A drag protection device for a rear propeller type aircraft and an aircraft

Abstract

The application discloses a rear propeller type aircraft arresting protection device and an aircraft, and relates to the field of aircrafts. The arresting hook is hinged below the tail of the aircraft body; the telescopic limiting buffer mechanism is installed on the aircraft body and located between the arresting hook and the propeller, and the telescopic limiting buffer mechanism comprises a retracted state and an elongated locked state; the trigger mechanism is arranged on the telescopic limiting buffer mechanism. Therefore, the application effectively reduces the impact force of the arresting hook on the aircraft body by increasing the first angle a of the first upward swing of the arresting hook, which is beneficial to the lightweight design of the telescopic limiting buffer mechanism and the load-bearing area of the aircraft body; the telescopic limiting buffer mechanism can switch between different states, limit the upward swing angle of the arresting hook, and keep the arresting cable below the lowest rotation plane of the propeller, so that the propeller and the aircraft body are prevented from colliding, the safety of the propeller and the aircraft body is ensured, and the safety of the rear propeller type aircraft in the recovery process is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a rear propeller type aircraft arresting protection device and an aircraft. BACKGROUND

[0002] At present, the low-altitude economy is booming, and the aircraft is widely used in many fields such as logistics distribution, agricultural plant protection, surveying and mapping exploration, etc. due to its flexible and efficient characteristics.

[0003] However, its recycling technology is facing severe challenges. The traditional arresting system mainly adopts a fixed arresting hook at the lower part of the fuselage, which is mainly suitable for front propeller type aircraft and can play a good role in recycling. However, when the rear propeller aircraft adopts the traditional arresting system, the arresting cable is prone to collide with the rear propeller during recycling, which not only causes the propeller to be damaged and the fuselage to lose control, but also may endanger the safety of ground personnel, thereby greatly hindering the safe recycling of unmanned aerial vehicles and the stable development of the low-altitude economy industry. SUMMARY

[0004] The present application provides a rear propeller type aircraft arresting protection device and an aircraft, which solves the technical problems that the arresting cable is prone to collide with the rear propeller when the rear propeller aircraft adopts the traditional arresting system for recycling, thereby causing the propeller to be damaged, the fuselage to lose control, and other series of technical problems.

[0005] In a first aspect, the present application provides a rear propeller type aircraft arresting protection device, comprising: an arresting hook hingedly connected below the tail of the aircraft fuselage; a telescopic limiting and buffering mechanism installed on the fuselage and located between the arresting hook and the propeller, the telescopic limiting and buffering mechanism comprising a retracted state and an elongated locked state; wherein in the retracted state, the telescopic limiting and buffering mechanism allows the arresting hook to swing up by a first angle after mounting the arresting cable; in the elongated locked state, the telescopic limiting and buffering mechanism limits the maximum swing angle of the arresting hook to a second angle smaller than the first angle, so that the arresting cable is always located below the lowest rotation plane of the propeller; a trigger mechanism is provided on the telescopic limiting and buffering mechanism, configured to drive the telescopic limiting and buffering mechanism to switch from the retracted state to the elongated locked state when the arresting hook swings up to the first angle and hits the telescopic limiting and buffering mechanism.

[0006] With reference to the first aspect, in a possible implementation manner, the telescopic limiting and buffering mechanism comprises an inner cylinder, an outer cylinder, a power elastic member and a locking assembly; the outer cylinder is fixedly installed on the fuselage; the inner cylinder is axially slidably sleeved in the outer cylinder, and both ends of the inner cylinder extend out of the outer cylinder in the retracted state; the power elastic member is sleeved on the outer wall of the inner cylinder, and both ends of the power elastic member abut against the bottom of the outer cylinder and the bottom of the inner cylinder respectively; the power elastic member is configured to provide an elastic force to the inner cylinder to move the inner cylinder to the elongated and locked state; the locking assembly is arranged at the end of the outer cylinder and is configured to lock the relative position of the inner cylinder and the outer cylinder when the inner cylinder moves to the elongated and locked state.

[0007] With reference to the first aspect, in a possible implementation manner, the locking assembly comprises an outer disc, a first locking pin, a handle sliding block and at least one locking unit; the outer wall of the side of the inner cylinder close to the fuselage is circumferentially provided with at least one first limiting groove corresponding to the locking unit; the outer disc is arranged at the end of the outer cylinder away from the power elastic member and surrounds the inner cylinder; the locking unit is rotatably arranged in the outer disc and has a pre-tightening force tending to be clamped into the first limiting groove; the top of the outer disc is provided with a clamping groove and a circumferential groove in communication with the clamping groove; the handle sliding block is installed on the first locking pin and is slidingly connected to the circumferential groove and connected to the locking unit; wherein the first locking pin is located in the clamping groove, and the locking unit is clamped into the first limiting groove to achieve locking under the action of the pre-tightening force thereof; when the first locking pin moves along the circumferential groove, the handle sliding block is driven to drive the locking unit to rotate and exit the first limiting groove against the pre-tightening force, thereby releasing the locking.

