An ejection seat and attitude correction method using vector detonation propulsion

Abstract

The present invention discloses an ejection seat and posture correction method using vector detonation propulsion, comprising a seat, a restraining device for restraining a person on the seat, and a locking device for activating the restraining device; a sliding track is arranged on the back of the seat, and the sliding track can slide along the sliding track; the integrated circuit control system is used to control the circuit system arranged on the seat; the fuel tank and the detonation combustion chamber are arranged at the bottom of the seat; the fuel tank and the rocket pack are used to provide a power source. The integrated circuit control system takes ejection modes P1, P2, P3, and P4 as constraint conditions, and different modes set different execution steps. The execution steps are written into the integrated circuit control system through a computer compiler program, and can respond quickly when the ejection is triggered, thereby improving the control effect. At the same time, detonation combustion is used as the power, and the detonation combustion process is equivalent to isochoric combustion, which has higher thermal efficiency and a larger thrust-to-weight ratio. In addition, detonation also has self-pressurization capability, and turbocharging equipment is no longer required in the power propulsion system, which greatly simplifies the system structure and can be well applied to aviation ejection seats.

Description

Technical Field

[0001] The invention relates to the field of aerospace lifesaving, and in particular to an ejection seat using vector detonation propulsion and a posture correction method. Background Art

[0002] The ejection seat is a vehicle for the pilot to escape in an emergency. When the aircraft loses control, the pilot is ejected from the cabin and flies over the tail of the aircraft, allowing the pilot to parachute safely. However, in actual flight, there are various extremely harsh flight conditions, which increases the uncertainty of ejection life-saving. At the same time, the ejection seat after ejection is equivalent to a complex aircraft. The ejection height and ejection angle cannot be accurately predicted, and the low-altitude unfavorable posture ( Figure 3 The safety rescue under the condition shown in the figure increases the difficulty. Summary of the invention

[0003] In view of the deficiencies in the prior art, the present invention provides an ejection seat and attitude correction method using vector detonation propulsion, which executes the corresponding ejection steps through a modular ejection program to control the time scale of ejection escape. The detonation power unit has a large thrust-to-weight ratio, high combustion efficiency, and a simple structure. It is an ideal power unit for a high-precision escape system such as an ejection seat. In this way, the ejection life-saving problem under low-altitude conditions is solved, the seat attitude correction is achieved, the height from the ground is increased, and the purpose of safe life-saving is achieved.

[0004] The present invention achieves the above technical objectives through the following technical means.

[0005] An ejection seat using vector detonation propulsion comprises a seat, on which a restraining device, a locking device, a sliding track, an integrated circuit control system, a fuel tank and a rocket pack are provided; the restraining device is used to restrain the person on the seat, and the locking device is used to activate the restraining device; the sliding track is provided on the back of the seat, and the sliding track can slide along the sliding track; the integrated circuit control system is used to control a circuit system provided on the seat; the fuel tank and the detonation combustion chamber are provided at the bottom of the seat; the fuel tank and the rocket pack are used to provide a power source.

[0006] In the above scheme, the fuel in the fuel tank and the rocket pack and the gas in the air intake pipe enter the detonation combustion chamber and are ignited by the high-frequency pulse igniter to generate energy for pushing the seat.

[0007] The above scheme also includes several one-way electric valves, and the opening and closing of the one-way electric valves are controlled by an integrated circuit control system.

[0008] The above scheme also includes an angle sensor; the angle sensor is used to monitor and transmit the ejection angle of the seat to the integrated circuit control system.

[0009] In the above scheme, there are two rocket packs and two fuel tanks; one-way electric valves and high-frequency pulse igniters are installed on the rocket packs and the fuel tanks.

[0010] In the above scheme, a guide platform is provided at the outlet end of the detonation combustion chamber.

[0011] In the above solution, the integrated circuit control system is a single chip microcomputer.

