Aircraft drag parachute lock and drag parachute throwing method

Abstract

The invention provides an aircraft drag parachute lock and a drag parachute throwing method. The drag parachute lock comprises an EMA actuator, a GMA actuator and two same lock head mechanisms. One end of the drag parachute lock is fixed to a body of an aircraft drag parachute cabin through an EMA tail connector and a GMA tail connector, the other end of the drag parachute lock is connected with two padlock rings through a lock hook of an EMA actuator lock head mechanism and a lock hook of a GMA actuator lock head mechanism, and the two padlock rings are connected with the same drag parachute through connecting ropes. The drag parachute lock and the drag parachute throwing system are high in redundancy and reliability, the electrical control process of the EMA actuator and the GMA actuator is convenient and fast, cold air supply of a traditional pneumatic drag parachute lock is not needed, hydraulic oil supply of a traditional hydraulic drag parachute lock is not needed, and initiating explosive device filling used by an explosion type drag parachute lock is not needed; the whole drag parachute jettisoning system is high in redundancy, high in control precision, capable of achieving rapid installation and disassembly and convenient to use and maintain.

Description

Technical Field

[0001] The invention relates to an aircraft system design technology, in particular to a drag parachute lock used for an aircraft drag parachute and a method for throwing and releasing the drag parachute. Background Art

[0002] The aircraft drag parachute is installed in the drag parachute compartment at the tail of the fuselage, and is used to shorten the aircraft's taxiing distance during the landing process. The drag parachute lock is an important device for the aircraft's drag parachute to be deployed or thrown. The reliability of the drag parachute is of great significance to temporarily terminate the flight mission in the event of sudden incidents such as wheel explosion during the landing process of the aircraft, and to ensure flight safety.

[0003] At present, the drag parachute system of aircraft landing mainly consists of control part, drag parachute lock, drag parachute door lock, drag parachute, etc. After the aircraft lands, the pilot manipulates the drag parachute switch on the instrument panel to put it in the parachute release position. Cold air enters the drag parachute lock cavity, pushing the piston to move in the opposite direction, and the drag parachute lock moves to the locked position. At the same time, the fork mechanism pulls the door lock by adjusting the steel cable, and the drag parachute door opens. Under the action of its own guide spring, the guide parachute pops out forcefully and quickly opens, pulling out the main parachute, and the main parachute opens in about three seconds. This is the first parachute release action. The completion of the parachute throwing action is still driven by the cold air system. The pilot manipulates the drag parachute switch on the instrument panel to turn it to the parachute throwing position, and cold air enters the drag parachute lock cavity, pushing the piston to move in the same direction, completing the entire stroke of the piston. The drag parachute lock hook opens to the maximum angle, the drag parachute hanging ring falls off, and the drag parachute is thrown away, completing the entire procedure. The completion of the parachute throwing action must be carried out after the parachute release action is completed, which is guaranteed by the interlocking on the circuit.

[0004] As an important system for aircraft landing deceleration, the drag parachute lock used above adopts traditional pneumatic technology, which has low reliability. During landing, the aircraft often encounters faults such as failure to open the parachute door, accidental parachute release, inability to release the parachute, and inability to jettison the parachute, which affect the completion of the flight mission. In serious cases, the aircraft cannot effectively decelerate and may run off the runway. Summary of the invention

[0005] According to the demand for the development of aircraft drag parachute locks and the problems existing in the prior art, the purpose of the present invention is to provide a drag parachute lock with all-electric motor electric actuation technology and giant magnetostrictive technology to reduce the failure rate of the aircraft drag parachute system, avoid the influence of the traditional cold air source pressure reduction, air leakage and increased mechanism load on the drag parachute system, and save maintenance time. The drag parachute lock and drag parachute jettisoning system of the present invention have high redundancy and high reliability, and the EMA and GMA electrical control processes are convenient and fast. It does not require the cold air supply of the traditional pneumatic drag parachute lock, nor the hydraulic oil supply of the traditional hydraulic drag parachute lock, nor does it require the filling of pyrotechnics used in the explosive drag parachute lock.

[0006] In a first aspect, the present invention provides an aircraft drag parachute lock, one end of which is fixed to the body of an aircraft drag parachute cabin through an EMA tail joint and a GMA tail joint, and the other end of the drag parachute lock is connected to two padlock rings through a lock hook of an EMA actuator locking mechanism and a lock hook of a GMA actuator locking mechanism, respectively, and the two lock rings are connected to the same drag parachute through a connecting rope.

