High-compatibility anti-ablation launching separation mechanism

Abstract

A high-compatibility anti-ablation launching separation mechanism comprises a motor protective cover, a protective shell group, a protective flashboard, a separation mechanism box body, a motor, an electric push rod, a fire rope type falling plug hair control cable, a spring counter-recoil lock, a protective flashboard handle, three groups of steel wire ropes, a pulley block, a magnetic ring sensor, a protective flashboard spring and the like. The separation mechanism box body is an installation platform of all modules, serves as a foundation of whole machine integration and also has a protection function; and after the drop-off plug is separated, the motor drives the electric push rod, the launch control cable is pulled into the separation mechanism box body through the steel wire rope, and meanwhile, the protective flashboard covers the upper part. The high-compatibility ablation-resistant launch separation mechanism is achieved, launch of aircrafts of multiple models can be compatible, stable separation of launch control cables and the aircrafts can be remotely controlled when the aircrafts are launched, the launch control cables are protected from being ablated by tail flames of the aircrafts, reutilization of the launch control cables is achieved, and the launch control cables can be recycled. The device has the advantages of stable separation, high integration level, few operators, simple operation and the like.

Description

Technical Field

[0001] The present invention relates to a highly compatible ablation-proof launch separation mechanism, belonging to the field of aircraft launch. Background Art

[0002] In order to address the current problems of multi-model and multi-batch aircraft launch tests, there is an urgent need for a launch separation mechanism that can be applied to the launch tasks of multiple models of aircraft and can be reused. Currently, the main launch separation mechanisms are electromagnetic separation or tail mechanical pull-off methods, which do not have the function of protecting against tail flames. Since the launch separation mechanism and the launch control cable are damaged after being ablated by the tail flame and cannot be reused, the entire set of launch separation mechanism and launch control cable need to be replaced for the next launch, resulting in a high usage cost, and it is also difficult to ensure separation stability. This is not an economical and practical solution.

[0003] In order to meet the usage requirements of multi-model and multi-batch launch tasks, it is necessary to design a launch separation mechanism that can be compatible with multiple models and can be reused in the environment of aircraft tail flame ablation.

[0004] Through the retrieval of existing technical patent documents, the following documents were found:

[0005] Existing technical patent, Chinese invention publication number CN107328317B, discloses a flame shielding device for an electrical plug-in and unplug-in mechanism of a launch device, adopting a passive separation scheme of separating through an aircraft motion guiding mechanism, with a clever structural design and reliable separation. Due to the limitations of the mechanism design, it needs to be closely attached to the aircraft body during installation, and it cannot be applied to aircraft with a booster larger than the body diameter at the rear end, nor can it be easily applied to special-shaped aircraft with changing front and rear cross-sections, resulting in slightly insufficient compatibility. At the same time, the design limitation of the rigid connection at the position of the separation socket of this mechanism also makes the installation of the device more difficult.

[0006] Existing technical patent, Chinese invention publication number CN113154959A, discloses an automatic separation device for a launch control cable and an aircraft body socket, adopting a passive separation scheme of separating through an aircraft motion guiding mechanism, with a clever structural design and reliable separation. Similar to CN107328317B, due to the limitations of the mechanism design, it needs to be closely attached to the aircraft body during installation, and it cannot be applied to aircraft with a booster larger than the body diameter at the rear end, nor can it be easily applied to special-shaped aircraft with changing front and rear cross-sections, resulting in slightly insufficient compatibility. Moreover, due to the poor closing performance and notch problems of the flame shielding mechanism, it is impossible to completely protect the launch control cable.

[0007] The prior art patent, China Invention Publication No. CN117663915A, discloses an axial separation guide and flame blocking device for an electrical connector of a tail-pushing launch aircraft. The device is axially installed and uses the aircraft movement to pull off and separate the electrical connector. The structure is simple and reliable, but it is only applicable to aircraft with the separation electrical connector located at the tail. The separation point is located at the tail of the aircraft, which causes the separation device and the cable to be directly subjected to the impact of the aircraft tail flame, resulting in poor cable protection and a high damage rate of the separation device.