[0012] A method for correcting the attitude of an ejection seat using vector detonation propulsion comprises the following steps:

[0013] Ejection modes are divided into: P1: high altitude ejection parachuting, H>300m; P2: low altitude small angle ejection parachuting, H≤300m, 0°≤α≤30°, 150°≤α≤180°; P3: low altitude large angle ejection parachuting, H≤300m, 30°<β<150°; P4: low altitude negative angle ejection parachuting, H≤300m, 180°<γ<0°; the ejection mode P1, P2, P3, P4 division parameters are saved to the integrated circuit control system through code;

[0014] Set the ejection execution steps: execute each running program through the program priority level and delay time; after the ejection command response, the running program includes activating the locking device, igniting the rocket package and selecting the ejection mode, and the power unit response;

[0015] The flight platform and angle sensor continuously transmit the altitude and angle signals to the integrated circuit control system respectively. When the pilot makes an ejection action, the ejection mode is determined based on the two state parameters of altitude and angle.

[0016] After the ejection command is issued, the integrated circuit control system executes the ejection steps according to the program: first, the locking device is activated to fix the person's body on the seat by driving the restraint device;

[0017] After the delay time is over, the ignition procedure is executed, the rocket pack is detonated, and the seat is ejected from the cockpit along the sliding track;

[0018] The control system responds to the angle sensor signal and flight altitude signal during ejection and executes one of the four modes of program plan;

[0019] The detonation vector power system works under the control of the corresponding ejection program. In P1 mode, the power ignition program does not respond and the power unit does not work. In P2, P3, and P4 modes, the power unit starts.

[0020] In P2, P3, and P4 modes, the output program instructions include the start and stop of the one-way electric valve and the response of the high-frequency pulse igniter. During operation, the one-way electric valve is opened first, and then the high-frequency pulse igniter ignites.

[0021] In the above scheme, in P3 mode, the ignition program controls the combustion chamber and the rocket pack to start simultaneously to provide lift; in P2 and P4 modes, the detonation combustion chamber on the side with a smaller angle between the ejection direction and the horizontal plane works first, and changes the seat posture under the action of the guide table, transitioning to P3 mode. After 0.5s, the detonation combustion chamber on the other side ignites and burns, moving upward.

[0022] In the above scheme, the ranges of ejection angles α and β in different modes can be adjusted by modifying the upper and lower limits of the angle parameters in the integrated circuit control system.

[0023] The present invention has the following beneficial effects:

[0024] 1. The ejection seat device and attitude correction method using vector detonation propulsion designed by the present invention can effectively improve the safety of ejection life-saving, and the modular ejection scheme and program automatic control steps have fast execution speed, simple module division, few state control parameters and high reliability.

[0025] 2. The integrated circuit control system uses ejection modes P1, P2, P3, and P4 as constraints, and sets different execution steps for different modes. The execution steps are written into the integrated circuit control system through a computer compiler program, which can respond quickly when the ejection is triggered to improve the control effect. At the same time, detonation combustion is used as the power source. The detonation combustion process is equivalent to isochoric combustion, which has higher thermal efficiency and a greater thrust-to-weight ratio. In addition, detonation also has self-pressurization capability, and turbocharging equipment is no longer required in the power propulsion system, which greatly simplifies the system structure and can be well applied to aviation ejection seats.

[0026] 3. The parameter division range of P2, P3, and P4 can be modified according to the ejection requirements by modifying the constraint parameters of the program control system without establishing a new program control structure again.

[0027] 4. The state parameters obtained by the sensor are mapped to the control system constraint range to determine the ejection mode. The technical solution is mature and can meet actual requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the overall structure of the detonation vector propulsion ejection seat provided by the present invention;

[0029] Figure 2 It is a structural schematic diagram of the detonation vector propulsion device provided by the present invention;

[0030] Figure 3 It is a schematic diagram of the mode division of the present invention.

[0031] The reference numerals are as follows:

[0032] 1 restraining device; 2 locking device; 3 sliding track; 4 integrated circuit control system; 5 power supply; 6 angle sensor; 7 fuel tank; 8 detonation combustion chamber; 9 guide platform; 10 rocket pack; 11 air intake duct; 12 high-frequency pulse igniter; 13 one-way electric valve. DETAILED DESCRIPTION

[0033] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0034] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "axial", "radial", "vertical", "horizontal", "inner", "outer" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0035] An ejection seat using vector detonation propulsion comprises a seat, on which is provided a restraining device 1, a locking device 2, a sliding track 3, an integrated circuit control system 4, a fuel tank 7 and a rocket pack 10; the restraining device 1 is used to restrain a person on the seat, and the locking device 2 is used to activate the restraining device 1; the sliding track 3 is arranged on the back of the seat, and the sliding track 3 can slide along the sliding track; the integrated circuit control system 4 is used to control a circuit system arranged on the seat; the fuel tank 7 and the detonation combustion chamber 8 are arranged at the bottom of the seat; the fuel tank 7 and the rocket pack 10 are used to provide a power source.

