Aircraft recovery mechanism and method of operation thereof

Abstract

The application discloses an aircraft recovery mechanism and an operating method thereof, and relates to the technical field of aircraft recovery.The aircraft recovery mechanism comprises a parachute cabin arranged on an aircraft, the parachute cabin being used for accommodating a main parachute bag and a guide parachute, the main parachute bag accommodating a main parachute, a parachute cabin cover being arranged on the parachute cabin, and an inner side of the parachute cabin cover being connected with the guide parachute; a first end of the parachute cabin is connected with a first end of the parachute cabin cover through a first separation device, a second end of the parachute cabin is connected with a second end of the parachute cabin cover through a second separation device, and the first separation device and the second separation device are simultaneously or sequentially unlocked when the aircraft lands to a first preset height.The aircraft recovery mechanism is controlled to simultaneously or sequentially unlock the first separation device and the second separation device, so that the parachute cabin cover is rapidly separated from the parachute cabin and is bounced away by a certain distance under the pushing action of external airflow, the parachute cabin cover does not interfere with the unfolding process of the subsequent guide parachute and the main parachute, and the stability and reliability of the aircraft recovery mechanism are improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft recovery technology, and in particular to an aircraft recovery mechanism and its operation method. Background Technology

[0002] Most aircraft are designed with recovery systems. The first step in the recovery system is to successfully deploy and open the pilot chute, thereby pulling out the main parachute. Some aircraft are not recovered completely undamaged; in such cases, it's necessary to control the aircraft's attitude to effectively minimize damage. Currently, there are two main methods for deploying pilot chute. The first method involves designing a spring inside the pilot chute. The spring is compressed and stores energy through a canopy cover, and the pilot chute and spring are deployed together after the canopy cover opens. The second method involves using pyrotechnics to detonate the pilot chute.

[0003] However, the first approach requires integrating springs into the pilot parachute, increasing the volume of the parachute compartment. Furthermore, the compartment cover is needed to hold the springs in place, placing high demands on its strength. Additionally, the springs lose elasticity under prolonged pressure during storage, leading to decreased reliability. The second approach poses significant safety risks and is inconvenient and costly to store. Therefore, this paper proposes an aircraft recovery mechanism and its operating method to address these issues. Summary of the Invention

[0004] The purpose of this invention is to provide an aircraft recovery mechanism and its operating method, which solves the technical problems of existing aircraft recovery mechanisms having large parachute compartments, poor reliability, and significant safety hazards.

[0005] To achieve the above objectives, the present invention provides an aircraft recovery mechanism and its operating method. The aircraft recovery mechanism includes:

[0006] A parachute compartment, located on an aircraft, is used to store the main parachute pack and the pilot parachute. The main parachute pack contains the main parachute, and the parachute compartment is equipped with a canopy. The inner side of the canopy is connected to the pilot parachute.

[0007] The first end of the parachute compartment is connected to the first end of the parachute compartment cover via a first separation device, and the second end of the parachute compartment is connected to the second end of the parachute compartment cover via a second separation device. When the aircraft lands at a first preset altitude, the first separation device and the second separation device are unlocked simultaneously or sequentially, causing the parachute compartment cover to detach from the parachute compartment.

[0008] Preferably, the main parachute is connected to a group of carrying straps via several parachute lines. The group of carrying straps is connected to the center of gravity of the aircraft via a break rope. The group of carrying straps is connected to the front end of the aircraft via a front lower sling and to the rear end of the aircraft via a rear lower sling. The lengths of both the front and rear lower slings are greater than the length of the break rope, with the front lower sling being longer than the rear lower sling, so that the aircraft forms an angle of inclination with the ground surface.

[0009] Preferably, the first separation device includes: a first fixing part and a second fixing part that are locked together, the first fixing part being connected to the first end of the parachute compartment, and the second fixing part being connected to the first end of the parachute compartment cover; when the aircraft lands to a first preset altitude, the first fixing part and the second fixing part separate from each other, so that the first end of the parachute compartment cover detaches from the first end of the parachute compartment.

[0010] Preferably, the second separation device includes: a first connecting part and a second connecting part that are rotatably connected, the first connecting part being connected to the second end of the umbrella compartment, and the second connecting part being connected to the second end of the umbrella compartment cover; when the first end of the umbrella compartment cover disengages from the first end of the umbrella compartment, and the first end of the umbrella compartment cover rotates relative to the umbrella compartment to a preset angle, the first connecting part and the second connecting part separate from each other, so that the second end of the umbrella compartment cover disengages from the second end of the umbrella compartment.