[0008] The prior art patent, China Invention Publication No. CN217358261U, discloses an active separation type launch device with an electric connector, in which the separation mechanism adopts an active separation type separation mechanism driven by a motor, which has a simple and reliable structure, but is only applicable to aircraft with the separation electric connector located at the tail. The separation mechanism does not take tail flame protection measures, and cannot protect the separation mechanism, launch control cables and electric connectors, etc. The mechanism has a high damage rate, and the impact of the aircraft tail flame can cause the electric connector to short-circuit and damage the launch control equipment. The separation mechanism adopts a single motor solution, which cannot guarantee the operation of the mechanism when the motor fails. Summary of the invention

[0009] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a highly compatible ablation-resistant launch separation mechanism, and to solve the problems of tail flame protection and reusability.

[0010] The technical solution of the present invention is:

[0011] A highly compatible ablation-proof launch separation mechanism, comprising: a motor protection cover, a protective housing group, a protective gate, a separation mechanism box, a motor, an electric push rod, a trigger-type drop-out plug launch control cable, a spring return lock, a protective gate handle, a first steel wire rope, a second steel wire rope, a third steel wire rope, a protective gate spring and a protective gate lock hole;

[0012] The motor protection cover and the protective shell assembly are installed outside the separation mechanism box to provide protection for the functional components inside the separation mechanism box. There is a motor protection cover on each side of the separation mechanism box; the separation mechanism box provides an installation interface for the internal functional components; the protective gate is installed in the upper slide groove of the separation mechanism box, and the separation and launch separation mechanism is opened and closed by translation in the slide groove, providing protection for the internal functional components;

[0013] The motor and the electric push rod are located in the motor protection cover. The motor is installed on the electric push rod. There are two sets in total. They are connected to the electrical control cabinet through cables respectively, and receive instructions from the electrical control cabinet to drive the electric push rod to perform telescopic movements. The ends of the two electric push rods are both extended into the separation mechanism box body, and are connected to the pull rope of the pull rope type shedding plug control cable through the first wire rope and the second wire rope respectively.

[0014] The protection shutter is provided with a protection shutter lock hole and a protection shutter handle. The protection shutter lock hole is used to cooperate with the spring return lock to lock and unlock the protection shutter; the spring return lock is installed in the separation mechanism box body and includes a lock body, a lock shaft and a spring. One end of the lock shaft is used to insert into the protection shutter lock hole to fix the protection shutter, and the other end is connected to the first steel wire rope through the third steel wire rope and thus connected to the electric push rod; the protection shutter springs are respectively connected to the protection shutter and the separation mechanism box body, and drive the protection shutter to move in the chute of the separation mechanism box body.

[0015] Further, one end of the firing cord type detachable plug hair control cable is connected to the firing control system. The firing cord type detachable plug hair control cable passes through the separation mechanism box body, and the plug end passes out from the protection shutter and is connected to the aircraft system port.

[0016] Further, it also includes a pulley block installed in the separation mechanism box body to provide a steering function for the first steel wire rope and the second steel wire rope, so that the movement directions of the first steel wire rope and the second steel wire rope after being tightened are perpendicular to the bottom surface of the separation mechanism box body, ensuring that the separation direction of the firing cord type detachable plug hair control cable is perpendicular to the aircraft axis direction.

[0017] Further, it also includes a magnetic ring sensor installed in the electric push rod to detect the movement stroke of the electric push rod and feedback it in the form of discrete digital quantity signals.

[0018] Further, the electrical control cabinet is used for power supply and to realize the drive control of the motor. The remote control cable is connected to the electrical control cabinet and the remote control box to remotely control the launch separation mechanism to realize the separation operation of the firing cord type detachable plug hair control cable and the aircraft during launch.

[0019] Further, the first steel wire rope and the second steel wire rope can adapt to the launch requirements of different diameter aircraft by adjusting the rope length.

[0020] Further, the third steel wire rope controls the unlocking time of the protection shutter after the detachable plug is separated by adjusting the connection position with the first steel wire rope, so as to ensure that the protection shutter is closed after the firing cord type detachable plug hair control cable falls into the separation mechanism box body.

[0021] Further, the remote signal of the electrical control cabinet uses a DC / DC module to realize the voltage pull-up and hold of the signal, ensuring the high-level signal voltage value of the remote signal under the condition of 500m long-distance signal transmission and ensuring that there is no signal loss phenomenon after the remote control signal is transmitted.