[0036] Among them, after the fuel in the fuel tank 7 and the rocket pack 10 and the gas in the air intake pipe 11 enter the detonation combustion chamber 8 and are ignited by the high-frequency pulse igniter 12, energy is generated to propel the seat.

[0037] It also includes a plurality of one-way electric valves 13 , the opening and closing of which are controlled by the integrated circuit control system 4 .

[0038] It also includes an angle sensor 6 ; the angle sensor 6 is used to monitor and transmit the ejection angle of the seat to the integrated circuit control system 4 .

[0039] There are two rocket packs 10 and two fuel tanks 7; one-way electric valves 13 and high-frequency pulse igniters 12 are installed on the rocket packs 10 and the fuel tanks 7.

[0040] A guide platform 9 is provided at the outlet end of the detonation combustion chamber 8 .

[0041] The integrated circuit control system 4 is a single chip microcomputer.

[0042] An ejection seat and attitude correction method using vector detonation propulsion specifically include the following steps:

[0043] (1) A detonation vector-propelled ejection seat, having four ejection modes, namely, P1: high-altitude ejection parachuting, H>300m; P2: low-altitude small-angle ejection parachuting, H≤300m, 0°≤α≤30°, 150°≤α≤180°; P3: low-altitude large-angle ejection parachuting, H≤300m, 30°<β<150°; P4: low-altitude negative-angle ejection parachuting, H≤300m, 180°<γ<0°.

[0044] (2) The division parameters of P1, P2, P3, and P4 are saved to the integrated circuit control system 4 through code. The integrated circuit control system 4 is a single-chip microcomputer that can write programs. The compilation process is relatively simple and easy to implement;

[0045] (3) The program compiled into the integrated circuit control system 4 includes several modules, including starting the restraint device 1, detonating the rocket package, judging the ejection mode, and responding to the detonation thrust system. The program execution steps are determined by dividing the program priority and the delay time. A delay time is set between each step of the program execution. After the delay ends, the next program is executed;

[0046] (4) The flight platform and the angle sensor 6 respectively continuously transmit the altitude and angle signals to the integrated circuit control system. When the pilot makes an ejection action, the ejection mode is determined based on the two state parameters of altitude and angle as the identification object;

[0047] (5) After the ejection command is issued, the control system executes the ejection steps according to the program. First, the locking device 2 is activated. The tension provided by the locking device 2 when working is about 130N, which drives the restraint device 1 to fix the pilot's body on the seat;

[0048] (6) After the delay time, the ignition procedure is executed and the rocket pack is detonated, causing the seat to be ejected from the cockpit along the sliding track;

[0049] (7) The control system responds to the angle sensor signal and the flight altitude signal during ejection and executes one of the four modes of program plans. The execution programs in the four modes are different;

[0050] (8) The detonation vectoring power system operates under the control of the corresponding ejection program. In P1 mode, the power ignition program does not respond and the power unit does not operate. In P2, P3, and P4 modes, the power unit starts;

[0051] (9) In P2, P3, and P4 modes, the output program instructions include the start and stop of the one-way electric valve and the response of the high-frequency pulse igniter. When working, the one-way electric valve opens first, and the high-frequency pulse igniter ignites 0.1s later;

[0052] (10) In P3 mode, the ignition program controls the four combustion chambers to start simultaneously, providing thrust to continue moving upward in the ejection direction;

[0053] (11) When the ejection mode is P2 or P4, the ignition program triggers the side with the smaller angle between the ejection direction and the horizontal plane, that is, the side with the smaller angle between the ejection direction and the horizontal plane is ignited first, and 0.5s later, the combustion chamber on the other side is ignited. First, after the two detonation combustion chambers on the side with the smaller angle are working, they interact with the guide table to change the seat angle. The function of the guide table is: the guide table is perpendicular to the ground direction. Due to the change in the inclination angle of the combustion chamber, the gap between the guide table and the combustion chamber wall is inconsistent, showing that the gap is small on the inclined side and large on the side away from the inclination, resulting in different flow rates and expansion acceleration effects of the detonation products, generating torques of different sizes, and achieving the purpose of correcting the unfavorable posture of the seat. Subsequently, after a delay of 0.5s, the detonation combustion chamber on the other side is ignited under the control of the ignition program, while providing upward lift to increase the landing height.

