Unmanned helicopter emergency use device and working method
By designing rotor shaft sleeves and magnetic suction devices on the unmanned helicopter to control the opening and separation of the parachute, the problem of the unmanned helicopter crash in emergency situations is solved, and safe emergency response in different environments is achieved, reducing risks and losses.
Patent Information
- Application Number
- CN202510582748.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-07
- Publication Date
- 2025-07-08
AI Technical Summary
Unmanned helicopters are easily directly damaged in emergency situations and cannot be controlled and adjusted by themselves, especially in extreme environments such as sea or desert, resulting in crashes and data loss.
An emergency use device for unmanned helicopters is designed, including rotor shaft sleeve, parachute and bearings in rotor shaft sleeve. The opening and separation of parachutes are controlled through pins and magnetic suction devices, and combined with the umbrella surface inflation module, safe emergency response in different environments is achieved.
It effectively reduces the risk of unmanned helicopter flight tests, reduces crashes and secondary losses, enhances environmental adaptability in different scenarios, and ensures the integrity of the test data.
Smart Images
Figure CN120270520A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the technical field of unmanned helicopters, and particularly relates to an emergency use device and working method for an unmanned helicopter. Background Art
[0002] Due to its vertical takeoff and landing capabilities and hovering characteristics in the air, unmanned helicopters have a wide range of application scenarios in fields such as emergency rescue, logistics transportation, and environmental monitoring. For newly developed unmanned helicopters, in the emergency response procedure, the unmanned helicopter often uses autorotation gliding to make an emergency landing. However, during the test flight process, different from manned helicopters, the unmanned helicopter can conduct flight tests through manual control. In the face of emergency situations, it is easy to cause a crash accident, especially during tests at sea or in the desert.
[0003] For example, for a newly developed unmanned helicopter during a flight test at sea, once an emergency situation occurs, the unmanned helicopter may fall into the sea, resulting in the crash of the unmanned helicopter and the loss of flight data, making it difficult to provide effective support for the improvement design of the unmanned helicopter. In addition, during flight tests in high plateaus or deserts, the climate environment in these areas is harsh, and sometimes the local air convection is intense. If the surface wrapping area of the unmanned helicopter is large, even if the unmanned helicopter completes a ground emergency landing, it may cause secondary impact damage. Summary of the Invention
[0004] The purpose of the present invention is to overcome the above-mentioned shortcomings of the prior art and provide an emergency use device and working method for an unmanned helicopter to solve the problems in the prior art that when the unmanned helicopter encounters an emergency or abnormal situation, it is easy to be directly damaged, and the unmanned helicopter cannot control and adjust itself in abnormal situations.
[0005] To achieve the above purpose, the present invention adopts the following technical solutions: An emergency use device for an unmanned helicopter, comprising a rotor shaft, a parachute, and a rotor shaft sleeve; Inside the rotor shaft sleeve, a first bearing and a second bearing are installed coaxially up and down. A shaft pin is connected in the inner ring of the first bearing, and the upper end of the rotor shaft is inserted into the inner ring of the second bearing; A first magnetic attraction device and a second magnetic attraction device are arranged outside the rotor shaft sleeve, and a first pin and a second pin are installed inside. One end of the first pin is inserted into the first magnetic attraction device, and the other end passes through the shaft pin; the first end of the second pin is inserted into the second magnetic attraction device, and the other end passes through the shaft pin; A lock is sleeved on the first pin, and the lock is used to fix the parachute canopy; a pull pin is sleeved on the second pin, and the pull pin is used to connect the parachute; A sleeve communication module is installed on the rotor shaft sleeve, and the sleeve communication module is electrically connected to the first magnetic attraction device and the second magnetic attraction device.
[0006] A further improvement of the present invention lies in: Preferably, the first bolt and the second bolt are respectively arranged on the upper side and the lower side of the first bearing.
[0007] Preferably, both the first bolt and the second bolt are perpendicular to the shaft pin.
[0008] Preferably, a relay is arranged outside the rotor shaft sleeve, and the sleeve communication module is electrically connected to the first magnetic attraction device and the second magnetic attraction device through the relay.
[0009] Preferably, the upper end of the rotor shaft is connected with a nut, and the nut is above the second bearing.
[0010] Preferably, a stop washer is arranged between the nut and the second bearing.
[0011] Preferably, a parachute inflation module is arranged on the parachute surface, and the parachute surface is connected to the pull pin through a parachute rope.