[0022] Furthermore, the two sets of motors and electric push rods are backup to each other. The combination of a single set of motors and electric push rods can work normally to pull off the control cable of the pull-fire-rope type drop plug from the aircraft, ensuring that the system can operate normally when a set of motors and electric push rods fails; the internal components, motors and electric push rods of the electric control cabinet are all selected with low-temperature resistant models and can work normally in low-temperature environments below zero.

[0023] In a second aspect, the present invention also provides a launch separation method based on a highly compatible anti-ablative launch separation mechanism, including the following steps:

[0024] Step 1: Adjust the launch rack to a predetermined angle. After receiving the launch command, drive the motors on both sides to control the electric push rod to contract to the minimum stroke;

[0025] Step 2: During the contraction of the electric push rod, pull the first steel wire rope and the second steel wire rope to tighten until the drop plug is pulled off. The control cable of the pull-fire-rope type drop plug falls into the interior of the separation mechanism box under the combined action of gravity and the tensile force transmitted by the first steel wire rope and the second steel wire rope;

[0026] Step 3: After the drop plug of the control cable of the pull-fire-rope type drop plug is pulled off under the tensile force transmitted by the first steel wire rope and the second steel wire rope, the electric push rod continues to contract until the third steel wire rope is stressed and straightened and continues to contract to the minimum stroke;

[0027] Step 4: The locking shaft of the spring return lock moves downward under the tensile force transmitted by the third steel wire rope. The locking shaft disengages from the lock hole of the protective shutter, and the protective shutter is unlocked and slides horizontally along the internal chute of the separation mechanism box under the contraction force of the protective shutter spring until the protective shutter reaches the bottom of the chute. At this point, the mechanism is closed, and the protective shutter can protect the internal mechanism and the control cable of the pull-fire-rope type drop plug from the subsequent aircraft tail flame ablation during launch.

[0028] The beneficial effects of the present invention compared with the prior art are:

[0029] The present invention is a launch separation mechanism resistant to aircraft tail flame ablation. It can remotely control the stable separation of the control cable from the aircraft through a remote control box during aircraft launch, and after separation, the protective shutter is closed through linkage to protect the control cable from aircraft tail flame ablation, realizing the reuse of the control cable, and can adapt to the general launch requirements of multiple types of aircraft by adjusting the length of the steel wire rope. Description of the Drawings

[0030] Figure 1 It is a schematic diagram of the shell composition of the present invention;

[0031] Figure 2 It is a schematic diagram of the internal composition of the present invention;

[0032] Figure 3 It is a schematic diagram of the electric control composition of the present invention;

[0033] Figure 4 This is the internal perspective schematic diagram of the present invention;

[0034] Figure 5 This is the schematic diagram of the bottom wire outlet of the present invention;

[0035] Figure 6 This is the schematic diagram of the emission state of the present invention;

[0036] Figure 7 This is the schematic diagram of the internal structure of the separation mechanism box body of the present invention;

[0037] In the figure: 1 is the motor protective cover, 2 is the protective housing group, 3 is the protective shutter, 4 is the separation mechanism box body, 5 is the motor, 6 is the electric push rod, 7 is the pull-fire-rope type detachable plug hair control cable, 8 is the spring return lock, 9 is the protective shutter handle, 10 is the first steel wire rope, 11 is the second steel wire rope, 12 is the third steel wire rope, 13 is the pulley group, 14 is the magnetic ring sensor, 15 is the protective shutter spring, 16 is the protective shutter lock hole, 17 is the electrical control cabinet, 18 is the remote control cable, and 19 is the remote control box. Specific embodiments

[0038] The following further describes the specific embodiments of the present invention in detail with reference to the accompanying drawings.