[0054] The ejection angle α and β ranges in different modes can be adjusted by modifying the upper and lower limits of the angle parameters in the control system.

[0055] The power supply installed behind the seat back is used to supply power to the control system, the high-frequency pulse igniter 12, the one-way electric valve 13, the angle sensor 6, and the locking device 2.

[0056] The sliding track 3 on the back of the seat is embedded and connected with the flight cabin component, and when ejected, it pops up upward along the sliding track path.

[0057] The angle sensor 6 is installed horizontally under the seat.

[0058] The rocket pack 10 and the fuel tank 7 are fixed under the seat through a supporting pedestal and are alternately distributed in a circle. The fuel tank contains premixed gas with a relatively high pressure.

[0059] The one-way electric valve 13, the high-frequency pulse igniter 12 and the guide platform 9 are all installed in a cross shape. The one-way electric valve 13 is installed at the air intake end of the combustion chamber to prevent the gas entering the combustion chamber from flowing back; the high-frequency pulse igniter 12 is installed in opposite directions at the head position of the detonation combustion chamber, and the guide platform 9 is installed at the tail end of the detonation combustion chamber.

[0060] The restraint device 1 has anti-static and flame-retardant functions.

[0061] The Rafale nozzle is used as the exhaust form at the tail of the thrust combustion chamber. The Rafale nozzle can fully accelerate the detonation products and improve the thrust performance.

[0062] A method for correcting the attitude of an ejection seat using vector detonation propulsion comprises the following steps:

[0063] Step 1: Divide the ejection mode according to the parameter setting range, and based on this, write the program execution plan under different modes; among them, the P1 state constraint parameter is H>300m; P2 is H≤300m, 0°≤α≤30°, 150°≤α≤180°; P3 is H≤300m, 30°<β<150°; P4 is H≤300m, 180°<γ<0°. By selecting the two key parameter groups of height and angle as constraint conditions, the corresponding program is saved in the integrated circuit control system;

[0064] Step 2: Divide the program priorities according to the ejection steps, set a delay time between different programs, and execute the next program after the delay time ends;

[0065] Step 3: The program compiled into the integrated circuit control system includes several modules such as starting the restraint device, detonating the rocket package, judging the ejection mode, and responding to the detonation thrust system;

[0066] Step 4: During ejection, the flight altitude and ejection angle signals are mapped to the control system, and the corresponding ejection module program is executed through parameter range judgment.

[0067] Implementation

[0068] First, after the ejection program is started, the locking device is driven by electricity to pull the restraint device to fix the pilot's body. Then, after the delay time is reached, the ignition command is output, and the rocket pack responds quickly to form thrust and ejects from the cockpit along the glide track. At the same time of ejection, the flight altitude and ejection angle signals are mapped to the control system, and the corresponding ejection module program is executed through the parameter range.

[0069] Option 1: P1 mode, the altitude is sufficient, the hovering time is sufficient, the impact with the ground is small when landing, the ignition program does not respond, and the power device does not work;

[0070] Option 2: P3 mode, the ignition program controls the four combustion chambers to start simultaneously, providing thrust to continue moving upward in the ejection direction;

[0071] Option 3: In P2 and P4 modes, during low-altitude ejection, the landing speed is too high, the power unit is started, and the ignition program is set according to the ejection angle. The detonation combustion chamber on the side with a smaller angle between the ejection direction and the horizontal plane works first, and the seat angle is changed under the action of the guide table, and then the transition to P3 mode is made. After 0.5s, the detonation combustion chamber on the other side ignites and works, providing upward lift and increasing the landing height.

[0072] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0073] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention without departing from the principles and intent of the present invention.