[0012] Preferably, the parachute inflation module includes a gas generator, a parachute surface communication module and a water inductor, and the parachute surface communication module is connected to the gas generator and the water inductor at the same time; the gas output port of the gas generator is communicated with the inside of the parachute surface.
[0013] A working method of the above unmanned helicopter emergency use device includes the following four situations: Situation 1: When the unmanned helicopter is in a normal working state, a lock is sleeved on the first bolt, and a pull pin is sleeved on the second bolt; the unmanned helicopter carries the parachute to perform tasks; Situation 2: When the unmanned helicopter is in an emergency state, the sleeve communication module controls the first magnetic attraction device to cut off the power supply, the first bolt disengages from the first magnetic attraction device, the lock disengages, and the parachute surface opens; Situation 3: When the unmanned helicopter crashes into the sea, the sleeve communication module controls the first magnetic attraction device to cut off the power supply, the first bolt disengages from the first magnetic attraction device, the lock disengages, the parachute surface opens, and the inside of the parachute surface is filled with gas; Situation 4: When the unmanned helicopter crashes on the ground and there is a gust of wind, the sleeve communication module controls the first bolt and the second bolt to be pulled out, the first bolt disengages from the lock, the second bolt disengages from the pull pin, and the parachute separates from the unmanned helicopter.
[0014] Preferably, in Case 4, when the unmanned helicopter makes a vertical landing, the sleeve communication module first controls the first bolt and the latch to disengage, the parachute surface opens, gas is filled into the parachute surface, the parachute is hung high, and after the rescue personnel reach the corresponding position, the sleeve communication module controls the second bolt to be pulled out, and the parachute is separated from the unmanned helicopter.
[0015] Compared with the prior art, the present invention has the following beneficial effects: An emergency use device for an unmanned helicopter according to the present invention. A rotor shaft sleeve is provided at the connection between the unmanned helicopter and the parachute. Two bearings are installed in the rotor shaft sleeve and are respectively used to connect the shaft pin and the rotor shaft, so that the rotor shafts can all rotate relative to the rotor shaft sleeve. The shaft pin is provided with a first bolt and a second bolt. The first bolt is used to lock the latch for fixing the parachute surface and is connected to the first magnetic attraction device at the same time. The second bolt is used to lock the pull pin for connecting the parachute and is connected to the second magnetic attraction device at the same time. The sleeve communication module controls the energization of the magnetic attraction device, so that the latch and the pull pin can disengage from the two bolts, and further the parachute surface can be opened, or the entire parachute can be separated from the unmanned helicopter. The setting of this connection device enables the parachute to correspond to different states in different situations, provides better safety protection for the test of the unmanned helicopter, effectively reduces the flight test risk of the unmanned helicopter, and reduces the secondary losses caused by the crash of the unmanned helicopter. This device can be applied in the field of unmanned helicopters and can also be applied in the field of other rotary-wing aircraft, effectively enhancing the emergency handling ability of unmanned helicopters and reducing the losses caused by secondary crashes or disappearances of unmanned helicopters.
[0016] Furthermore, the two bolts are respectively arranged on the upper side and the lower side of the two bearings to prevent interference between the latch and the pull pin sleeved on the two bolts.
[0017] Furthermore, the axial directions of the two bolts are both perpendicular to the shaft pin, so that the bolts can be inserted and disengaged conveniently.
[0018] Furthermore, a nut is connected to the upper end of the rotor shaft, and the set nut can prevent the rotor shaft from disengaging from the bearing.
[0019] Furthermore, a stop washer is arranged between the nut and the second bearing to limit the movement of the second bearing.
[0020] Furthermore, a parachute inflation module is arranged on the parachute surface. When the unmanned helicopter crashes into the sea, gas is filled into the parachute surface, which can ensure that the unmanned helicopter floats on the sea surface and will not sink.