[0039] As Figure 1 and Figure 2 shown, the present invention provides a highly compatible anti-ablative launch separation mechanism, which is characterized by including: a motor protective cover 1, a protective housing group 2, a protective shutter 3, a separation mechanism box body 4, a motor 5, an electric push rod 6, a pull-fire-rope type detachable plug hair control cable 7, a spring return lock 8, a protective shutter handle 9, a first steel wire rope 10, a second steel wire rope 11, a third steel wire rope 12, a protective shutter spring 15, and a protective shutter lock hole 16;

[0040] The motor protective cover 1 and the protective housing group 2 are installed outside the separation mechanism box body 4 to provide protection for the internal functional components of the separation mechanism box body 4. There is one motor protective cover 1 on each side of the separation mechanism box body 4; the separation mechanism box body 4 provides an installation interface for the internal functional components; the protective shutter 3 is installed in the upper chute of the separation mechanism box body 4 and realizes the opening and closing of the separation launch separation mechanism by translating in the chute to provide protection for the internal functional components;

[0041] The motor 5 and the electric push rod 6 are located inside the motor protective cover 1. The motor 5 is installed on the electric push rod 6, with a total of two groups, which are respectively connected to the electrical control cabinet 17 through cables and receive instructions from the electrical control cabinet 17 to drive the electric push rod 6 to perform telescopic movements; the ends of the two electric push rods 6 both extend into the separation mechanism box body 4 and are respectively connected to the pull-fire rope of the pull-fire-rope type detachable plug hair control cable 7 through the first steel wire rope 10 and the second steel wire rope 11;

[0042] The protection shutter 3 is provided with a protection shutter lock hole 16 and a protection shutter handle 9. The protection shutter lock hole 16 is used to cooperate with the spring return lock 8 to realize the locking and unlocking of the protection shutter 3. The spring return lock 8 is installed in the separation mechanism box body 4 and includes a lock body, a lock shaft and a spring. One end of the lock shaft is used to insert into the protection shutter lock hole 16 to fix the protection shutter 3, and the other end is connected to the first steel wire rope 10 through the third steel wire rope 12 and thus connected to the electric push rod 6. The protection shutter spring 15 is respectively connected to the protection shutter 3 and the separation mechanism box body 4, and drives the protection shutter 3 to move in the chute of the separation mechanism box body 4.

[0043] One end of the pull-fire rope type detachable plug firing control cable 7 is connected to the firing control system. The pull-fire rope type detachable plug firing control cable 7 passes through the separation mechanism box body 4, and the plug end passes out from the protection shutter 3 and is connected to the aircraft system port.

[0044] The separation mechanism of the present invention further includes a pulley block 13, which is installed in the separation mechanism box body 4 and provides a steering function for the first steel wire rope 10 and the second steel wire rope 11, so that the moving directions of the first steel wire rope 10 and the second steel wire rope 11 after being tightened are perpendicular to the bottom surface of the separation mechanism box body 4, ensuring that the separation direction of the pull-fire rope type detachable plug firing control cable 7 is perpendicular to the aircraft axis direction.

[0045] The separation mechanism of the present invention further includes a magnetic ring sensor 14, and the magnetic ring sensor 14 is installed in the electric push rod 6 to detect the movement stroke of the electric push rod 6 and feed it back in the form of discrete digital quantity signals.

[0046] As Figure 3 shown, the electric control cabinet 17 is used for power supply and realizing the drive control of the motor 5. The remote control cable 18 is connected to the electric control cabinet 17 and the remote control box 19 to remotely control the launch separation mechanism to realize the separation operation of the pull-fire rope type detachable plug firing control cable 7 from the aircraft during launch.

[0047] Preferably, the first steel wire rope 10 and the second steel wire rope 11 can adapt to the launch requirements of aircrafts with different diameters by adjusting the rope lengths.

[0048] Preferably, the third steel wire rope 12 controls the unlocking time of the protection shutter after the detachable plug is separated by adjusting the connection position with the first steel wire rope 10, so as to ensure that the pull-fire rope type detachable plug firing control cable 7 falls into the separation mechanism box body 4 and then the protection shutter 3 is closed.

[0049] Embodiment:

[0050] Please also refer to Figures 1 to 7 .