[0011] Preferably, one of the first connecting part and the second connecting part is a bushing, and a U-shaped groove is provided on one side of the bushing. The extending direction of the U-shaped groove is set at an angle to the top surface of the parachute compartment. The other of the first connecting part and the second connecting part is a rotating shaft, and the U-shaped groove is rotatably connected to the rotating shaft.

[0012] Preferably, the second separation device includes: a third fixing part and a fourth fixing part that are locked together, the third fixing part being connected to the second end of the parachute compartment, and the fourth fixing part being connected to the second end of the parachute compartment cover; when the aircraft lands to a first preset altitude, the third fixing part and the fourth fixing part separate from each other, so that the second end of the parachute compartment cover detaches from the second end of the parachute compartment cover.

[0013] Preferably, the guide umbrella is located above the main umbrella, and the guide umbrella is connected to the seal of the main umbrella pack via a guide cord.

[0014] Accordingly, the present invention also provides an operating method for an aircraft recovery mechanism, applicable to any of the above-mentioned aircraft recovery mechanisms, the operating method comprising:

[0015] When the aircraft lands at the first preset altitude, the first separation device and the second separation device are unlocked simultaneously or sequentially. At this time, under the pushing action of the external airflow, the canopy is detached from the canopy and the guide parachute is brought out of the canopy.

[0016] After the pilot parachute leaves the canopy, the pilot parachute begins to inflate until it is fully open, until the pilot parachute lines are taut to pull the seal of the main parachute pack.

[0017] After the main parachute pack is opened, the main parachute begins to inflate until it is fully deployed, in order to pull the aircraft until it lands smoothly.

[0018] Preferably, the step of controlling the first separation device and the second separation device to unlock simultaneously or sequentially further includes: first controlling the first separation device to unlock; under the pushing action of external airflow, the first end of the canopy cover leaves the first end of the canopy; the second end of the canopy cover rotates relative to the second end of the canopy; after the second end of the canopy cover rotates relative to the second end of the canopy to a preset angle, the second end of the canopy cover leaves the second end of the canopy along a preset throwing path; the second separation device automatically unlocks; and the canopy cover completely detaches from the canopy.

[0019] Preferably, the step of controlling the first separation device and the second separation device to unlock further includes: controlling the first separation device and the second separation device to unlock simultaneously, so that under the driving force of the external airflow, the first end of the umbrella compartment cover leaves the first end of the umbrella compartment, and at the same time, the second end of the umbrella compartment cover leaves the second end of the umbrella compartment, and the umbrella compartment cover is completely separated from the umbrella compartment.

[0020] Compared with the above-mentioned background technology, the aircraft recovery mechanism provided by the present invention has the following beneficial effects:

[0021] (1) In this invention, when the aircraft lands to a first preset altitude, the first separation device and the second separation device are unlocked simultaneously or sequentially. After the unlocking actions of the first separation device and the second separation device are completed, the parachute canopy quickly detaches from the parachute compartment under the pushing action of the external airflow, preventing the parachute canopy from interfering with the subsequent deployment process of the pilot parachute and the main parachute, and effectively improving the stability and reliability of the aircraft recovery mechanism. Furthermore, under the continuous force of the airflow, the pilot parachute connected to the parachute canopy is synchronously brought out of the parachute compartment, effectively ensuring the smooth deployment of the pilot parachute. The operating method of the aircraft recovery mechanism used in this invention also has the above-mentioned beneficial effects.

[0022] (2) After the first and second separation devices are unlocked, the present invention relies on airflow to separate the parachute canopy and deploy the guide parachute, ensuring normal deployment of the guide parachute after long-term storage. Compared to integrating springs on the guide parachute, there is no need to reserve space for spring installation and extension inside the parachute canopy, significantly reducing the overall volume required for the parachute canopy, achieving lightweighting and miniaturization of the aircraft recovery mechanism, thereby reserving more space for the aircraft layout. Moreover, there is no issue of reduced elasticity or decreased reliability due to long-term pressure storage of the spring structure. Compared to detonating the guide parachute with pyrotechnics, there is less safety hazard, and there is no need to consider the storage of pyrotechnics, effectively reducing storage costs. The operating method of the aircraft recovery mechanism used in the present invention also has the above-mentioned beneficial effects. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0024] Figure 1 This is an assembly diagram of the parachute compartment and parachute compartment cover provided in the first embodiment of the present invention;

[0025] Figure 2 This is a schematic diagram of the assembly of the parachute compartment and the parachute compartment cover after the first separation device provided in the first embodiment of the present invention has been unlocked;

[0026] Figure 3 This is an assembly diagram of the parachute canopy after it has been rotated a preset angle relative to the parachute canopy, according to the first embodiment of the present invention.

