CN108791814B - Aircraft radome fairing with impact resistance - Google Patents

Abstract

The invention discloses an aircraft fairing with good impact resistance and a manufacturing method thereof, and relates to the technical field of aircraft. The aircraft body is placed between the bodies, and the hood tail is placed on the right side of the aircraft body. The aircraft fairing with good impact resistance and the manufacturing method thereof have the function of reducing the friction between the whole and the airflow, have the advantages of good impact resistance, improve the overall buffer performance, and further ensure the safety of the aircraft body , has the function of reducing the friction between the whole and the airflow, further improving the overall impact resistance, and ensuring the safety and integrity of the aircraft body, with the function of protecting the aircraft body, and ensuring the safety and integrity of the aircraft body. The advantage of integrity prevents foreign objects from colliding with the aircraft body through the first port.

Description

An aircraft fairing with impact resistance

technical field

The invention relates to the technical field of aircraft, in particular to an aircraft fairing with impact resistance.

Background technique

The aerospace industry usually includes production companies and repair companies, as well as research departments, design departments, sales departments, test and flight test bases and management departments that are independent or subordinate to production companies. Most aerospace industry companies are based on their own technology and production. condition to produce some non-aerospace products.

The fairing used to protect the aircraft in the aerospace industry. During the flight of the aircraft, the fairing will rub against the surrounding airflow, which is easy to cause damage, thereby losing the protective effect on the aircraft and having poor impact resistance.

SUMMARY OF THE INVENTION

The purpose of the present invention is to make up for the deficiencies of the prior art, and to provide an aircraft fairing with impact resistance, which has the advantages of good impact resistance and solves the problem of poor impact resistance of the existing aircraft.

In order to solve the above-mentioned technical problems, the present invention provides the following technical solutions: an aircraft fairing with impact resistance, comprising a cowl head, and two symmetrical cowl bodies are fixedly connected to the right side of the cowl head, and the two The aircraft body is placed between the hood bodies, the hood tail is placed on the right side of the aircraft body, the right side of each hood body is fixedly connected with the left side of the hood tail, and the A rectifying mechanism is installed inside, a first anti-shock mechanism is installed inside the aircraft body, and a second shock-resistant mechanism is installed outside the aircraft body.

The rectification mechanism includes a forward and reverse rotation motor, a cavity, a first bearing, a worm, a rectifying plate, a groove, a second bearing, a fixed column, a third bearing and a worm wheel, and the inside of each cover body is provided with a hollow space. There are grooves on one side of the two cover bodies away from each other, and the inner side wall of each groove close to the cavity is fixedly embedded with a first bearing, and the two first bearings are respectively connected with the two hollows. The cavities are connected, the inner wall of each of the grooves away from the cavity is fixedly inlaid with a second bearing, and the inner walls of the two cavities close to each other are fixedly connected with a forward and reverse motor, and each of the forward and reverse rotations The output ends of the motor are fixedly connected with worms, the two worms respectively penetrate the two first bearings and extend into the grooves, and the outer surfaces of the two worms are respectively fixedly connected with the inner rings of the two first bearings, And the right sides of the two worms are respectively fixedly connected with the inner rings of the two second bearings, the inner wall of each of the grooves is fixedly embedded with a third bearing, and the inner rings of each of the third bearings are fixedly connected. There are fixed columns, the front of each fixed column is fixedly connected with a worm wheel, and the two worm wheels are respectively engaged with the two worms, and the outer surface of each of the fixed columns is fixedly connected with a rectifying plate.

Further, the first anti-impact mechanism includes a slider, a first strong spring, a chute, a fixing block, a first pin, a fixing rod, a second pin and a fixing plate, and the right side of the cover head is fixed Two relatively symmetrical fixing blocks are connected, the front of each of the fixing blocks is fixedly hinged with a fixing rod through the first pin, and the left side of the upper surface of the aircraft body and the left side of the bottom surface of the aircraft body are provided with slides. The upper part of the aircraft body and the lower part of the aircraft body are placed with fixed plates, and the two sides of the two fixed plates that are close to each other are fixedly connected with sliders that are adapted to the chute, and the sliders are clamped on In the chute, the front side of each fixed plate is fixedly hinged with the side of the front side of the fixed rod away from the fixed block through the second pin shaft, and the right side of each sliding block is fixedly connected with a first strong spring, And the right ends of the two first strong springs are respectively fixedly connected with the inner side walls of the two sliding grooves.