[0007] Further, the drag parachute lock structure comprises a lock shell, a lock hook, a bushing, a spring, a roller, a slider, an output rod-piston, a butterfly spring, an upper end cover, a magnetic side wall, a permanent magnet, an excitation coil, a coil skeleton, a lower magnetic ring, a lower magnetic body, a GMA shell, a Terfenol-D rod, an upper magnetic body, an upper magnetic ring, a GMA actuator controller, a GMA current sensor, a GMA displacement sensor, a DC power supply, a GMA actuator power switch, a GMA tail connector, a GMA padlock ring, an EMA actuator locking mechanism, a permanent magnet synchronous motor, a motor driver, an EMA actuator controller, an EMA force sensor, an EMA displacement sensor, a ball screw, a reducer, a coupling, an EMA actuator power switch, a three-phase AC power line, an EMA tail connector, an EMA padlock ring and a connecting rope;

[0008] The GMA tail connector 2-1 is connected to the external thread at one end of the lower magnetizer 2-8 through the internal thread, and the lower magnetizer 2-8 is connected to the external thread of the lower magnetizer ring 2-9 through the internal thread at the other end; the Terfenol-D rod 2-10 is inserted into the center hole between the lower magnetizer ring 2-9 and the upper magnetizer ring 2-11, and the external thread at one end of the upper magnetizer ring 2-11 is connected to the internal thread at one end of the upper magnetizer 2-12; the upper end cover 2-13 is coaxial with the output rod-piston 2-15, and the upper end cover 2-13 is connected to the output rod-piston 2-1 through the inner hole. 5, the end faces are connected, the gaps between the two are matched, and there is an air gap 2-14 in the middle; there is also an air gap 2-14 between the upper magnetic ring 2-11 and the inner hole of the upper magnetic body 2-12; the air gap 2-14 ensures that the Terfenol-D rod 2-10 can extend or contract along the axial direction, thereby driving the output rod-piston 2-15 to move along the axial direction; the butterfly spring 2-3 is installed between the output rod-piston 2-15 and the GMA housing 2-2; the slider 2-16 is connected to the external thread of the output rod-piston 2-15 by the internal thread;

[0009] The coil skeleton 2-7 is connected to the outer circle of the lower magnetic ring 2-9 and the outer circle of the upper magnetic ring 2-11; the excitation coil 2-6 is wound on the coil skeleton 2-7; the internal thread of the magnetic side wall 2-4 is connected to the external thread of the upper magnetic body 2-12; the permanent magnet 2-5 is embedded in the magnetic side wall 2-4, and is matched by their respective structural bosses; the GMA shell 2-2 wraps the entire GMA actuator rear part 2; the GMA current sensor 2-22 and the GMA displacement sensor 2-23 are installed in the inner hole of the GMA shell 2-2, and their respective signals are fed back to the GMA actuator controller 3; the GMA actuator locking mechanism 17 is connected to the GMA padlock ring 19 through the lock hook 2-18; the GMA padlock ring 19 is connected to the drag parachute through the connecting rope 20;

[0010] The EMA actuator locking mechanism 1 is the same as the GMA actuator locking mechanism 17. The EMA actuator locking mechanism 1 is connected to the EMA padlock ring 18, and the EMA padlock ring 18 is connected to the drag parachute through a connecting rope 20. The motor driver 10 is connected to the permanent magnet synchronous motor 9 through a wire. The rotating shaft of the permanent magnet synchronous motor 9 is connected to the input shaft of the reducer 7 through a coupling 8. The output shaft of the reducer 7 is connected to the ball screw 6. The ball screw 6 is equipped with a matching EMA force sensor 4 and an EMA displacement sensor 5. The EMA force sensor 4 and the EMA displacement sensor 5 feed back different signals to the EMA actuator controller 11 through wires. The three-phase AC power line 12 is connected to the EMA actuator power switch 13 and is responsible for powering the permanent magnet synchronous motor 9 and the motor driver 10. The EMA tail connector 15 is connected to the external thread of the rear part 21 of the EMA actuator through an internal thread. The EMA tail connector 15 is connected to the ear seat in the drag parachute cabin of the fuselage through bolts.

