Drag reducer for aircraft

Abstract

The present invention discloses a drag reducer for an aircraft, comprising: cylinders that can be telescopically sleeved with each other, with a plurality of cylinders having a hollow interior and gradually increasing in size; and a buckling structure is provided between the inner and outer diameter surfaces of the cylinders to achieve a cooperation that can extend but not retract. Since the cooperation that can extend but not retract is achieved between the inner and outer diameter surfaces of the cylinders through the buckling structure, after the plurality of cylinders slide and extend with each other, they are always in the extended state through the buckling structure without the need to apply force to maintain, and more energy on the aircraft can be used for flight, thereby improving the flight range of the aircraft and solving the problem that the telescopic rod needs to continuously consume energy during flight drag reduction.

Description

Technical Field

[0001] The present invention relates to a drag reducer for an aircraft, belonging to the technical field of devices for reducing air resistance. Background Art

[0002] When an aircraft is flying at high speed, it needs to overcome the earth's gravity and air friction resistance. In order to reduce the air resistance received by the whole head of the aircraft, a drag reducer needs to be installed at the head of the aircraft to reduce the aerodynamic drag, thereby increasing the flight range of the aircraft.

[0003] In a telescopic thermal protection nose of a space aircraft with a Chinese patent publication number of CN113501146A, the adopted technology is as follows: the telescopic rod is telescopically arranged at the front of the nose cone of the space aircraft and coincides with the axis of the nose cone of the space aircraft; although the telescopic rod installed at the head of the aircraft can reduce the aerodynamic drag, however, when the flight acceleration reaches 2g, the telescopic rod will also be subjected to a large retracting force, then a power source for the telescopic rod is required to provide a force to maintain the extended state of the telescopic rod, and there is a problem that the telescopic rod needs to continuously consume energy during flight drag reduction, resulting in a reduction in the flight range of the aircraft. Summary of the Invention

[0004] To solve the above technical problems, the present invention provides a drag reducer for an aircraft.

[0005] The present invention is achieved through the following technical solutions.

[0006] A drag reducer for an aircraft provided by the present invention includes:

[0007] Barrels that can be slidably and telescopically sleeved with each other, and the number of barrels is multiple, and the inner parts are hollow and the sizes increase in sequence;

[0008] The inner and outer diameter surfaces of the barrels are in a non-retractable but extendable fit through an inverted buckle structure.

[0009] The inner and outer diameter surfaces of the barrels are hermetically and slidably sleeved through a rubber sealing ring.

[0010] A sealing disc is fixed at the end of the barrel to seal the mating ends of the barrels.

[0011] The reverse buckling structure includes a first reverse buckle and a second reverse buckle that cooperates with the inclined surface of the first reverse buckle. The first reverse buckle is fixedly connected to the inner diameter surface at one end of the cylinder body by screws or pins or integrally. The first reverse buckle extends obliquely towards the inner diameter surface. The second reverse buckle is fixedly connected to the outer diameter surface at the other end of the cylinder body by screws or pins or integrally. There is a gap between the second reverse buckle and the outer diameter surface of the cylinder body. During the cooperation process between the second reverse buckle and the inclined surface of the first reverse buckle, the second reverse buckle on the smaller outer diameter surface of the cylinder body undergoes elastic deformation and is in the gap with the outer diameter surface of the cylinder body. After the second reverse buckle cooperates with the inclined surface of the first reverse buckle, the first reverse buckle on the larger inner diameter surface of the cylinder body presses against the second reverse buckle to form a reverse buckle, so that the cylinder bodies cannot retract from each other.

[0012] A sealing plate is fixed to the outer side end of the cylinder body at the leftmost end. The sealing plate blocks the hollow port of the cylinder body for sealing.

[0013] A male card lock device is fixed to the outer side end of the cylinder body at the leftmost end, and a female card lock device is fixed to the outer side of the cylinder body at the rightmost end. The female card lock device can inject high-pressure gas into the interiors of multiple cylinder bodies to make the cylinder bodies slide and extend from each other. The smaller cylinder body with the second reverse buckle extends into and is installed through the right port of the larger cylinder body. When the cylinder bodies are in a completely overlapping state, the male card lock device on the leftmost cylinder body is locked with the female card lock device on the rightmost cylinder body.