By adopting the above technical solution, the function of making the hood head drive the hood body and the hood tail moving left and right can reduce the friction between the whole body and the airflow, play a certain buffering effect, and have the advantages of good impact resistance, and more Further guarantee the overall security and integrity.

Further, the second anti-impact mechanism includes a support block, a support rod, a second strong spring, a slip ring, a slide rod, a first connecting block and a second connecting block, and the upper surface of the aircraft body is connected to the bottom surface of the aircraft body. Both are fixedly connected with a first connecting block, the upper surface of the aircraft body and the bottom surface of the aircraft body are both fixedly connected with a second connecting block, and the two second connecting blocks are respectively located on the right side of the two first connecting blocks, each Slide bars are fixedly connected to the right sides of each of the first connecting blocks, and the right sides of the two slide bars are respectively fixedly connected to the left sides of the two second connecting blocks. The surface is sleeved with a slip ring that is adapted to the sliding rod, the right side of each of the slip rings is fixedly connected with a second strong spring, and the two second strong springs are respectively sleeved on the two sliding rods and the right ends of the two second strong springs are fixedly connected to the left sides of the two second connection blocks respectively, and the two sides of the two slip rings away from each other are fixedly connected with support rods, and the two Support blocks are fixedly connected to one side of the support rods away from each other, and one side of the two support blocks that are far away from each other is fixedly connected to one side of the two cover bodies that are close to each other.

By adopting the above technical solution, the function of making the cover body drive the cover head and the cover tail to move left and right can reduce the friction between the whole body and the airflow, further improve the buffering effect, and further improve the impact resistance performance. The overall service life is relatively prolonged.

Further, a first through port is opened on the left side of the cover head, the inner top wall of the first through port is fixedly connected with a first filter screen, and the bottom surface of the first filter screen is connected to the inner surface of the first through port. Bottom wall fixed connection.

By adopting the above technical solution, the function of blocking debris is provided, the collision of foreign objects on the aircraft body is prevented during the flight, and the aircraft body has the advantage of protecting the aircraft body.

Further, the right side of the cover tail is provided with a second through port, the inner top wall of the second through port is fixedly connected with a second filter screen, and the bottom surface of the second filter screen is connected to the inner surface of the second port. Bottom wall fixed connection.

By adopting the above technical solution, the problem of reducing the flight efficiency due to the partition of the hood tail affecting the air exhaust of the aircraft body during the flight of the aircraft body is avoided, and the overall practical effect is improved.

Further, the upper and lower sides of the left side of the cover head are arc-shaped, and the maximum vertical length value of the cover head is equal to the vertical length value of the cover tail.

By adopting the above technical solution, the friction between the airflow and the hood head can be effectively reduced, and the flight efficiency is improved.

Further, the vertical length value of the first through opening is equal to the vertical length value of the second through opening, and the vertical length value of the aircraft body is smaller than the vertical length value of the first through opening.

By adopting the above technical solution, the collision between the cowl head and the aircraft body is prevented when it moves left and right.

Further, the manufacturing method comprises the steps:

S1, blank blanking, the cover head and cover tail are machined and formed, and titanium alloy sheets with a thickness greater than the height of the cover body are used for cutting, and a certain machining allowance is left around the cover body. To determine the length of the body, select a titanium alloy plate with a thickness greater than the wall thickness of the cover body, cut the material, and fine-mill the outer surface to the thickness of the cover body for polishing;

S2, the cover body is hot-pressed, the parting surface of the hot-pressing die is evenly coated with alcohol graphite solution, and after air-drying, it is slightly polished with fine sandpaper, put into the workpiece, aligns the concave and convex molds, hot-pressed, and the pressure is maintained for 10- 25s, then cool down, open the mold and take out the workpiece;

S3, the hood head, hood body and hood tail are welded by laser welding or electron beam welding, and the welding temperature is kept at 750-800 degrees, and the aircraft fairing can be made.

