Seat-parallel cover-throwing ejection electronic instruction system
By designing the electronic command system for ejection of seat-coiled covers, the collision interference problem in the ejection control of the passengers of seat-coiled aircraft is solved, and the safety and sequential exit of the crew are achieved, ensuring the stability and safety of seat-coiled discharge.
Patent Information
- Application Number
- CN202422754988.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-12
- Publication Date
- 2025-08-19
- Estimated Expiration
- 2034-11-12
AI Technical Summary
The prior art is difficult to achieve ejection control of aircraft crew members, especially to achieve accurate sequential launches while avoiding collision interference.
A electronic command system for ejecting the seat and cover is designed, including a left ejecting seat, a right ejecting seat, a cover throwing device and an electronic command system. Through the coordinated control of the command system controller, an electric detonation device and a micro switch, the right chair is bounced first and the left chair is bounced out of the cabin in the order of ejecting the cabin.
It realizes stable and precise control of seat-to-seater occupants in emergency situations, avoids collision interference between occupants, and ensures a safe and effective ejection sequence.
Smart Images
Figure CN223237937U_ABST
Abstract
Description
Technical Field
[0001] The present application belongs to the field of aviation design, and in particular relates to an electronic command system for ejection with a seat and a canopy jettisoned. Background Art
[0002] To achieve controlled ejection for crew members in two-seater aircraft, a corresponding ejection control system must be designed. To avoid collisions caused by simultaneous ejections, ejection from two seats must be performed sequentially, with appropriate timing to prevent interference between the two. Currently, ejection seats eject in the right-hand seat first, followed by the left-hand seat. Achieving precise and stable ejection control for these ejections is a challenge that needs to be addressed. Utility Model Content
[0003] The purpose of this application is to provide an electronic command system for ejection with a side-by-side ejection cover, so as to solve the problem that it is difficult to control the ejection of the side-by-side launch scheme.
[0004] The technical solution of the present application is: a side-by-side cover-jetting ejection electronic command system, comprising an ejection seat, a cover-jetting device and an electronic command system; the ejection seat comprises a left ejection seat and a right ejection seat; the left ejection seat and the right ejection seat are arranged side by side and are both installed in the cockpit, for ejecting the occupants out of the cabin under emergency conditions; the cover-jetting device comprises a pressure relief port cutting device, a left cover-jetting device and a right cover-jetting device; the left cover-jetting device is connected to the left ejection seat, and the right cover-jetting device is connected to the right ejection seat; the left cover-jetting device and the right cover-jetting device are both installed on the top of the cockpit; the electronic command system comprises a command system controller, an electric detonator and a micro switch; the electric detonator has three groups and is respectively connected to the pressure relief port cutting device, the left cover-jetting device and the right cover-jetting device, and the micro switch has two groups and is respectively connected to the left cover-jetting device and the right cover-jetting device.
[0005] Preferably, the command system controller is connected to a central pull ring, an onboard power supply and a thermal battery; the onboard power supply and the thermal battery both supply power to the command system controller, and the central pull ring is provided in the ejection seat.
[0006] Preferably, the command system controller further includes a left ejection seat controller and a right ejection seat controller, and the left ejection seat controller and the right ejection seat controller are both connected to the electric detonator for controlling the left cover ejection device and the right cover ejection device.
[0007] Preferably, the electric detonator includes a first electric detonator, a second electric detonator and a third electric detonator, the first electric detonator is connected to a pressure relief port cutting device, the second electric detonator is connected to a left throwing cover device, and the third electric detonator is connected to a right throwing cover device.
[0008] Preferably, the microswitch includes a first microswitch and a second microswitch; the first microswitch is correspondingly connected to the left cover throwing device, and the second microswitch is correspondingly connected to the right cover throwing device; the first microswitch is in a normal state of passage, and when the left cover throwing device works and cuts and throws the canopy, the first microswitch turns to an open circuit; the second microswitch is in a normal state of passage, and when the right cover throwing device works and cuts and throws the canopy, the second microswitch turns to an open circuit.
[0009] The electronic command system for ejection with side-by-side covers of the present application comprises an ejection seat, a cover ejection device and an electronic command system; the ejection seat comprises a left ejection seat and a right ejection seat; the left ejection seat and the right ejection seat are arranged side by side and are both installed in the cockpit, and are used to eject the occupants from the cabin under emergency conditions; the cover ejection device comprises a pressure relief port cutting device, a left cover ejection device and a right cover ejection device; the left cover ejection device is connected to the left ejection seat, and the right cover ejection device is connected to the right ejection seat; the left cover ejection device and the right cover ejection device are both installed on the top of the cockpit; the electronic command system comprises a command system controller, an electric detonator and a micro switch; when ejecting the covers, the command system controller receives a signal from the optical fiber micro switch, and sequentially controls the third electric detonator and the second electric detonator in turn, thereby realizing the sequential exit of the right ejection seat and the left ejection seat. BRIEF DESCRIPTION OF THE DRAWINGS
[0010] In order to more clearly illustrate the technical solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this application.