[0027] Figure 4 This is a schematic diagram of the assembly of the parachute compartment and the parachute compartment cover after the second separation device provided in the first embodiment of the present invention is unlocked;

[0028] Figure 5 This is a three-dimensional structural diagram of the guide umbrella after it has been opened, according to the first embodiment of the present invention.

[0029] Figure 6 This is a three-dimensional structural diagram of the main umbrella after it is opened, according to the first embodiment of the present invention.

[0030] Figure 7 This is a three-dimensional structural diagram of the broken rope provided in the first embodiment of the present invention.

[0031] Figure 8 for Figure 2 Enlarged view of point A in the middle;

[0032] Figure 9 This is a schematic diagram of the assembly of the first connecting part and the second connecting part in their initial state, as provided in the second embodiment of the present invention.

[0033] Figure 10 This is an assembly diagram of the second connecting part after rotating relative to the first connecting part by a preset angle, according to the second embodiment of the present invention.

[0034] Figure 11 This is a schematic diagram of the assembly of the parachute compartment and the parachute compartment cover provided in the second embodiment of the present invention.

[0035] Specifically, 1-Aircraft; 2-Parachute compartment; 3-Main parachute pack; 4-Main parachute; 5-Guide parachute; 6-Parachute compartment cover; 7-Carrying straps; 8-Break rope; 9-Front lower sling; 10-Rear lower sling; 11-First fixing part; 12-Second fixing part; 13-Third fixing part; 14-Fourth fixing part; 15-First connecting part; 16-Second connecting part; 17-Hinge; 1701-Assembly slot; 18-Busset; 1801-U-groove; 1802-Matching hole; 19-Guide rope. Detailed Implementation

[0036] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0037] To enable those skilled in the art to better understand the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0038] like Figure 1 , Figure 2 and Figure 7 As shown, to achieve the above objectives, the present invention provides an aircraft recovery mechanism, comprising: a parachute compartment 2 and a parachute compartment cover 6. The parachute compartment 2 is located on the top of the aircraft 1 and is mainly used to store the main parachute pack 3 and the pilot parachute 5. The main parachute pack 3 contains the main parachute 4. The parachute compartment cover 6 is located above the parachute compartment 2, and the pilot parachute 5 is connected to the inner side of the parachute compartment cover 6. It should be noted that the pilot parachute 5 is fixed to the inner side of the parachute compartment cover 6 by adhesive or snap-fit ​​connection. When there is a force between the pilot parachute 5 and the parachute compartment cover 6 that causes them to separate and the force causes them to separate exceeds a preset value, the pilot parachute 5 separates from the parachute compartment cover 6, ensuring that the pilot parachute 5 is not damaged by the parachute compartment cover 6 due to the parachute compartment cover 6 detaching from the parachute compartment 2.

[0039] The front end of the parachute compartment 2 is connected to the front end of the parachute compartment cover 6 via a first separation device, and the rear end of the parachute compartment 2 is connected to the rear end of the parachute compartment cover 6 via a second separation device. When the aircraft 1 descends to a first preset altitude, the first and second separation devices are unlocked simultaneously or sequentially. After the unlocking actions of the first and second separation devices are completed, the parachute compartment cover 6 quickly detaches from the parachute compartment 2 under the propulsion of the external airflow, effectively preventing the parachute compartment cover 6 from interfering with the deployment process of the guide parachute 5 and the main parachute 4, and improving the stability and reliability of the aircraft recovery mechanism. Furthermore, under the continuous propulsion of the airflow, the guide parachute 5, which is connected to the parachute compartment cover 6, is synchronously brought out of the parachute compartment 2, effectively ensuring the smooth deployment of the guide parachute 5.

[0040] It should be noted that after the first and second separation devices are unlocked, the parachute canopy 6 is separated and the guide parachute 5 is deployed by airflow, ensuring the normal deployment of the guide parachute 5 after long-term storage. Compared to integrating springs into the guide parachute 5, there is no need to reserve space for spring installation and extension inside the parachute canopy 2, significantly reducing the overall volume required for the parachute canopy 2, achieving lightweighting and miniaturization of the aircraft recovery mechanism, thus reserving more space for the layout of the aircraft 1. Moreover, there is no issue of reduced elasticity or decreased reliability due to long-term pressure storage of the spring structure. On the other hand, after eliminating the spring, the parachute canopy 6 no longer bears the load of resisting the spring force, thereby reducing the design requirements for the material strength and structural strength of the parachute canopy 6, effectively reducing the overall manufacturing cost of the aircraft recovery mechanism.