[0008] With reference to the first aspect, in a possible implementation manner, the locking assembly comprises an outer disc, a first locking pin, a handle sliding block and at least one locking unit; the outer wall of the side of the inner cylinder close to the fuselage is circumferentially provided with at least one first limiting groove corresponding to the locking unit; the outer disc is arranged at the end of the outer cylinder away from the power elastic member and surrounds the inner cylinder; the locking unit is rotatably arranged in the outer disc and has a pre-tightening force tending to be clamped into the first limiting groove; the top of the outer disc is provided with a clamping groove and a circumferential groove in communication with the clamping groove; the handle sliding block is installed on the first locking pin and is slidingly connected to the circumferential groove and connected to the locking unit; wherein the first locking pin is located in the clamping groove, and the locking unit is clamped into the first limiting groove to achieve locking under the action of the pre-tightening force thereof; when the first locking pin moves along the circumferential groove, the handle sliding block is driven to drive the locking unit to rotate and exit the first limiting groove against the pre-tightening force, thereby releasing the locking.

[0009] With reference to the first aspect, in a possible implementation manner, the locking assembly further comprises at least one second locking pin; the top of the outer disc is provided with at least one first locking hole in the circumferential direction, and the second locking pin is detachably connected to the first locking hole; the shell is provided with a second locking hole corresponding to the first locking hole; when the locking piece extends into the first limiting groove, the first locking hole is aligned with the second locking hole, so that the second locking pin is inserted into the aligned second locking hole to circumferentially fix the shell.

[0010] With reference to the first aspect, in a possible implementation manner, the trigger mechanism comprises an unlocking slider, a plurality of limiting blocks and a plurality of third elastic members; the outer wall of the inner cylinder is provided with an axially extending second limiting groove; the unlocking slider is sleeved on the outer wall of the second limiting groove and is slidingly clamped in the second limiting groove; the inner wall of the outer cylinder is provided with a plurality of radial grooves in the circumferential direction; a plurality of the limiting blocks are radially movably arranged in the radial grooves; two ends of a plurality of the third elastic members are respectively connected to the inner wall of the corresponding radial groove and the end of the corresponding limiting block away from the inner cylinder, and exert a radially inward elastic force on the corresponding limiting block, so that in the retracted state, the limiting block is clamped in the second limiting groove to limit the movement of the inner cylinder; when the arresting hook hits the bottom of the inner cylinder, the inner cylinder is axially displaced relative to the outer cylinder, driving the unlocking slider to slide along the second limiting groove and extrude the limiting block, so that the limiting block compresses the third elastic member and radially exits the second limiting groove to unlock the inner cylinder.

[0011] With reference to the first aspect, in a possible implementation manner, the end face of the limiting block towards the side of the unlocking slider is provided with a first guide inclined surface.

[0012] With reference to the first aspect, in a possible implementation manner, the outer wall of the unlocking slider is provided with a second guide inclined surface corresponding to the first guide inclined surface.

[0013] With reference to the first aspect, in a possible implementation manner, the telescopic limiting and buffering mechanism further comprises a buffering member; the buffering member is arranged at the bottom of the inner cylinder.

[0014] The second aspect, the embodiments of the present application provide a kind of aircraft, including the rear propeller type aircraft of the arresting protection device described in the first aspect and any possible implementation manner of the first aspect.

[0015] The one or more technical solutions provided in the embodiments of the present application have at least the following technical effects:

[0016] The rear propeller type aircraft arresting protection device provided by the application comprises an arresting hook, a telescopic limiting buffer mechanism and a triggering mechanism. By increasing the first angle a of the first upward swing of the arresting hook, the impact force of the arresting hook on the fuselage is reduced. At the same time, the telescopic limiting buffer mechanism is used to limit the maximum upward swing angle of the arresting hook, so that the arresting cable is always below the lowest rotation plane of the propeller, thereby protecting the propeller. After the arresting hook swings upward for the first time and hits the telescopic limiting buffer mechanism, the arresting hook will swing downward due to the impact reaction force. At this time, the telescopic limiting buffer mechanism is ejected to the extended locking state position and is locked. Thereafter, the maximum upward swing angle of the arresting hook is limited to the second angle β state. As the aircraft continues to slide forward, the included angle between the arresting cable and the ground is continuously reduced, but the arresting cable can always remain below the lowest rotation plane of the propeller, thereby avoiding interference with the normal operation of the propeller. The triggering mechanism is arranged on the telescopic limiting buffer mechanism, and functions to drive the telescopic limiting buffer mechanism to switch from the retracted state to the extended locking state when the arresting hook swings upward to hit the telescopic limiting buffer mechanism to the first angle a and hits the telescopic limiting buffer mechanism, thereby ensuring that the entire rear propeller type aircraft arresting protection device can normally work according to the preset logic. Therefore, by increasing the first angle a of the first upward swing of the arresting hook, the impact force of the arresting hook on the fuselage is effectively reduced, which is conducive to the lightweight design of the telescopic limiting buffer mechanism and the fuselage bearing area. The telescopic limiting buffer mechanism can switch between different states to limit the upward swing angle of the arresting hook, so that the arresting cable is always below the lowest rotation plane of the propeller, thereby avoiding collision with the propeller, ensuring the safety of the propeller and the fuselage, improving the safety of the rear propeller aircraft during the recovery process, and providing solid technical support for the stable development of low-altitude economic industry. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the application, the drawings needed in the description of the embodiments of the application will be briefly introduced. Obviously, the drawings in the following description are some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor.