[0011] Figure 1 This is a schematic diagram of the overall structure of this application.
[0012] 1. Command system controller; 2. Central pull ring; 3. Onboard power supply; 4. Thermal battery; 5. Left ejection seat controller; 6. Right ejection seat controller; 7. First electric detonator; 8. Second electric detonator; 9. Third electric detonator; 10. First micro switch; 11. Second micro switch; 12. Pressure relief port cutting device; 13. Left ejection cover device; 14. Right ejection cover device. DETAILED DESCRIPTION
[0013] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.
[0014] A seat-and-cover ejection electronic command system, such as Figure 1As shown, it includes the ejection seat, cover jettisoning device and electronic command system.
[0015] The ejection seats consist of a left ejection seat and a right ejection seat. These seats are located side by side and mounted in the cockpit, allowing passengers to eject from the cabin in an emergency. The ejection cover mechanism includes a pressure relief port cutting device 12, a left ejection cover mechanism 13, and a right ejection cover mechanism 14. The left ejection cover mechanism 13 is connected to the left ejection seat, while the right ejection cover mechanism 14 is connected to the right ejection seat. Both the left ejection cover mechanism 13 and the right ejection cover mechanism 14 are mounted on the roof of the cockpit.
[0016] The electronic command system includes a command system controller 1, an electric initiator, and a microswitch. There are three sets of electric initiators, connected to the pressure relief port cutting device 12, the left ejection cover device 13, and the right ejection cover device 14, respectively. There are two sets of microswitches, connected to the left ejection cover device 13 and the right ejection cover device 14, respectively. The command system controller 1 is connected to a central pull ring 2, an onboard power supply 3, and a thermal battery 4. The onboard power supply 3 and thermal battery 4 both supply power to the command system controller 1. The central pull ring 2 is located in the ejection seat. In the event of an aircraft emergency, the passenger pulls the central pull ring 2, activating the thermal battery 4 inside the ejection seat and transmitting a start signal to the command system controller 1. The onboard power supply 3 is used to power the command system controller 1.
[0017] The command system controller 1 utilizes a dual-power supply structure, powered by an onboard power supply 3 and a thermal battery 4, to enhance control stability. A state lever is installed on the command system controller 1, with two modes, "single mode" and "dual mode," manually selected by the pilot. The command system controller 1 connects to the electromechanical system via a bus, acquiring signals such as the cabin pressure differential and flight altitude. It is also hardware-connected to the electric detonator, ejection seat, and microswitch.
[0018] The command system controller 1 also includes a left ejection seat controller 5 and a right ejection seat controller 6 . The left ejection seat controller 5 and the right ejection seat controller 6 are both connected to the electric detonator for controlling the left cover ejection device 13 and the right cover ejection device 14 .
[0019] The ejection seats feature an ejection dispersion function, with the left ejection seat dispersing to the left during ejection and the right ejection seat dispersing to the right during ejection, preventing interference between the left and right ejection seats. Each ejection seat houses a central pull ring 2, a thermal battery 4, and either a left ejection seat controller 5 or a right ejection seat controller 6. The central pull ring 2 is used to initiate ejection, the thermal battery 4 provides power to the seat after ejection is initiated, and the left and right ejection seat controllers 5 and 6 control the ejection process.
[0020] The electric detonator includes a first electric detonator 7, a second electric detonator 8 and a third electric detonator 9. The first electric detonator 7 is connected to a pressure relief port cutting device 12, the second electric detonator 8 is connected to a left cover throwing device 13, and the third electric detonator 9 is connected to a right cover throwing device 14.
[0021] The microswitches include a first microswitch 10 and a second microswitch 11. The first microswitch 10 is connected to the left canopy jettisoning mechanism 13, and the second microswitch 11 is connected to the right canopy jettisoning mechanism 14. The first microswitch 10 is normally closed. When the left canopy jettisoning mechanism 13 operates, cutting and dropping the canopy, the first microswitch 10 is open. The second microswitch 11 is normally closed. When the right canopy jettisoning mechanism 14 operates, cutting and dropping the canopy, the second microswitch 11 is open.