Compared with the prior art, the aircraft fairing with good impact resistance and the manufacturing method thereof have the following beneficial effects:

1. The present invention is provided with a rectifying mechanism, and uses the rotation of the forward and reverse motor to drive the rectifying plate to rotate, thereby driving the rectifying plate to turn left and right, and has the function of reducing the flight speed, which can increase the resistance of the aircraft body when landing, thereby Making the landing deceleration more efficient has the advantage of use, passing the overall practical effect.

2. The present invention is provided with a first anti-impact mechanism, and uses the cooperation among the slider, the first strong spring, the chute, the fixing block, the first pin, the fixing rod, the second pin and the fixing plate to achieve the In order to make the hood head drive the hood body and the hood tail to move left and right, it has the function of reducing the friction between the whole and the airflow, has the advantages of good impact resistance, improves the overall buffer performance, and further ensures the aircraft body. safety.

3. The present invention is provided with a second anti-impact mechanism and utilizes the cooperation among the support block, support rod, second strong spring, slip ring, slide rod, first connecting block and second connecting block, so as to achieve the The body drives the hood head and the hood tail moves left and right, which has the function of reducing the friction between the whole body and the airflow, further improving the overall impact resistance performance, and ensuring the safety and integrity of the aircraft body.

4. By being provided with a cover head, and the cooperation among the first port, the first filter, the second filter and the second port, the effect of blocking foreign objects is achieved, and the function of protecting the aircraft body is achieved. , has the advantage of ensuring the safety and integrity of the aircraft body, and prevents the collision of foreign objects with the aircraft body through the first port.

Description of drawings

Fig. 1 is the front view of the cover body of the present invention;

2 is a sectional view of a cover body of the present invention;

Fig. 3 is the enlarged schematic diagram of the structure at place A in Fig. 2 of the present invention;

Fig. 4 is the enlarged schematic diagram of the structure at place B in Fig. 2 of the present invention;

FIG. 5 is an enlarged schematic view of the structure at C in FIG. 2 of the present invention.

In the picture: 1-rectifier mechanism, 101-forward and reverse rotation motor, 102-cavity, 103-first bearing, 104-worm, 105-rectifier plate, 106-groove, 107-second bearing, 108-fixed column , 109-Third bearing, 110-Worm gear, 2-First anti-shock mechanism, 201-Slider, 202-First strong spring, 203-Chute, 204-Fixing block, 205-First pin, 206- Fixed rod, 207-Second pin, 208-Fixed plate, 3-Second impact resistance mechanism, 301-Support block, 302-Support rod, 303-Second strong spring, 304-Slip ring, 305-Slide rod, 306-first connection block, 307-second connection block, 4-hood head, 5-first filter screen, 6-first port, 7-cover tail, 8-second filter screen, 9-aircraft body, 10-Second port, 11-Cover body.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

1-5, the present invention provides a technical solution: an aircraft fairing with impact resistance, comprising a cowl head 4, and two symmetrical cowl bodies 11 are fixedly connected to the right side of the cowl head 4, An aircraft body 9 is placed between the two cover bodies 11 , a cover tail 7 is placed on the right side of the aircraft body 9 , the right side of each cover body 11 is fixedly connected with the left side of the cover tail 7 , and each cover body is The rectification mechanism 1 is installed inside the aircraft body 9 , the first impact resistance mechanism 2 is installed inside the aircraft body 9 , and the second impact resistance mechanism 3 is installed outside the aircraft body 9 .