[0011] Furthermore, the GMA actuator controller controls the giant magnetostrictive actuator below, and the tail joint of the GMA actuator is connected to the ear seat of the aircraft drag parachute cabin through a bolt hole. The GMA actuator lock mechanism is connected to the padlock ring of the drag parachute through a lock hook. According to the giant magnetostrictive principle, the magnitude and direction of the current are changed to control the output rod-piston and the slider to move back and forth under the action of force, so that the lock hook of the drag parachute is closed or opened, and the GMA padlock ring of the drag parachute is locked or thrown out, so that the drag parachute is released or thrown out.

[0012] Furthermore, the EMA electromechanical actuator part of the drag parachute lock is composed of an EMA force sensor, an EMA displacement sensor, a ball screw, a reducer, a coupling, a permanent magnet synchronous motor, a motor driver, an EMA actuator controller, an EMA actuator power switch, an EMA tail connector and a three-phase AC circuit to realize the function of the electromechanical actuator. When the three-phase AC is turned on, the permanent magnet synchronous motor starts to move, and the mechanical energy is transmitted to the coupling, the reducer, and the ball screw. The movement of the screw realizes the movement of the output rod-piston and the slider of the drag parachute lock, and the lock hook of the drag parachute is closed or opened, and the padlock ring of the drag parachute is locked or thrown out, so that the drag parachute is released or thrown out. The EMA electromechanical actuator part of the drag parachute lock is connected to the body ear seat of the drag parachute cabin by bolts via the EMA tail connector, and the lock hook of the EMA electromechanical actuator lock mechanism is connected to the EMA padlock ring of the drag parachute.

[0013] Furthermore, the GMM actuator uses the giant magnetostrictive effect of the Terfenol-D rod to open and close the drag parachute lock. Applying different currents to the coil produces a changing magnetic field strength, thereby changing the length of the output rod piston, thereby generating displacement, and moving the drag parachute lock slider. The slider mechanism moves back and forth under the action of force, opening the drag parachute lock hook, and the drag parachute padlock ring is thrown out, realizing the drag parachute parachute.

[0014] Furthermore, the EMA electromechanical actuator has a connecting hole, and a bushing is crimped into the connecting hole to form a bolt hole of the joint, which is convenient for installation on the body structure of the aircraft drag parachute cabin.

[0015] In a second aspect, the present invention further provides a method for releasing an aircraft drag parachute, the method being implemented by using the drag parachute structure, the method comprising:

[0016] 1) The aircraft cockpit is provided with the pilot EMA control button and the pilot GMA control button; the pilot EMA control button has two positions: the parachute release position and the parachute jettison position, and the pilot GMA control button has two positions: the parachute release position and the parachute jettison position;

[0017] 2) Simultaneously press the pilot's EMA control button or the pilot's GMA control button to the parachute release position, the aircraft's drag parachute cabin door electromagnetic switch opens, and the drag parachute cabin door lock opens; the GMA actuator switch power supply at the front end of the drag parachute lock is turned on, and the current direction is controlled to push the piston to move in the reverse direction, and the drag parachute lock moves to the upper locking position; the rear end EMA actuator AC power supply is turned on, the motor rotates forward, pushing the piston to move in the reverse direction, and the drag parachute lock moves to the upper locking position; the drag parachute hanging ring is locked by the drag parachute lock hook, and the drag parachute is in the parachute release state;

[0018] 3) Simultaneously press the pilot's EMA control button or the pilot's GMA control button to the parachute jettison position, the aircraft's drag parachute compartment door electromagnetic switch opens, and the hydraulic door lock opens; the GMA actuator switch power supply at the front end of the drag parachute lock is energized to control the current direction, push the piston to move along the heading, and the drag parachute lock moves to the unlocked position; the rear end EMA actuator AC power supply is energized, the motor reverses, pushes the piston to move along the heading, and the drag parachute lock moves to the unlocked position; the drag parachute's hanging ring is thrown out, and the drag parachute is in the parachute jettison state.

[0019] Furthermore, the interlocking in the circuit ensures that the parachute throwing action must be completed after the parachute releasing action is completed.

