Aircraft emergency landing device and method for detection

Abstract

The invention belongs to the technical field of aircraft emergency processing, and relates to an aircraft emergency landing device and method for detection. Comprising a storage box; the sliding seat is connected into the storage box in a sliding mode, the sliding seat is connected with the storage box through a storage rope, and a pushing piece matched with the sliding seat in an extrusion mode is placed in the storage box; the first fixing ring is fixedly connected to the sliding seat, the first fixing ring is rotationally connected with rotating seats which are distributed at intervals, and telescopic pieces are fixedly connected to the back sides of the rotating seats which are distributed at intervals; the guide shell is fixedly connected to the sliding seat; and the winding assemblies are arranged on the adjacent telescopic pieces, all the winding assemblies are jointly provided with a parachute, and the guide shell is used for supporting the parachute. The mode that the parachute cords are actively thrown towards the periphery is adopted, the parachute cords can preferentially diffuse outwards, and therefore the problem that the parachute cords are wound due to uneven tension in the parachute forming process is effectively solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft emergency handling, and in particular to an emergency landing device and method for an aircraft for detection. Background Art

[0002] In natural disasters or emergencies, the use of detection aircraft (such as manned helicopters) becomes crucial. These aircraft can respond quickly and provide key information to help rescue workers make timely and effective decisions. However, in complex environments, aircraft may face various risks, including sudden failures or severe weather conditions. Therefore, emergency landing devices are particularly important to ensure the safety and reliability of aircraft.

[0003] In the event of a malfunction or other emergency, the emergency landing device can help the aircraft land safely in a predetermined area, reducing potential harm to ground personnel and equipment. Existing emergency landing devices mainly include parachute equipment and airbag cushioning equipment.

[0004] During the use of parachute equipment, the parachute will be released from the parachute bag and fully deployed with the help of airflow to slow down the descent speed of the aircraft. However, when the parachutes are released from the parachute bag, they will become entangled with each other, resulting in the parachute being unable to be fully or asymmetrically deployed (during the release process, the parachute will shake randomly due to the influence of external wind, which will cause the parachute rope to be unable to be stretched evenly), thereby failing to provide sufficient resistance to slow down the descent speed of the aircraft, causing the aircraft to be unable to land normally, and ultimately leading to the failure of the entire detection or rescue mission. Summary of the invention

[0005] The present invention adopts the following technical solutions to solve the above-mentioned shortcomings. An emergency landing device for a detection aircraft includes:

[0006] Storage boxes;

[0007] A sliding seat is slidably connected to the storage box, the sliding seat and the storage box are connected by a storage rope, and a pushing member that is pressed and matched with the sliding seat is placed in the storage box;

[0008] A first fixed ring, fixedly connected to the sliding seat, the first fixed ring is rotatably connected to the rotating seats arranged at intervals, and the back sides of the rotating seats arranged at intervals are all fixedly connected to telescopic members;

[0009] A guide shell, fixedly connected to the sliding seat;

[0010] The winding assemblies are the same in number as the telescopic members and are arranged at adjacent telescopic members, all the winding assemblies are commonly provided with a parachute located in the storage box, and the guide shell is used to support the parachute;

[0011] The first limiting component is arranged on the first fixing ring and is used for limiting the swing range of all the telescopic members.

[0012] As a further preferred solution, the winding assembly includes:

[0013] A protective shell, fixedly connected to the telescopic end of the adjacent telescopic member;

[0014] A rotating member, rotatably connected to the protective shell, a first elastic member fixed to the rotating member is fixed in the protective shell, a first connecting rope passing through the adjacent protective shell is wound around the rotating member, and the first connecting rope is fixed to the parachute;

[0015] The traction components are the same in number as the telescopic members and are arranged in adjacent telescopic members to limit the movement of adjacent protective shells.

[0016] As a further preferred solution, the winding assembly further includes:

[0017] A protective member, wound around the rotating member, wherein the first connecting rope is located inside the protective member, the protective member passes through the protective shell and is fixedly connected to the parachute, and the protective member and the first connecting rope are connected via a rope buckle;

[0018] A fixing member is fixedly connected to the rotating member, the fixing member is fixedly connected to both the first connecting rope and the protecting member, and the protecting member is fixedly connected with symmetrically distributed blocking members.

[0019] As a further preferred solution, two sides of the protective member are inclined, the cross section of the protective member is a trapezoidal structure, and the cross section of the fixing member is a trapezoid.