[0041] It should be further noted that pyrotechnics are inherently flammable and explosive, posing a high safety hazard during the transportation, storage, and deployment of the guide parachute 5 of the aircraft 1. Compared to using pyrotechnics to detonate the guide parachute 5, this invention has no flammable or explosive components, thus posing a lower safety hazard. Furthermore, it eliminates the need to consider the storage of pyrotechnics, effectively reducing the overall storage cost of the aircraft recovery mechanism.

[0042] like Figures 1 to 7 As shown, when the aircraft 1 lands, when the aircraft 1 lands to the first preset altitude, the first separation device and the second separation device are unlocked simultaneously or sequentially. At this time, under the pushing action of the external airflow, the parachute canopy 6 is separated from the parachute compartment 2, and the guide parachute 5 is brought out of the parachute compartment 2. After the guide parachute 5 leaves the parachute compartment 2, the guide parachute 5 begins to inflate until it is fully opened, until the guide parachute 5 rope of the guide parachute 5 is taut to pull the seal of the main parachute pack 3. After the seal of the main parachute pack 3 is pulled open, the main parachute 4 begins to inflate until it is fully opened to pull the aircraft 1 until the aircraft 1 lands smoothly.

[0043] In some embodiments of the present invention, the main parachute 4 is connected to the assembly carrying strap 7 by several parachute lines. The parachute lines have sufficient strength to pull the aircraft 1. The assembly carrying strap 7 is connected to the center of gravity of the aircraft 1 by a breakaway rope 8. The assembly carrying strap 7 is connected to the front end of the aircraft 1 by a front lower sling 9 and to the rear end of the aircraft 1 by a rear lower sling 10. The lengths of both the front lower sling 9 and the rear lower sling 10 are greater than the length of the breakaway rope 8. When the main parachute 4 is deployed and an opening overload occurs, the shortest breakaway rope will break. Rope 8 will be fully straightened first, thus absorbing the impact force generated at the moment of parachute opening. This effectively prevents the front lower strap 9 and the rear lower strap 10 from being deformed or damaged due to premature stress. At the same time, the fixing point of rope 8 is precisely aligned with the center of gravity of aircraft 1. The key to this design is to quickly balance the traction force on aircraft 1 during the critical stress phase of parachute opening, preventing aircraft 1 from flipping, swaying, or becoming unstable due to force deviation, and effectively ensuring a smooth transition of aircraft 1's attitude during the deployment of the main parachute 4.

[0044] In some specific embodiments, the length of the front lower sling 9 is greater than the length of the rear lower sling 10. This allows the aircraft 1 to naturally form a fixed tilt angle in the pitch direction during its stable descent under the traction of the main parachute 4, until the aircraft 1 lands. This ensures that the aircraft 1 does not touch the ground synchronously as a whole upon landing, but rather that specific parts of the aircraft make contact with the ground first according to a preset tilt posture. By rationally planning the landing sequence, the cargo carried in key positions on the aircraft 1 can be selectively avoided, thereby preventing the cargo from directly bearing the impact force during landing and reducing the risk of damage to important cargo caused by landing vibration and impact. This protects the cargo and also reduces the risk of damage to the main structure of the aircraft 1 due to overall landing, effectively improving the safety of the aircraft 1 and its cargo throughout the recovery process.

[0045] In some embodiments of the present invention, the first separation device includes a first fixing part 11 and a second fixing part 12 connected by a locking mechanism. The first fixing part 11 is connected to the front end of the parachute compartment 2, and the second fixing part 12 is connected to the front end of the parachute compartment cover 6. The first fixing part 11 and the second fixing part 12 form a reliable closed state through the latching structure of the locking mechanism, ensuring that the parachute compartment 2 remains sealed during synchronous flight with the aircraft 1, thus protecting the guide parachute 5 and the main parachute 4 inside the parachute compartment 2. It should be noted that an altitude sensor is installed in the aircraft 1 to monitor the altitude position of the aircraft 1 in real time. When the aircraft 1 lands at a first preset altitude, the control system of the aircraft 1 issues an unlocking command based on the signal transmitted by the altitude sensor. After receiving the command, the locking mechanism responds quickly to unlock, driving the first fixing part 11 and the second fixing part 12 to complete the separation action, so that the front end of the parachute compartment cover 6 detaches from the front end of the parachute compartment 2. This creates a key prerequisite for the subsequent detachment of the parachute compartment cover 6 from the parachute compartment 2 under the propulsion of the external airflow and the smooth deployment of the guide parachute 5, effectively improving the stability and reliability of the aircraft recovery mechanism.