[0051] A highly compatible anti-ablative launch separation mechanism, including: motor protective cover 1, protective housing group 2, protective shutter 3, separation mechanism box body 4, motor 5, electric push rod 6, pull-fire-rope type detachable plug firing control cable 7, spring return lock 8, protective shutter handle 9, first steel wire rope 10, second steel wire rope 11, third steel wire rope 12, pulley group 13, magnetic ring sensor 14, protective shutter spring 15, protective shutter lock hole 16, electrical control cabinet 17, remote control cable 18, remote control box 19, etc. Among them,

[0052] - Separation mechanism box body 4: The separation mechanism box body 4 is made of stainless steel, has good anti-corrosion and high-temperature resistance capabilities, and provides installation interfaces for various components;

[0053] - Motor protective cover 1, protective housing group 2: The motor protective cover 1 and the protective housing group 2 are installed outside the separation mechanism box body to provide protection for internal functional components;

[0054] - Protective shutter 3: The protective shutter 3 is installed in the upper chute of the separation mechanism box body 4 and realizes the opening and closing of the mechanism by translating in the chute, providing protection for internal functional components, as shown in Figure 4 、 5 Figure 7;

[0055] - Motor 5: The motor 5 is installed on the electric push rod 6, with a total of two groups, and is respectively connected to the electrical control cabinet 17 through cables, receiving instructions from the electrical control cabinet 17 to drive the electric push rod 6 to perform telescopic motion;

[0056] - Electric push rod 6: The electric push rod 6 has a total of two groups, which are respectively fixed on both side positions of the separation mechanism box body 4 and perform telescopic motion driven by the respective connected motors 5;

[0057] - Pull-fire-rope type detachable plug firing control cable 7: The pull-fire-rope type detachable plug firing control cable 7 is connected to the two side electric push rods 6 through the first steel wire rope 10 and the second steel wire rope 11. The pull-fire-rope type detachable plug end of the firing control cable is connected to the aircraft system port, and the other end is connected to the firing control system;

[0058] - Spring return lock 8: The spring return lock 8 is installed inside the separation mechanism box body 4, mainly including a lock body, a lock shaft and a spring. One end of the lock shaft is used to insert into the protective shutter lock hole 15 to fix the protective shutter 3, and the other end is connected to the first steel wire rope 10 through the third steel wire rope 12 and thus connected to the electric push rod 6.

[0059] - Protective shutter handle 9: The protective shutter handle 9 is installed on the protective shutter 3 and is used to pull the protective shutter 4 and close the spring notch on the separation mechanism box body 4;

[0060] - First steel wire rope 10, second steel wire rope 11: The first steel wire rope 10 and the second steel wire rope 11 are used to connect the pull-rope type detachable plug hair control cable 7 at the detachable plug end and the electric push rod 6;

[0061] - Third steel wire rope 12: The third steel wire rope 12 is used to connect the spring return lock 8 and the first steel wire rope 10;

[0062] - Pulley block 13: The pulley block 13 provides a steering function for the first steel wire rope 10 and the second steel wire rope 11, so that the moving directions of the first steel wire rope 10 and the second steel wire rope 11 after being tightened are perpendicular to the bottom surface of the separation mechanism box body 4, ensuring that the separation direction of the pull-rope type detachable plug hair control cable 7 is perpendicular to the axis direction of the aircraft;

[0063] - Magnetic ring sensor 14: The magnetic ring sensor is installed inside the electric push rod 6 to detect the movement stroke of the electric push rod 6 and feedback it in the form of discrete digital quantity signals.

[0064] - Protection gate plate spring 15: The protection gate plate spring 15 is respectively connected to the protection gate plate 3 and the separation mechanism box body 4, driving the protection gate plate 3 to move in the chute of the separation mechanism box body 4;

[0065] - Protection gate plate lock hole 16: The protection gate plate lock hole 16 is installed on the protection gate plate 3, and cooperates with the spring return lock 8 to realize the locking and unlocking of the protection gate plate 3;

[0066] - Electrical control cabinet 17: The electrical control cabinet 17 supplies power to the whole mechanism and drives the motor 5 to operate to realize the movement of the whole mechanism;

[0067] - Remote control cable 18: The remote control cable 18 connects the electrical control cabinet 17 and the remote control box 19 to realize the long-distance operation of the whole mechanism;

[0068] - Remote control box 19: The remote control box 19 is connected to the electrical control cabinet 17 through the remote control cable 18, and is used to remotely control the mechanism to realize the separation operation of the pull-rope type detachable plug hair control cable 7 and the aircraft during launch;

[0069] The first steel wire rope 10 and the second steel wire rope 11 can adapt to the launch requirements of aircraft with different diameters by adjusting the rope length. The third steel wire rope 12 can control the unlocking time of the protection gate plate after the detachable plug is separated by adjusting the connection position with the first steel wire rope 10, so as to ensure that the pull-rope type detachable plug hair control cable 7 falls into the separation mechanism box body 4 and then the protection gate plate 3 is closed.

