CN114537668B - Locking and ejecting mechanism of throwing type flight parameter recorder and control method thereof - Google Patents

Abstract

The invention discloses a locking and ejecting mechanism of a throwable flying parameter recorder and a control method thereof. The locking and ejecting mechanism comprises an installation frame, the bottom plate of the installation frame is provided with the ejection mechanism, and the side opposite to the upper cover plate is placed on the installation frame. The wall is provided with a mounting hole and an assembly hole for setting an unlocking and separating mechanism after being matched; the unlocking and separating mechanism includes a micro-motor, the output shaft of the micro-motor is fixedly connected with a screw rod, the upper surface of the screw rod is in contact with the bottom surface of the connecting rod, and the connecting rod is provided with a screw rod. The external thread has the same rotation direction as the thread on the screw rod; the connecting sleeve is provided with a stepped hole passing through it; the stepped hole is provided with an internal thread that cooperates with the connecting rod and the screw rod, and the assembly hole is vertically provided with extending to the bottom surface of the upper cover plate. A chute, the slider fixed on the connecting sleeve extends into the chute; the controller installed in the installation box is connected with the micro motor. The solution can ensure the stability of the connection between the mounting frame and the upper cover plate through the threaded connection, and solves the problem that the existing explosive product throwing structure needs to be frequently replaced and replaced.

Description

Locking and ejecting mechanism of throwing type flying parameter recorder and its control method

technical field

The invention relates to the technical field of throwing flight parameter recorders of aircraft, in particular to a locking and ejecting mechanism of a throwing type flying parameter recorder and a control method thereof.

Background technique

The flight parameter recorder is a device for recording flight data. It has the characteristics of small size, light weight and high accuracy of collection and recording. It plays an indispensable role in the fields of accident status monitoring, investigation and evidence collection, and flight control evaluation. With the development of aviation industry, the acquisition of flight parameter recorder is more and more urgent. The pop-up flight parameter recorder can be separated from the aircraft before the aircraft crashes, preventing it and the wreckage of the aircraft from falling into the deep sea, valleys and other difficult-to-search places.

At present, the drop-type flying parameter recorder uses the method of detonation of pyrotechnics to eject the recorder from the body. In this method, the stored explosive is ignited, and the recorder is quickly ejected by using the energy generated by the combustion and explosion of the gunpowder. This pop-up method is simple in structure and low in cost. However, the explosive ejection method has some defects in use, such as the inconsistency of the explosive deflagration degree, the uncertainty of the throwing motion law of the flying parameter recorder, the short service life of the explosive, and the complicated disassembly and replacement.

SUMMARY OF THE INVENTION

In view of the above-mentioned deficiencies in the prior art, the locking and ejecting mechanism of the throwing type flying parameter recorder and the control method thereof provided by the present invention solve the problem that the existing explosive product throwing structure needs to be frequently changed and replaced.

In order to achieve the above-mentioned purpose of the invention, the technical scheme adopted in the present invention is:

In the first aspect, a locking and ejecting mechanism of a throwable flying parameter recorder is provided, which includes a mounting frame, an upper cover plate and a mounting box for placing the flying parameter recorder, and a bottom plate of the mounting frame is placed with a mechanism for ejecting the mounting box. For the ejection mechanism, at least one mounting hole and an assembly hole are respectively opened on the opposite side walls of the mounting frame and the upper cover. between the cover plate and the ejection mechanism;

The unlocking and separating mechanism includes a connecting sleeve, a connecting rod fixed on the top surface of the assembly hole, and a micro motor fixed on the bottom surface of the mounting hole; the output shaft of the micro motor is fixedly connected with a screw rod, and the upper surface of the screw rod is in contact with the bottom surface of the connecting rod, and is connected The rod is provided with an external thread with the same rotation direction as the thread on the screw rod; the connecting sleeve is provided with a stepped hole passing through it;

The stepped hole is provided with an internal thread that matches the connecting rod and the screw rod. The assembly hole is vertically provided with a chute extending to the bottom surface of the upper cover plate. The length of the slot is greater than the length of the connecting section between the step hole and the connecting rod; the controller installed in the installation box is connected with the micro motor.

The beneficial effects of the present invention are as follows: when the locking and ejecting mechanism of this scheme receives the aircraft crash signal, the controller starts the micro-motor with the connecting sleeve to move downward, and when the connecting sleeve is separated from the connecting rod, the locking mounting frame and the upper part can be released. The force of the cover plate, at this time, the ejection mechanism restores the deformation and ejects the installation box to realize the ejection of the flight parameter recorder.