The rectifying mechanism 1 includes a forward and reverse rotation motor 101, a cavity 102, a first bearing 103, a worm 104, a rectifying plate 105, a groove 106, a second bearing 107, a fixed column 108, a third bearing 109 and a worm wheel 110, each cover The interior of the body 11 is provided with a cavity 102, and the side surfaces of the two cover bodies 11 away from each other are provided with grooves 106. The inner side wall of each groove 106 close to the cavity 102 is fixedly embedded with a first bearing 103, and The two first bearings 103 are respectively communicated with the two cavities 102, the inner walls of each groove 106 away from the cavities 102 are fixedly inlaid with the second bearings 107, and the inner walls of the two cavities 102 close to each other are fixedly connected with The forward and reverse motor 101, the forward and reverse motor 101 represents the clockwise and counter-clockwise rotation of the motor, the clockwise rotation of the motor is the forward rotation of the motor, the counterclockwise rotation of the motor is the motor reverse rotation, the forward and reverse control circuit diagram and its principle analysis To realize the forward and reverse rotation of the motor, it is only necessary to connect any two phases connected to the three-phase power supply line of the motor to achieve the purpose of reverse rotation. The forward and reverse rotation motor 101 is a well-known device in the prior art. The output ends of the rotating electrical machine 101 are fixedly connected with worms 104 . The two worms 104 respectively penetrate the two first bearings 103 and extend into the grooves 106 . The rings are fixedly connected, and the right sides of the two worms 104 are fixedly connected to the inner rings of the two second bearings 107 respectively, and the inner wall of each groove 106 is fixedly embedded with a third bearing 109. The inner ring is fixedly connected with a fixed column 108, the front of each fixed column 108 is fixedly connected with a worm wheel 110, and the two worm wheels 110 are respectively engaged with the two worms 104, and the outer surface of each fixed column 108 is fixedly connected with a Rectifier plate 105 .

Further, the first anti-impact mechanism 2 includes a slider 201, a first strong spring 202, a chute 203, a fixing block 204, a first pin 205, a fixing rod 206, a second pin 207 and a fixing plate 208, the cover head The right side of 4 is fixedly connected with two relatively symmetrical fixing blocks 204, the front of each fixing block 204 is fixedly hinged with a fixing rod 206 through a first pin 205, and the left side of the upper surface of the aircraft body 9 is connected to the aircraft body 9. The left side of the bottom surface is provided with a chute 203, a fixing plate 208 is placed above the aircraft body 9 and below the aircraft body 9, and one side of the two fixing plates 208 close to each other is fixedly connected with the sliding slot 203. and the slider 201 is snapped into the chute 203, the front of each fixing plate 208 is fixedly hinged with the side of the front of the fixing rod 206 away from the fixing block 204 through the second pin 207, and each slider The right side of the 201 is fixedly connected with a first strong spring 202, and the right ends of the two first strong springs 202 are respectively fixedly connected with the inner side walls of the two chutes 203, so that the cover head 4 drives the cover body 11, and The function of the hood tail 7 moving left and right can reduce the friction between the whole and the airflow, play a certain buffering role, and have the advantage of good impact resistance, which further ensures the overall safety and integrity.

Further, the second anti-shock mechanism 3 includes a support block 301 , a support rod 302 , a second strong spring 303 , a slip ring 304 , a slide rod 305 , a first connection block 306 and a second connection block 307 . The upper surface of the aircraft body 9 A first connecting block 306 is fixedly connected to the bottom surface of the aircraft body 9, and a second connecting block 307 is fixedly connected to the upper surface of the aircraft body 9 and the bottom surface of the aircraft body 9, and the two second connecting blocks 307 are located at two On the right side of the first connecting block 306 , a sliding rod 305 is fixedly connected to the right side of each first connecting block 306 , and the right sides of the two sliding rods 305 are respectively connected with the left side of the two second connecting blocks 307 . The outer surface of each sliding rod 305 is sleeved with a sliding ring 304 that is adapted to the sliding rod 305, and the right side of each sliding ring 304 is fixedly connected with a second strong spring 303. The two strong springs 303 are respectively sleeved on the outer surfaces of the two sliding rods 305 , and the right ends of the two second strong springs 303 are fixedly connected to the left sides of the two second connecting blocks 307 respectively, and the two sliding rings 304 are away from each other. A support rod 302 is fixedly connected to one side of the two support rods 302, and a support block 301 is fixedly connected to one side of the two support rods 302 that are far away from each other, and one side of the two support blocks 301 that are far away from each other is respectively close to the two cover bodies 11. One side is fixedly connected, and has the function of making the cover body 11 drive the cover head 4 and the cover tail 7 to move left and right, which can reduce the friction between the whole and the airflow, further improve the buffering effect, and further improve the impact resistance performance. , so that the overall service life is relatively prolonged.