[0070] The remote control cable 18 adopts a segmented design with a length of 100 m per segment, and its length can be adjusted according to the distance between the bunker position and the launch position, ensuring that the operator can operate the remote control box 19 in the safety bunker. The remote signal of the electrical control cabinet 17 uses a DC / DC module to realize the voltage pull-up and holding of the signal, ensuring the high-level signal voltage value of the remote signal under the condition of long-distance signal transmission of 500 m, and ensuring that there is no signal loss after the remote control signal is transmitted.

[0071] The magnetic ring sensor 14 is installed inside the electric push rod 6, and the movement stroke of the electric push rod is detected by the magnetic inductor, so as to obtain the real-time position of the current electric push rod, and it can prevent the push rod from overextending and overretracting, as well as the phenomena of motor stalling and driver overcurrent.

[0072] The two groups of motors 5 and electric push rods 6 are backup to each other. The combination of a single group of motor 5 and electric push rod 6 can normally work to pull off the firing cord type detachable plug hair control cable 7 from the aircraft, ensuring that the system can operate normally when a group of motor 5 and electric push rod 6 combination fails.

[0073] The internal components (such as PLC, relay, and drive, etc.) of the electrical control cabinet 17, the motor 5, and the electric push rod 6 are all selected with low-temperature resistant models, which can ensure the normal operation of the system in a low-temperature environment below zero.

[0074] This embodiment realizes a highly compatible ablation-resistant launch separation mechanism, which can be compatible with the launch of multiple models of aircraft, realizes the stable separation of the remote control hair control cable and the aircraft during the launch of the aircraft, protects the hair control cable from being ablated by the tail flame of the aircraft, realizes the reuse of the hair control cable, and has the advantages of stable separation, high integration, few operators, and simple operation.

[0075] Working process and principle:

[0076] Install the present invention at the predetermined position of the launch rack, remove the motor protective cover 1 and the protective housing group 2, pull the protective gate handle 9 to unfold the protective gate 3 until the locking shaft of the spring return lock 8 is inserted into the protective gate lock hole 16. Only after confirming that the protective gate 3 is in place and locked can the next operation be carried out. Pass the power supply cable through the wire hole of the motor protective cover 1 to connect with the motor, and the other end is connected to the electrical control cabinet 17. After confirming that the motor is normally powered on, install the two groups of motor protective covers. Send instructions through the electrical control cabinet 17 to drive the motors 5 on both sides to control the electric push rod 6 to extend to the maximum stroke, and pass the firing cord type detachable plug hair control cable 7 through the bottom wire hole of the separation mechanism box 4 and upward through the opening position after the protective gate 3 is pulled open and connect it to the aircraft system port, such as Figure 6As shown. After confirming the firm connection, connect the pull-fire rope type detachable plug to the first steel wire rope 10 and the second steel wire rope 11. Send an instruction through the electrical control cabinet 17 to drive the motors 5 on both sides to control the electric push rod 6 to contract until the first steel wire rope 10 and the second steel wire rope 11 are tightened and straightened, ensuring that the first steel wire rope 10 and the second steel wire rope 11 are respectively embedded in the pulley grooves of the two pulleys of the pulley block 13. After confirming the firm connection of the first steel wire rope 10, the second steel wire rope 11, and the third steel wire rope 12, the protective housing group 2 can be installed. Finally, connect the remote control box 19 to the electrical control cabinet 17 through the remote control cable 18 to complete the installation of the entire mechanism.