[0022] As a specific implementation method, the seat layout in a certain type of flight cockpit adopts a two-seat side-by-side mode, with two ejection modes: single mode and dual mode: in single mode, the left seat is started and the left seat is ejected. The right seat is started and the right seat is ejected. In dual mode, any seat is started, and the ejection order is the right seat first, followed by the left seat. When the aircraft is flying at a certain altitude, the command system controller 1 receives the pressure difference signal inside and outside the cabin and the flight altitude signal to determine whether an ejection decompression delay is required. If necessary, the decompression delay is 1-2s, and the decompression port is cut and ejected. After the delay judgment is over, the command system controller 1 detects the position of the status handle to determine the ejection mode. The specific work is as follows:
[0023] After the single-state left seat is started, the ejection start signal is output to the command system controller 1, and the command system controller 1 outputs an electric actuation signal to the pressure relief port electric detonator, which detonates the pressure relief port cutting device 12 and cuts the canopy to form a pressure relief port. After 2 seconds, the command system controller 1 outputs an actuation signal to the left cabin cover electric detonator, and the electric detonator activates the left cabin cover ejection device 13. The left cabin cover is cut and ejected and a feedback signal is output to the command system controller 1. The command system controller 1 outputs an ejection signal to the left ejection seat, and the left ejection seat is ejected from the cabin.
[0024] After the dual-state left seat is started, the first microswitch 10 and the second microswitch 11 output the ejection start signal to the command system controller 1, and the command system controller 1 outputs the electric actuation signal to the first electric detonator 7, which detonates the pressure relief port cutting device 12 through the first electric detonator 7, cutting the canopy to form a pressure relief port. After 2 seconds, the command system controller 1 outputs the actuation signal to the third electric detonator 9 through the right ejection seat controller 6, and the third electric detonator 9 activates the right cover ejection device 14, and the right canopy is cut and ejected and outputs a feedback signal to the command system controller 1. The command system controller 1 outputs the ejection signal to the right ejection seat, and the right ejection seat is ejected from the cabin. 0.15s after the right hatch cover cutting device works, the command system controller 1 outputs an actuation signal to the second electric detonator 8 through the left ejection seat controller 5. The second electric detonator 8 activates the left hatch cover ejection device 13. The left hatch cover is cut and ejected and a feedback signal is output to the command system controller 1. 0.4s after outputting the ejection signal to the right ejection seat, the command system controller 1 outputs an ejection signal to the left ejection seat, and the left ejection seat is ejected out of the cabin.
[0025] Finally, it should be noted that the drawings of the embodiments disclosed in this utility model only involve structures related to the embodiments disclosed in this utility model. Other structures can refer to common designs. In the absence of conflicts, the same embodiment and different embodiments of the utility model can be combined with each other.
[0026] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.
Claims
1. An electronic command system for ejection of a cover and a seat, characterized by: It includes an ejection seat, a cover ejection device and an electronic command system; the ejection seat includes a left ejection seat and a right ejection seat; the left ejection seat and the right ejection seat are arranged side by side and are both installed in the cockpit, and are used to eject the occupants from the cabin under emergency conditions; the cover ejection device includes a pressure relief port cutting device, a left cover ejection device and a right cover ejection device; the left cover ejection device is connected to the left ejection seat, and the right cover ejection device is connected to the right ejection seat; the left cover ejection device and the right cover ejection device are both installed on the top of the cockpit; the electronic command system includes a command system controller, an electric detonator and a micro switch; the electric detonator has three groups and is respectively connected to the pressure relief port cutting device, the left cover ejection device and the right cover ejection device, and the micro switch has two groups and is respectively connected to the left cover ejection device and the right cover ejection device.
2. The electronic command system for ejection of a cover by ejection seat according to claim 1, characterized in that: The command system controller is connected to a central pull ring, an onboard power supply and a thermal battery; both the onboard power supply and the thermal battery supply power to the command system controller, and the central pull ring is provided in the ejection seat.
3. The electronic command system for ejecting the cover from the seat as claimed in claim 1, characterized in that: The command system controller also includes a left ejection seat controller and a right ejection seat controller. The left ejection seat controller and the right ejection seat controller are both connected to the electric detonator and are used to control the left and right cover throwing devices.
4. The electronic command system for ejecting a cover from a seat as claimed in claim 1, characterized in that: The electric detonator includes a first electric detonator, a second electric detonator and a third electric detonator. The first electric detonator is connected to a pressure relief port cutting device, the second electric detonator is connected to a left throwing cover device, and the third electric detonator is connected to a right throwing cover device.
5. The electronic command system for ejection of a cover by ejection seat according to claim 1, characterized in that: The micro switch includes a first micro switch and a second micro switch; the first micro switch is correspondingly connected to the left cover throwing device, and the second micro switch is correspondingly connected to the right cover throwing device; the first micro switch is in a normal state of passage, and when the left cover throwing device works and cuts and throws the canopy, the first micro switch turns to an open circuit; the second micro switch is in a normal state of passage, and when the right cover throwing device works and cuts and throws the canopy, the second micro switch turns to an open circuit.