Further, the left side of the cover head 4 is provided with a first through port 6 , the inner top wall of the first through port 6 is fixedly connected with a first filter screen 5 , and the bottom surface of the first filter screen 5 is connected to the first through port 6 . The inner bottom wall of the fuselage is fixedly connected, and has the function of blocking debris, which prevents the collision of foreign objects on the aircraft body 9 during the flight, and has the advantage of protecting the aircraft body 9.

Further, a second through port 10 is opened on the right side of the cover tail 7, the inner top wall of the second through port 10 is fixedly connected with the second filter screen 8, and the bottom surface of the second filter screen 8 is connected with the second through port 10. The inner bottom wall is fixedly connected to avoid the problem of reducing the flight efficiency and improving the overall practical effect of the aircraft body 9 due to the partition of the hood tail 7 affecting the exhaust air of the aircraft body 9 during the flight.

Further, the upper and lower sides of the left side of the cover head 4 are arc-shaped, and the maximum vertical length value of the cover head 4 is equal to the vertical length value of the cover tail 7, which can effectively reduce the air flow between the cover head 4. friction, improving flight efficiency.

Further, the vertical length value of the first port 6 is equal to the vertical length value of the second port 10, and the vertical length value of the aircraft body 9 is smaller than the vertical length value of the first port 6, which prevents the cover When the head 4 moves left and right, it collides with the aircraft body 9 .

Further, the manufacturing method is as follows:

S1, blanking the blank, the cover head 4 and cover tail 7 are machined and formed, and titanium alloy plates with a thickness greater than the height of the cover body are used for cutting, and a certain machining allowance is left around. The cover body 11 is formed by hot pressing. For the required length of the cover body 11, a titanium alloy plate with a thickness greater than the wall thickness of the cover body 11 is selected for blanking, and the outer surface is finely milled to the thickness of the cover body 11 for polishing;

S2, the cover body 11 is hot-pressed, the parting surface of the hot-pressing die is evenly coated with alcohol graphite solution, and after air-drying, it is slightly polished with fine sandpaper, put into the workpiece, aligning the concave and convex molds, hot-pressed, and maintained at a pressure of 10 -25s, then cool down, open the mold and take out the workpiece;

S3 , the hood head 4 , the hood body 11 and the hood tail 7 are welded by laser welding or electron beam welding, and the welding temperature is kept at 750-800 degrees, and the aircraft fairing can be made.

Working principle: connect the forward and reverse rotation motor 101 with the power storage, drive the cover head 4 through the aircraft body 9, the cover body 11 and the cover tail 7 to fly, when friction occurs with the air flow, the sliding block 201 and the chute 203 pass through the gap. The cooperating movement between the fixing rods 206, the fixing block 204, the first pin 205, the second pin 207 and the fixing plate 208 enables the cover head 4 to drive the cover body 11, and the cover tail 7 to It moves to the right, thereby squeezing the first strong spring 202, and the overall impact resistance is improved through the reset of the first strong spring 202. Similarly, when the cover body 11 moves to the right, the slip ring 304 and the The coordinated movement between the first pins 205 squeezes the second strong spring 303, and the overall impact resistance performance is further improved by the returnability of the second strong spring 303. When the aircraft body 9 is ready to land, The rotation of the forward and reverse motor 101 is used to drive the worm 104 to rotate, and the worm 104 is engaged with the worm wheel 110, so that the fixed column 108 drives the fairing plate 105 to rotate, so that the fairing plate 105 is kept perpendicular to the cover body 11, thereby reducing the flying speed, and preparing When landing, the protection of the aircraft body 9 can be realized, the friction between the airflow and the hood head 4, the hood body 11 and the hood tail 7 can be effectively reduced, the impact resistance is good, and the flight efficiency is effectively improved.