This solution can ensure the stability of the connection between the mounting frame and the upper cover by means of threaded connection, and the components that release the locking force of the mounting frame and the cover are mainly mechanical parts, and the connection is reliable. The corresponding parts are replaced, and the unlocking structure uses the principle of the screw nut, which has the advantages of simple structure and low cost.

Further, the ejection mechanism includes an installation strut and an upper sleeve, and the stage stage of the installation strut is sheathed with a number of stacked disc springs; the upper sleeve is slidably sheathed on the installation strut for closing the disc springs.

The beneficial effects of the above technical solutions are as follows: this solution uses a disc spring as the power for throwing, which is not easy to fail, and can ensure that the force when the flying parameter recorder is thrown is equal to the force preset during installation; the disc spring is in the shape of a sheet, The required number of disc springs can be adjusted according to the required force.

Further, the locking and ejecting mechanism of the throwing type flying parameter recorder also includes a power assist mechanism, which includes an installation cavity opened on the installation pillar, and the installation pillar just below the disc spring is provided with a plurality of arc grooves that communicate with the installation cavity. The installation cavity is provided with an electric push rod electrically connected with the controller, and a force transmission member whose upper end extends into the arc groove and is in contact with the disc spring is fixed on the electric push rod.

The beneficial effects of the above technical solutions are: after the power assist mechanism is set in this solution, when the aircraft crashes and the external environment is relatively bad, the deformation of the disc spring can be adjusted, and the flight parameter recorder is thrown out with a large enough throw. The force overcomes the external resistance to ensure that the flight parameter recorder can be ejected.

Further, the design method of the number of stacks of disc springs includes:

Obtain the theoretical environmental parameters of the aircraft during flight, and calculate the theoretical air resistance based on the theoretical environmental parameters:

为阻力系数；S为参考面积；ρ为空气密度；v ₁为飞机飞行速度；Among them, D is the theoretical air resistance;

is the drag coefficient; S is the reference area; ρ is the air density; v ₁ is the flight speed of the aircraft;

According to the weight of the upper cover and the installation box and the theoretical air resistance, calculate the kinetic energy increment when the installation box is thrown out:

为动能增量；G为上盖板和安装盒的重量；

为若干碟形弹簧的初始压缩距离；v ₂为安装盒抛出时的初始速度；g为重力加速度；in,

is the kinetic energy increment; G is the weight of the upper cover and the installation box;

is the initial compression distance of several disc springs; v ₂ is the initial velocity when the installation box is thrown out; g is the acceleration of gravity;

According to the kinetic energy increment and the deformation and bearing load of the single disc spring, calculate the stacking number of disc springs:

Among them, i is the stacking number of disc springs; P is the bearing load of the single disc spring; f is the deformation amount of the single disc spring.

The beneficial effects of the above technical solutions are: in this solution, by accurately designing the stacking number of the disc springs, the force thrown by the flight parameter recorder can be accurately determined, so as to ensure that there is a large enough throw when the flight parameter recorder is thrown. contribute.

Further, the diameter of the connecting section between the stepped hole and the connecting rod is larger than the diameter of the connecting section with the screw rod; in this way, the connecting sleeve can smoothly move downward along the screw rod.

Further, both the mounting bracket and the upper cover are in the shape of a "scratch", and the unlocking and separating mechanism is installed on the side plates of the mounting bracket and the upper cover.

In a second aspect, a method for controlling a locking and ejecting mechanism of a throwable flying parameter recorder is provided, comprising:

S1. Receive the aircraft crash signal, and obtain the real-time environmental parameters of the aircraft flight;

S2. Calculate real-time air resistance according to real-time environmental parameters:

Calculate real-time air resistance based on real-time environmental parameters:

为当前空气阻力；

为阻力系数；S为参考面积；

为当前空气密度；v _实为飞机当前飞行速度；in,

is the current air resistance;

is the resistance coefficient; S is the reference area;

is the current air density; v _is the current flight speed of the aircraft;

S3, determine whether the current air resistance is greater than the theoretical air resistance, if it goes to step S4, otherwise go to step S5;

S4, open the electric push rod to move upward to compress the disc spring, and then enter step S5;

S5. The controller starts the micro-motor, and the micro-motor rotates and moves down along the screw rod with the connecting sleeve. When the connecting sleeve is detached from the connecting rod, the ejecting mechanism pops out the installation box.

The beneficial effects of the present invention are as follows: when the flight parameter recorder is thrown out in this scheme, it can be determined whether the flight parameter recorder can be thrown at the expected speed after overcoming the external resistance during the throwing by calculating the real-time air resistance. The deformation of the disc spring can be adjusted by the power assist mechanism to increase the power of the throw.

