cover as described in claim 1, characterized in that: Both the left and right ejection seats are equipped with ejection divergence modules. During ejection, the ejection divergence modules can control the left ejection seat to diverge to the left and the right ejection seat to diverge to the right. The command system controller (1) is equipped with a status handle, which has two modes: single-state and dual-state.

5. The laser command system for launching a cover as described in claim 1, characterized in that: The ejection device includes a left ejection device (11), a right ejection device (12), and a pressure relief port cutting device (10). The pressure relief port cutting device (10) can cut the top structure of the cockpit to form a pressure relief port. The laser focusing detonation device includes a first laser focusing detonation device (2), a second laser focusing detonation device (3), and a third laser focusing detonation device (4). The first laser focusing detonation device (2) is electrically connected to the pressure relief port cutting device (10), and the first laser focusing detonation device (2) can drive the pressure relief port cutting device (10) to cut the top structure of the cockpit. The second laser focusing detonation device (3) can drive the left ejection device (11) to eject the ejection device. The third laser focusing detonation device (4) can drive the right ejection device (12) to eject the ejection device.

6. A control method for a side-mounted ejector laser command system, employing the method described in any one of claims 1-5, characterized in that: When a certain ejection seat is activated, the command system controller (1) receives the pressure difference signal inside and outside the cabin and the flight altitude signal, compares them with the set standard value, and determines whether ejection depressurization delay is required. If so, after depressurization delay T0, the depressurization port is cut and thrown. After the depressurization delay determination is completed, the command system controller (1) detects the position of the status handle and determines the ejection mode. In single-state mode, the command system controller (1) identifies the source of the ejection start signal. If the signal source is the left ejection seat, the laser reflector is activated and the left canopy ejection device (11) is controlled to work, cutting and ejecting the left canopy. When the ejection begins, the laser fiber micro switch is disconnected and the laser reflector is disconnected. After receiving the signals from the fiber micro switch and the laser reflector, the command system performs AND gate judgment. If the judgment is successful, the actuation signal is output to the left ejection seat, and the left ejection seat ejects out of the cabin. If the signal source is the right ejection seat, the laser reflector is activated and the right canopy ejection device (12) is controlled to work, cutting and ejecting the right canopy. At the same time, AND gate judgment is performed. If the judgment is successful, the actuation signal is output to the right ejection seat, and the right ejection seat ejects out of the cabin. In dual-state mode, the ejection start signal is output to the command system controller (1). After receiving the actuation signal of the right ejection seat, the command system controller (1) activates the laser reflection device and outputs the start signal to the right ejection device (12) after a delay of T1. The right ejection device (12) cuts and ejects the left cockpit canopy. When the ejection begins, the laser fiber micro switch is turned off and the laser reflection device is disconnected. After receiving the signals from the fiber micro switch and the laser reflection device, the command system performs AND gate judgment. After the judgment is successful, the actuation signal is output to the right ejection seat, and the right ejection seat ejects out of the cabin. The command system controller (1) outputs an ejection start signal to the left ejection seat. After the fiber optic micro-switch and laser reflection device signals are successfully determined by AND gate, the left ejection seat ejects out of the cabin after a delay of T2 after the right ejection seat is ejected.

7. The control method for the laser command system for launching a lid by a side-mounted launcher as described in claim 6, characterized in that: T0 = ​​T1 = 2s, and T2 is 0.4s.

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