[0020] As a further preferred solution, the first limiting component includes:

[0021] The arc-shaped shells are distributed at intervals and are consistent with the number of the telescopic parts, and are all fixed to the first fixing ring. The arc-shaped shells are limitedly matched with the adjacent telescopic parts. The arc-shaped shells are slidably connected with arc-shaped columns fixed with the adjacent telescopic parts, and all the arc-shaped columns are slidably matched with the guide shell;

[0022] The first limiting pins are distributed at intervals and are consistent in number with the arc-shaped shells, and are respectively slidably connected to adjacent arc-shaped shells.

[0023] As a further preferred solution, the first limiting component further includes:

[0024] A counterweight block, fixedly connected to the upper sides of all the first limiting pins;

[0025] There are a plurality of second elastic members, all of which are fixedly connected to the first fixing ring, and the telescopic ends of the plurality of second elastic members are all fixedly connected to the counterweight block.

[0026] As a further preferred solution, the squeezing force applied by the arc-shaped shell to the adjacent arc-shaped column is greater than the thrust of the telescopic member on the adjacent protective shell, so as to prevent the protective shell from swinging freely in the storage box.

[0027] As a further preferred solution, the traction assembly includes:

[0028] Rectangular plates are distributed at intervals and are consistent with the number of the telescopic members, and are respectively fixed to the adjacent rotating seats, and the portion of the rectangular plate away from the adjacent rotating seat is located in the adjacent telescopic member, and the rectangular plate is provided with a corrugated groove;

[0029] A second connecting rope is located in the corrugated groove of the rectangular plate, one end of the second connecting rope is fixedly connected to the sliding seat, the other end of the second connecting rope is fixedly connected to the adjacent protective shell, and a shielding member for shielding the adjacent second connecting rope is fixedly connected to the rectangular plate;

[0030] The second limiting component is arranged on the storage box and is used for limiting the moving position of the sliding seat.

[0031] As a further preferred solution, the second limiting component includes:

[0032] A second fixing ring, fixedly connected to the storage box;

[0033] The second limit pins are distributed at intervals and are all slidably connected to the storage box and the second fixed ring. A spring is fixed between the second limit pin and the second fixed ring. The second limit pin is limitedly matched with the sliding seat.

[0034] A method for using an emergency landing device for a detection aircraft comprises the following steps:

[0035] S1: First, the storage box is installed in the aircraft, and the aircraft carries the storage box to perform rescue missions. When the aircraft encounters a malfunction or other emergency situation, which causes the aircraft power to fail, the aircraft controls the pusher to expand and press the sliding seat upward;

[0036] S2: The storage rope is stretched during the upward movement of the sliding seat, and the sliding seat drives all the protective shells to move, so that when the protective shells pass through the adjacent second limiting pins, the protective shells are squeezed by the adjacent second limiting pins, so that the adjacent telescopic parts retract;

[0037] S3: When the sliding seat drives the attached parts thereon to move until all the protective shells are exposed to the outside world, all the telescopic parts throw out all the protective shells, so that the parachute is exposed to the outside world, and the parachute opens to all sides after contacting with the outside airflow;

[0038] S4: during the process of the protective shell being thrown out, the adjacent second connecting rope is pulled out from the adjacent rectangular plate, the second connecting rope is released, and driven by the airflow, the parachute pulls the first connecting rope, the adjacent protective element and the two adjacent blocking elements out of the adjacent protective shell;

[0039] S5: After the first connecting rope, the adjacent protective member and the two adjacent blocking members are all pulled out from the adjacent protective shells, the release of the “parachute rope” is completed;

[0040] S6: After the “parachute rope” is released and the parachute is also released, pull the collection rope;

[0041] S7: After all the storage ropes are released, all the rotating seats drive all the telescopic members and all the protective shells to swing inward, so that all the second elastic members are inserted into all the arc columns;

[0042] S8: When the aircraft lands smoothly, you can tidy up the parachute.

[0043] The beneficial effects of the present invention are as follows: the present invention adopts a method of actively throwing the parachute ropes to all sides, so that the parachute ropes can be spread outwards first, thereby effectively preventing the parachute ropes from being entangled due to uneven tension during the parachute forming process;

[0044] The segmented storage method is adopted, so that the parachute rope is divided into two parts during the storage process, and the parachute ropes will not be entangled with each other during the storage process. When the parachute rope is released, the parachute rope is released indirectly, so that the parachute rope is released according to a regular pattern during the release process, thereby preventing the parachute ropes from being entangled with each other;