[0018] Figure 1 The structure schematic diagram of the rear propeller type aircraft arresting protection device provided by the embodiments of the application is shown in the figure.

[0019] Figure 2 The initial position of the arresting hook, the retracted state and the extended locking state position of the telescopic limiting buffer mechanism provided by the embodiments of the application are shown in the figure.

[0020] Figure 3 The structure schematic diagram of the telescopic limiting buffer mechanism provided by the embodiments of the application is shown in the figure.

[0021] Figure 4 A front view of the telescopic limiting and buffering mechanism provided by the embodiment of the present application;

[0022] Figure 5 A F-F sectional view of the embodiment of the present application; Figure 4

[0023] Figure 6 A local enlarged view of A of the embodiment of the present application; Figure 5

[0024] Figure 7 A structure schematic view of the locking assembly provided by the embodiment of the present application;

[0025] Figure 8 A top view of the locking assembly provided by the embodiment of the present application;

[0026] Figure 9 A B-B sectional view of the embodiment of the present application; Figure 8

[0027] Figure 10 A C-C sectional view of the embodiment of the present application; Figure 8

[0028] Figure 11 A structure schematic view of the outer cylinder provided by the embodiment of the present application;

[0029] Figure 12 A top view of the outer cylinder provided by the embodiment of the present application;

[0030] Figure 13 A D-D sectional view of the embodiment of the present application; Figure 12

[0031] Figure 14 A structure schematic view of the outer and inner cylinders provided by the embodiment of the present application;

[0032] Figure 15 A E-E sectional view of the embodiment of the present application. Figure 14

[0033] ​​​​​​Icon: 1 - arresting hook; 2 - telescopic limiting buffer mechanism; 21 - inner cylinder; 211 - first limiting groove; 212 - second limiting groove; 22 - outer cylinder; 221 - radial groove; 23 - power elastic piece; 24 - locking assembly; 241 - outer disc; 2411 - clamping groove; 2412 - circumferential groove; 242 - first locking pin; 243 - handle slider; 244 - locking unit; 2441 - first elastic piece; 2442 - shell; 24421 - second locking hole; 2443 - locking piece; 245 - second locking pin; 246 - rotating steel ball; 247 - fourth elastic piece; 25 - buffer piece; 3 - trigger mechanism; 31 - unlocking slider; 311 - second guide inclined surface; 32 - limiting block; 321 - first guide inclined surface; 33 - third elastic piece; 4 - arresting cable; 5 - propeller. DETAILED DESCRIPTION

[0034] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0035] In the description of the embodiments of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only used to facilitate the description of the embodiments of the present application and simplify the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application. The terms "first", "second", "third" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance. In addition, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0036] The embodiments of the present application provide an arresting protection device for a rear propeller type aircraft, as shown in Figures 1 to 15The rear propeller aircraft's arresting protection device includes arresting hook 1, telescopic limiting buffer mechanism 2 and trigger mechanism 3. Arresting hook 1 is hinged below the tail of the aircraft body. Telescopic limiting buffer mechanism 2 is installed on the body between arresting hook 1 and propeller 5, and includes a retracted state and an extended locked state. In the retracted state, telescopic limiting buffer mechanism 2 allows arresting hook 1 to swing upward by a first angle a after arresting cable 4 is mounted. In the extended locked state, telescopic limiting buffer mechanism 2 limits the maximum upward swing angle of arresting hook 1 to a second angle β that is less than the first angle a, so that arresting cable 4 is always below the lowest rotation plane of propeller 5.

[0037] As shown in Figure 2 , arresting hook 1 swings from the initial position to the position corresponding to the retracted state of telescopic limiting buffer mechanism 2, and the angle of swing during this process is the first angle a. Adding this upward swing angle to arresting hook 1 can effectively control the impact force of arresting hook 1 on the body, which is very beneficial to the lightweight design of telescopic limiting buffer mechanism 2 and the body bearing area.

[0038] When the aircraft lands at a certain speed, arresting hook 1 will swing upward due to inertia at the moment of hooking arresting cable 4. By controlling the variable method, it is found that by adjusting only the length of telescopic limiting buffer mechanism 2, arresting hook 1 can achieve a larger first upward swing angle a when it is in the retracted state, thereby significantly reducing the impact force on the body.