[0046] like Figure 2 and Figure 8 As shown, in some embodiments of the present invention, the second separation device includes: a first connecting part 15 and a second connecting part 16 that are rotatably connected. The first connecting part 15 is connected to the tail end of the parachute compartment 2, and the second connecting part 16 is connected to the tail end of the parachute compartment cover 6. That is, the first connecting part 15 and the second connecting part 16 are connected by a rotatable connection structure to ensure that the tail end of the parachute compartment cover 6 can rotate relative to the parachute compartment 2. After the aircraft 1 lands at the first preset altitude, the front end of the parachute canopy 6 detaches from the front end of the parachute compartment 2. After the front end of the parachute canopy 6 completes the separation action from the front end of the parachute compartment 2, under the push of the external airflow, the parachute canopy 6 will rotate relative to the parachute compartment 2 to a preset angle with the connection between the first connecting part 15 and the second connecting part 16 of the second separation device as the axis. The first connecting part 15 and the second connecting part 16 will separate from each other, so that the tail end of the parachute canopy 6 detaches from the tail end of the parachute compartment 2. The key to this design is that one end separates first, and the other end of the parachute canopy 6 is unlocked after rotating to the preset angle. This can accurately control the initial attitude and trajectory of the parachute canopy 6 when it detaches from the parachute compartment 2, and avoid the parachute canopy 6 from colliding and getting entangled with the aircraft 1 and the already deployed guide parachute 5 or the subsequently deployed main parachute 4 due to loss of control of the route during the jettison process. This is conducive to the smooth deployment of the subsequent guide parachute 5 and main parachute 4 and the stabilization of the landing attitude of the aircraft 1. On the other hand, the controllable launch path and position of the parachute canopy 6 can also prevent the parachute canopy 6 from causing accidental impacts on personnel and facilities in the area below after drifting around at high altitudes, thereby improving the safety of the entire aircraft recovery mechanism.

[0047] In some embodiments of the present invention, one of the first connecting part 15 and the second connecting part 16 is a bushing 18. A U-shaped groove 1801 is provided on one side of the bushing 18. The extension direction of the U-shaped groove 1801 is set at an angle to the top surface of the parachute compartment 2. That is, the extension direction of the U-shaped groove is not at a conventional horizontal or vertical angle to the top surface of the parachute compartment 2. Specifically, the angle between the extension direction of the U-shaped groove 1801 and the top surface of the parachute compartment 2 is designed according to the initial posture and movement trajectory of the parachute compartment cover 6 when it leaves the parachute compartment 2. The extension direction of the U-shaped groove set at a specific angle can define a precise trajectory for the rotation of the parachute compartment cover 6 around the rotating axis 17, effectively avoiding problems such as deviation during rotation, so that the parachute compartment cover 6 can form a throw posture that meets the expectations when it rotates to a preset angle, and form a movement trajectory that meets the expectations during the subsequent landing process. In addition, the other of the first connecting part 15 and the second connecting part 16 is a rotating shaft 17. The U-shaped groove 1801 is rotatably connected to the rotating shaft 17. The U-shaped groove 1801 can just accommodate the rotating shaft 17, and the inner wall of the U-shaped groove 1801 has a certain degree of fit with the outer peripheral side of the rotating shaft 17. While ensuring that the bushing 18 and the rotating shaft 17 can rotate relatively stably, it can also reduce the frictional resistance during rotation, and ensure the flexibility of the parachute canopy 6 when rotating relative to the parachute canopy 2.

[0048] like Figure 9 and Figure 10 As shown, to prevent the parachute canopy 6 from separating from the parachute canopy 2 before rotating to the preset angle, the structure of the U-shaped groove and the rotating shaft 17 is further optimized. Specifically, two mounting grooves 1701 are opened on the outer peripheral side of the rotating shaft 17, and the two mounting grooves 1701 are symmetrically arranged about the axis of the rotating shaft 17. At the same time, a mating hole 1802 is opened at the end of the U-shaped groove away from the port. The mating hole 1802 and the rotating shaft 17 are clearance-fitted to ensure that the rotating shaft 17 can rotate flexibly. In addition, the diameter of the rotating shaft 17 is set to be greater than the width of the U-shaped groove, and the distance between the two mounting grooves 1701 is smaller than the width of the U-shaped groove. In the initial state, the surfaces of the two assembly slots 1701 are not parallel to the two inner walls of the U-shaped groove. The rotating shaft 17 is confined within the U-shaped groove and can only rotate relative to the bushing 18. When the tail end of the parachute cover 6 rotates to a preset angle relative to the tail end of the parachute compartment 2, the surfaces of the two assembly slots 1701 will be parallel to the two inner walls of the U-shaped groove. At this time, the rotating shaft 17 can slide out of the U-shaped groove, and the parachute cover 6 and the parachute compartment 2 will separate. This allows for precise control of the initial posture and trajectory of the parachute cover 6 when it leaves the parachute compartment 2.