[0045] When the parachute ropes are released or even the parachute is formed, the swing of all the telescopic parts can buffer the instantaneous tension applied to the storage ropes of the parachute and reduce the tension on the storage ropes when they are tightened, thereby protecting the storage ropes. By limiting the swing position of the telescopic parts, the parachute ropes around the parachute remain stable during its descent, avoiding the parachute ropes around the parachute from shaking randomly due to the influence of external wind, which can prevent the parachute from being able to drive the aircraft to land safely in a stable state. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention;

[0047] Figure 2 It is a three-dimensional structural cross-sectional view of the storage box of the present invention;

[0048] Figure 3 It is a sectional view of the three-dimensional structure of the parachute of the present invention;

[0049] Figure 4 It is a three-dimensional structural cross-sectional view of the sliding seat of the present invention;

[0050] Figure 5 It is a three-dimensional structural cross-sectional view of the first fixing ring of the present invention;

[0051] Figure 6 It is a three-dimensional structural cross-sectional view of the arc column of the present invention;

[0052] Figure 7 It is a three-dimensional structural cross-sectional view of the telescopic member of the present invention;

[0053] Figure 8 It is a schematic diagram of the three-dimensional structure of the second connecting rope and the shielding member of the present invention;

[0054] Fig. 9 It is an exploded view of the three-dimensional structure of the rectangular plate, the second connecting rope and the shielding member of the present invention;

[0055] Fig.10 It is a three-dimensional structural cross-sectional view of the rotating part of the present invention;

[0056] Fig.11 It is an exploded view of the three-dimensional structure of the first connecting rope and the protective member of the present invention.

[0057] The names and serial numbers of the parts in the figure are: 101-storage box, 102-sliding seat, 103-pushing member, 104-first fixed ring, 105-rotating seat, 106-telescopic member, 107-protective shell, 1071-rotating member, 1072-first elastic member, 1073-first connecting rope, 1074-protective member, 1075-fixing member, 1076-blocking member, 108-parachute, 201-guide shell, 301-arc shell, 302-arc column, 303-first limit pin, 304-counterweight, 305-second elastic member, 401-rectangular plate, 402-second connecting rope, 403-shielding member, 501-second fixed ring, 502-second limit pin. DETAILED DESCRIPTION

[0058] The present invention will be further described below in conjunction with specific embodiments. The illustrative embodiments and descriptions of the present invention are used to explain the present invention but are not intended to limit the present invention.

[0059] In order to solve the problem that the parachute cannot be opened normally due to the entanglement of parachute ropes during the use of existing parachute equipment, thereby causing the failure of detection or rescue missions, the present invention adopts a method of actively throwing the parachute ropes to all sides, so that the parachute ropes can be spread outwards first, thereby effectively preventing the parachute ropes from being entangled due to uneven tension during the parachute molding process, and changing the storage method of the parachute ropes to ensure that they will not be entangled during the winding process.

[0060] See also Figure 1-Figure 6 , an emergency landing device for a detection aircraft, comprising: a storage box 101; a sliding seat 102, slidably connected to the storage box 101, the sliding seat 102 and the storage box 101 are connected by a storage rope, and a pushing member 103 that is squeezed and matched with the sliding seat 102 is placed in the storage box 101; a first fixed ring 104, fixedly connected to the sliding seat 102, the first fixed ring 104 is rotatably connected to the rotating seats 105 distributed at intervals, and the back sides of the rotating seats 105 distributed at intervals are all fixedly connected with telescopic members 106; a guide shell 201, fixedly connected to the sliding seat 102; a winding assembly, the number of which is the same as that of the telescopic members 106, and is arranged on adjacent telescopic members 106, all the winding assemblies are commonly provided with a parachute 108 located in the storage box 101, and the guide shell 201 is used to support the parachute 108.

[0061] In the above scheme, a protective film is fixed to the upper side of the storage box 101, and the protective film is used to cover the upper side of the storage box 101. The sliding seat 102 is composed of a circular plate and fixed blocks evenly distributed in the circumference, and the upper side of the fixed block is provided with an inclined surface. The storage box 101 is provided with circumferentially evenly distributed sliding grooves, and the number of sliding grooves in the storage box 101 is consistent with the number of fixed blocks on the sliding seat 102. The fixed blocks on the sliding seat 102 are limited and slidably matched with adjacent sliding grooves in the storage box 101. Through the above description, the sliding seat 102 can only move vertically and cannot rotate when moving along the storage box 101. The pushing member 103 is a safety airbag in a car. When the pushing member 103 is triggered, the sliding seat 102 moves upward along the storage box 101. The rotating seats 105 are evenly distributed, and the number of rotating seats 105 is consistent with the number of parachute ropes in the prior art. The spaced-apart rotating seats 105 are used to keep the same interval between each parachute rope. The telescopic member 106 is a multi-stage elastic rod, and when the telescopic member 106 is located in the storage box 101, all the telescopic parts of the telescopic member 106 are in a retracted state. When the telescopic member 106 leaves the storage box 101, the telescopic part of the telescopic member 106 can be extended outward. Within the extendable range of the present invention, a truncated cone groove connected to the guide shell 201 can be provided on the lower side of the sliding seat 102, so that after the sliding seat 102 slides out of the storage box 101, the sliding seat 102 is exposed to the outside world, and the outside airflow can enter the guide shell 201 through the truncated cone groove on the lower side of the sliding seat 102. The guide shell 201 guides the airflow to the parachute 108 in a stable state, and the surrounding sides and the middle part of the parachute 108 are simultaneously inhaled, thereby shortening the molding time of the parachute 108.