In the description of the present invention, the terms "comprising", "comprising" or any other variation thereof are intended to encompass a non-exclusive inclusion such that a process, method, article or apparatus comprising a series of elements includes not only those elements, but also Include other elements not expressly listed, or which are inherent to such a process, method, article or apparatus. Without further limitation, an element defined by the phrase "comprises a reference structure" does not preclude the presence of additional identical elements in the process, method, article or apparatus that includes the element. It should be noted that, herein, relational terms such as "first", "second", etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply these There is no such actual relationship or sequence between entities or operations.

Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, and substitutions can be made in these embodiments without departing from the principle and spirit of the invention and modifications, the scope of the present invention is defined by the appended claims and their equivalents.

Claims (6)

1. An aircraft fairing with impact resistance, comprising a hood head (4), the right side of the hood head (4) is fixedly connected with two relatively symmetrical hood bodies (11), two of the hoods An aircraft body (9) is placed between the bodies (11), a hood tail (7) is placed on the right side of the aircraft body (9), and the right side of each hood body (11) is connected to the hood tail (7). 7) The left side is fixedly connected, and it is characterized in that: a rectifying mechanism (1) is installed inside each said cover body (11), and a first anti-shock mechanism (1) is installed inside the aircraft body (9). 2), a second anti-impact mechanism (3) is installed on the outside of the aircraft body (9); The rectifying mechanism (1) comprises a forward and reverse rotation motor (101), a cavity (102), a first bearing (103), a worm (104), a rectifying plate (105), a groove (106), a second bearing ( 107), a fixed column (108), a third bearing (109) and a worm gear (110), a cavity (102) is opened inside each of the cover bodies (11), and two of the cover bodies (11) Grooves (106) are provided on the side faces away from each other, and a first bearing (103) is fixedly embedded in the inner side wall of each of the grooves (106) close to the cavity (102), and the two first bearings ( 103) are respectively communicated with the two cavities (102), the inner wall of each groove (106) away from the cavity (102) is fixedly embedded with a second bearing (107), and the two cavities (103) 102) A forward and reverse rotation motor (101) is fixedly connected to the inner walls that are close to each other, and a worm (104) is fixedly connected to the output end of each of the forward and reverse rotation motors (101), and the two worm screws (104) are respectively Passing through the two first bearings (103) and extending into the groove (106), the outer surfaces of the two worms (104) are respectively fixedly connected with the inner rings of the two first bearings (103), and the two worms The right side of the (104) is fixedly connected to the inner rings of the two second bearings (107) respectively, and the inner wall of each groove (106) is fixedly embedded with a third bearing (109). The inner rings of the three bearings (109) are fixedly connected with fixed columns (108), the front surfaces of each of the fixed columns (108) are fixedly connected with a worm wheel (110), and the two worm wheels (110) are respectively connected with the two worms (104) engage with each other, the outer surface of each of the fixing columns (108) is fixedly connected with a rectifying plate (105), and the first anti-impact mechanism (2) includes a slider (201), a first strong spring ( 202), a chute (203), a fixing block (204), a first pin (205), a fixing rod (206), a second pin (207) and a fixing plate (208), the cover head (4) The right side of the aircraft is fixedly connected with two relatively symmetrical fixing blocks (204), and the front of each said fixing block (204) is fixedly hinged with a fixing rod (206) through a first pin (205). A chute (203) is provided on the left side of the upper surface of the main body (9) and the left side of the bottom surface of the aircraft main body (9), and a fixing plate is placed above the aircraft main body (9) and below the aircraft main body (9). (208), one side of the two fixing plates (208) that are close to each other is fixedly connected with a slider (201) adapted to the chute (203), and the slider (201) is clamped in the chute (208). 