[0021] The present invention also discloses a working method of an emergency use device for an unmanned helicopter. This working method unlocks different pins according to the environmental conditions when the unmanned helicopter is falling, so that the parachute is in different states, which can be opened, released or inflated. This enables the unmanned helicopter to be safely used whether it is in the plateau, desert, high-rise building or floating on the sea, and can greatly enhance the environmental adaptability in different scenarios. BRIEF DESCRIPTION OF THE DRAWINGS
[0022] Figure 1 It is a schematic diagram of the parachute surface structure of the present invention; Figure 2 It is a sectional view structure diagram of the first side of the rotor shaft sleeve of the present invention; Figure 3 It is a sectional view structure diagram of the second side of the rotor shaft sleeve of the present invention; Figure 4 It is a structure diagram of the second side of the rotor shaft sleeve of the present invention when installing the lock and the pull pin; Figure 5 It is a sectional view structure diagram of the third side of the rotor shaft sleeve of the present invention; Wherein: 1, parachute surface; 2, parachute rope; 3, first magnetic attraction device; 4, second magnetic attraction device; 5, first bearing; 6, shaft pin; 7, first pin; 8, relay; 9, storage battery; 10, second pin; 11, rotor shaft sleeve; 12, rotor shaft; 13, second bearing; 14, sleeve communication module; 15, nut; 16, stop washer; 17, lock; 18, pull pin. DETAILED DESCRIPTION OF THE EMBODIMENTS
[0023] As the problems raised in the background art, for the development of a new unmanned helicopter, autorotation gliding is usually used as an emergency landing mode in its emergency disposal procedures. However, in the test flight stage, compared with a manned helicopter equipped with a manual control unit, the unmanned system needs to rely on preset control logic and remote instructions to execute flight tests, and there is a phenomenon of response lag when facing sudden failures, which is likely to cause irreversible crash accidents. Such risks are particularly prominent in sea or desert test scenarios.
[0024] Taking a sea trial as an example, when a new unmanned helicopter encounters an emergency condition, if it loses control and crashes into the sea, it will result in double losses: firstly, the immersion of the airframe causes structural damage to the platform; secondly, the flight parameter storage unit is eroded by seawater, resulting in irreversible loss of data and inability to obtain complete key flight test data. In plateau and desert tests, extreme environmental conditions pose multiple threats to the safety of forced landings: firstly, strong convective weather disturbances exacerbate the dynamic instability of the airframe; secondly, the surface characteristics of the forced landing area (such as soft sandy or rugged terrain) may cause secondary collisions; in addition, when the large-size airframe configuration is subjected to local impact loads at the moment of touchdown, there is a risk of overload failure of key components. To solve the above problems, the present invention discloses an emergency use device and working method for an unmanned helicopter.
[0025] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary and are only used to explain the present invention and should not be construed as a limitation of the present invention.
[0026] In the first aspect of the present invention, an emergency use device for an unmanned helicopter is provided, which includes a parachute main body component, a parachute connection component, and a parachute inflation module.
[0027] See Figure 1 , the parachute main body component includes the parachute canopy 1 and several parachute ropes 2. The upper ends of the several parachute ropes 2 are fixedly connected to the edge of the canopy 1. The ends of all the parachute ropes 2 converge into a bundle, which is connected to the pull pin 18, and the pull pin is connected to the parachute connection component; the bundle formed by the convergence of the ends of the parachute ropes 2 is installed directly above the rotor hub through the parachute connection component. When the unmanned helicopter is in a normal state, the parachute main body component is in a compressed state. When the unmanned helicopter is triggered to open emergently, the restraint of the parachute main body component is opened, and the parachute ropes 2 will be in a straightened state. The parachute ropes 2 are connected to the upper end of the unmanned helicopter through the bundle.
[0028] In some embodiments of the present invention, the parachute ropes 2 are equally divided circumferentially around the parachute canopy 1, and the ends of all the parachute ropes 2 are connected through penetration, so that the connection force between the entire canopy 1 and the unmanned helicopter is uniform.
[0029] In some embodiments of the present invention, the canopy 1 is a hollow structure formed by sewing multiple layers of fabrics, and after unfolding and inflating, it is an airbag structure, which can slow down the further fall of the unmanned helicopter.
[0030] Preferably, the canopy 1 adopts a hollow structure formed by sewing upper and lower layers of fabrics, which can reduce the weight of the entire canopy 1. When the canopy 1 unfolds, an airbag is formed inside, thereby reducing the weight of the entire canopy 1.
[0031] When the parachute canopy 1 is not opened, it is in a stowed state. The entire parachute canopy 1 is locked by a buckle to prevent the parachute from opening. It should be noted that the form of the buckle of the parachute canopy 1 in the present invention is not fixed. The parachute canopy 1 can be arranged in a storage structure and fixed by a buckle. Once the buckle is opened, the parachute canopy 1 disengages from the storage structure and inflates, or it can also be directly stored through the buckle structure. When the buckle is opened, the parachute canopy 1 expands and inflates immediately.