[0020] The beneficial effects of the present invention are as follows: the aircraft drag parachute lock of the present invention is simple to install, and the use process is convenient and quick. No other special tools are required except the cockpit control button. By directly converting electrical energy into mechanical energy, the complex and extra-long pipelines of traditional hydraulic or pneumatic actuation are omitted. The electromechanical actuator (EMA) completely eliminates the hydraulic or pneumatic links and adopts mechanical devices such as reducers and ball screws to achieve motion conversion. The giant magnetostrictive actuator further increases the redundancy of the drag parachute lock. The entire drag parachute lock can be quickly installed and disassembled, which is convenient for use and maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the aircraft drag parachute lock;

[0022] Figure 2 It is a schematic diagram of the structure of the GMA actuator of the aircraft drag parachute lock;

[0023] Figure 3 This is a schematic diagram of the lock mechanism of the aircraft drag parachute lock in the open state;

[0024] Figure 4 This is a schematic diagram of the aircraft drag parachute lock, parachute release and parachute throwing method;

[0025] Figure 1 Explanation of the numbers: 1EMA actuator locking mechanism, 2GMA actuator rear, 3GMA actuator controller, 4EMA force sensor, 5EMA displacement sensor, 6 ball screw, 7 reducer, 8 coupling, 9 permanent magnet synchronous motor, 10 motor driver, 11EMA actuator controller, 12 three-phase AC power line, 13EMA actuator power switch, 14GMA actuator power switch, 15EMA tail connector, 16 DC power supply, 17GMA actuator locking mechanism, 18EMA padlock ring, 19GMA padlock ring, 20 connecting rope, 21EMA actuator rear.

[0026] Figure 2Explanation of the numbers: 2-1 GMA tail connector, 2-2 GMA housing, 2-3 disc spring, 2-4 magnetic side wall, 2-5 permanent magnet, 2-6 excitation coil, 2-7 coil frame, 2-8 lower magnetic conductor, 2-9 lower magnetic ring, 2-10 Terfenol-D rod, 2-11 upper magnetic ring, 2-12 upper magnetic conductor, 2-13 upper end cover, 2-14 air gap, 2-15 output rod-piston, 2-16 slider, 2-17 lock housing, 2-18 lock hook, 2-19 bushing, 2-20 spring, 2-21 roller, 2-22 GMA current sensor, 2-23 GMA displacement sensor. DETAILED DESCRIPTION

[0027] The present invention is further described in detail below with reference to the accompanying drawings.

[0028] See attached Figure 1 and 2 The aircraft drag parachute lock structure of the present invention comprises an EMA actuator locking mechanism 1, a GMA actuator rear part 2, a GMA actuator controller 3, an EMA force sensor 4, an EMA displacement sensor 5, a ball screw 6, a reducer 7, a coupling 8, a permanent magnet synchronous motor 9, a motor driver 10, an EMA actuator controller 11, a three-phase AC power line 12, an EMA actuator power switch 13, a GMA actuator power switch 14, an EMA tail connector 15, a DC power supply 16, a GMA actuator locking mechanism 17, an EMA padlock ring 18, a GMA padlock ring 19 and a connecting rope 20.

[0029] The EMA tail joint 15 is fixed to the body structure of the aircraft drag parachute cabin by means of a bolt hole. In practice, there is a connection hole on the EMA tail joint, and a bolt and a nut are connected in the connection hole to connect with the ear on the aircraft body. The ball screw 6 is connected to the EMA actuator locking mechanism 1, and the locking mechanism 1 is connected to the EMA padlock ring 17 of the drag parachute.

[0030] When the electromechanical actuator is actuated, the EMA actuator power switch 12 is turned on, the three-phase AC line 11 supplies power to the permanent magnet synchronous motor 9, the coupling 8 connects to the reducer 7 to rotate, driving the ball screw 6 to rotate, and the EMA force sensor 4 and the EMA displacement sensor 5 provide the force value and displacement value of the ball screw 6 to the EMA actuator controller 11. The EMA actuator controller 11 can control the forward and reverse rotation of the motor. When the permanent magnet synchronous motor 9 rotates forward, it pushes the ball screw 6 to move in the reverse direction, thereby pushing the output rod-piston of the EMA actuator locking mechanism to move to the upper locking position, and the EMA padlock ring of the drag parachute lock is locked. When the permanent magnet synchronous motor 9 reverses, it pushes the ball screw 6 to move in the same direction, thereby pushing the output rod-piston at the front end of the EMA actuator to move in the same direction, and moves to the unlocking position, and the EMA padlock ring of the drag parachute lock is thrown out.

