CN111377048A - Escape canopy structure and canopy separation bolt throwing method - Google Patents
Escape canopy structure and canopy separation bolt throwing method Download PDFInfo
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- CN111377048A CN111377048A CN201811632047.4A CN201811632047A CN111377048A CN 111377048 A CN111377048 A CN 111377048A CN 201811632047 A CN201811632047 A CN 201811632047A CN 111377048 A CN111377048 A CN 111377048A
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- bolt
- rear hinge
- canopy
- separation
- guide groove
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/32—Severable or jettisonable parts of fuselage facilitating emergency escape
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Emergency Lowering Means (AREA)
Abstract
The invention belongs to the technical field of airplane protection and lifesaving, and provides an escape canopy structure and a canopy separation bolt throwing method, which comprises a canopy frame integrated with an airplane body, and a canopy hermetically connected to the canopy frame, wherein the canopy is movably connected with the canopy frame through a rear hinge mechanism; and a throwing rocket for throwing the hatch cover separated from the hatch cover frame is fixedly arranged on the inner side surface of the hatch cover far away from the rear hinge mechanism. The invention can push the cabin cover to move upwards by means of the impact force generated after the separation bolt assembly explodes, is convenient for the rotation of the cabin cover and does not interfere with the airplane body; the cabin cover can be thrown more timely and quickly, and safety guarantee is provided for pilots in the escape process.
Description
Technical Field
The invention relates to the technical field of aviation protection and lifesaving, in particular to an escape canopy structure and a canopy separation bolt throwing method.
Background
The canopy and the fuselage of present combat aircraft all separate the setting, take place emergency under, throw the canopy and put, and then form escape passage, supply the pilot to flee and use, but along with stealthy combat aircraft's use, adopt canopy and fuselage disconnect-type setting, stealthy effect is relatively poor, can not the effectual stealthy performance and the biography power of structure of guaranteeing the combat aircraft. In order to achieve the purpose, the design that the canopy and the machine body are connected through the separation bolt assembly is adopted, the canopy and the machine body can be connected in a sealing mode, meanwhile, the separation bolt assembly can achieve automatic separation, in the practical process, the canopy can be smoothly thrown and put, and meanwhile, the canopy and the machine body cannot interfere with each other, and therefore the problem is mainly solved.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide an escape canopy structure and a canopy separation bolt throwing method, which are convenient to throw in use, effectively improve the force transmission of a combat aircraft structure and reduce the escape risk.
In order to achieve the purpose, the invention adopts the following technical scheme that the escape hatch cover structure is characterized by comprising a hatch cover frame integrated with a machine body, and a hatch cover hermetically connected to the hatch cover frame, wherein the hatch cover is movably connected with the hatch cover frame through a rear hinge mechanism; a throwing rocket for throwing the hatch cover separated from the hatch cover frame is fixedly arranged on the inner side surface of the hatch cover far away from the rear hinge mechanism;
when the airplane meets an emergency, the separation bolt assembly is separated, the hatch cover is separated from the end part of the hatch cover frame connected through the separation bolt assembly, the rocket is thrown to push the hatch cover and the rear hinge mechanism to rotate to a certain angle around the end part of the rear hinge mechanism, the rear hinge mechanism is cut off, and the hatch cover is thrown away.
And a sealing ring is arranged at the joint of the hatch cover and the hatch cover frame.
The separation bolt component comprises a separation bolt support fixedly connected with the inner side surface of the cabin cover frame, a pulling-in bolt fixedly connected with the inner side surface of the hatch cover, and the pulling-in bolt is vertical to the inner side surface of the hatch cover and extends downwards, a medicine cavity for placing gunpowder is arranged in the separation bolt support, the medicine cavity is sealed by a separation piston inserted in the medicine cavity, the separation piston is in sealing contact with the cavity wall of the medicine cavity, a separation bolt is fixedly connected on the surface of the end part of the separation piston, which is opposite to the separation bolt support, the separation bolt is fixedly connected with a pull-in bolt through a bidirectional nut, and when gunpowder in the powder cavity explodes, the separating piston impacts the connecting part of the separating bolt and the separating bolt support under the explosive impact force of the gunpowder, so that the separating bolt is sheared from the separating bolt support, and the separating bolt and the drawing bolt are separated from the separating bolt support.