[0032] In some embodiments of the present invention, a parachute inflation module is provided on the parachute canopy 1. The parachute inflation module includes a gas generator and a canopy communication module, which are encapsulated in the upper part of the parachute canopy 1. The canopy communication module serves as a relay module and is electrically connected to the gas generator; the canopy communication module is wirelessly connected to a remote control device. Once the remote control device detects that the unmanned helicopter is abnormally dropped and the dropping location is on the sea surface, lake surface or other locations, the remote control device controls the gas generator to inflate the parachute canopy through the canopy communication module to prevent the unmanned helicopter from falling into the sea floor and being difficult to salvage.
[0033] The gas generator on the parachute is mainly used to quickly inflate and deploy the parachute canopy or provide emergency parachute-opening power in specific scenarios. Its design and application need to take into account reliability, safety and environmental adaptability. It can be an inflatable pyrotechnic gas generator inside, or it can also be gas generated by the reaction of two chemical substances. The gas output end of the gas generator is connected to the inside of the parachute canopy 1. Once the gas generator generates gas, the inside of the parachute canopy 1 can be quickly filled with gas.
[0034] Preferably, the parachute inflation module further includes a water sensor, which is also electrically connected to the canopy communication module. The water sensor is optionally installed in the parachute inflation module of the unmanned helicopter. When the unmanned helicopter lands on the water surface and the water sensor comes into contact with or is submerged by water, even if the gas generator does not receive a signal from the canopy communication module, it can automatically trigger the gas generator to work and inflate the inside of the parachute canopy 1, so that the parachute canopy 1 can float on the water surface when it is fully inflated; the water sensor simultaneously feeds back the situation of the unmanned helicopter falling into the water to the remote monitoring device through the canopy communication module.
[0035] Furthermore, the water sensor can be any one or several of a contact electrode sensor, a capacitive sensor, a photoelectric sensor and a humidity sensing film.
[0036] It should be understood that the above-mentioned remote monitoring device can be a control handle, a remote control computer and other devices; the above-mentioned remote monitoring device, in addition to being able to control the gas generator and obtain the signal transmitted by the water sensor, can also monitor and control the unmanned helicopter.
[0037] The parachute connecting component described in the present invention is installed inside the upper part of the rotor shaft and directly below the parachute main body component. The connecting component of the parachute includes a rotor shaft sleeve 11, a first bearing 5, a second bearing 13, a shaft pin 6, and a stop washer 16. The parachute opening module includes a parachute opening device and a parachute jettisoning device, and includes a first magnetic attraction device 3, a second magnetic attraction device 4, a first bolt 7, a second bolt 10, a relay 8, a storage battery 9, and a sleeve communication module 14.
[0038] The entire connecting component is externally a rotor shaft sleeve 11, which is a barrel-shaped structure with openings at both the top and bottom; the first bearing 5 is installed inside the rotor shaft sleeve 11. The outer ring of the first bearing 5 is connected to the rotor shaft sleeve 11, and the inner ring is connected to the shaft pin 6. The shaft pin 6 and the rotor shaft sleeve 11 are coaxial; the first bolt 7 and the second bolt 10 are inserted into the first shaft pin 6. The axial directions of the first bolt 7 and the second bolt 10 are both perpendicular to the first shaft pin 6. The first bolt 7 is above the first bearing 5, and the second bolt 10 is below the second shaft pin 10; two magnetic attraction devices are oppositely arranged outside the rotor shaft sleeve 11, namely the first magnetic attraction device 3 and the second magnetic attraction device 4. The first magnetic attraction device 3 is installed directly below the parachute main body component and at the upper end of the rotor hub. The outer end of the first bolt 7 is arranged in the first magnetic attraction device 3. The inner end of the first bolt 7 passes through the shaft pin 6. The outer end of the second bolt 10 is arranged in the second magnetic attraction device 4, and the inner end passes through the shaft pin 6 and abuts against the inner side wall of the rotor shaft sleeve 11.
[0039] It should be understood that Figure 3 a situation of the arrangement of the two magnetic attraction devices is given in. The first magnetic attraction device 3 and the second magnetic attraction device 4 are arranged oppositely, and correspondingly, the first bolt 7 and the second bolt 10 are arranged oppositely; the included angle between the two bolts is 90°. The included angle between the two bolts can also be other angles such as 45° and 60°, as long as the two bolts do not affect each other. Correspondingly, the positions of the magnetic attraction devices are adjusted so that they can be closer.