[0049] like Figure 11As shown, in some embodiments of the present invention, the second separation device includes a third fixing part 13 and a fourth fixing part 14 connected by a locking mechanism. The third fixing part 13 is connected to the tail end of the parachute compartment 2, and the fourth fixing part 14 is connected to the tail end of the parachute compartment cover 6. When the aircraft 1 lands to a first preset altitude, the third fixing part 13 and the fourth fixing part 14 separate from each other, causing the tail end of the parachute compartment cover 6 to detach from the tail end of the parachute compartment 2. Similarly, the third fixing part 13 and the fourth fixing part 14 form a reliable closed state through the locking and snapping structure of the locking mechanism, ensuring that the parachute compartment 2 remains sealed during synchronous flight with the aircraft 1, further protecting the guide parachute 5 and the main parachute 4 inside the parachute compartment 2.

[0050] It should be noted that when the aircraft 1 descends to the first preset altitude, the control system of the aircraft 1 will issue an unlocking command based on the signal transmitted by the altitude sensor. After receiving the command, the latch will respond quickly to unlock, driving the third fixing part 13 and the fourth fixing part 14 to complete the separation action, so that the tail end of the parachute canopy 6 separates from the tail end of the parachute compartment 2, which is synchronized with the front end of the parachute canopy 6 separating from the front end of the parachute compartment 2. This ensures that the two ends of the parachute canopy 6 and the parachute compartment 2 separate synchronously, so as to ensure that the force on both ends of the parachute canopy 6 is even, preventing the parachute canopy 6 from getting stuck at the port of the parachute compartment 2 and ensuring that the airflow can act smoothly on the guide parachute 5 inside the parachute compartment 2, thereby ensuring that the guide parachute 5 is successfully deployed from the parachute compartment 2.

[0051] It should be further noted that, compared to the method of unlocking the parachute canopy 6 one side at a time relative to the parachute compartment 2, simultaneous unlocking can significantly shorten the overall time for the parachute canopy 6 to detach from the parachute compartment 2, reduce the preparation time before the deployment of the guide parachute 5 and the main parachute 4, improve the working efficiency of the entire aircraft recovery mechanism, adapt to the environment of variable wind speed and complex airflow at high altitudes, effectively avoid the problem of disordered deployment sequence of the guide parachute 5 and the main parachute 4 caused by the delay in the detachment of the parachute canopy 6, improve the stability and safety of the overall aircraft recovery mechanism, and effectively ensure the smooth deceleration and safe landing of the aircraft 1.

[0052] In some embodiments of the present invention, during the descent of the aircraft 1, the guide parachute 5 is positioned directly above the main parachute 4 to ensure that the guide parachute 5 quickly contacts the airflow and unfolds first after being deployed. After the guide parachute 5 is carried out of the parachute compartment 2 by the airflow and unfolds, the guide rope 19 is used to steadily and precisely pull the seal of the main parachute pack 3, allowing the main parachute pack 3 to open smoothly, thereby enabling the main parachute 4 to smoothly deploy and unfold gradually along a preset trajectory. It should be noted that placing the guide parachute 5 above the main parachute 4 can prevent problems such as tangling and knotting of the main parachute 4 during deployment, indirectly ensuring a smooth landing of the aircraft 1.

[0053] like Figures 1 to 7As shown, the operation method of the aircraft recovery mechanism adopted in this invention specifically includes the following steps: When the aircraft 1 lands to the first preset altitude, the first separation device and the second separation device are unlocked simultaneously or sequentially. At this time, under the pushing action of the external airflow, the parachute canopy 6 is separated from the parachute compartment 2, and the guide parachute 5 is brought out of the parachute compartment 2. After the guide parachute 5 leaves the parachute compartment 2, the guide parachute 5 begins to inflate until it is fully opened, until the guide parachute 5 rope is taut to pull the seal of the main parachute pack 3. After the seal of the main parachute pack 3 is opened, the main parachute 4 begins to inflate until it is fully opened. When the main parachute 4 is deployed and an opening overload occurs, the shortest break rope 8 will be fully straightened first, thereby absorbing the impact force generated at the moment of opening. Then, the front lower sling 9 and the rear lower sling 10 pull the aircraft 1, so that the aircraft 1 naturally forms a fixed tilt angle in the pitch direction during the stable descent under the traction of the main parachute 4, until the aircraft 1 lands smoothly.