Claims

1. An ejection seat using vector detonation propulsion, comprising a seat, characterized in that: The seat is provided with a restraining device (1), a locking device (2), a sliding track (3), an integrated circuit control system (4), a fuel tank (7) and a rocket pack (10); the restraining device (1) is used to restrain the person on the seat, and the locking device (2) is used to start the restraining device (1); the sliding track (3) is arranged on the back of the seat, and the sliding track (3) can slide along the sliding track; the integrated circuit control system (4) is used to control the circuit system arranged on the seat; the fuel tank (7) and the detonation combustion chamber (8) are arranged at the bottom of the seat; the fuel tank (7) and the rocket pack (10) are used to provide a power source; and also includes a posture correction method, which specifically comprises the following steps: The ejection modes are divided into: P1: high altitude ejection parachuting, H>300m; P2: low altitude small angle ejection parachuting, H≤300m, 0°≤α≤30°, 150°≤α≤180°; P3: low altitude large angle ejection parachuting, H≤300m, 30°<β<150°; P4: low altitude negative angle ejection parachuting, H≤300m, 180°<γ<0°; the ejection mode division parameters of P1, P2, P3 and P4 are saved to the integrated circuit control system (4) through code; Set the ejection execution steps: execute each running program through the program priority level and delay time; after the ejection command response, the running program includes activating the locking device, igniting the rocket package and selecting the ejection mode, and the power unit response; The flight platform and the angle sensor (6) respectively continuously transmit the height and angle signals to the integrated circuit control system (4). When the pilot performs the ejection action, the ejection mode is determined based on the two state parameters of height and angle as the identification object; After the ejection command is issued, the integrated circuit control system (4) executes the ejection steps according to the program: first, the locking device (2) is activated to fix the person's body on the seat by driving the restraining device (1); After the delay time is over, the ignition procedure is executed, the rocket pack is detonated, and the seat is ejected from the cockpit along the sliding track (3); The control system responds according to the angle sensor (6) signal and the flight altitude signal during ejection, and executes one of the four modes of program plans; The detonation vector power system works under the control of the corresponding ejection program. In P1 mode, the power ignition program does not respond and the power unit does not work. In P2, P3, and P4 modes, the power unit starts. In the P2, P3 and P4 modes, the output program instructions include the start and stop of the one-way electric valve (13) and the response of the high-frequency pulse igniter (12). When working, the one-way electric valve (13) is first opened, and then the high-frequency pulse igniter (12) ignites.

2. The ejection seat using vector detonation propulsion according to claim 1, characterized in that: The fuel in the fuel tank (7) and the rocket pack (10) and the gas in the air intake pipe (11) enter the detonation combustion chamber (8) and are ignited by the high-frequency pulse igniter (12) to generate energy for pushing the seat.

3. The ejection seat using vector detonation propulsion according to claim 1, characterized in that: It also includes a plurality of one-way electric valves (13), the opening and closing of the one-way electric valves (13) being controlled by an integrated circuit control system (4).

4. The ejection seat using vector detonation propulsion according to claim 1, characterized in that: It also includes an angle sensor (6); the angle sensor (6) is used to monitor and transmit the ejection angle of the seat to the integrated circuit control system (4).

5. The ejection seat using vector detonation propulsion according to claim 1, characterized in that: There are two rocket packs (10) and two fuel tanks (7); one-way electric valves (13) and high-frequency pulse igniters (12) are installed on the rocket packs (10) and the fuel tanks (7).

6. The ejection seat using vector detonation propulsion according to claim 1, characterized in that: A flow guide platform (9) is provided at the outlet end of the detonation combustion chamber (8).

7. The ejection seat using vector detonation propulsion according to claim 1, characterized in that: The integrated circuit control system (4) is a single chip microcomputer.

8. The ejection seat using vector detonation propulsion according to claim 1, characterized in that: In the P3 mode, the ignition program controls the fuel tank (7) and the rocket pack (10) to start simultaneously to provide lift; in the P2 and P4 modes, the detonation combustion chamber (8) on the side with a smaller angle between the ejection direction and the horizontal plane works first, and changes the seat posture under the action of the guide platform, and transitions to the P3 mode. After 0.5 seconds, the detonation combustion chamber (8) on the other side ignites and burns, moving upward.

9. The ejection seat using vector detonation propulsion according to claim 8, characterized in that: The ranges of the ejection angles α and β in different modes can be adjusted by modifying the upper and lower limits of the angle parameters in the integrated circuit control system (4).

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