Description of drawings

FIG. 1 is a partially cutaway structural schematic diagram of the locking and ejecting mechanism of the throwable flying parameter recorder.

FIG. 2 is an enlarged view of part A in FIG. 1 .

FIG. 3 is a cross-sectional view of the ejection mechanism.

Among them, 1. Mounting frame; 11. Mounting hole; 2. Upper cover plate; 21. Mounting hole; 211. Chute; 3. Mounting box; 4. Electrical interface; 5. Pop-up mechanism; 51. Mounting pillar; 52. Upper sleeve; 53, disc spring; 6, unlocking and separating mechanism; 61, connecting rod; 62, micro motor; 63, connecting sleeve; 631, step hole; 632, slider; 64, screw rod; 7, booster mechanism ; 71, installation cavity; 72, arc groove; 73, electric push rod; 74, force transmission parts.

Detailed ways

The specific embodiments of the present invention are described below to facilitate those skilled in the art to understand the present invention, but it should be clear that the present invention is not limited to the scope of the specific embodiments. For those of ordinary skill in the art, as long as various changes Such changes are obvious within the spirit and scope of the present invention as defined and determined by the appended claims, and all inventions and creations utilizing the inventive concept are within the scope of protection.

As shown in Figures 1 and 2, the locking and ejecting mechanism 5 of the throwable flying parameter recorder provided by this solution includes a mounting frame 1, an upper cover 2 and a mounting box 3 for placing the flying parameter recorder. An electrical interface 4 and an ejection mechanism 5 for ejecting the installation box 3 are placed on the bottom plate. The installation box 3 is provided with a controller, and the controller communicates with other devices in the aircraft through the electrical interface 4 .

As shown in FIG. 3 , in one embodiment of the present invention, the ejection mechanism 5 includes an installation strut 51 and an upper sleeve 52 , and a plurality of stacked disc springs 53 are sheathed on the stage of the installation strut 51 ; the upper sleeve 52 slides It is sleeved on the mounting post 51 to close the disc spring 53 .

This solution uses the disc spring 53 as the power for throwing, which is not easy to fail, and can ensure that the force when throwing the flying parameter recorder is equal to the force preset during installation; size, adjust the number of disc springs needed.

At least one mounting hole 11 and an assembly hole 21 are respectively opened on the opposite side walls of the mounting frame 1 and the upper cover 2. The diameters of the mounting hole 11 and the mounting hole 21 can be set to be the same; the mounting hole 11 and the mounting hole 21 are set after matching The unlocking and separating mechanism 6 connecting the mounting frame 1 and the upper cover 2 , and the mounting box 3 is placed between the upper cover 2 and the ejecting mechanism 5 .

As shown in FIG. 2 , the unlocking and separating mechanism 6 includes a connecting sleeve 63 , a connecting rod 61 fixed on the top surface of the mounting hole 21 , and a micromotor 62 fixed on the bottom surface of the mounting hole 11 ; the output shaft of the micromotor 62 is fixedly connected with a screw rod 64 The upper surface of the screw rod 64 is in contact with the bottom surface of the connecting rod 61, and the connecting rod 61 is provided with an external thread with the same threading direction as the thread on the screw rod 64; the connecting sleeve 63 is provided with a stepped hole 631 passing through it.

When implemented, the diameter of the connecting section between the stepped hole 631 and the connecting rod 61 is preferably greater than or equal to the diameter of the connecting section with the screw rod 64 ; this can ensure that the connecting sleeve 63 moves down smoothly along the screw rod 64 .

The stepped hole 631 is provided with an internal thread that cooperates with the connecting rod 61 and the screw rod 64, the assembly hole 21 is vertically provided with a chute 211 extending to the bottom surface of the upper cover 2, and the slider 632 fixed on the connecting sleeve 63 extends to the chute In 211 , the length of the chute 211 located below the connecting rod 61 is greater than the length of the connecting section between the step hole 631 and the connecting rod 61 ; the controller installed in the installation box 3 is connected to the micro motor 62 .

When the locking and ejecting mechanism 5 is installed, the connecting rod 61 and the micro motor 62 are respectively installed, and the lead screw 64 is welded to the output end of the micro motor 62; The other end of the chute 211 is welded with the connecting sleeve 63, the upper cover 2 is fastened on the mounting frame 1, and the step hole 631 is aligned with the screw rod 64, and then the micro motor 62 is started to rotate with the screw rod 64 to screw in inside the connecting sleeve 63 .