[0054] In some embodiments of the present invention, the step of controlling the first separation device and the second separation device to unlock simultaneously or sequentially further includes: first controlling the first separation device to unlock, under the propulsion of external airflow, the front end of the parachute canopy 6 leaves the front end of the parachute compartment 2, and the rear end of the parachute canopy 6 rotates relative to the rear end of the parachute compartment 2. After the rear end of the parachute canopy 6 rotates relative to the rear end of the parachute compartment 2 to a preset angle, the rear end of the parachute canopy 6 leaves the rear end of the parachute compartment 2 along a preset throwing path, and the second separation device automatically unlocks, and the parachute canopy 6 completely detaches from the parachute compartment 2. Separating one end first, and then unlocking the other end of the parachute canopy 6 after rotating to a preset angle, precisely controls the initial attitude and trajectory of the parachute canopy 6 when it detaches from the parachute compartment 2, avoiding collisions and entanglements between the parachute canopy 6 and the already deployed guide parachute 5 or the subsequently deployed main parachute 4 due to loss of control during the throwing process, which is conducive to the smooth deployment of the subsequent guide parachute 5 and the main parachute 4 and the stable landing attitude of the aircraft 1.

[0055] In some embodiments of the present invention, the step of controlling the unlocking of the first separation device and the second separation device further includes: controlling the first separation device and the second separation device to unlock simultaneously. At this time, the first separation device and the second separation device have the same structure. Under the pushing action of the external airflow, the front end of the canopy cover 6 leaves the front end of the canopy 2, and at the same time, the rear end of the canopy cover 6 leaves the rear end of the canopy 2, and the canopy cover 6 is completely detached from the canopy 2. At this time, the two ends of the canopy cover 6 and the canopy 2 separate synchronously, and the two ends of the canopy cover 6 are subjected to uniform force, preventing the canopy cover 6 from getting stuck at the port of the canopy 2 and failing to detach smoothly, effectively ensuring that the guide umbrella 5 is smoothly ejected from the canopy 2.

[0056] In summary, when the aircraft 1 lands at the first preset altitude, the first separation device and the second separation device are unlocked simultaneously or sequentially, so that the parachute canopy 6 can quickly detach from the parachute canopy 2 under the push of the external airflow. This effectively prevents the parachute canopy 6 from interfering with the subsequent deployment process of the guide parachute 5 and the main parachute 4, and improves the stability and reliability of the aircraft recovery mechanism.

[0057] It should be noted that in this specification, relational terms such as first and second are used only to distinguish one entity from several other entities, and do not necessarily require or imply any such actual relationship or order between these entities.

[0058] This article uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. It should be noted that those skilled in the art can make several improvements and modifications to the present invention without departing from the principles of the present invention, and these improvements and modifications also fall within the protection scope of the present invention.

Claims

1. An aircraft recovery mechanism, characterized in that, include: Parachute compartment (2), located on aircraft (1), is used to store main parachute pack (3) and pilot parachute (5). The main parachute pack (3) contains the main parachute (4). Parachute compartment cover (6) is provided on parachute compartment (2). The inner side of parachute compartment cover (6) is connected to the pilot parachute (5). The first end of the parachute compartment (2) is connected to the first end of the parachute compartment cover (6) through the first separation device, and the second end of the parachute compartment (2) is connected to the second end of the parachute compartment cover (6) through the second separation device. When the aircraft (1) lands to the first preset altitude, the first separation device and the second separation device are unlocked simultaneously or sequentially, so that the parachute compartment cover (6) is separated from the parachute compartment. After the first separation device and the second separation device are unlocked, the separation of the canopy cover (6) and the ejection of the guide parachute (5) are achieved by relying on airflow; When the first separation device and the second separation device are unlocked in sequence, the second separation device includes: a first connecting part (15) and a second connecting part (16) that are rotatably connected. The first connecting part (15) is connected to the second end of the umbrella compartment (2), and the second connecting part (16) is connected to the second end of the umbrella compartment cover (6). When the first end of the umbrella compartment cover (6) is separated from the first end of the umbrella compartment (2), and the first end of the umbrella compartment cover (6) is rotated relative to the umbrella compartment (2) to a preset angle, the first connecting part (15) and the second connecting part (16) are separated from each other, so that the second end of the umbrella compartment cover (6) is separated from the second end of the umbrella compartment (2). The main parachute (4) is connected to the group carrying strap (7) by several parachute lines. The group carrying strap (7) is connected to the center of gravity of the aircraft (1) by a break rope (8). The group carrying strap (7) is connected to the front end of the aircraft (1) by a front lower sling (9). The group carrying strap (7) is connected to the rear end of the aircraft (1) by a rear lower sling (10). The length of the front lower sling (9) and the length of the rear lower sling (10) are both greater than the length of the break rope (8). The length of the front lower sling (9) is greater than the length of the rear lower sling (10) so that the aircraft (1) forms an angle of inclination with the ground surface. One of the first connecting part (15) and the second connecting part (16) is a bushing (18), and a U-shaped groove (1801) is provided on one side of the bushing (18). The extension direction of the U-shaped groove (1801) is set at an angle to the top surface of the parachute compartment (2). The other of the first connecting part (15) and the second connecting part (16) is a rotating shaft (17). The U-shaped groove (1801) is rotatably connected to the rotating shaft (17). Two mounting grooves (1701) are provided on the outer peripheral side of the rotating shaft (17), and the two mounting grooves (1701) are symmetrically arranged about the axis of the rotating shaft (17). At the same time, a mating hole (1802) is provided at the end of the U-shaped groove away from the port.