The rear hinge mechanism comprises a rear hinge support arm fixedly connected with the cabin cover and a rear hinge support fixedly connected with the cabin cover frame, two parallel support plates are arranged in the middle of the rear hinge support, symmetrical guide grooves are formed in the two parallel support plates, the end part of the rear hinge support arm extends to the position between the parallel support plates and is connected with a rotating shaft penetrating through the symmetrical guide grooves, and the rear hinge support arm rotates when moving to the upper end of the guide grooves and is separated from the rear hinge support.
The rear hinged support arm comprises a base fixedly connected with the canopy, a support arm fixedly connected to the base, and a stop block connected to the support arm and positioned between the support plates which are parallel to each other;
the end part of the support arm connected with the stop block is provided with a first buckling block integrated with the support arm, and the first buckling block is provided with a first semicircular groove;
the stop block comprises a second buckling block which is matched and buckled with the first buckling block, the first buckling block and the second buckling block are connected through a rivet, a second semicircular groove is formed in the second buckling block, the second semicircular groove is buckled with the first semicircular groove to form a shaft hole for a rotating shaft to pass through, and when the rear hinge support arm rotates around the rotating shaft, the top of the surface, opposite to the rear hinge support, of the second buckling block is abutted against the rear hinge support;
the end part of the second buckling block is provided with a slot into which the first buckling block is inserted, and the first buckling block is inserted into the slot and is fixedly connected with the second buckling block through a rivet.
The guide groove is divided into three sections with different aperture sizes from top to bottom, a lower guide groove positioned at the lower part of the guide groove is in clearance fit with the rotating shaft, a middle guide groove positioned at the middle part of the guide groove is in transition fit with the rotating shaft, an upper guide groove positioned at the upper part of the guide groove is in interference fit with the rotating shaft, and the lower guide groove, the middle guide groove and the upper guide groove are in smooth transition;
the ratio of the pitch of the middle guide groove to the pitch of the upper guide groove to the pitch of the lower guide groove is 1:1: 8.
The rotating shaft comprises a shaft body with a nut, the shaft body sequentially penetrates through the guide groove and the rear hinge support arm and is fixedly connected with the nut at the end part of the rear hinge support, and a limiting pin is inserted at the outer end of the shaft body connecting nut.
The throwing rocket is fixedly connected with the cabin cover, and a fire jet of the throwing rocket is vertical to the cabin cover.
A method for throwing separating bolts of a canopy is carried out according to the following steps:
the method comprises the following steps: when an emergency occurs to the aircraft, the separation bolt assembly is started, gunpowder in the separation bolt assembly is ignited to explode, a separation piston in the separation bolt assembly is pushed by the explosive impact force of the gunpowder to approach the end of the separation bolt to cut the separation bolt from the separation bolt support, and the hatch cover is separated from the hatch cover frame through the connecting part of the separation bolt assembly;
step two: in the process of explosion of the separation bolt assembly, the formed impact force drives the cabin cover and the rear hinged support arm to move upwards along the guide groove, and the rear hinged support arm reaches the top of the guide groove;
step three: when the rear hinged support arm reaches the top of the guide groove, the rocket is thrown and released to start, the cabin cover and the rear hinged support arm are pushed to rotate around the rotating shaft, when the stop dog is completely abutted against the rear hinged support, the rivet connecting the first buckling block and the second buckling block is sheared, the cabin cover and the rear hinged support arm are separated from the rear hinged support, and the cabin cover is thrown away.
The explosion time of the separation bolt assembly is 50ms away from the starting time of the rocket for throwing.
The invention has the beneficial effects that: the cabin cover is movably connected with one end of the cabin cover frame through the rear hinge mechanism, the other end of the cabin cover is fixedly connected through the separation bolt assembly, the cabin cover and the cabin cover frame can be fixedly and hermetically connected to guarantee the sealing performance of the cabin, meanwhile, when an emergency occurs, the cabin cover can be conveniently thrown and placed, a reliable escape channel can be provided for a pilot, when the separation bolt assembly can be automatically separated, with the help of explosion impact force, a stroke of the cabin cover upwards is designed, the cabin cover is convenient to rotate, interference with an airplane body is avoided, and meanwhile, the explosion impact is reduced.