[0039] The working principle of the arresting protection device is as follows: by increasing the first upward swing angle a of arresting hook 1, the impact force of arresting hook 1 on the body is reduced; at the same time, the maximum upward swing angle of arresting hook 1 is limited by telescopic limiting buffer mechanism 2, so that arresting cable 4 is always below the lowest rotation plane of propeller 5, thereby protecting propeller 5. After the first upward swing of arresting hook 1 and the impact on telescopic limiting buffer mechanism 2, arresting hook 1 will swing downward due to the impact reaction force. At this time, telescopic limiting buffer mechanism 2 is ejected to the extended locked state position and is locked. Thereafter, the maximum upward swing angle of arresting hook 1 is limited to the second angle β state. As the aircraft continues to slide forward, the included angle between arresting cable 4 and the ground continuously decreases, but arresting cable 4 can always remain below the lowest rotation plane of propeller 5, avoiding interference with the normal operation of propeller 5. Trigger mechanism 3 is provided on telescopic limiting buffer mechanism 2, which functions to drive telescopic limiting buffer mechanism 2 to switch from the retracted state to the extended locked state when arresting hook 1 swings up to the first angle a and impacts telescopic limiting buffer mechanism 2, ensuring that the entire arresting protection device of the rear propeller aircraft can work normally according to the preset logic.

[0040] In summary, the application effectively reduces the impact force of the arresting hook 1 on the fuselage by increasing the first angle a of the first upward swing of the arresting hook 1, which is beneficial to the lightweight design of the telescopic limiting and buffering mechanism 2 and the fuselage bearing area. The telescopic limiting and buffering mechanism 2 can switch between different states, limit the upward swing angle of the arresting hook 1, and keep the arresting cable 4 below the lowest rotation plane of the propeller 5 to avoid collision with the propeller 5, thereby ensuring the safety of the propeller 5 and the fuselage and improving the safety of the rear-mounted propeller 5 aircraft recovery process, providing a solid technical support for the stable development of low-altitude economic industry.

[0041] In the embodiment of the application, the telescopic limiting and buffering mechanism 2 includes an inner cylinder 21, an outer cylinder 22, a power elastic member 23, and a locking assembly 24. The outer cylinder 22 is fixedly installed on the fuselage. As shown in Figure 3 the inner cylinder 21 is axially slidably sleeved in the outer cylinder 22, and in the retracted state, the two ends of the inner cylinder 21 extend out of the outer cylinder 22. The power elastic member 23 is sleeved on the outer wall of the inner cylinder 21, and its two ends abut against the bottom of the outer cylinder 22 and the bottom of the inner cylinder 21. The power elastic member 23 is configured to provide the inner cylinder 21 with an elastic force to move it to the elongated locked state. The locking assembly 24 is arranged at the end of the outer cylinder 22 and is configured to lock the relative position of the inner cylinder 21 and the outer cylinder 22 when the inner cylinder 21 moves to the elongated locked state.

[0042] Specifically, in an embodiment of the application, the bottom of the inner cylinder 21 is circumferentially provided with a boss, and the power elastic member 23 abuts against the boss.

[0043] In the embodiment of the application, the telescopic limiting and buffering mechanism 2 works in the initial retracted state, at which time the two ends of the inner cylinder 21 extend out of the outer cylinder 22, and the power elastic member 23 is sleeved on the outer wall of the inner cylinder 21 and abuts against the bottom of the outer cylinder 22 and the bottom of the inner cylinder 21 to provide the inner cylinder 21 with an elastic force to move it to the elongated locked state. When the arresting hook 1 upward swing hits the inner cylinder 21 and compresses the power elastic member 23, the inner cylinder 21 axially slides relative to the outer cylinder 22 until it moves to the elongated locked state, at which time the locking assembly 24 at the end of the outer cylinder 22 locks the relative position of the inner cylinder 21 and the outer cylinder 22 to prevent the inner cylinder 21 from retracting, thereby limiting the further upward swing of the arresting hook 1. The telescopic limiting and buffering mechanism 2 realizes the telescopic movement of the inner cylinder 21 through the power elastic member 23, and cooperates with the locking function of the locking assembly 24 in the elongated locked state, which can not only allow the arresting hook 1 to have a suitable upward swing angle after mounting the arresting cable 4 to reduce the impact force on the fuselage, but also accurately limit the maximum upward swing angle of the arresting hook 1 when needed, so that the arresting cable 4 is always below the lowest rotation plane of the propeller 5 to effectively avoid collision between the arresting cable 4 and the propeller 5, thereby ensuring the safety and stability of the rear-mounted propeller 5 aircraft recovery process.