When receiving the plane crash signal, the controller rotates by starting the micro motor 62 (the rotation direction at this time is opposite to the rotation direction when the locking and ejecting mechanism 5 is installed), and the belt connecting sleeve 63 moves downward. At 61, the force that locks the mounting frame 1 and the upper cover 2 can be released. At this time, when the ejection mechanism 5 recovers its deformation, the upward force first makes the upper cover 2 move. At this time, the slider 632 of the connecting sleeve 63 will slide from The lower end of the slot 211 slides out to ensure the smooth opening of the upper cover 3, thereby ensuring the smooth ejection of the installation box 3, and realizing the ejection of the flying parameter recorder.

This solution can ensure the stability of the connection between the mounting frame 1 and the upper cover plate 2 by means of threaded connection, and the components that release the locking force of the mounting frame 1 and the cover plate are mainly mechanical parts, and the connection is reliable. The corresponding parts need to be replaced, and the unlocking structure uses the principle of the screw 64 nut, which has the advantages of simple structure and low cost.

During implementation, it is preferable that the connection between the mounting frame 1 and the upper cover plate 2 of this solution is in the shape of a “screw”, and the unlocking and separating mechanism 6 is installed on the side plates of the mounting frame 1 and the upper cover plate 2 . After this arrangement, the edges of the mounting frame 1 and the upper cover 2 have sufficient thickness, which facilitates the opening of the mounting holes 11 and the mounting holes 21 .

Referring to FIG. 3 again, the locking and ejecting mechanism 5 of the throw-away flying parameter recorder also includes a power assist mechanism 7, which includes an installation cavity 71 opened on the installation pillar 51, and the installation pillar 51 directly below the disc spring 53 is provided with a plurality of The arc-shaped groove 72 communicates with the installation cavity 71. The installation cavity 71 is provided with an electric push rod 73 that is electrically connected to the controller. The force transmission member 74 ; the force transmission member 74 includes a circular bottom plate, and the edge of the circular bottom plate is connected with a plurality of arc-shaped plates passing through the arc-shaped groove 72 .

After the assist mechanism 7 is set in this scheme, when the plane crashes and the external environment is relatively bad, the deformation amount of the disc spring 53 can be adjusted to ensure that the flight parameter recorder is thrown with a large enough throwing force.

In one embodiment of the present invention, the method for designing the stacking number of the disc springs 53 includes:

Obtain the theoretical environmental parameters of the aircraft during flight, and calculate the theoretical air resistance based on the theoretical environmental parameters:

为阻力系数；S为参考面积；ρ为空气密度；v ₁为飞机飞行速度；Among them, D is the theoretical air resistance;

is the drag coefficient; S is the reference area; ρ is the air density; v ₁ is the flight speed of the aircraft;

According to the weight of the upper cover plate 2 and the installation box 3 and the theoretical air resistance, calculate the kinetic energy increment when the installation box 3 is thrown out:

为动能增量；G为上盖板2和安装盒3的重量；

为若干碟形弹簧53的初始压缩距离；v ₂为安装盒3抛出时的初始速度；g为重力加速度；in,

is the kinetic energy increment; G is the weight of the upper cover 2 and the installation box 3;

is the initial compression distance of several disc springs 53; v ₂ is the initial speed when the installation box 3 is thrown out; g is the acceleration of gravity;

According to the kinetic energy increment and the deformation and bearing load of the single disc spring 53, calculate the stacking number of the disc spring 53:

Among them, i is the stacking number of disc springs; P is the bearing load of the single disc spring; f is the deformation amount of the single disc spring.

In this scheme, by accurately designing the stacking number of the disc springs 53, the force thrown by the flight parameter recorder can be accurately determined, so as to ensure that the flight parameter recorder has a sufficiently large throwing force.

This solution also provides a control method for the locking and ejecting mechanism 5 of the throwable flying parameter recorder, which includes:

S1. Receive the aircraft crash signal, and obtain the real-time environmental parameters of the aircraft flight;

S2. Calculate real-time air resistance according to real-time environmental parameters:

为当前空气阻力；

为阻力系数；S为参考面积；

为当前空气密度；v _实为飞机当前飞行速度；in,

is the current air resistance;

is the resistance coefficient; S is the reference area;

is the current air density; v _is the current flight speed of the aircraft;

S3, determine whether the current air resistance is greater than the theoretical air resistance, if it goes to step S4, otherwise go to step S5;

S4, open the electric push rod 73 to move upward to compress the disc spring, and then enter step S5;

S5. The controller starts the micro motor 62, the micro motor 62 rotates and moves the connecting sleeve 63 downward along the screw rod 64. When the connecting sleeve 63 is disengaged from the connecting rod 61, the ejecting mechanism 5 ejects the installation box 3.