Drawings
FIG. 1 is a schematic view of an escape canopy according to the present invention;
FIG. 2 is a schematic view of the mechanism for separating the bolt assembly of the present invention;
FIG. 3 is a cross-sectional structural view of the break-away bolt assembly of the present invention;
FIG. 4 is a schematic structural view of the rear hinge mechanism of the present invention;
FIG. 5 is an exploded view of the rear hinge mechanism of the present invention;
FIG. 6 is a schematic diagram of the structure of the aperture size of the guide groove according to the embodiment of the present invention;
FIG. 7 is a schematic illustration of the process of attaching the deck lid and the deck lid frame by the breakaway bolt assembly of the present invention;
fig. 8 is a schematic structural view of the hatch cover and the hatch cover frame after the hatch cover and the hatch cover frame are connected by the separation bolt assembly.
In the figure: 1. a hatch cover frame; 2. detaching the bolt assembly; 3. throwing a rocket; 4. a rear hinge assembly; 5. a hatch cover; 6. a rear hinged support arm; 7. a rear hinged support; 8. a rotating shaft; 9. a stopper; 10. riveting; 11. a support plate; 12. a guide groove; 13. a seal ring; 201. separating the bolt support; 202. separating the piston; 203. separating the bolt; 204. a two-way nut; 205. drawing the bolt closer; 206. a medicine cavity; 601. a base; 602. a support arm; 603. a first fastening block; 604. a first semicircular groove; 801. a shaft body; 802. a nut; 803. a spacing pin; 901. a second fastening block; 902. a second semicircular groove; 903. a slot; 1201. a lower guide groove; 1202. a middle guide groove; 1203. an upper guide groove.
Detailed Description
The invention is described in detail below with reference to the figures and examples.
In the description of the present invention, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature; in the description of the present invention, "a plurality" means two or more unless otherwise specified.
Examples
The escape canopy structure shown in fig. 1 comprises a canopy frame 1 integrated with a machine body, wherein the canopy frame 1 is provided with an escape passage at the top of the machine body, the escape passage is positioned right above a driver in the machine body, and the edge of the escape passage extends vertically downwards to form a downward flanging so as to form a canopy frame, so that a later-stage separation bolt assembly 2 can be fixedly connected to the downward flanging of the canopy frame, the canopy 5 and the canopy frame are conveniently and fixedly connected through the separation bolt assembly 2, specifically, a plurality of separation bolt assemblies 2 are uniformly distributed on the flanging of the canopy frame, the fixed connection of the canopy can be ensured, and the separation bolt assemblies are simultaneously separated when separation is carried out; the cabin cover 5 is hermetically connected to the cabin cover frame 1, the sealing performance of the interior of the engine body can be guaranteed through the sealing connection between the cabin cover 5 and the cabin cover frame 1, specifically, the cabin cover 5 covers the cabin cover frame 1 to seal the cabin cover frame 1, meanwhile, a sealing ring 13 is arranged at the joint of the cabin cover frame 1 and the cabin cover 5 to guarantee the sealing performance of the cabin cover frame, and the sealing ring 13 is specifically arranged at the edge of the cabin cover frame 1 to guarantee the sealing performance of the cabin cover frame 1 through the alignment and extrusion of the cabin cover 5;
meanwhile, the cabin cover 5 is pressed on the cabin cover frame 1, so that a certain height difference exists between the cabin cover 5 and the aircraft body, and in the process of high-speed flight, the friction force borne by the height difference is large, so that the flight of a fighter is influenced, therefore, an arc-shaped guide surface is arranged on the upper edge of the cabin cover 5, when the cabin cover 5 is fixedly connected with the cabin cover frame 1, the bottom of the guide surface is completely matched and contacted with the surface of the aircraft body, so that the friction force can be effectively reduced, and the stability of the fixed connection between the cabin cover 5 and the cabin cover frame 1 is ensured; the hatch cover 5 is movably connected with the hatch cover frame 1 through the rear hinge mechanism 4, the hatch cover 5 is movably connected with one end of the hatch cover frame 1 through the rear hinge mechanism 4, the hatch cover 5 can be ensured to be capable of reversing along the hatch cover frame 1 during installation, the installation is convenient, in particular, during installation, one end of the rear hinge mechanism 4 penetrates through the hatch cover frame 1 to be fixedly connected with the inner wall of the machine body, the other end of the rear hinge mechanism is fixedly connected with the hatch cover 5, when the hatch cover 5 is thrown and placed, the hatch cover 5 drives the rear hinge mechanism 4 to rotate, the rotating angle is specifically 30-45 degrees, the hatch cover and the rear hinge mechanism can be ensured to generate shearing force for shearing the rear hinge mechanism when the hatch cover and the rear hinge mechanism rotate, and the hatch cover 5 is separated from the hatch cover frame 1; a plurality of separation bolt assemblies 2 for fixedly connecting the hatch cover 5 with the hatch cover frame 1 are arranged on the inner side surface of the hatch cover frame 1, the bodies of the separation bolt assemblies 2 are fixed on downward vertical turned edges of the hatch cover frame 1, the connecting sections of the separation bolt assemblies 2 are fixedly connected with the hatch cover 5, and in case of emergency of the airplane, the separation bolt assemblies 2 are automatically separated, and the hatch cover 5 is separated from the hatch cover frame 1; the inner side surface of the hatch cover 5 far away from the rear hinge mechanism 4 is fixedly provided with a throwing rocket 3 for throwing the hatch cover 5 separated from the hatch cover frame 1;
specifically, in an emergency situation of the airplane, the separation bolt assembly 2 is separated, the hatch cover 5 is separated from the end part of the hatch cover frame 1 connected through the separation bolt assembly 2, the throwing rocket 3 pushes the hatch cover 5 and the rear hinge mechanism 4 to rotate to a certain angle around the end part of the rear hinge mechanism 4, the rear hinge mechanism 4 is cut off, and the hatch cover 5 is thrown away.