[0044] In the embodiment of the present application, the locking assembly 24 comprises an outer disc 241, a first locking pin 242, a handle sliding block 243 and at least one locking unit 244. The inner cylinder 21 is provided with at least one first limiting groove 211 corresponding to the locking unit 244 on the outer wall of the side close to the machine body. The outer disc 241 is arranged at the end of the outer cylinder 22 away from the power elastic member 23 and surrounds the inner cylinder 21. The locking unit 244 is rotatably arranged in the outer disc 241 and has a pre-tightening force tending to be clamped into the first limiting groove 211. The top of the outer disc 241 is provided with a clamping groove 2411 and a circumferential groove 2412 communicating with the clamping groove 2411. The handle sliding block 243 is installed on the first locking pin 242 and slidingly connected to the circumferential groove 2412 and connected to the locking unit 244.

[0045] In a specific embodiment of the present application, the first limiting groove 211 is provided with two, and the corresponding locking unit 244 is provided with two, the two locking units 244 are connected by a first connecting rod, and the handle sliding block 243 is connected to one of the locking units 244 by a second connecting rod.

[0046] In the embodiment of the present application, when the locking assembly 24 works, the locking unit 244 has a tendency to move in the direction of clamping into the first limiting groove 211 on the outer wall of the inner cylinder 21 due to its own pre-tightening force, thereby realizing initial locking and ensuring that the telescopic limiting and buffering mechanism 2 can reliably limit the relative position of the inner cylinder 21 and the outer cylinder 22 in the elongated locking state, and guaranteeing the normal work of the arresting protection device. When it is necessary to release the locking, the operator lifts the first locking pin 242 and pushes the first locking pin 242 to move, so that it moves along the circumferential groove 2412 on the top of the outer disc 241, and then drives the handle sliding block 243 installed thereon to move, and the handle sliding block 243 drives the locking unit 244 connected thereto to rotate against the pre-tightening force, and finally exits the first limiting groove 211.

[0047] In another specific embodiment of the present application, the handle sliding block 243 is provided with a sliding groove in the axial direction thereof, and the first locking pin 242 is slidingly connected to the sliding groove. In actual operation, when it is necessary to lift the first locking pin 242, the operator can easily lift the first locking pin 242 because the first locking pin 242 can slide in the sliding groove. The special design of the sliding groove makes the handle sliding block 243 not be lifted during the process of lifting the first locking pin 242, thereby avoiding the situation that the handle sliding block 243 is lifted to drive the locking unit 244 to be lifted, ensuring the stability and reliability of the locking assembly 24 in the operation process, and further improving the use convenience and safety of the whole device.

[0048] In the embodiment of the present application, the locking unit 244 comprises a first elastic member 2441, a shell 2442 corresponding to the first limiting groove 211, and a plurality of locking members 2443 arranged in the shell 2442. A plurality of rotating steel balls 246 are arranged between the inner wall of the outer disc 241 and the first elastic member 2441. The locking members 2443 are configured to be radially movably accommodated in the shell 2442. One end of the first elastic member 2441 abuts against the rotating steel balls 246, and the other end extends into the shell 2442 and abuts against the locking members 2443 therein, so that the first elastic member 2441 applies a spring force to the shell 2442 towards the inner cylinder 21. When the inner cylinder 21 moves to the elongated locking state, the locking members 2443 extend into the first limiting groove 211 under the action of the spring force of the first elastic member 2441.

[0049] In a specific embodiment of the present application, the locking members 2443 are steel balls, and the first elastic member 2441 is a folding spring. The side of the shell 2442 towards the inner cylinder 21 is provided with a sliding groove, the steel balls are placed in the sliding groove, and the diameter of the steel balls is smaller than the height of the sliding groove. Such a size design allows the steel balls to partially extend out of the sliding groove but cannot completely come out, which not only ensures the locking function but also limits the movement range of the steel balls. When the inner cylinder 21 moves to the elongated locking state, the locking members 2443 (steel balls) move radially outward and extend into the first limiting groove 211 under the action of the spring force of the first elastic member 2441, achieving reliable locking of the relative position of the inner cylinder 21 and the outer cylinder 22, effectively limiting the return movement of the inner cylinder 21, and ensuring the stability of the blocking hook 1.

[0050] When it is necessary to release the locking, the first locking pin 242 is moved along the circumferential groove 2412 at the top of the outer disc 241, thereby driving the handle sliding block 243 mounted thereon to move. The handle sliding block 243 drives the locking unit 244 to rotate against the spring force of the first elastic member 2441 through the second connecting rod (if there are multiple locking units 244 connected by the first connecting rod), so that the locking members 2443 are withdrawn from the first limiting groove 211.

[0051] Specifically, the length of the circumferential groove 2412 is carefully designed to be the same as the length of the locking members 2443. Such a design ensures that the movement stroke of the handle sliding block 243 is accurately matched with the movement stroke of the locking members 2443, so that the locking members 2443 can be smoothly moved out of the first limiting groove 211 of the inner cylinder 21, achieving reliable unlocking.