[0062] See also Figure 3-Figure 11 The winding assembly includes: a protective shell 107, fixedly connected to the telescopic end of the adjacent telescopic member 106; a rotating member 1071, rotatably connected to the protective shell 107, a first elastic member 1072 fixedly connected to the rotating member 1071 is fixedly connected to the protective shell 107, a first connecting rope 1073 passing through the adjacent protective shell 107 is wound around the rotating member 1071, and the first connecting rope 1073 is fixedly connected to the parachute 108; a traction assembly, the number of which is the same as that of the telescopic member 106, and is arranged in the adjacent telescopic member 106, for limiting the movement of the adjacent protective shell 107, a protective member 1074, wound around the rotating member The movable part 1071 and the first connecting rope 1073 are located in the protective part 1074, the protective part 1074 passes through the protective shell 107 and is fixedly connected to the parachute 108, the protective part 1074 and the first connecting rope 1073 are connected by a rope buckle, the fixed part 1075 is fixedly connected to the rotating part 1071, the fixed part 1075 is fixedly connected to the first connecting rope 1073 and the protective part 1074, the protective part 1074 is fixedly connected with symmetrically distributed blocking parts 1076, the two sides of the protective part 1074 are inclined, the cross section of the protective part 1074 is a trapezoidal structure, and the cross section of the fixed part 1075 is a trapezoid.

[0063] In the above scheme, the first elastic member 1072 is a clockwork spring, the first connecting rope 1073 is an existing parachute rope, and when the parachute 108 is located in the storage box 101, the first connecting rope 1073 is in a reeled state, which is used to reduce the space occupied by the first connecting rope 1073 when it is reeled in. The first connecting rope 1073 is located in an adjacent protective member 1074, and the protective member 1074 is a flexible steel sheet. The cross-section of the fixing member 1075 is trapezoidal, so that the cross-section of the protective member 1074 when wrapped around the adjacent fixing member 1075 can be inclined on both sides, thereby realizing the protection of the adjacent first connecting rope 1073, so that the first connecting rope 1073 will not be entangled with other parts of the first connecting rope 1073 when released, and the blocking member 1076 is made of a flexible deformable material, which is used to block the edge of the adjacent protective member 1074.

[0064] Please refer to 4- Figure 6 The first limiting assembly includes: arc shells 301, which are distributed at intervals and are consistent with the number of telescopic members 106, and are all fixed to the first fixing ring 104. The arc shells 301 are limited and matched with adjacent telescopic members 106. The arc shells 301 are slidably connected with arc columns 302 fixed to adjacent telescopic members 106, and all arc columns 302 are slidably matched with the guide shell 201; the first limiting pins 303 are distributed at intervals and are consistent with the number of arc shells 301, and are respectively slidably connected to adjacent The arc-shaped shell 301, the first limiting assembly also includes: a counterweight block 304, which is fixedly connected to the upper side of all the first limiting pins 303; there are several second elastic members 305, and they are all fixedly connected to the first fixing ring 104, and the telescopic ends of the several second elastic members 305 are all fixedly connected to the counterweight block 304. The squeezing force applied by the arc-shaped shell 301 to the adjacent arc-shaped column 302 is greater than the thrust of the telescopic member 106 on the adjacent protective shell 107, so as to prevent the protective shell 107 from swinging freely in the storage box 101.

[0065] In the above scheme, the arc shells 301 are distributed at equal intervals, and the arc shells 301 are located above the adjacent telescopic parts 106. A limiting groove is set in the middle of the arc column 302. The first limiting pin 303 is limitedly matched with the limiting groove on the adjacent arc column 302. After the first limiting pin 303 is inserted into the limiting groove on the adjacent arc column 302, the upper side of the telescopic part 106 is already in contact with the lower side of the adjacent arc shell 301. When the telescopic part 106 is not in contact with the lower side of the adjacent arc shell 301, the first limiting pin 303 and the outer side of the adjacent arc column 302 are in a hard friction state. The second elastic part 305 is a spring rod, and is initially in a pressure state.