2. The aircraft recovery mechanism according to claim 1, characterized in that, The first separation device includes a first fixing part (11) and a second fixing part (12) that are locked together. The first fixing part (11) is connected to the first end of the parachute compartment (2), and the second fixing part (12) is connected to the first end of the parachute compartment cover (6). When the aircraft (1) lands to a first preset altitude, the first fixing part (11) and the second fixing part (12) separate from each other, so that the first end of the parachute compartment cover (6) is separated from the first end of the parachute compartment (2).

3. An aircraft recovery mechanism according to any one of claims 1-2, characterized in that, The second separation device includes a third fixing part (13) and a fourth fixing part (14) that are locked together. The third fixing part (13) is connected to the second end of the parachute compartment (2), and the fourth fixing part (14) is connected to the second end of the parachute compartment cover (6). When the aircraft (1) lands to the first preset altitude, the third fixing part (13) and the fourth fixing part (14) separate from each other, so that the second end of the parachute compartment cover (6) is separated from the second end of the parachute compartment (2).

4. An aircraft recovery mechanism according to any one of claims 1-2, characterized in that, The guide umbrella (5) is located above the main umbrella (4), and the guide umbrella (5) is connected to the seal of the main umbrella pack (3) by a guide pull rope (19).

5. A method for operating an aircraft recovery mechanism, applied to the aircraft recovery mechanism according to any one of claims 1-4, characterized in that, The operation method includes: When the aircraft (1) lands to the first preset altitude, the first separation device and the second separation device are unlocked simultaneously or sequentially. At this time, under the push of the external airflow, the canopy cover (6) is separated from the canopy (2), and the guide parachute (5) is brought out of the canopy (2). After the guide parachute (5) leaves the canopy (2), the guide parachute (5) begins to inflate until it is fully open, until the guide parachute (5) rope is taut to pull the seal of the main parachute pack (3); After the seal of the main parachute pack (3) is opened, the main parachute (4) begins to inflate until it is fully open, so as to pull the aircraft (1) until the aircraft (1) lands smoothly.

6. The operating method of the aircraft recovery mechanism according to claim 5, characterized in that, The step of controlling the first separation device and the second separation device to unlock simultaneously or sequentially further includes: first controlling the first separation device to unlock, under the pushing action of the external airflow, the first end of the parachute cover (6) leaves the first end of the parachute compartment (2), the second end of the parachute cover (6) rotates relative to the second end of the parachute compartment (2), after the second end of the parachute cover (6) rotates relative to the second end of the parachute compartment (2) to a preset angle, the second end of the parachute cover (6) leaves the second end of the parachute compartment (2) along a preset throwing path, the second separation device automatically unlocks, and the parachute cover (6) completely separates from the parachute compartment (2).

7. The operating method of the aircraft recovery mechanism according to claim 5, characterized in that, The step of controlling the first separation device and the second separation device to unlock further includes: controlling the first separation device and the second separation device to unlock simultaneously, and under the pushing action of the external airflow, the first end of the parachute cover (6) leaves the first end of the parachute compartment (2), and at the same time, the second end of the parachute cover (6) leaves the second end of the parachute compartment (2), and the parachute cover (6) is completely separated from the parachute compartment (2).

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