[0031] When the giant magnetostrictive actuator (GMA actuator) is actuated, the DC power supply 16 supplies power to the rear part 2 of the GMA actuator. When the current passes through the coil, a magnetic field is generated, which acts on the giant magnetostrictive material Terfenol-D rod 2-10. The giant magnetostrictive material deforms under the action of the magnetic field, and this deformation can be very precise. The deformation of the material is transmitted through the output end of the actuator, thereby driving the GMA actuator locking mechanism 17. Changing the magnitude and direction of the current can control the displacement and direction of the actuator, thereby achieving precise control of the load. The entire GMA actuator has a fast response speed, high displacement control accuracy, large output force, and good reliability.

[0032] The embodiment of the present invention also provides an aircraft drag parachute lock, which includes a lock shell, a lock hook, a bushing, a spring, a roller, a slider, an output rod-piston, a butterfly spring, an upper end cover, a magnetic side wall, a permanent magnet, an excitation coil, a coil skeleton, a lower magnetic ring, a lower magnetic body, a GMA shell, a Terfenol-D rod, an upper magnetic body, an upper magnetic ring, a GMA actuator controller, a GMA current sensor, a GMA displacement sensor, a DC power supply, a GMA actuator power switch, a GMA tail connector, a GMA padlock ring, an EMA actuator locking mechanism, a permanent magnet synchronous motor, a motor driver, an EMA actuator controller, an EMA force sensor, an EMA displacement sensor, a ball screw, a reducer, a coupling, an EMA actuator power switch, a three-phase AC power line, an EMA tail connector, an EMA padlock ring and a connecting rope.

[0033] The drag parachute lock comprises an EMA actuator, a GMA actuator and two identical lock mechanisms. One end of the entire drag parachute lock is fixed to the body of the drag parachute cabin of the aircraft through an EMA connector and a GMA connector respectively, and the other end of the drag parachute lock is connected to two padlock rings through a lock hook of the EMA actuator and a lock hook of the GMA actuator respectively, and the two lock rings are connected to the same drag parachute through a connecting rope.

[0034] like Figure 2As shown, the GMA tail connector 2-1 is connected to the external thread at one end of the lower magnetizer 2-8 through the internal thread, and the lower magnetizer 2-8 is connected to the external thread of the lower magnetizer ring 2-9 through the internal thread at the other end; the Terfenol-D rod 2-10 is inserted into the center hole between the lower magnetizer ring 2-9 and the upper magnetizer ring 2-11, and the external thread at one end of the upper magnetizer ring 2-11 is connected to the internal thread at one end of the upper magnetizer 2-12; the upper end cover 2-13 is coaxial with the output rod-piston 2-15, and the upper end cover 2-13 is connected to the output rod-piston 2-15 through the inner hole. The end faces of the upper magnetic ring 2-11 and the upper magnetic body 2-12 are connected to each other, and the gap between the two is matched, and there is an air gap 2-14 in the middle; there is also an air gap 2-14 between the upper magnetic ring 2-11 and the inner hole of the upper magnetic body 2-12; the air gap 2-14 ensures that the Terfenol-D rod 2-10 can be extended or contracted along the axial direction, thereby driving the output rod-piston 2-15 to move along the axial direction; the butterfly spring 2-3 is installed between the output rod-piston 2-15 and the GMA housing 2-2; the slider 2-16 is connected to the external thread of the output rod-piston 2-15 by the internal thread;

[0035] The coil skeleton 2-7 is connected to the outer circle of the lower magnetic ring 2-9 and the outer circle of the upper magnetic ring 2-11; the excitation coil 2-6 is wound on the coil skeleton 2-7; the internal thread of the magnetic side wall 2-4 is connected to the external thread of the upper magnetic body 2-12; the permanent magnet 2-5 is embedded in the magnetic side wall 2-4, and is matched by their respective structural bosses; the GMA shell 2-2 wraps the entire GMA actuator rear part 2; the GMA current sensor 2-22 and the GMA displacement sensor 2-23 are installed in the inner hole of the GMA shell 2-2, and their respective signals are fed back to the GMA actuator controller 3; the GMA actuator locking mechanism 17 is connected to the GMA padlock ring 19 through the lock hook 2-18; the GMA padlock ring 19 is connected to the drag parachute through the connecting rope 20;