When the flight parameter recorder is thrown in this scheme, the real-time air resistance calculation can be used to determine whether the flight parameter recorder can be thrown at the expected speed after overcoming the external resistance during the throwing. The amount of deformation of the shape spring 53 is increased to increase the throwing power.

To sum up, the locking and ejecting mechanism 5 of the throwable flying parameter recorder provided by this solution mainly realizes locking and releasing through mechanical components. Once installed, the corresponding components do not need to be replaced, and the structure is stable.

Claims (4)

1. the locking and pop-up mechanism of throwing type flying parameter recorder, is characterized in that, comprises mounting frame, upper cover plate and the installation box that places flying parameter recorder, the bottom plate of described mounting frame is placed with for ejecting the installation box. For the ejection mechanism, at least one mounting hole and an assembly hole are respectively opened on the opposite side walls of the mounting frame and the upper cover. The box is placed between the upper cover and the ejection mechanism; The unlocking and separating mechanism includes a connecting sleeve, a connecting rod fixed on the top surface of the assembly hole, and a micro motor fixed on the bottom surface of the mounting hole; the output shaft of the micro motor is fixedly connected with a screw rod, and the upper surface of the screw rod is connected to the The bottom surface of the rod is in contact, and the connecting rod is provided with an external thread with the same rotation direction as the thread on the screw rod; the connecting sleeve is provided with a stepped hole passing through it; The stepped hole is provided with an internal thread matched with the connecting rod and the screw rod, the assembly hole is vertically provided with a chute extending to the bottom surface of the upper cover plate, and the sliding block fixed on the connecting sleeve extends to the chute Inside, the length of the chute located under the connecting rod is greater than the length of the connecting section between the step hole and the connecting rod; the controller installed in the installation box is connected with the micro motor; The ejection mechanism includes an installation strut and an upper sleeve, and the stage stage of the installation strut is sheathed with a number of stacked disc springs; the upper sleeve is slidably sleeved on the installation strut for closing the disc springs; The locking and ejecting mechanism also includes a power assist mechanism, which includes an installation cavity opened on the installation pillar, the installation pillar just below the disc spring is provided with a plurality of arc-shaped grooves that communicate with the installation cavity, and the installation cavity is provided with an electric push rod electrically connected to the controller, the electric push rod is fixed with a force transmission member whose upper end extends into the arc groove and is in contact with the disc spring; The control method of the locking and ejecting mechanism of the throwable flying parameter recorder includes: S1. Receive the aircraft crash signal, and obtain the real-time environmental parameters of the aircraft flight; S2. Calculate real-time air resistance according to real-time environmental parameters:

in,

is the current air resistance;

is the resistance coefficient; S is the reference area;

is the current air density; v _is the current flight speed of the aircraft; S3, determine whether the current air resistance is greater than the theoretical air resistance, if it goes to step S4, otherwise go to step S5; S4, open the electric push rod to move upward to compress the disc spring, and then enter step S5; S5. The controller starts the micro-motor, the micro-motor rotates with the screw rod and reversely rotates, the connecting sleeve pushes the connecting rod, and then pushes the upper cover to move upward. When the connecting sleeve and the screw rod are disengaged, the pop-up mechanism pops out the installation box. 2. the locking ejection mechanism of throwing type flying parameter recorder according to claim 1, is characterized in that, the design method of the stacking number of disc spring comprises: Obtain the theoretical environmental parameters of the aircraft during flight, and calculate the theoretical air resistance based on the theoretical environmental parameters:

Among them, D is the theoretical air resistance;

is the drag coefficient; S is the reference area; ρ is the air density; v ₁ is the flight speed of the aircraft; According to the weight of the upper cover and the installation box and the theoretical air resistance, calculate the kinetic energy increment when the installation box is thrown out:

in,

is the kinetic energy increment; G is the weight of the upper cover and the installation box;

is the initial compression distance of several disc springs; v ₂ is the initial velocity when the installation box is thrown out; g is the acceleration of gravity; According to the kinetic energy increment and the deformation and bearing load of the single disc spring, calculate the stacking number of disc springs:

Among them, i is the stacking number of disc springs; P is the bearing load of the single disc spring; f is the deformation amount of the single disc spring. 3 . The locking and ejecting mechanism of the throwable flying parameter recorder according to claim 1 , wherein the diameter of the connecting section between the stepped hole and the connecting rod is larger than the diameter of the connecting section with the screw rod. 4 . 4. the locking ejection mechanism of throwing type flying parameter recorder according to claim 1, is characterized in that, described mounting frame and upper cover plate are all in " 匚" shape, and described unlocking separation mechanism is installed in the mounting frame and the side panels of the upper cover.

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