[0014] The male card lock device includes a lock disc fixed to the cylinder body. A blind hole is provided on the axis of the lock disc. Through holes are provided on the lock disc on both sides of the blind hole. Elastic reset telescopic installations of clamping shafts are arranged in the through holes on both sides through a plug A and a spring A. The two clamping shafts can radially extend into the blind hole on the axis of the lock disc to be locked with the locking holes of the female card lock device.

[0015] The female card lock device includes a gas generating body that can generate high-pressure gas and inject it into the cylinder body, a chuck installed on the gas generating body. An air passage through hole is provided in the middle of the chuck to communicate with the exhaust hole of the gas generating body. A top shaft is installed in the air passage through hole of the chuck through a plug B and a spring B. The top shaft can press the spring B and slide in the air passage through hole of the chuck. Locking holes for the two clamping shafts to extend into and be locked are provided on both sides of the chuck.

[0016] It further includes a fixed disc fixedly installed on the cylinder body. The fixed disc is fixedly installed on the outer periphery of the cylinder body away from the second section of the female card lock device.

[0017] The beneficial effects of the present invention are as follows: Since the cylinder bodies are cooperated to be extendable but not retractable through the reverse buckling structure between their inner and outer diameter surfaces, after multiple cylinder bodies slide and extend from each other, they are always in an extended state through the reverse buckling structure without the need to provide force to maintain. The energy on the aircraft can be more used for flight, thereby increasing the flight range of the aircraft and solving the problem that the retractable telescopic rod needs to continuously consume energy during flight to reduce drag. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a cross-sectional schematic diagram of the present invention in an extended state;

[0019] Figure 2 yes Figure 1 Partial schematic diagram at the middle left end;

[0020] Figure 3 is an external schematic diagram of the present invention in an extended state;

[0021] Figure 4 is a cross-sectional schematic diagram of the present invention when overlapping and ready to be extended;

[0022] Figure 5 It is a cross-sectional schematic diagram of the undercut structure of the present invention;

[0023] Figure 6 It is a cross-sectional schematic diagram of the cylinder and the male card lock device of the present invention;

[0024] Figure 7 It is a partial cross-sectional schematic diagram of the female locking device of the present invention;

[0025] Figure 8 It is a cross-sectional schematic diagram of the cylinder of the present invention;

[0026] In the figure: 1-sealing plate; 2-cylinder; 3-sealing disk; 4-inverted structure; 41-first inverted; 42-second inverted; 5-rubber sealing ring; 6-male locking device; 7-fixing disk; 8-female locking device; 21-locking disk; 22-screw plug A; 23-spring A; 24-clamping shaft; 31-gas generating body; 30-clamping disk; 27-screw plug B; 28-spring B; 29-top shaft. DETAILED DESCRIPTION

[0027] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0028] like Figures 1 to 8 shown.

[0029] The present application discloses a drag reducer for an aircraft, specifically a drag reducer installed at the front end of the aircraft, comprising:

[0030] There are multiple hollow cylinders 2 with increasing sizes that can slide and telescope mutually. The cylinders 2 can be nine sections. The inner and outer diameter surfaces of the cylinders 2 are sealed and can slide mutually via rubber sealing rings 5. The ends of the cylinders 2 are fixed with sealing disks 3 via threaded pairs to seal the ends of the cylinders 2. The outer periphery of the cylinders 2 is provided with grooves for installing and accommodating the rubber sealing rings 5.

[0031] The inner and outer diameter surfaces of the cylinders 2 are connected to each other via an undercut structure 4 to achieve an extendable but non-retractable fit.

[0032] The reverse buckle structure 4 includes a first reverse buckle 41 and a second reverse buckle 42 that cooperates with the inclined surface of the first reverse buckle 41. The first reverse buckle 41 is fixedly connected to the inner diameter surface of one end of the cylinder 2 by screws or pins or integrally. The first reverse buckle 41 extends obliquely towards the inner diameter surface. The second reverse buckle 42 is fixedly connected to the outer diameter surface of the other end of the cylinder 2 by screws or pins or integrally. There is a gap between the second reverse buckle 42 and the outer diameter surface of the cylinder 2. During the cooperation process between the second reverse buckle 42 and the inclined surface of the first reverse buckle 41, the second reverse buckle 42 located on the smaller outer diameter surface of the cylinder 2 undergoes elastic deformation and is in the gap with the outer diameter surface of the cylinder 2. After the second reverse buckle 42 and the inclined surface of the first reverse buckle 41 are matched, the first reverse buckle 41 located on the larger inner diameter surface of the cylinder 2 abuts against the second reverse buckle 42 to form a reverse buckle, so that the cylinders 2 cannot retract from each other.