[0036] The EMA actuator locking mechanism 1 is the same as the GMA actuator locking mechanism 17. The EMA actuator locking mechanism 1 is connected to the EMA padlock ring 18, and the EMA padlock ring 18 is connected to the drag parachute through a connecting rope 20. The motor driver 10 is connected to the permanent magnet synchronous motor 9 through a wire. The rotating shaft of the permanent magnet synchronous motor 9 is connected to the input shaft of the reducer 7 through a coupling 8. The output shaft of the reducer 7 is connected to the ball screw 6. The ball screw 6 is equipped with a matching EMA force sensor 4 and an EMA displacement sensor 5. The EMA force sensor 4 and the EMA displacement sensor 5 feed back different signals to the EMA actuator controller 11 through wires. The three-phase AC power line 12 is connected to the EMA actuator power switch 13 and is responsible for powering the permanent magnet synchronous motor 9 and the motor driver 10. The EMA tail connector 15 is connected to the external thread of the rear part 21 of the EMA actuator through an internal thread. The EMA tail connector 15 is connected to the ear seat in the drag parachute cabin of the fuselage through bolts.

[0037] Figure 3 This is a schematic diagram of the lock mechanism of the aircraft drag parachute lock in the open state.

[0038] The embodiment of the present invention also provides a method for placing and throwing a drag parachute of an aircraft, such as Figure 4 As shown, it contains the following contents:

[0039] 1) The aircraft cockpit is equipped with the pilot EMA control button and the pilot GMA control button. The pilot EMA control button has two positions: parachute release position and parachute jettison position, and the pilot GMA control button has two positions: parachute release position and parachute jettison position;

[0040] 2) Simultaneously press the pilot's EMA control button or the pilot's GMA control button to the parachute release position, the aircraft's drag parachute cabin door electromagnetic switch opens, and the drag parachute cabin door lock opens. The GMA actuator switch power supply at the front end of the drag parachute lock is turned on, controlling the current direction, pushing the piston to move in the reverse direction, and the drag parachute lock moves to the locked position. The AC power supply of the rear end EMA actuator is turned on, the motor rotates forward, pushing the piston to move in the reverse direction, and the drag parachute lock moves to the locked position. The drag parachute's hanging ring is locked by the drag parachute lock's lock hook, and the drag parachute is in the parachute release state;

[0041] 3) Simultaneously press the pilot's EMA control button or the pilot's GMA control button to the parachute jettison position, the aircraft's drag parachute compartment door electromagnetic switch opens, and the hydraulic door lock opens. The front-end GMA actuator switch power supply of the drag parachute lock is powered on, and the current direction is controlled to push the piston to move in the same direction, and the drag parachute lock moves to the unlocked position. The rear-end EMA actuator AC power supply is powered on, the motor reverses, and pushes the piston to move in the same direction, and the drag parachute lock moves to the unlocked position. The drag parachute's hanging ring is thrown out, and the drag parachute is in the parachute jettisoning state;

[0042] 4) The interlocking circuit ensures that the parachute throwing action must be completed after the parachute releasing action is completed;

[0043] 5) A controller hardware is provided to filter the disturbance signal in the electromagnetic signal to avoid the false triggering of the drag parachute ejection mechanism.

[0044] The aircraft drag parachute lock of the present invention is simple to install and is quick and convenient to use. No special tools are required except the cockpit control button. By directly converting electrical energy into mechanical energy, the complex and long pipelines of traditional hydraulic or pneumatic actuation are eliminated. The electromechanical actuator (EMA) completely eliminates the hydraulic or pneumatic links and uses mechanical devices such as reducers and ball screws to achieve motion conversion. The giant magnetostrictive actuator further increases the redundancy of the drag parachute lock. The entire drag parachute lock can be quickly installed and disassembled, which is convenient for use and maintenance.

Claims

1. An aircraft drag parachute lock, characterized in that: One end of the drag parachute lock is fixed to the body of the aircraft drag parachute cabin through an EMA tail joint and a GMA tail joint, and the other end of the drag parachute lock is connected to two padlock rings through a lock hook of an EMA actuator lock head mechanism and a lock hook of a GMA actuator lock head mechanism, and the two padlock rings are connected to the same drag parachute through a connecting rope.