[0052] The structure makes full use of the elastic pre-tightening force of the first elastic member 2441 and the radial movement characteristics of the steel ball, realizes the automatic locking function, has the advantages of compact structure and small space occupation, and has rapid response and can complete the locking action in an instant. Moreover, the locking is reliable and can effectively prevent locking failure caused by vibration and other factors during the recovery of the aircraft. In addition, the design of rotating the steel ball 246 reduces the friction resistance between the components, reduces energy loss, improves the sensitivity and durability of the device, and provides a solid and reliable technical support for the arresting protection of the rear-mounted propeller 5 aircraft.

[0053] After successfully completing the arresting operation of the aircraft, in order to quickly restore the telescopic limiting and buffering mechanism 2 to the initial standby state to ensure the smooth development of the next arresting task, the operator pushes the handle slider 243 in the opposite direction along the circumferential groove 2412 to drive the locking unit 244 to rotate, and the first locking pin 242 is clamped back into the clamping groove 2411 of the outer disc 241. At this time, the telescopic limiting and buffering mechanism 2 is reset and can be used for the next arresting.

[0054] In the embodiment of the application, the locking assembly 24 further comprises at least one second locking pin 245. The top of the outer disc 241 is circumferentially provided with at least one first locking hole, and the second locking pin 245 is detachably connected to the first locking hole. The shell 2442 is provided with a second locking hole 24421 corresponding to the first locking hole. When the locking member 2443 extends into the first limiting groove 211, the first locking hole is aligned with the second locking hole 24421, so that the second locking pin 245 is inserted into the aligned second locking hole 24421 to circumferentially fix the shell 2442.

[0055] In a specific embodiment of the application, the locking assembly 24 further comprises at least two fourth elastic members 247, the two ends of each fourth elastic member 247 being connected to the top of the corresponding second locking pin 245 and the top of the outer disc 241, and one fourth elastic member 247 being arranged on each side of each second locking pin 245 to provide stable elastic pre-tightening. This design realizes the circumferential interlocking of the shell 2442 and the outer disc 241 through the second locking pin 245, effectively prevents accidental rotation and loosening of the mechanism under vibration or impact, and improves the reliability and safety of the locking state. The symmetrical arrangement of the fourth elastic members 247 ensures that the second locking pin 245 is balanced in force and moves smoothly, while providing automatic reset capability to facilitate repeated locking and unlocking operations.

[0056] As an extended solution, the diameter of the second locking hole 24421 is designed to be larger than that of the first locking hole. In this way, even if there is a certain deviation in the alignment of the first locking hole and the second locking hole 24421 due to various factors in actual operation, the second locking pin 245 can be smoothly inserted due to the larger diameter of the second locking hole 24421, greatly facilitating the insertion operation of the second locking pin 245.

[0057] In the embodiment of the present application, the triggering mechanism 3 comprises an unlocking slider 31, a plurality of limiting blocks 32 and a plurality of third elastic members 33. The outer wall of the inner cylinder 21 is provided with an axially extending second limiting groove 212. The unlocking slider 31 is sleeved on the outer wall of the second limiting groove 212 and is slidingly clamped in the second limiting groove 212. The inner wall of the outer cylinder 22 is circumferentially provided with a plurality of radial grooves 221. The plurality of limiting blocks 32 are radially movably arranged in the radial grooves 221. The two ends of the plurality of third elastic members 33 are respectively connected to the inner wall of the corresponding radial groove 221 and the end of the corresponding limiting block 32 away from the inner cylinder 21, and exert a radial inward elastic force on the corresponding limiting block 32, so that in the retracted state, the limiting block 32 is clamped into the second limiting groove 212 to limit the movement of the inner cylinder 21. When the arresting hook 1 hits the bottom of the inner cylinder 21, the inner cylinder 21 is axially displaced relative to the outer cylinder 22, driving the unlocking slider 31 to slide along the second limiting groove 212 and press the limiting block 32, so that the limiting block 32 compresses the third elastic member 33 and radially exits the second limiting groove 212, to unlock the inner cylinder 21.

[0058] In the embodiment of the present application, the end face of the limiting block 32 towards the unlocking slider 31 side is provided with a first guide inclined surface 321.

[0059] In the embodiment of the present application, the outer wall of the unlocking slider 31 is provided with a second guide inclined surface 311 corresponding to the first guide inclined surface 321.

[0060] In the embodiment of the present application, when the bottom of the inner cylinder 21 is first hit by the arresting hook 1, the inner cylinder 21 moves upward relative to the outer cylinder 22, driving the unlocking slider 31 to slide synchronously. The unlocking slider 31 slides along the second limiting groove 212, and the second guide inclined surface 311 thereon is in contact with the first guide inclined surface 321 of the limiting block 32. Under the interaction of the inclined surfaces, the unlocking slider 31 generates a radial inward component force on the limiting block 32, driving the limiting block 32 to compress the third elastic member 33 and exit the second limiting groove 212 radially inward. This process does not require complex external operation, can achieve fast automatic unlocking, and ensures that the device responds quickly and runs stably in emergency working conditions.