[0040] See Figure 3 and Figure 4, the buckle 17 of the umbrella surface 1 is sleeved on the first bolt 7, and the pull pin 18 of the parachute is sleeved on the second bolt 10, so that the buckle 17 is above the pull pin 18. If the buckle 17 needs to be disengaged, it will not be affected by the pull pin 18. In the normal state, the buckle 17 is sleeved on the first bolt 7. When only the parachute needs to be inflated and opened, but the unmanned helicopter and the parachute do not need to be separated, the first magnetic attraction device 3 no longer has magnetism, and the first bolt 7 moves from the shaft pin 6 towards the first magnetic attraction device 3. The buckle 17 disengages from the first bolt 7, and the parachute opens. Since the pull pin 18 is still set on the second bolt 10, the parachute and the unmanned helicopter are not separated. In the emergency state, when it is necessary to separate the unmanned helicopter and the parachute, both the first magnetic attraction device 3 and the second magnetic attraction device 4 no longer have magnetism. The buckle 17 disengages from the first bolt 7, and the pull pin 18 disengages from the second bolt 10. The parachute and the unmanned helicopter are separated.
[0041] Outside the rotor shaft sleeve 11, at the height where the first bolt 7 is located, a relay 8 is provided. The relay 8 is installed in front of the first magnetic attraction device 3 and controls whether the first magnetic attraction device 3 is energized, thereby controlling whether the first magnetic attraction device 3 adsorbs and separates from the first bolt 7. The second magnetic attraction device 4 is installed on the lower side of the first magnetic attraction device 3, and the adsorption and separation of the bolt by the magnetic attraction device are controlled by the relay; the relay 8 is installed outside the rotor shaft, between the two magnetic attraction devices. The relay 8 is provided with three bundles of leads. One bundle of leads is connected to the first magnetic attraction device 3 for controlling the adsorption and separation of the first magnetic attraction device 3. One bundle of leads is used to connect to the second magnetic attraction device 4 for controlling the adsorption and separation of the magnetic attraction device. One bundle of leads is connected to the storage battery for receiving the power signal.
[0042] An outer sleeve communication module 14 is also installed outside the rotor shaft sleeve 11. The sleeve communication module 14 and the remote monitoring device are connected by a wireless device for receiving control instructions to determine whether the relay 8 supplies power to the first magnetic attraction device 3 and the second magnetic attraction device 4. Under normal circumstances, the relay 8 continuously supplies power to the first magnetic attraction device 3 and the second magnetic attraction device 4, enabling the first magnetic attraction device 3 and the second magnetic attraction device 4 to be connected to their respective corresponding bolts. In case of an emergency, the opening and throwing functions of the parachute in the emergency state are controlled remotely.
[0043] In some embodiments of the present invention, refer to Figure 2 、 Figure 3 、 Figure 4 Figure 5, the upper end of the rotor shaft of the unmanned helicopter is inserted into the inner ring of the second bearing 13 and connected to the inner ring of the second bearing 13. The second bearing 13 is installed inside the rotor shaft sleeve 11, and the rotational freedom of the rotor shaft is released. When the parachute is opened, the parachute will not rotate and entangle. A nut 15 and a stop washer 16 are installed at the upper end of the second bearing 13. The nut 15 is fixedly connected to the rotor shaft 12, and the stop washer 16 is installed between the second bearing 13 and the nut 15 to prevent the rotor shaft 12 from sliding outwards and at the same time be able to stop the movement towards the second bearing 13.
[0044] See Figure 3 and Figure 4 , as a preferred solution, two second bearings 13 are installed in the rotor shaft sleeve 11, both connected to the rotor shaft 12. When the rotor shaft 12 and the rotor shaft sleeve 11 rotate relative to each other, it is used to stabilize the rotor shaft 12 and prevent the rotor shaft 12 from shaking.