2. The aircraft drag parachute lock according to claim 1, characterized in that: The drag parachute lock structure comprises a GMA actuator rear part (2), a GMA actuator controller (3), a DC power supply 16, a GMA actuator power switch (14), a GMA padlock ring (19), an EMA actuator lock mechanism (1), a permanent magnet synchronous motor (9), a motor driver (10), an EMA actuator controller (11), an EMA force sensor (4), an EMA displacement sensor (5), a ball screw (6), a reducer (7), a coupling (8), an EMA actuator power switch (13), a three-phase AC power line (12), an EMA tail connector (15), an EMA padlock ring (18) and a connecting rope (20); The rear part (2) of the GMA actuator includes: a lock housing (2-17), a lock hook (2-18), a bushing (2-19), a spring (2-20), a roller (2-21), a slider (2-16), an output rod-piston (2-15), a butterfly spring (2-3), an upper end cover (2-13), a magnetic side wall (2-4), a permanent magnet (2-5), an excitation coil (2-6), a coil frame (2-7), a lower magnetic ring (2-9), a lower magnetic body (2-8), a GMA housing (2-2), a Terfenol-D rod (2-10), an upper magnetic body (2-12), an upper magnetic ring (2-11), a GMA current sensor (2-22), a GMA displacement sensor (2-23), and a GMA tail connector (2-1); The GMA tail connector (2-1) is connected to the external thread of one end of the lower magnetizer (2-8) through the internal thread, and the lower magnetizer (2-8) is connected to the external thread of the lower magnetizer ring (2-9) through the internal thread of the other end; the Terfenol-D rod (2-10) is inserted into the center hole between the lower magnetizer ring (2-9) and the upper magnetizer ring (2-11), and the external thread of one end of the upper magnetizer ring (2-11) is connected to the internal thread of one end of the upper magnetizer (2-12); the upper end cover (2-13) is coaxial with the output rod-piston (2-15), and the upper end cover (2-13) is connected to the output rod-piston (2-15) through the inner hole. 5) are connected to the outer circle of the end faces, the two are gap-matched, and there is an air gap (2-14) in the middle; there is also an air gap (2-14) between the upper magnetic ring (2-11) and the inner hole of the upper magnetic body (2-12); the air gap (2-14) ensures that the Terfenol-D rod (2-10) can extend or contract along the axial direction, thereby driving the output rod-piston (2-15) to move along the axial direction; the butterfly spring (2-3) is installed between the output rod-piston (2-15) and the GM housing (2-2); the slider (2-16) is connected to the external thread of the output rod-piston (2-15) by the internal thread; The coil frame (2-7) is connected to the outer circle of the lower magnetic conductive ring (2-9) and the outer circle of the upper magnetic conductive ring (2-11); the excitation coil (2-6) is wound on the coil frame (2-7); the internal thread of the magnetic conductive side wall (2-4) is connected to the external thread of the upper magnetic conductive body (2-12); the permanent magnet (2-5) is embedded in the magnetic conductive side wall (2-4) and matched with the respective structural bosses; the GMA shell (2-2) wraps the entire rear part (2) of the GMA actuator; the GMA current sensor (2-22) and the GMA displacement sensor (2-23) are installed in the inner hole of the GMA shell (2-2) to feed back their respective signals to the GMA actuator controller (3); the GMA actuator locking mechanism (17) is connected to the GMA padlock ring (19) through the lock hook (2-18); the GMA padlock ring (19) is connected to the drag parachute through the connecting rope (20); The EMA actuator locking mechanism (1) is the same as the GMA actuator locking mechanism (17), the EMA actuator locking mechanism (1) is connected to the EMA padlock ring (18), and the EMA padlock ring (18) is connected to the drag parachute through a connecting rope (20); the motor driver (10) is connected to the permanent magnet synchronous motor (9) through a wire, the rotating shaft of the permanent magnet synchronous motor (9) is connected to the input shaft of the reducer (7) through a coupling (8), the output shaft of the reducer (7) is connected to the ball screw (6), and the ball screw (6) is equipped with a matching EMA force sensor (4) and an EMA displacement sensor (5); the EMA force sensor (4) and the EMA displacement sensor (5) feed back different signals to the EMA actuator controller (11) through the wire; The three-phase AC power line (12) is connected to the EMA actuator power switch (13) and is responsible for supplying power to the permanent magnet synchronous motor (9) and the motor driver (10); the EMA tail connector (15) is connected to the external thread of the rear part (21) of the EMA actuator through an internal thread; the EMA tail connector (15) is connected to the ear seat in the drag parachute compartment of the fuselage through bolts.