[0061] When the unlocking slider 31 completely forces the limiting block 32 to retract, it is positioned between the limiting block 32 and the inner cylinder 21 under the elastic force of the third elastic member 33. At this time, the inner cylinder 21 is released from the radial constraint of the limiting block 32, and immediately pops out downward along the outer cylinder 22 under the elastic force of the power elastic member 23, to realize the predetermined protection action.

[0062] In one specific embodiment of the present application, in combination with Figures 11 to 13In order to optimize the structure of the device and improve the assembly convenience, the disc is arranged on the side of the outer cylinder 22 facing the fuselage. The disc has a specific structural design, and the inside is reserved with a mounting space matched with the limiting block 32 and the third elastic member 33, so that the limiting block 32 can be accurately installed in the corresponding position in a radial direction, and the third elastic member 33 can be stably connected between the inner wall of the disc and the limiting block 32, greatly facilitating the installation operation of the limiting block 32 and the third elastic member 33, and improving the assembly efficiency and accuracy. At the same time, the mounting disc of the locking assembly 24 is arranged on the top of the outer cylinder 22, and the mounting disc is designed according to the structural characteristics of the locking assembly 24, and has a mounting interface and a positioning structure matched with each component of the locking assembly 24, so as to provide a stable and reliable mounting basis for the locking assembly 24, further facilitating the installation of the locking assembly 24 on the outer cylinder 22, and ensuring the compactness of the structure and the stability of the operation of the whole telescopic limiting and buffering mechanism 2.

[0063] In a specific embodiment of the present application, the fuselage and the disc are fixedly connected.

[0064] In the embodiment of the present application, the telescopic limiting and buffering mechanism 2 further comprises a buffering member 25. The buffering member 25 is arranged at the bottom of the inner cylinder 21.

[0065] It should be noted that the buffering member 25 is arranged at the bottom of the inner cylinder 21, and when the inner cylinder 21 is ejected under the action of the power elastic member 23 or moves quickly due to external force, the buffering member 25 can directly act on the arresting hook 1, effectively absorbing and dispersing the impact force generated in the movement process of the inner cylinder 21, avoiding damage to the inner cylinder 21, the outer cylinder 22 and the whole telescopic limiting and buffering mechanism 2 due to excessive impact force, and prolonging the service life of the mechanism.

[0066] The embodiment of the present application provides a kind of aircraft, including the arresting protection device of rear propeller type aircraft described above.

[0067] Each embodiment in the present specification is described in a progressive manner, and the same or similar parts between each embodiment can be referred to each other, and each embodiment mainly describes the difference from other embodiments.

[0068] The above embodiments are only used to illustrate the technical solutions of the present application, and are not limited to the present application; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that they can modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the present application.

Claims

1. An arresting protection device for a rear-mounted propeller-type aircraft, characterized in that, include: Arresting hook (1) is hinged to the lower part of the tail of the aircraft fuselage; A telescopic limiting buffer mechanism (2) is installed on the fuselage and located between the arresting hook (1) and the propeller (5). The telescopic limiting buffer mechanism (2) includes a retracted state and an extended locking state. In the retracted state, the telescopic limiting buffer mechanism (2) allows the arresting hook (1) to swing upward at a first angle after the arresting cable (4) is attached. In the extended locking state, the telescopic limiting buffer mechanism (2) limits the maximum upward swing angle of the arresting hook (1) to a second angle that is less than the first angle, so that the arresting cable (4) is always located below the lowest rotation plane of the propeller (5). The triggering mechanism (3), located on the telescopic limiting buffer mechanism (2), is configured to drive the telescopic limiting buffer mechanism (2) to switch from the retracted state to the extended locking state when it swings on the blocking hook (1) and impacts the telescopic limiting buffer mechanism (2) to the first angle.

2. The arresting protection device for a rear-propeller-type aircraft according to claim 1, characterized in that, The telescopic limiting buffer mechanism (2) includes an inner cylinder (21), an outer cylinder (22), a dynamic elastic element (23), and a locking component (24). The outer cylinder (22) is fixedly installed on the machine body; The inner cylinder (21) is axially slidably fitted inside the outer cylinder (22), and in the retracted state, both ends of the inner cylinder (21) extend out of the outer cylinder (22). The dynamic elastic element (23) is sleeved on the outer wall of the inner cylinder (21), and its two ends abut against the bottom of the outer cylinder (22) and the bottom of the inner cylinder (21), respectively; the dynamic elastic element (23) is configured to provide the inner cylinder (21) with an elastic force to move it to the elongated locking state; The locking component (24) is disposed at the end of the outer cylinder (22) and is configured to lock the relative position of the inner cylinder (21) and the outer cylinder (22) when the inner cylinder (21) moves to the elongated locking state.