[0066] Please refer to Figure 6-Figure 9The traction assembly includes: rectangular plates 401, which are distributed at intervals and are consistent with the number of telescopic members 106, and are respectively fixed to adjacent rotating seats 105. The part of the rectangular plate 401 away from the adjacent rotating seat 105 is located in the adjacent telescopic member 106, and the rectangular plate 401 is provided with a corrugated groove; a second connecting rope 402 is located in the corrugated groove of the rectangular plate 401, one end of the second connecting rope 402 is fixed to the sliding seat 102, and the other end of the second connecting rope 402 is fixed to the adjacent protective shell 107, and the rectangular plate 401 is fixed with a shielding member 403 for shielding the adjacent second connecting rope 402; a second limiting assembly is arranged on the storage box 101, and is used to limit the moving position of the sliding seat 102.

[0067] In the above scheme, the rectangular plates 401 are distributed at equal intervals, and each rectangular plate 401 is respectively fixed to the middle part of the adjacent rotating seat 105. The corrugated groove in the rectangular plate 401 is used to increase the storage length of the second connecting rope 402. The second connecting rope 402 is an umbrella rope in the prior art. The vertical planes at both ends of the second connecting rope 402 are different from the vertical plane in the middle. The shielding member 403 is made of silicone. The shielding member 403 is used to prevent the second connecting rope 402 from being easily pulled out when it is located in the corrugated groove of the rectangular plate 401, thereby ensuring the storage state of the second connecting rope 402.

[0068] Please refer to Figure 2 and Figure 3 The second limiting assembly includes: a second fixing ring 501, fixedly connected to the storage box 101; second limiting pins 502, which are distributed at intervals and are slidably connected to the storage box 101 and the second fixing ring 501, a spring is fixedly connected between the second limiting pin 502 and the second fixing ring 501, and the second limiting pin 502 cooperates with the sliding seat 102 for limiting.

[0069] In the above scheme, the second fixing ring 501 is located on the upper side of the storage box 101, the second limit pins 502 are distributed at equal intervals, and an inclined surface is provided on the lower side of the second limit pin 502. The inclined surface of the second limit pin 502 is squeezed and matched with the inclined surface of the adjacent fixed block on the sliding seat 102. When the pushing member 103 expands, the height to which the sliding seat 102 moves cannot make the sliding seat 102 contact with all the second limit pins 502, and the elastic coefficient of the adjacent spring of the second limit pin 502 is greater than the elastic coefficient of the adjacent telescopic member 106.

[0070] Working principle: Before the aircraft takes off, the operator first installs the present invention on the position required for work on the aircraft, and then connects the pusher 103 to the aircraft to complete the preparatory action before takeoff.

[0071] After completing the preparatory actions before the aircraft takes off, the operator controls the aircraft to perform the mission. When the aircraft encounters a malfunction or other emergency situation, which causes the power of the aircraft to fail, the operator activates the push member 103 through the aircraft, and the push member 103 expands to squeeze the sliding seat 102 and its attached parts upward, so that the sliding seat 102 drives all the telescopic members 106 and all the protective shells 107 to move upward along the storage box 101 (the storage rope is stretched during the upward movement of the sliding seat 102).

[0072] During the upward movement of the sliding seat 102 and the guide shell 201, the guide shell 201 drives the upper part of the parachute 108 to contact the protective film on the storage box 101. Under the thrust provided by the pushing member 103, the guide shell 201 punctures the protective film on the storage box 101 through the parachute 108, so that the sliding seat 102 continues to drive the attached parts thereon to move upward.

[0073] During the upward movement of the sliding seat 102, when all the protective shells 107 pass through the adjacent second limit pins 502 respectively, all the protective shells 107 drive the adjacent telescopic parts 106 to retract downward. When the sliding seat 102 drives all the protective shells 107 to move until they are no longer in contact with the adjacent second limit pins 502, all the protective shells 107 are exposed to the outside world, and then the telescopic parts of all the telescopic parts 106 are fully extended, and all the protective shells 107 are thrown outward. Then all the protective shells 107 drive the lower side of the parachute 108 to expand and expose the parachute 108 to the outside world. The parachute 108 then contacts the external airflow and opens to the surroundings.