3. The aircraft drag parachute lock structure according to claim 2, characterized in that: The GMA actuator controller controls the GMA actuator. The tail joint of the GMA actuator is connected to the ear seat of the aircraft drag parachute cabin through a bolt hole; the GMA actuator locking mechanism is connected to the padlock ring of the drag parachute through a locking hook; according to the giant magnetostrictive principle, the magnitude and direction of the current are changed to control the output rod-piston and the slider to move back and forth under the action of force, so that the locking hook of the drag parachute is closed or opened, and the GMA padlock ring of the drag parachute is locked or thrown out, so that the drag parachute is released or thrown out.

4. The aircraft drag parachute lock structure according to claim 2, characterized in that: The EMA electromechanical actuator part of the drag parachute lock is composed of an EMA force sensor, an EMA displacement sensor, a ball screw, a reducer, a coupling, a permanent magnet synchronous motor, a motor driver, an EMA actuator controller, an EMA actuator power switch, an EMA tail connector and a three-phase AC power line to realize the function of the electromechanical actuator. When the three-phase AC power is turned on, the permanent magnet synchronous motor starts to move, and the mechanical energy is transmitted to the coupling, the reducer, and the ball screw. The movement of the ball screw realizes the movement of the output rod-piston and the slider of the drag parachute lock, realizes the closing or opening of the lock hook of the drag parachute, and the padlock ring of the drag parachute is locked or thrown out, so that the drag parachute is released or thrown out; the EMA electromechanical actuator part of the drag parachute lock is connected to the body ear seat of the drag parachute cabin by bolts via the EMA tail connector, and the lock hook of the EMA electromechanical actuator lock head mechanism is connected to the EMA padlock ring of the drag parachute.

5. The aircraft drag parachute lock structure according to claim 3, characterized in that: The GMA actuator uses the giant magnetostrictive effect of the Terfenol-D rod to open and close the drag parachute lock; applying different currents to the coil produces varying magnetic field strengths, which in turn changes the length of the output rod piston, resulting in displacement to move the drag parachute lock slider. The slider mechanism moves back and forth under the action of force to open the drag parachute's lock hook, and the parachute's padlock ring is thrown out to jettison the parachute.

6. The aircraft drag parachute lock structure according to claim 4, characterized in that: The EMA electromechanical actuator has a connecting hole, in which a bushing is crimped to form a bolt hole of a joint, so as to facilitate installation on the body structure of the aircraft drag parachute cabin.

7. A method for releasing an aircraft drag parachute, characterized in that: The method is implemented by using the drag parachute structure according to any one of claims 1 to 6, and the method comprises: 1) The cockpit of the aircraft is provided with the pilot's EMA control button and the pilot's GMA control button; the pilot's EMA control button has the parachute release position and the parachute jettison position, and the pilot's GMA control button has the parachute release position and the parachute jettison position; 2) Simultaneously press the pilot's EMA control button or the pilot's GMA control button to the parachute release position, the aircraft's drag parachute cabin door electromagnetic switch opens, and the drag parachute cabin door lock opens; the GMA actuator switch power supply at the front end of the drag parachute lock is turned on, and the current direction is controlled to push the piston to move in the reverse direction, and the drag parachute lock moves to the upper locking position; the rear end EMA actuator AC power supply is turned on, the motor rotates forward, pushing the piston to move in the reverse direction, and the drag parachute lock moves to the upper locking position; the drag parachute hanging ring is locked by the drag parachute lock hook, and the drag parachute is in the parachute release state; 3) Simultaneously press the pilot's EMA control button or the pilot's GMA control button to the parachute jettison position, the aircraft's drag parachute compartment door electromagnetic switch opens, and the hydraulic door lock opens; the GMA actuator switch power supply at the front end of the drag parachute lock is energized to control the current direction, push the piston to move along the heading, and the drag parachute lock moves to the unlocked position; the rear end EMA actuator AC power supply is energized, the motor reverses, pushes the piston to move along the heading, and the drag parachute lock moves to the unlocked position; the drag parachute's hanging ring is thrown out, and the drag parachute is in the parachute jettison state.

8. The method for releasing an aircraft drag parachute according to claim 7, characterized in that: The interlocking of the circuit ensures that the parachute throwing action must be completed after the parachute releasing action is completed.

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