[0077] During operation, the launch rack is adjusted to the predetermined angle. After issuing the launch command, click the control button on the remote control box 19 to drive the motors 5 on both sides to control the electric push rod 6 to contract to the minimum stroke. During the contraction of the electric push rod 6, the first steel wire rope 10 and the second steel wire rope 11 are pulled to tighten until the detachable plug is pulled off. The control cable 7 of the pull-fire rope type detachable plug falls into the internal part of the separation mechanism box 4 under the combined action of gravity and the pulling force transmitted by the first steel wire rope 10 and the second steel wire rope 11. After the detachable plug of the control cable 7 of the pull-fire rope type detachable plug is pulled off under the pulling force transmitted by the first steel wire rope 10 and the second steel wire rope 11, the electric push rod 6 continues to contract until the third steel wire rope 12 is stressed and straightened and continues to contract to the minimum stroke. The lock shaft of the spring return lock 8 moves downward under the pulling force transmitted by the third steel wire rope 12, and the lock shaft disengages from the lock hole 16 of the protective shutter. The protective shutter 3 is unlocked and slides horizontally along the internal chute of the separation mechanism box 4 under the contraction force of the protective shutter spring 15 until the protective shutter 3 reaches the bottom of the chute. At this point, the mechanism is closed, and the protective shutter 3 can protect the internal mechanism and the control cable 7 of the pull-fire rope type detachable plug from the ablation of the subsequent aircraft tail flame during launch. The time from the detachable plug of the control cable 7 of the pull-fire rope type detachable plug being pulled off under the pulling force transmitted by the first steel wire rope 10 and the second steel wire rope 11 to the unlocking and closing of the protective shutter 3 can be adjusted by adjusting the connection position of the third steel wire rope 12 to the first steel wire rope 10. The first steel wire rope 10 and the second steel wire rope 11 can be reversed by adding pulley blocks to adapt to the separation operation of aircraft with separation electrical connectors at different positions.

[0078] The parts not detailed in the present invention are common general knowledge in the art.

Claims

1. A highly compatible anti-ablative launch separation mechanism, characterized in that Including: Motor protection cover (1), protection housing group (2), protection shutter (3), separation mechanism box body (4), motor (5), electric push rod (6), pull-fire-rope type detachable plug hair control cable (7), spring return lock (8), protection shutter handle (9), first steel wire rope (10), second steel wire rope (11), third steel wire rope (12), protection shutter spring (15) and protection shutter lock hole (16); The motor protection cover (1) and the protection housing group (2) are installed outside the separation mechanism box body (4) to provide protection for the internal functional components of the separation mechanism box body (4). There is one motor protection cover (1) on each side of the separation mechanism box body (4); the separation mechanism box body (4) provides an installation interface for the internal functional components; the protection shutter (3) is installed in the upper chute of the separation mechanism box body (4) and realizes the opening and closing of the separation and launch separation mechanism by translating in the chute, providing protection for the internal functional components; The motor (5) and the electric push rod (6) are located inside the motor protection cover (1). The motor (5) is installed on the electric push rod (6), with a total of two groups, which are respectively connected to the electrical control cabinet (17) through cables and receive instructions from the electrical control cabinet (17) to drive the electric push rod (6) to perform telescopic motion; the ends of the two electric push rods (6) both extend into the separation mechanism box body (4) and are respectively connected to the pull-fire-rope of the pull-fire-rope type detachable plug hair control cable (7) through the first steel wire rope (10) and the second steel wire rope (11); The protection shutter (3) is provided with a protection shutter lock hole (16) and a protection shutter handle (9). The protection shutter lock hole (16) is used to cooperate with the spring return lock (8) to realize the locking and unlocking of the protection shutter 3; the spring return lock (8) is installed inside the separation mechanism box body (4), including a lock body, a lock shaft and a spring. One end of the lock shaft is used to insert into the protection shutter lock hole (16) to fix the protection shutter (3), and the other end is connected to the first steel wire rope (10) through the third steel wire rope (12) and thus connected to the electric push rod (6); the protection shutter spring (15) is respectively connected to the protection shutter (3) and the separation mechanism box body (4) to drive the protection shutter (3) to move in the chute of the separation mechanism box body (4).

2. The highly compatible anti-ablative launch separation mechanism according to claim 1, wherein: One end of the pull-fire-rope type detachable plug hair control cable (7) is connected to the firing control system. The pull-fire-rope type detachable plug hair control cable (7) passes through the separation mechanism box body (4), and the plug end passes out from the protection shutter (3) and is connected to the aircraft system port.