The separation bolt assembly 2 is started, the separation bolt assembly 2 is separated, the hatch cover and the hatch cover frame are separated through the end part connected with the separation bolt assembly, meanwhile, the rear hinge mechanism 4 moves upwards under the impact action after the separation of the separation bolt assembly, when the upward movement cannot be carried out any more, the throwing rocket 3 is started to push the hatch cover 5 to rotate through the rear hinge mechanism 4, the rotation is specifically that the hatch cover 5 and the rear hinge mechanism rotate to 45 degrees around one end of the rear hinge mechanism 4, when the rotation cannot be carried out, the rear hinge mechanism 4 is sheared, the hatch cover 5 is thrown away, in order to conveniently push the hatch cover 5 through the throwing rocket 3, the throwing rocket 3 is fixedly connected with the hatch cover 5, and a fire ejecting opening of the throwing rocket 3 is perpendicular to the hatch cover 5.
Further, as shown in fig. 2 and 3, the separation bolt assembly 2 includes a separation bolt support 201 fixedly connected to the inner side surface of the deck lid frame 1, specifically, the separation bolt support 201 is fixed to the downward turned edge of the deck lid frame 1 and fixedly connected to the downward turned edge by a fixing screw, and a draw-in bolt 205 fixedly connected to the inner side surface of the deck lid 5, and when in use, the draw-in bolt 205 is fixedly connected to the inner surface of the deck lid 5, as shown in fig. 7, the end of the draw-in bolt may also pass through the outer surface of the deck lid 5 and extend to the inner surface for fixedly connecting, and after the fixing is completed, the through hole formed on the outer surface of the deck lid 5 is sealed and polished flat;
the pulling-in bolt 205 is vertical to the inner side surface of the hatch cover 5 and extends downwards, a medicine cavity 206 for placing powder is arranged in the separation bolt support 201, the medicine cavity 206 is used for loading powder and is used for leading the separation piston 202 to impact the connecting part of the separation bolt 203 and the separation bolt support 201 under the explosive impact force of the powder by igniting the loaded powder in the emergency situation so as to lead the separation bolt 203 to be cut off from the separation bolt support 201, the specific amount of the powder loaded in the medicine cavity 206 is determined according to the connecting strength of the separation piston 202 and the separation bolt support 201, the separation piston 202 and the separation bolt support 201 can ensure that the hatch cover 5 and the hatch cover frame are firmly connected when being connected, and simultaneously, the powder loaded in the medicine cavity can separate the separation piston from the separation bolt support when being ignited and cannot cause injury to flying personnel, the amount of gunpowder is not subject to the protection of the invention, and the amount of gunpowder is not described in detail;
the medicine cavity 206 is sealed by the separation piston 202 inserted into the medicine cavity 206, the separation piston 202 can be fixedly connected with the cavity wall of the medicine cavity when in use, the end part of the separation bolt support close to the separation piston 202 is fixedly connected with the separation bolt 203, and meanwhile, the separation piston 202 is in sealed contact with the cavity wall of the medicine cavity 206, so that when gunpowder in the medicine cavity explodes, the generated impact force can push the separation piston to move towards the end part of the separation bolt, the separation piston forms huge impact force on the connection part of the separation bolt and the separation bolt support, the separation bolt can be cut off from the separation bolt support, and the separation bolt support are separated;
the separation bolt 203 and the pull-in bolt 205 are fixedly connected through a bidirectional nut 204, the separation bolt 203 is fixedly connected to the separation piston 202 or is in an integral structure with the separation piston, and the bidirectional nut can ensure that the pull-in bolt and the separation bolt can be pulled and locked in the rotating process of the bidirectional nut, so that the connection between the pull-in bolt and the separation bolt is completed; specifically, the two-way nut 204 may have two nuts for directional welding; when the hatch 5 is fixedly connected as shown in fig. 8, the closing bolt and the detaching bolt are moved in opposite directions by rotating the bidirectional nut 204, thereby ensuring that the hatch and the hatch frame are fixedly connected.