[0074] After the parachute 108 opens to all sides, taking the action of the telescopic part of the right telescopic member 106 extending out as an example, the protective shell 107 moves to the upper right side, causing the telescopic part of the adjacent telescopic member 106 to move to the upper right side. During the movement of the protective shell 107, the adjacent second connecting rope 402 is pulled out from the adjacent rectangular plate 401, allowing the second connecting rope 402 to pass through the obstruction of the adjacent shielding member 403, thereby realizing the release of the second connecting rope 402.

[0075] When the telescopic part of the telescopic member 106 is extended, the sliding seat 102 moves to its upper side and contacts the lower sides of all the second limit pins 502. At this time, the parachute 108 continues to open, and the thrust of the pushing member 103 has disappeared. The parachute 108 pulls the sliding seat 102 upward under the drive of the airflow. However, at this time, the pulling force applied by the parachute 108 does not exceed the extrusion force provided by the springs of all the second limit pins 502, so the sliding seat 102 is blocked by all the second limit pins 502.

[0076] After the supporting force given to the parachute 108 by the airflow is greater than the supporting force provided by all the first elastic members 1072 to the adjacent rotating members 1071, the lower side of the parachute 108 drives all the first connecting ropes 1073 and the upper sides of the protective members 1074 to move upward, and the first connecting ropes 1073, the adjacent protective members 1074 and the two adjacent blocking members 1076 are pulled out from the adjacent protective shells 107 to release the rear section of the “parachute rope”. The protection of the connecting rope 1073 prevents the first connecting rope 1073 from being entangled with each other during the pulling-out process, and reduces the interference force of the airflow on the first connecting rope 1073 when it comes into contact with the airflow during the releasing process, so that the first connecting rope 1073 can be released in a stable state. Through the above operation, the protective shell 107 containing the first connecting rope 1073 is first thrown around, so that the first connecting rope 1073 will not be entangled with the surrounding first connecting ropes 1073 during the subsequent release process.

[0077] After the first connecting rope 1073, the adjacent protective member 1074 and the two adjacent blocking members 1076 are pulled out, the parachute 108 is formed. At this time, the supporting force given to the parachute 108 by the airflow is greater than the squeezing force applied to it by the springs on all the second limit pins 502, so that the sliding seat 102 is sufficient to squeeze all the second limit pins 502 to move backwards. The backward movement of all the second limit pins 502 releases the limitation on the sliding seat 102, so that the sliding seat 102 drives the attached parts thereon to move upward. During the movement of the sliding seat 102, the storage rope continues to be pulled out until the storage rope is pulled to the limit position.

[0078] When the storage rope on the lower side of the sliding seat 102 is pulled to the extreme position, the parachute 108, all the first connecting ropes 1073, all the protective shells 107, all the telescopic members 106, all the rotating seats 105 and the sliding seat 102 and their attached parts will generate an instantaneous pulling force with the storage rope, so that the storage rope is instantly tightened. In order to reduce the instantaneous tightening force of the storage rope, thereby ensuring the firmness of the storage rope during use, the following process is now described: When the storage rope is tightened, the parachute 108 pulls all the protective shells 107, all the telescopic members 106 and all the rotating seats 105 through all the first connecting ropes 1073. Some rotating seats 105 enable all rotating seats 105 to drive all telescopic parts 106 and all protective shells 107 to swing inward (at this time, the swinging force of the telescopic parts 106 is greater than the friction force applied by the adjacent arc shells 301 to the adjacent arc columns 302). During the swinging of the telescopic parts 106, the adjacent arc columns 302 are driven to slide along the adjacent arc shells 301. At this time, through the swinging of all rotating seats 105, the instantaneous tension applied to the storage rope of the parachute 108 is buffered, reducing the tension applied to the storage rope when it is tightened, and relying on the friction force mentioned above, the effect of protecting the storage rope is achieved.

[0079] When the telescopic member 106 drives the adjacent arc column 302 to slide along the adjacent arc shell 301 until the telescopic member 106 contacts the arc shell 301, the telescopic member 106 stops swinging. At this time, the first limit pin 303 enters the adjacent arc column 302 under the action of the thrust provided by the second elastic member 305, and limits the arc column 302 to prevent the arc column 302 from being affected by the wind during the falling process of the parachute 108, thereby driving the adjacent telescopic member 106 to swing randomly, thereby causing the parachute 108 to fall unstably.

[0080] After the aircraft lands smoothly, the operator inspects or replaces the present invention.