3. The highly compatible anti-ablative launch separation mechanism according to claim 2, characterized in that: It also includes a pulley group (13), which is installed inside the separation mechanism box body (4) to provide a steering function for the first steel wire rope (10) and the second steel wire rope (11), so that the moving directions of the first steel wire rope (10) and the second steel wire rope (11) after being tightened are perpendicular to the bottom surface of the separation mechanism box body (4), ensuring that the separation direction of the pull-fire-rope type detachable plug hair control cable (7) is perpendicular to the aircraft axis direction.

4. A highly compatible anti-ablative launch separation mechanism according to claim 3, characterized in that: It also includes a magnetic ring sensor (14). The magnetic ring sensor (14) is installed inside the electric push rod (6) to detect the movement stroke of the electric push rod (6) and feedback it in the form of discrete digital quantity signals.

5. A highly compatible anti-ablative launch separation mechanism according to claim 1, characterized in that: The electrical control cabinet (17) is used for power supply and realizing the drive control of the motor (5). The remote control cable (18) connects the electrical control cabinet (17) and the remote control box (19) to remotely control the launch separation mechanism to realize the separation operation of the pull-fire-rope type drop plug hair control cable (7) and the aircraft during launch.

6. The high-compatibility anti-ablative launch separation mechanism according to claim 1, characterized in that: The first steel wire rope (10) and the second steel wire rope (11) can adapt to the launch requirements of aircraft with different diameters by adjusting the rope length.

7. A highly compatible anti-ablative launch separation mechanism according to any one of claims 1-6, characterized in that: The third steel wire rope (12) controls the unlocking time of the protective shutter after the drop plug is separated by adjusting the connection position with the first steel wire rope (10), so as to ensure that the protective shutter (3) is closed after the pull-fire-rope type drop plug hair control cable (7) falls into the separation mechanism box body (4).

8. A highly compatible anti-ablative launch separation mechanism according to claim 5, characterized in that: The remote signal of the electrical control cabinet (17) uses a DC / DC module to realize the voltage pull-up and holding of the signal, ensuring the high-level signal voltage value of the remote signal under the condition of 500m long-distance signal transmission, and ensuring that there is no signal loss after the remote control signal is transmitted.

9. A highly compatible anti-ablative launch separation mechanism according to claim 5, characterized in that: The two sets of motors (5) and electric push rods (6) are backups for each other. The normal operation of a single set of motors (5) and electric push rods (6) combined can pull off the pull-fire-rope type drop plug hair control cable (7) from the aircraft, ensuring that the system can operate normally when a set of motors (5) and electric push rods (6) combined fails; the internal components, motors (5) and electric push rods (6) of the electrical control cabinet (17) are all selected with low-temperature resistant models and can work normally in a sub-zero low-temperature environment.

10. A launch separation method of a highly compatible anti-ablative launch separation mechanism as described in claim 4, characterized in that, It includes the following steps: Step 1: The launch rack is adjusted to the predetermined angle. After the launch command is issued, the two side motors (5) are driven to control the electric push rod (6) to contract to the minimum stroke. Step 2: During the contraction of the electric push rod (6), the first steel wire rope (10) and the second steel wire rope (11) are pulled tight until the drop plug is pulled off. The pull-fire-rope type drop plug hair control cable (7) falls into the interior of the separation mechanism box body (4) under the combined action of gravity and the pulling force transmitted by the first steel wire rope (10) and the second steel wire rope (11). Step 3: After the drop plug of the pull-fire-rope type drop plug hair control cable (7) is pulled off under the pulling force transmitted by the first steel wire rope (10) and the second steel wire rope (11), the electric push rod (6) continues to contract until the third steel wire rope (12) is stressed and straightened and continues to contract to the minimum stroke. Step 4: The lock shaft of the spring return lock (8) moves downward under the pulling force transmitted by the third steel wire rope (12), the lock shaft disengages from the protective shutter lock hole (16), the protective shutter (3) is unlocked and is subjected to the contraction force of the protective shutter spring (15), and slides horizontally along the internal chute of the separation mechanism box body (4) until the protective shutter (3) reaches the bottom of the chute. At this point, the mechanism is closed, and the protective shutter (3) can protect the internal mechanism and the pull-fire-rope type drop plug hair control cable (7) from the subsequent aircraft tail flame erosion during launch.

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