Specifically, when gunpowder in the explosive cavity 206 explodes, the separating piston 202 is pushed by the explosive impact of the gunpowder to approach the end of the separating bolt 203, and the separating bolt 203 is sheared from the separating bolt support 201, so that the separating bolt 203 and the drawing bolt 205 are separated from the separating bolt support 201; when gunpowder explodes, the huge impact force generated by the gunpowder moves the separating piston to the end part of the separating bolt, the separating piston shears the connecting part between the separating bolt and the separating bolt support, the separating bolt is separated from the separating bolt support, and then the part, connected with the hatch cover frame through the separating bolt assembly, is separated.
Further, as shown in FIG. 4 and as shown in FIG. 5
The rear hinge mechanism 4 comprises a rear hinge support arm 6 fixedly connected with the cabin cover 5 and a rear hinge support 7 fixedly connected with the cabin cover frame 1, two parallel support plates 11 are arranged in the middle of the rear hinge support 7, symmetrical guide grooves 12 are formed in the two parallel support plates 11, the guide grooves can ensure that after the separation bolt assembly is automatically separated, the cabin cover 5 can ascend and then overturn, and further ensure that the cabin cover 5 cannot interfere with a machine body when overturning, the end part of the rear hinge support arm 6 extends between the parallel support plates 11 and is connected with a rotating shaft 8 penetrating in the symmetrical guide grooves 12, and the rear hinge support arm 6 rotates when moving to the upper end of the guide grooves 12 and is separated from the rear hinge support 7. The rear hinged support 7 is vertically fixed on the machine body, meanwhile, the extending end of the support plate 11 is perpendicular to the hatch cover 5, one end of the rear hinged support arm 6 is fixedly connected with the hatch cover 5, and the other end of the rear hinged support arm is positioned between the support plates 11 and can move up and down along the guide groove 12.
Further, in order to facilitate the rear hinge arm 6 to move up and down along the rear hinge support 7, specifically, the base 601 is fixedly connected with the hatch 5, and an extension surface of the base 601 is perpendicularly intersected with an extension surface of the rear hinge support 7, so as to ensure that the guide groove 12 of the rear hinge support 7 moves up and down, as shown in fig. 3 and 5, the rear hinge arm 6 includes a base 601 fixedly connected with the hatch 5, an arm 602 fixedly connected to the base 601, and a stopper 9 connected to the arm 602 and located between the support plates 11 parallel to each other; the arm-shaped support arm 602 is adopted, the main principle is that the arm is used for lifting after bending for 90 degrees, so that the hatch cover 5 can be ensured to stably move upwards along the guide groove 12 by impact force generated after the hatch cover 5 is separated by the separation bolt assembly; in order to ensure that the stop block 9 is in an ascending process and reduce explosion impact in a separation process of a separation bolt assembly in a sliding process, as shown in fig. 6, the guide groove 12 is divided into three sections with different aperture sizes from top to bottom, a lower guide groove 1201 positioned at the lower part of the guide groove 12 is in clearance fit with the rotating shaft 8, a middle guide groove 1202 positioned at the middle part of the guide groove 12 is in transition fit with the rotating shaft 8, an upper guide groove 1203 positioned at the upper part of the guide groove 12 is in interference fit with the rotating shaft 8, and smooth transition is performed among the lower guide groove 1201, the middle guide groove 1202 and the upper guide groove 1203.