[0033] Since the cylinders 2 can be extended but not retracted through the reverse buckle structure 4 between their inner and outer diameter surfaces, after multiple cylinders 2 slide out from each other, they are always in the extended state through the reverse buckle structure 4 without the need to provide force to maintain. The energy on the aircraft can be more used for flight, thereby increasing the flight range of the aircraft and solving the problem that the telescopic telescopic rod needs to continuously consume energy during flight to reduce drag.

[0034] A sealing plate 1 is screwed and sealedly fixed to the outer side end of the cylinder 2 at the leftmost end. The sealing plate 1 blocks the hollow port of the cylinder 2 for sealing.

[0035] A male card lock device 6 is screwed and fixed to the outer side end of the cylinder 2 at the leftmost end, and a female card lock device 8 is screwed and fixed to the outer side of the cylinder 2 at the rightmost end. The female card lock device 8 can inject high-pressure gas into the interiors of multiple cylinders 2 to make the cylinders 2 slide out from each other. During production and assembly, the smaller cylinder 2 with the second reverse buckle 42 is inserted into the right port of the larger cylinder 2 from the right. When the nine cylinders 2 are in a completely overlapping state, the male card lock device 6 on the leftmost cylinder 2 is locked with the female card lock device 8 on the rightmost cylinder 2 to ensure that the nine cylinders 2 are locked in a completely overlapping state.

[0036] The male card lock device 6 includes a lock plate 21 fixed to the cylinder 2 by screws. A blind hole is provided on the axis of the lock plate 21. Through holes are provided on the lock plate 21 on both sides of the blind hole. In the through holes on both sides, clamping shafts 24 are elastically and retractably installed through plug A 22 and spring A 23. The two clamping shafts 24 can radially extend into the blind hole on the axis of the lock plate 21 to be locked with the locking holes of the female card lock device 8.

[0037] The female locking device 8 comprises a gas generator 31 which can generate high-pressure gas to rush into the cylinder 2, a chuck 30 installed on the gas generator 31, an airway through hole is provided in the middle of the chuck 30 to communicate with the exhaust hole of the gas generator 31, a top shaft 29 is installed in the airway through hole of the chuck 30 via a screw plug B27 and a spring B28, and the top shaft 29 can slide in the airway through hole of the chuck 30 by pressing the spring B28, and there are locking holes on both sides of the chuck 30 for two locking shafts 24 to extend into the locking, and when the gas generator 31 generates high-pressure gas to be discharged, the gasway through hole of the chuck 30 that first enters the top shaft is pressed against the airway through hole of the chuck 30. 29 presses the spring B28 to slide, and the card shaft 24 is pushed out by the top shaft 29 to realize the release of the locking state of the male locking device 6 and the female locking device 8. Then, the high-pressure gas continuously generated by the gas generator 31 can be discharged from the card hole and rushed into the interior of multiple cylinders 2 to make the cylinders 2 slide and extend relative to each other. The cylinders 2 slide and extend relative to each other, so that the second undercut 42 is elastically deformed and is in the gap with the outer diameter surface of the cylinder 2. After the second undercut 42 is matched with the inclined surface of the first undercut 41, the first undercut 41 is against the second undercut 42 and is in an undercut state, so that the cylinders 2 cannot be retracted after extending relative to each other.

[0038] It also includes a fixing plate 7 fixedly mounted on the cylinder 2. The fixing plate 7 is fixedly mounted on the outer periphery of the cylinder 2 away from the second section of the female locking device 8. The fixing plate 7 provides a basis for the whole to be installed on the aircraft.