[0081] In addition, the present invention also provides a method for using the emergency landing device for a detection aircraft, comprising the following steps:

[0082] S1: First, the storage box 101 is installed in the aircraft. The aircraft carries the storage box 101 to perform a rescue mission. When the aircraft encounters a malfunction or other emergency situation, which causes the aircraft power to fail, the aircraft controls the pusher 103 to expand and press the sliding seat 102 upward;

[0083] S2: The storage rope is stretched during the upward movement of the sliding seat 102, and the sliding seat 102 drives all the protective shells 107 to move, so that when the protective shells 107 pass through the adjacent second limiting pins 502, the protective shells 107 are squeezed by the adjacent second limiting pins 502, so that the adjacent telescopic members 106 retract;

[0084] S3: When the sliding seat 102 drives the attached parts thereon to move until all the protective shells 107 are exposed to the outside, all the telescopic parts 106 throw out all the protective shells 107, so that the parachute 108 is exposed to the outside, and the parachute 108 opens to the surroundings after contacting with the outside airflow;

[0085] S4: During the process of the protective shell 107 being thrown out, the adjacent second connecting rope 402 is pulled out from the adjacent rectangular plate 401, and the second connecting rope 402 is released. Driven by the airflow, the parachute 108 pulls the first connecting rope 1073, the adjacent protective member 1074 and the two adjacent blocking members 1076 out of the adjacent protective shell 107;

[0086] S5: After the first connecting rope 1073, the adjacent protective member 1074 and the two adjacent blocking members 1076 are all pulled out from the adjacent protective shells 107, the release of the “parachute rope” is completed;

[0087] S6: After the “parachute rope” is released and the parachute 108 is also released, pull the storage rope;

[0088] S7: After all the storage ropes are released, all the rotating seats 105 drive all the telescopic members 106 and all the protective shells 107 to swing inward, so that all the second elastic members 305 are inserted into all the arc columns 302;

[0089] S8: After the aircraft lands smoothly, the parachute 108 can be arranged.

[0090] Those skilled in the art will readily appreciate other embodiments of the present disclosure after considering the specification and practicing the invention disclosed herein. This application is intended to cover any modifications, uses or adaptations of the present disclosure, which follow the general principles of the present disclosure and include common knowledge or customary technical means in the art that are not disclosed in the present disclosure.

Claims

1. An emergency landing device for a detection aircraft, characterized in that: include: Storage box (101); A sliding seat (102) is slidably connected to the storage box (101); the sliding seat (102) and the storage box (101) are connected via a storage rope; a pushing member (103) which is pressed and matched with the sliding seat (102) is placed in the storage box (101); A first fixed ring (104) is fixedly connected to the sliding seat (102), the first fixed ring (104) is rotatably connected to the rotating seats (105) arranged at intervals, and the back sides of the rotating seats (105) arranged at intervals are all fixedly connected to telescopic parts (106); A guide shell (201) fixedly connected to the sliding seat (102); winding assemblies, the number of which is the same as that of the telescopic members (106), and which are arranged on adjacent telescopic members (106), all of the winding assemblies being provided with a parachute (108) located in the storage box (101), and the guide shell (201) being used to support the parachute (108); A first limiting component is arranged on the first fixing ring (104) and is used to limit the swing range of all the telescopic members (106).

2. The emergency landing device for a detection aircraft according to claim 1, characterized in that: The winding assembly comprises: A protective shell (107) is fixedly connected to the telescopic end of the adjacent telescopic member (106); A rotating member (1071) is rotatably connected to the protective shell (107), a first elastic member (1072) fixedly connected to the rotating member (1071) is fixedly connected to the protective shell (107), a first connecting rope (1073) passing through the adjacent protective shell (107) is wound around the rotating member (1071), and the first connecting rope (1073) is fixedly connected to the parachute (108); The traction components are the same in number as the telescopic members (106) and are arranged in adjacent telescopic members (106) to limit the movement of adjacent protective shells (107).

3. The emergency landing device for a detection aircraft according to claim 2, characterized in that: The winding assembly also includes: a protective member (1074) wound around the rotating member (1071), the first connecting rope (1073) being located inside the protective member (1074), the protective member (1074) passing through the protective shell (107) and being fixedly connected to the parachute (108), the protective member (1074) and the first connecting rope (1073) being connected via a rope buckle; The fixing member (1075) is fixedly connected to the rotating member (1071). The fixing member (1075) is fixedly connected to both the first connecting rope (1073) and the protective member (1074). The protective member (1074) is fixedly connected with symmetrically distributed blocking members (1076).

4. The emergency landing device for a detection aircraft according to claim 3, characterized in that: Both sides of the protection member (1074) are inclined, the cross section of the protection member (1074) is a trapezoidal structure, and the cross section of the fixing member (1075) is a trapezoid.