[0045] See Figures 1-5 , in a specific embodiment of the present invention, the parachute canopy 1 is connected to a plurality of suspension lines 2. The parachute canopy 1 is a hollow structure composed of multiple layers of fabrics sewn together. A gas generator, a water sensor, and a canopy communication module are installed on the parachute; the ends of all the suspension lines 2 converge into a bundle, and this bundle is connected to a pull pin 18. The parachute canopy 1 is packed and locked through a buckle 17; the main structure of the parachute connecting component is a rotor shaft sleeve 11 with openings at both the top and bottom. Inside the rotor shaft sleeve 11, a first bearing 5 and two second bearings 13 are arranged in sequence from top to bottom. A shaft pin 6 is connected inside the first bearing 5. The rotor shaft 12 passes through the two second bearings 13 at the same time, and the rotor shaft 12 is connected to the two second bearings 13. The first pin 7 and the second pin 10 in two directions are inserted into the shaft pin 6. The first pin 7 is above the second pin 10. The outer ends of the two pins are respectively connected to a magnetic attraction device, and the two magnetic attraction devices are jointly connected to a relay 8. The relay 8 is used to supply power to the two magnetic attraction devices so that the two pins can be stably inserted into the shaft pin 6. A buckle 17 is sleeved on the first pin 7, a pull pin 18 is sleeved on the second bearing 13, and a nut 15 is installed at the upper end of the rotor shaft 12. The nut 15 can prevent the rotor shaft 12 from falling off from the second bearing 13; the setting of this structure enables the rotor shaft 12 to rotate relative to the rotor shaft sleeve 11.
[0046] In the second aspect of the present invention, a working method of an emergency use device for an unmanned helicopter is provided, which is realized based on the emergency use device for an unmanned helicopter described in the first aspect of the present invention. The working method of the emergency use device for an unmanned helicopter includes the following situations.
[0047] Situation 1, when the unmanned helicopter is in a normal working state, a buckle 17 is sleeved on the first pin 7, a pull pin 18 is sleeved on the second bearing 13, and the unmanned helicopter travels with a parachute loaded.
[0048] Situation 2: When the unmanned helicopter is in an emergency state, the unmanned helicopter can trigger the extraction of the first pin 7 of the parachute opening device through an embedded automatic program or ground remote control. The parachute surface of the parachute opens or inflates while opening. At the same time, the second pin 10 opens, the end of the parachute rope that is bound opens, and the parachute rope is straightened, which can increase the flight resistance, enabling the unmanned helicopter to make a buffered landing and reducing the damage loss caused by the crash of the unmanned helicopter.
[0049] Situation 3: When the unmanned helicopter crashes into the sea, the first pin 7 is pulled out, but the second pin 10 is always sleeved on the second pin 10. The parachute inflation module of the unmanned helicopter can trigger the parachute gas generator to inflate through an embedded automatic program or ground remote control, enabling the unmanned helicopter to float on the sea surface without sinking to the bottom of the sea, facilitating search and salvage, and reducing the risk of loss of the unmanned helicopter.
[0050] Situation 4: When the unmanned helicopter crashes in the desert, plain or plateau, if there is no strong gust on the ground, no control is performed when the unmanned helicopter is retrieved; if the weather forecast indicates that there will be strong gusts, the unmanned helicopter triggers the extraction of the first pin 7 and the second pin 10 of the parachute release device through ground remote control, and the parachute is separated from the unmanned helicopter to prevent the unmanned helicopter from being blown and rolling on the ground when the parachute moves due to the wind, reducing secondary ground losses; if the unmanned helicopter crashes and the first pin 7 opens and the parachute surface is in an open state, due to the parachute surface and ropes, it hangs on a tree or a high-rise building, and no operation is performed before the unmanned helicopter is retrieved. When it is convenient to capture, the second pin 10 of the parachute release device is triggered to be pulled out through ground remote control, so that the unmanned helicopter crashes at a safe location or place.
[0051] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention. In addition, features defined as "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise stated, the meaning of "a plurality" is two or more. In the description of the present invention, the first feature being "above" or "below" the second feature may include the first and second features being in direct contact, or may also include the first and second features not being in direct contact but being in contact through additional features therebetween.
[0052] In the description of the present invention, the first feature being "above", "over" and "on" the second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature has a higher horizontal height than the second feature.
[0053] In the description of the present invention, it should be noted that, unless otherwise clearly specified and defined, the terms "mounted", "connected" and "coupled" shall be construed in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention may be understood according to specific circumstances.
[0054] In the description of this specification, the descriptions referring to the terms "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic descriptions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in a suitable manner in any one or more embodiments or examples.
[0055] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the claims and their equivalents.
[0056] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.