Lower part guide way 1201 carries out clearance fit with the pivot, guarantees to drive under the effect of separation bolt impact force, and the hatch board 5 upwards moves, when rising to middle part guide way 1202 department, carries out transition fit, can slow down the speed that rises, when reacing top guide way 1203 department, because the frictional force of the consequently pivot of going on interference fit and top guide way 1203 increases, can guarantee that back hinge support arm and hatch board 5 speed of going upward reduces, stops until the top of guide way.
Specifically, in order to ensure that the stopper can smoothly reach the top of the guide groove, in a specific implementation process, the ratio of the pitch of the middle guide groove 1202 to the pitch of the upper guide groove 1203 to the pitch of the lower guide groove 1201 is 1:1: 8. The specific numerical value is that the hole length of the whole guide groove is 90mm, the hole length of the lower guide groove is 66mm, the hole length of the middle guide groove is 6mm, and the hole length of the upper guide groove is 6 mm.
In order to ensure that the stop block 9 is driven to rotate around the rotating shaft under the impact force of the throwing rocket when the stop block reaches the top of the guide groove, and meanwhile, when the stop block rotates to a certain angle, the rivet connected in the stop block can be sheared to throw the hatch 5, as shown in fig. 5, a first buckling block 603 integrated with the support arm 602 is arranged at the end part of the support arm 602 connected with the stop block 9, and a first semicircular groove 604 is arranged on the first buckling block 603.
The stop block 9 includes a second fastening block 901 which is fastened by matching with the first fastening block 603, the first fastening block 603 and the second fastening block 901 are connected by a rivet 10 (or connected by a shear pin), the second fastening block 901 is provided with a second semicircular groove 902, the second semicircular groove 902 and the first semicircular groove 604 are fastened to form a shaft hole for the rotating shaft 8 to pass through, and when the rear hinge support arm 6 rotates around the rotating shaft 8, the top of the surface of the second fastening block 901 opposite to the rear hinge support 7 is abutted to the rear hinge support 7.
When the rotating shaft rises to the top of the guide groove to be in interference fit with the guide groove, the throwing rocket pushes the hatch cover 5 to go upward, the shaft hole formed by the first buckling block and the second buckling block penetrates through the rotating shaft, so that the hatch cover and the rear hinged support arm rotate along the rotating shaft, when the rotating shaft rotates to a certain angle, the back of the second buckling block is propped against the rear hinged support 7 to be abutted against the rear hinged support 7, the rotation cannot be carried out, the throwing force of the throwing rocket enables the first buckling block to have torque around the rotating shaft, the second buckling block does not move, the stress of the connected rivet changes under the action of mutual force between the first buckling block and the second buckling block, the rivet is cut off, the first buckling block and the second buckling block in the rear hinged support arm are separated at the moment, the hatch cover 5 is completely separated from the machine body, and the throwing is finished.
Further, in order to improve the integrity of the whole rear hinge arm and facilitate connection, an insertion slot 903 into which the first fastening block 603 is inserted is formed in the end of the second fastening block 901, and the first fastening block 603 is inserted into the insertion slot 903 and is fixedly connected with the second fastening block 901 through a rivet 10.
The rotating shaft 8 comprises a shaft body 801 with a nut, the shaft body 801 sequentially penetrates through the guide groove 12 and the rear hinge support arm 6 and is fixedly connected with a nut 802 at the end part of the rear hinge support 7, and a limit pin 803 is inserted at the outer end of the shaft body 801, which is connected with the nut 802. The shaft is conveniently passed through the second semicircular groove 902 and the first semicircular groove 604 and can be fixed.
The canopy separation bolt throwing method is provided through the structure and comprises the following steps:
the method comprises the following steps:
the method comprises the following steps: when an emergency occurs in the aircraft, the separation bolt assembly 2 is started, gunpowder in the separation bolt assembly 2 is ignited and explodes, the separation piston 202 in the separation bolt assembly 2 is pushed by the explosive impact force of the gunpowder to approach the end of the separation bolt 203, the separation bolt 203 is sheared from the separation bolt support 201, specifically, the gunpowder generates huge impact force when exploding, the separation bolt moves towards the end of the separation bolt under the action of specific impact force and impacts a connecting plate of the separation bolt and the separation bolt support, the connecting part of the separation bolt and the separation bolt support is sheared, and the hatch cover 5 and the hatch cover frame 1 are separated through the connecting part of the separation bolt assembly 2;
step two: in the process of explosion of the separation bolt assembly 2, the formed impact force drives the hatch 5 and the rear hinged support arm 6 to move upwards along the guide groove 12, and the rear hinged support arm 6 reaches the top of the guide groove 12;
step three: when the rear hinge support arm 6 reaches the top of the guide groove 12, the throwing rocket 3 is started to push the cabin cover 5 and the rear hinge support arm 6 to rotate around the rotating shaft 8, when the stop block 9 completely collides with the rear hinge support 7, the rivet 10 connecting the first buckling block 603 and the second buckling block 901 is sheared, the cabin cover 5 and the rear hinge support arm 6 are separated from the rear hinge support 7, and the cabin cover 5 is thrown away.