203), the front surface of each fixing plate (208) is fixedly hinged with the side of the front surface of the fixing rod (206) away from the fixing block (204) through the second pin shaft (207), and each sliding block ( The right side of 201) is fixedly connected with a first strong spring (202), and the two first strong springs (202) ) are respectively fixedly connected to the inner side walls of the two sliding grooves (203), and the second anti-impact mechanism (3) includes a support block (301), a support rod (302), a second strong spring (303), a sliding The ring (304), the sliding rod (305), the first connecting block (306) and the second connecting block (307), the upper surface of the aircraft body (9) and the bottom surface of the aircraft body (9) are fixedly connected with the first connecting block (306). A connecting block (306), the upper surface of the aircraft body (9) and the bottom surface of the aircraft body (9) are fixedly connected with second connecting blocks (307), and the two second connecting blocks (307) are located at two On the right side of each of the first connecting blocks (306), a sliding rod (305) is fixedly connected to the right side of each of the first connecting blocks (306), and the right sides of the two sliding rods (305) are respectively are fixedly connected to the left sides of the two second connecting blocks (307), and the outer surface of each sliding rod (305) is sleeved with a sliding ring (304) that is adapted to the sliding rod (305). A second strong spring (303) is fixedly connected to the right side of each of the slip rings (304), and the two second strong springs (303) are respectively sleeved on the outer surfaces of the two sliding rods (305), And the right ends of the two second strong springs (303) are respectively fixedly connected with the left side surfaces of the two second connection blocks (307), and the side surfaces of the two slip rings (304) away from each other are fixedly connected with support rods. (302), one side of the two support rods (302) away from each other is fixedly connected with a support block (301), and one side of the two support blocks (301) away from each other is respectively connected with the two cover bodies (11) The sides that are close to each other are fixedly connected. 2 . The aircraft fairing with impact resistance according to claim 1 , wherein the left side of the cowl head ( 4 ) is provided with a first port ( 6 ), and the first port A first filter screen (5) is fixedly connected to the inner top wall of the port (6), and the bottom surface of the first filter screen (5) is fixedly connected to the inner bottom wall of the first through port (6). 3 . The aircraft fairing with impact resistance according to claim 2 , wherein a second port ( 10 ) is opened on the right side of the cowl tail ( 7 ), and the second port is 10 . 4 . A second filter screen (8) is fixedly connected to the inner top wall of the port (10), and the bottom surface of the second filter screen (8) is fixedly connected to the inner bottom wall of the second through port (10). 4 . The aircraft fairing with impact resistance according to claim 3 , wherein the upper and lower sides of the left side of the hood head ( 4 ) are arc-shaped, and the hood head ( 4 ) The maximum vertical length value of is equal to the vertical length value of the hood tail (7). 5. The aircraft fairing with impact resistance according to claim 4, characterized in that: the vertical length of the first through port (6) and the vertical length of the second through port (10) The values are equal, and the vertical length value of the aircraft body (9) is smaller than the vertical length value of the first port (6). 6. A kind of manufacturing method of the aircraft fairing with impact resistance according to claim 1, is characterized in that: the manufacturing method is as follows: S1, blank blanking, the cover head (4) and cover tail (7) are machined and formed, and a titanium alloy sheet with a thickness greater than the height of the cover body is used for blanking, and a certain machining allowance is left around, and the cover body (11) By hot pressing, according to the required length of the cover body (11), a titanium alloy plate with a thickness greater than the wall thickness of the cover body (11) is selected for blanking, and the outer surface is finely milled to the thickness of the cover body (11) for polishing; S2, the cover body (11) is hot-pressed, the parting surface of the hot-pressing die is evenly coated with alcohol graphite solution, and after air-drying, it is lightly polished with fine sandpaper, placed in the workpiece, and the concave and convex dies are aligned, and hot-pressed to ensure that the Press for 10-25s, then cool, open the mold and take out the workpiece; S3 , the hood head (4), the hood body (11) and the hood tail (7) are welded by laser welding or electron beam welding, and the welding temperature is kept at 750-800 degrees, so that the aircraft fairing can be made.

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