Claims

1. A decelerator for an aircraft, characterized in that, Including: A plurality of cylinders (2) that can slide and telescopically fit with each other, with a hollow interior and gradually increasing sizes; A reverse buckling structure (4) is provided between the inner and outer diameter surfaces of the cylinders (2) to achieve a cooperation that can extend but not retract; A male locking device (6) is fixed to the outer end of the cylinder (2) at the leftmost end, and a female locking device (8) is fixed to the outside of the cylinder (2) at the rightmost end. The female locking device (8) can inject high-pressure gas into the interiors of the plurality of cylinders (2) to cause the cylinders (2) to slide and extend relative to each other. The smaller cylinder (2) with the second reverse buckle (42) extends into and is installed through the right opening of the larger cylinder (2). When the cylinders (2) are in a completely overlapping state, the male locking device (6) on the leftmost cylinder (2) is locked with the female locking device (8) on the rightmost cylinder (2); The male locking device (6) includes a locking disk (21) fixed to the cylinder (2). A blind hole is provided on the axis of the locking disk (21), and through holes are provided on the locking disk (21) on both sides of the blind hole. A locking shaft (24) is elastically and telescopically installed in the through holes on both sides through a plug A (22) and a spring A (23), and the two locking shafts (24) can radially extend into the blind hole on the axis of the locking disk (21) to be locked with the locking holes of the female locking device (8); The female locking device (8) includes a gas generating body (31) that can generate high-pressure gas and inject it into the cylinder (2), a chuck (30) installed on the gas generating body (31). An air passage through hole is provided in the middle of the chuck (30) to communicate with the exhaust hole of the gas generating body (31). A top shaft (29) is installed in the air passage through hole of the chuck (30) through a plug B (27) and a spring B (28). The top shaft (29) can compress the spring B (28) and slide in the air passage through hole of the chuck (30). Locking holes for the two locking shafts (24) to extend into and be locked are provided on both sides of the chuck (30); After the high-pressure gas generated by the gas generating body (31) is discharged, it first enters the air passage through hole of the chuck (30) to push the top shaft (29) and compress the spring B (28) to slide. By the top shaft (29), the locking shafts (24) are pushed out to release the locked state between the male locking device (6) and the female locking device (8). Then, the high-pressure gas continuously generated by the gas generating body (31) can be discharged from the locking holes and injected into the interiors of the plurality of cylinders (2) to cause the cylinders (2) to slide and extend relative to each other.

2. The airspeed reducer of the aircraft according to claim 1, characterized in that: The cylinders (2) are sealed and slidably sleeved with each other through a rubber sealing ring (5) between their inner and outer diameter surfaces.

3. The decelerator of the aircraft as described in claim 1, characterized in that: A sealing disk (3) is fixed to the end of the cylinder (2) to seal the mating ends of the cylinders (2).

4. The decelerator of the aircraft according to claim 1, wherein: The reverse buckling structure (4) includes a first reverse buckle (41) and a second reverse buckle (42) that cooperates with the inclined surface of the first reverse buckle (41). The first reverse buckle (41) is fixedly connected to the inner diameter surface at one end of the cylinder body (2) by screws or pins or integrally. The first reverse buckle (41) extends obliquely towards the inner diameter surface. The second reverse buckle (42) is fixedly connected to the outer diameter surface at the other end of the cylinder body (2) by screws or pins or integrally. There is a gap between the second reverse buckle (42) and the outer diameter surface of the cylinder body (2). During the cooperation process between the second reverse buckle (42) and the inclined surface of the first reverse buckle (41), the second reverse buckle (42) on the outer diameter surface of the smaller cylinder body (2) undergoes elastic deformation and is in the gap with the outer diameter surface of the cylinder body (2). After the second reverse buckle (42) and the inclined surface of the first reverse buckle (41) are cooperated, the first reverse buckle (41) on the inner diameter surface of the larger cylinder body (2) abuts against the second reverse buckle (42) to form a reverse buckle, so that the cylinder bodies (2) cannot retract from each other.

5. The decelerator of the aircraft according to claim 1, characterized in that: A sealing plate (1) is fixed to the outer side end of the cylinder body (2) at the leftmost end. The sealing plate (1) blocks the hollow port of the cylinder body (2) for sealing.

6. The decelerator of the aircraft as claimed in claim 1, wherein: It further includes a fixed disk (7) fixedly installed on the cylinder body (2). The fixed disk (7) is fixedly installed on the outer circumference of the cylinder body (2) far from the second section of the female card locking device (8).

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