The starting time of the separation bolt assembly 2 is 50ms away from the starting time of throwing the rocket 3.
By means of the impact force of the separation bolt assembly during separation, an upward stroke of the canopy is designed, the canopy is convenient to rotate, interference with an airplane body is avoided, and meanwhile explosion impact of the separation bolt assembly in the explosion process is reduced.
The above embodiments are merely illustrative of the present invention, and should not be construed as limiting the scope of the present invention, and all designs identical or similar to the present invention are within the scope of the present invention.
Claims (10)
1. The escape canopy structure is characterized by comprising a canopy frame (1) and a canopy (5), wherein the canopy frame (1) and the canopy (5) are of an integral structure, the canopy (5) is connected to the canopy frame (1) in a sealing mode through a rear hinge mechanism (4) in a movable mode, a plurality of separating bolt assemblies (2) for fixedly connecting the canopy (5) and the canopy frame (1) are arranged on the inner side face of the canopy frame (1), and the separating bolt assemblies (2) are automatically separated under the emergency condition of an airplane, so that the canopy (5) is separated from the canopy frame (1); a throwing rocket (3) for throwing the hatch cover (5) separated from the hatch cover frame (1) is fixedly arranged on the inner side surface of the hatch cover (5) far away from the rear hinge mechanism (4);
when the airplane meets an emergency, the separation bolt assembly (2) is separated, the hatch cover (5) is separated from the end part of the hatch cover frame (1) connected through the separation bolt assembly (2), the throwing rocket (3) pushes the hatch cover (5) and the rear hinge mechanism (4) to rotate to a certain angle around the end part of the rear hinge mechanism (4), the rear hinge mechanism (4) is cut off, and the hatch cover (5) is thrown away.
2. An escape hatch cover structure according to claim 1, characterized in that a sealing ring (13) is arranged at the joint of the hatch cover (5) and the hatch cover frame (1).
3. The escape capsule cover structure of claim 1, wherein the separation bolt assembly (2) comprises a separation bolt support (201) fixedly connected with the inner side surface of the capsule cover frame (1), a draw-in bolt (205) fixedly connected with the inner side surface of the capsule cover (5), the draw-in bolt (205) is perpendicular to the inner side surface of the capsule cover (5) and extends downwards, a medicine cavity (206) for placing powder is arranged in the separation bolt support (201), the medicine cavity (206) is sealed by a separation piston (202) inserted in the medicine cavity (206), the separation piston (202) is in sealing contact with the cavity wall of the medicine cavity (206), a separation bolt (203) is fixedly connected on the surface of the end part of the separation piston (202) opposite to the separation bolt support (201), and the separation bolt (203) is fixedly connected with the draw-in bolt (205) through a bidirectional nut (204), when gunpowder in the explosive cavity (206) explodes, the separating piston (202) impacts the connecting part of the separating bolt (203) and the separating bolt support (201) under the explosive impact force of the gunpowder, so that the separating bolt (203) is sheared from the separating bolt support (201), and the separating bolt (203) and the drawing bolt (205) are separated from the separating bolt support (201).
4. An escape seat hatch structure according to claim 1, characterized in that the rear hinge mechanism (4) comprises a rear hinge support arm (6) fixedly connected with the hatch (5) and a rear hinge support (7) fixedly connected with the hatch frame (1), the middle of the rear hinge support (7) is provided with two parallel support plates (11), the two parallel support plates (11) are provided with symmetrical guide grooves (12), the end of the rear hinge support arm (6) extends between the parallel support plates (11) and is connected with a rotating shaft (8) penetrating in the symmetrical guide grooves (12), and the rear hinge support arm (6) rotates when moving to the upper end of the guide groove (12) and is separated from the rear hinge support (7).