3. The arresting protection device for a rear-propeller-type aircraft according to claim 2, characterized in that, The locking assembly (24) includes an outer plate (241), a first locking pin (242), a handle slider (243), and at least one locking unit (244). The outer wall of the inner cylinder (21) near the body is provided with at least one first limiting groove (211) corresponding to the locking unit (244). The outer disc (241) is disposed at the end of the outer cylinder (22) away from the dynamic elastic element (23) and surrounds the inner cylinder (21). The locking unit (244) is rotatably disposed within the outer disk (241) and has a preload force that tends to engage with the first limiting groove (211); The top of the outer disk (241) is provided with a slot (2411) and a circumferential groove (2412) communicating with the slot (2411). The handle slider (243) is mounted on the first locking pin (242) and slidably connected to the circumferential groove (2412), and is connected to the locking unit (244). The first locking pin (242) is located in the slot (2411), and the locking unit (244) is engaged in the first limiting slot (211) under its pre-tightening force to achieve locking; when the first locking pin (242) moves along the circumferential slot (2412), it drives the handle slider (243) to drive the locking unit (244) to overcome its pre-tightening force and rotate out of the first limiting slot (211), thereby releasing the lock.

4. The arresting protection device for a rear-propeller-type aircraft according to claim 3, characterized in that, The locking unit (244) includes a first elastic member (2441), a housing (2442) corresponding to the first limiting groove (211), and a plurality of locking members (2443) disposed in the housing (2442). A plurality of rotating steel balls (246) are disposed between the inner wall of the outer disk (241) and the first elastic member (2441); the locking member (2443) is configured to be radially movable and accommodated within the housing (2442); One end of the first elastic element (2441) abuts against the rotating steel ball (246), and the other end extends into the housing (2442) and abuts against the locking element (2443) therein, so that the first elastic element (2441) applies an elastic force toward the inner cylinder (21) to the housing (2442) through the locking element (2443); When the inner cylinder (21) moves to the elongated locking state, the locking member (2443) extends into the first limiting groove (211) under the elastic force of the first elastic member (2441).

5. The arresting protection device for a rear-propeller-type aircraft according to claim 4, characterized in that, The locking component (24) also includes at least one second locking pin (245); The top of the outer disk (241) is provided with at least one first locking hole in the circumferential direction, and the second locking pin (245) is detachably connected to the first locking hole. The housing (2442) is provided with a second locking hole (24421) corresponding to the first locking hole. When the locking member (2443) extends into the first limiting groove (211), the first locking hole is aligned with the second locking hole (24421) so that the second locking pin (245) is inserted into the aligned second locking hole (24421) to circumferentially fix the housing (2442).

6. The arresting protection device for a rear-propeller-type aircraft according to claim 2, characterized in that, The triggering mechanism (3) includes an unlocking slider (31), multiple limit blocks (32) and multiple third elastic elements (33). The outer wall of the inner cylinder (21) is provided with an axially extending second limiting groove (212); The unlocking slider (31) is sleeved on the outer wall of the second limiting groove (212) and slidably locked in the second limiting groove (212); The inner wall of the outer cylinder (22) is provided with a plurality of radial grooves (221) in the circumferential direction; The plurality of the limiting blocks (32) are radially movable within the radial groove (221); The two ends of the plurality of third elastic elements (33) are respectively connected to the inner wall of the corresponding radial groove (221) and the end of the corresponding limiting block (32) away from the inner cylinder (21), and apply a radially inward elastic force to the corresponding limiting block (32), so that when the retracted state, the limiting block (32) is inserted into the second limiting groove (212) to restrict the movement of the inner cylinder (21); When the blocking hook (1) strikes the bottom of the inner cylinder (21), the inner cylinder (21) generates an axial displacement relative to the outer cylinder (22), driving the unlocking slider (31) to slide along the second limiting groove (212) and squeeze the limiting block (32), causing the limiting block (32) to compress the third elastic element (33) and radially exit the second limiting groove (212) to unlock the inner cylinder (21).

7. The arresting protection device for a rear-propeller-type aircraft according to claim 6, characterized in that, The end face of the limiting block (32) facing the unlocking slider (31) is provided with a first guide slope (321).

8. The arresting protection device for a rear-propeller-type aircraft according to claim 7, characterized in that, The outer wall of the unlocking slider (31) is provided with a second guide slope (311) corresponding to the first guide slope (321).

9. The arresting protection device for a rear-propeller-type aircraft according to claim 2, characterized in that, The telescopic limiting buffer mechanism (2) also includes a buffer element (25); The buffer (25) is located at the bottom of the inner cylinder (21).

10. An aircraft, characterized in that, The arresting protection device for a rear-mounted propeller-type aircraft as described in any one of claims 1-9.

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