Claims
1. An emergency use device for an unmanned helicopter, characterized in that, It includes a rotor shaft (12), a parachute, and a rotor shaft sleeve (11); Inside the rotor shaft sleeve (11), a first bearing (5) and a second bearing (13) which are arranged vertically and coaxially are installed. A shaft pin (6) is connected in the inner ring of the first bearing (5), and the upper end of the rotor shaft (12) is inserted into the inner ring of the second bearing (13); Outside the rotor shaft sleeve (11), a first magnetic attraction device (3) and a second magnetic attraction device (4) are arranged, and a first bolt (7) and a second bolt (10) are installed inside. One end of the first bolt (7) is inserted into the first magnetic attraction device (3), and the other end passes through the shaft pin (6); One end of the second bolt (10) is inserted into the second magnetic attraction device (4), and the other end passes through the shaft pin (6); A latch (17) is sleeved on the first bolt (7), and the latch (17) is used to fix the parachute canopy (1); A pull pin (18) is sleeved on the second bolt (10), and the pull pin (18) is used to connect the parachute; A sleeve communication module (14) is installed on the rotor shaft sleeve (11), and the sleeve communication module (14) is electrically connected to the first magnetic attraction device (3) and the second magnetic attraction device (4).
2. The emergency use device for an unmanned helicopter according to claim 1, wherein, The first bolt (7) and the second bolt (10) are respectively arranged on the upper side and the lower side of the first bearing (5).
3. The emergency use device for an unmanned helicopter according to claim 1, characterized in that, Both the first bolt (7) and the second bolt (10) are perpendicular to the shaft pin (6).
4. An emergency use device for an unmanned helicopter according to claim 1, characterized in that, A relay (8) is arranged outside the rotor shaft sleeve (11), and the sleeve communication module (14) is electrically connected to both the first magnetic attraction device (3) and the second magnetic attraction device (4) through the relay (8).
5. An emergency use device for an unmanned helicopter according to claim 1, characterized in that, The upper end of the rotor shaft (12) is connected with a nut (15), and the nut (15) is above the second bearing (13).
6. An emergency use device for an unmanned helicopter according to claim 5, characterized in that, A stop washer (16) is arranged between the nut (15) and the second bearing (13).
7. An emergency use device for an unmanned helicopter according to claim 1, characterized in that, A parachute inflation module is arranged on the canopy (1), and the canopy (1) is connected to the pull pin through a parachute rope (2).
8. An emergency use device for an unmanned helicopter according to claim 7, characterized in that, The parachute inflation module includes a gas generator, a canopy communication module, and a water inductor. The canopy communication module is connected to both the gas generator and the water inductor at the same time; The gas output port of the gas generator is communicated with the inside of the canopy (1).
9. A working method of the emergency use device for the unmanned helicopter according to claim 1, characterized in that, It includes the following four situations: Situation 1: When the unmanned helicopter is in a normal working state, a latch (17) is sleeved on the first bolt (7), and a pull pin (18) is sleeved on the second bolt (10); The unmanned helicopter carries the parachute to perform tasks; Situation 2: When the unmanned helicopter is in an emergency state, the sleeve communication module (14) controls the first magnetic attraction device (3) to cut off the power supply, the first bolt (7) disengages from the first magnetic attraction device (3), the latch (17) disengages, and the canopy (1) opens; Situation 3: When the unmanned helicopter crashes into the sea, the sleeve communication module controls the first magnetic attraction device (3) to cut off the power supply, the first bolt (7) disengages from the first magnetic attraction device (3), the latch disengages, the canopy (1) opens, and gas is filled into the canopy (1); In Case 4, when the unmanned helicopter crashes on the ground and there is a gust of wind, the sleeve communication module (14) controls the first bolt (7) and the second bolt (10) to be pulled out. The first bolt (7) disengages from the latch (17), and the second bolt (10) disengages from the pull pin (18), separating the parachute from the unmanned helicopter.
10. The working method of an emergency use device for an unmanned helicopter according to claim 9, characterized in that, In Case 4, when the unmanned helicopter makes a vertical landing, the sleeve communication module (14) first controls the first bolt (7) to disengage from the latch (17), the parachute canopy (1) opens, the parachute canopy (1) is inflated with gas, and the parachute hangs high. After the rescue personnel reach the corresponding position, the sleeve communication module (14) controls the second bolt (10) to be pulled out, separating the parachute from the unmanned helicopter.