5. An escape hatch cover structure according to claim 4, characterized in that the rear hinge arm (6) comprises a base (601) fixedly connected to the cover (5), an arm (602) fixedly connected to the base (601), a stop (9) connected to the arm (602) and located between the parallel support plates (11);
the end part of the support arm (602) connected with the stop block (9) is provided with a first buckling block (603) which is integrated with the support arm (602), and the first buckling block (603) is provided with a first semicircular groove (604);
the stop block (9) comprises a second fastening block (901) which is matched and fastened with the first fastening block (603), the first fastening block (603) is connected with the second fastening block (901) through a rivet (10), a second semicircular groove (902) is formed in the second fastening block (901), the second semicircular groove (902) is fastened with the first semicircular groove (604) to form a shaft hole for the rotating shaft (8) to pass through, and when the rear hinged support arm (6) rotates around the rotating shaft (8), the top of the surface, opposite to the rear hinged support (7), of the second fastening block (901) is abutted to the rear hinged support (7);
the end part of the second buckling block (901) is provided with a slot (903) into which the first buckling block (603) is inserted, and the first buckling block (603) is inserted into the slot (903) and is fixedly connected with the second buckling block (901) through a rivet (10).
6. The escape cockpit cover structure of claim 4, wherein the guide groove (12) is divided into three sections with different aperture sizes from top to bottom, a lower guide groove (1201) located at the lower part of the guide groove (12) is in clearance fit with the rotating shaft (8), a middle guide groove (1202) located at the middle part of the guide groove (12) is in transition fit with the rotating shaft (8), an upper guide groove (1203) located at the upper part of the guide groove (12) is in interference fit with the rotating shaft (8), and the lower guide groove (1201), the middle guide groove (1202) and the upper guide groove (1203) are in smooth transition;
the ratio of the pitch of the middle guide groove (1202), the pitch of the upper guide groove (1203) and the pitch of the lower guide groove (1201) is 1:1: 8.
7. An escape cockpit lid structure according to claim 4 where the rotation shaft (8) comprises a shaft body (801) with a nut, the shaft body (801) sequentially passes through the guide slot (12) and the rear hinge arm (6) and is fixedly connected with the nut (802) at the end of the rear hinge support (7), and the outer end of the shaft body (801) connected with the nut (802) is inserted with a limit pin (803).
8. An escape hatch cover structure according to claim 1, characterized in that the jettisoning rocket (3) is fixedly connected with the hatch cover (5), and the fire jet of the jettisoning rocket (3) is perpendicular to the hatch cover (5).
9. A method for throwing separating bolts of a canopy is characterized by comprising the following steps:
the method comprises the following steps: when an emergency occurs in the aircraft, the separation bolt assembly (2) is started, gunpowder in the separation bolt assembly (2) is ignited and explodes, a separation piston (202) in the separation bolt assembly (2) is pushed by the explosive impact force of the gunpowder to approach the end of a separation bolt (203), the separation bolt (203) is sheared from a separation bolt support (201), and the cabin cover (5) is separated from the cabin cover frame (1) through the connecting part of the separation bolt assembly (2);
step two: in the explosion process of the separation bolt assembly (2), the formed impact force drives the hatch cover (5) and the rear hinge support arm (6) to move upwards along the guide groove (12), and the rear hinge support arm (6) reaches the top of the guide groove (12);
step three: when the rear hinge support arm (6) reaches the top of the guide groove (12), the throwing rocket (3) is started to push the cabin cover (5) and the rear hinge support arm (6) to rotate around the rotating shaft (8), when the stop block (9) is completely abutted to the rear hinge support (7), the rivet (10) connecting the first buckling block (603) and the second buckling block (901) is sheared off, the cabin cover (5) and the rear hinge support arm (6) are separated from the rear hinge support (7), and the cabin cover (5) is thrown away.
10. A canopy break bolt release method according to claim 9, characterized in that the detonation time of the break bolt assembly (2) is 50ms apart from the start time of the release rocket (3).
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| CN201811632047.4A CN111377048B (en) | 2018-12-29 | 2018-12-29 | Escape shelter cover structure and shelter cover separation bolt throwing method |
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| CN201811632047.4A CN111377048B (en) | 2018-12-29 | 2018-12-29 | Escape shelter cover structure and shelter cover separation bolt throwing method |
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| CN111377048B CN111377048B (en) | 2023-06-02 |
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| US20220250733A1 (en) * | 2021-02-05 | 2022-08-11 | The Boeing Company | Systems and methods for indicating release of a canopy an aircraft |
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