5. The emergency landing device for a detection aircraft according to claim 4, characterized in that: The first limiting component comprises: The arc-shaped shells (301) are distributed at intervals and are consistent with the number of the telescopic members (106), and are all fixed to the first fixing ring (104). The arc-shaped shells (301) are limitedly matched with the adjacent telescopic members (106). The arc-shaped shells (301) are slidably connected to the arc-shaped columns (302) fixed to the adjacent telescopic members (106), and all the arc-shaped columns (302) are slidably matched with the guide shell (201); The first limiting pins (303) are distributed at intervals and are consistent in number with the arc-shaped shells (301), and are respectively slidably connected to adjacent arc-shaped shells (301).

6. The emergency landing device for a detection aircraft according to claim 5, characterized in that: The first limiting component also includes: A counterweight block (304) is fixedly connected to the upper side of all the first limiting pins (303); There are a plurality of second elastic members (305), and all of them are fixedly connected to the first fixing ring (104); the telescopic ends of the plurality of second elastic members (305) are all fixedly connected to the counterweight block (304).

7. The emergency landing device for a detection aircraft according to claim 6, characterized in that: The squeezing force applied by the arc-shaped shell (301) to the adjacent arc-shaped column (302) is greater than the thrust of the telescopic member (106) on the adjacent protective shell (107), so as to prevent the protective shell (107) from swinging freely in the storage box (101).

8. The emergency landing device for a detection aircraft according to claim 7, characterized in that: The traction assembly comprises: The rectangular plates (401) are distributed at intervals and are consistent in number with the telescopic members (106), and are respectively fixed to the adjacent rotating seats (105); the portion of the rectangular plate (401) away from the adjacent rotating seat (105) is located in the adjacent telescopic member (106); and the rectangular plate (401) is provided with a corrugated groove; A second connecting rope (402) is located in the corrugated groove of the rectangular plate (401), one end of the second connecting rope (402) is fixedly connected to the sliding seat (102), and the other end of the second connecting rope (402) is fixedly connected to the adjacent protective shell (107); and a shielding member (403) for shielding the adjacent second connecting rope (402) is fixedly connected to the rectangular plate (401); A second limiting component is arranged on the storage box (101) and is used to limit the moving position of the sliding seat (102).

9. The emergency landing device for a detection aircraft according to claim 8, characterized in that: The second limiting component comprises: A second fixing ring (501) fixedly connected to the storage box (101); The second limiting pins (502) are distributed at intervals and are all slidably connected to the storage box (101) and the second fixing ring (501). A spring is fixed between the second limiting pin (502) and the second fixing ring (501). The second limiting pin (502) is limitedly matched with the sliding seat (102).

10. A method for using an emergency landing device for a detection aircraft, which is accomplished by using the emergency landing device for a detection aircraft according to claim 9, characterized in that: The method for emergency landing of a detection aircraft comprises the following steps: S1: firstly, the storage box (101) is installed in the aircraft, and the aircraft carries the storage box (101) to implement a rescue mission. When the aircraft encounters a malfunction or other emergency situation, resulting in a power failure of the aircraft, the aircraft controls the pusher (103) to expand and press the sliding seat (102) upwards; S2: the storage rope is stretched during the upward movement of the sliding seat (102), and the sliding seat (102) drives all the protective shells (107) to move, so that when the protective shell (107) passes through the adjacent second limiting pin (502), the protective shell (107) is squeezed by the adjacent second limiting pin (502), thereby causing the adjacent telescopic member (106) to retract; S3: When the sliding seat (102) drives the attached parts thereon to move until all the protective shells (107) are exposed to the outside, all the telescopic parts (106) throw out all the protective shells (107), so that the parachute (108) is exposed to the outside, and the parachute (108) opens to the surroundings after contacting with the external airflow; S4: when the protective shell (107) is thrown out, the adjacent second connecting rope (402) is pulled out from the adjacent rectangular plate (401), the second connecting rope (402) is released, and driven by the airflow, the parachute (108) pulls the first connecting rope (1073), the adjacent protective member (1074) and the two adjacent blocking members (1076) out of the adjacent protective shell (107); S5: After the first connecting rope (1073), the adjacent protective member (1074) and the two adjacent blocking members (1076) are all pulled out from the adjacent protective shells (107), the release of the "parachute rope" is completed; S6: After the "parachute rope" is released and the parachute (108) is also released, the collection rope is pulled; S7: After all the storage ropes are released, all the rotating seats (105) drive all the telescopic members (106) and all the protective shells (107) to swing inward, so that all the second elastic members (305) are inserted into all the arc-shaped columns (302); S8: After the aircraft lands smoothly, the parachute (108) can be arranged.

Images