CN113247276B - Two-stage pneumatic separation type hypersonic air inlet duct fairing - Google Patents
Two-stage pneumatic separation type hypersonic air inlet duct fairing Download PDFInfo
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- CN113247276B CN113247276B CN202110735606.XA CN202110735606A CN113247276B CN 113247276 B CN113247276 B CN 113247276B CN 202110735606 A CN202110735606 A CN 202110735606A CN 113247276 B CN113247276 B CN 113247276B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/06—Attaching of nacelles, fairings or cowlings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
- B64D2033/026—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
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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
Abstract
The invention discloses a two-stage pneumatic separation type hypersonic air inlet duct fairing which comprises a resistance reducing unit and a plugging unit, wherein the resistance reducing unit is connected with the plugging unit through a pipeline; the drag reduction unit comprises a first-stage drag reduction module and a second-stage drag reduction module which are hinged, the head of the drag reduction unit faces the head of the aircraft and is positioned on the first-stage drag reduction module, and the tail of the drag reduction unit faces the tail of the aircraft and is positioned on the second-stage drag reduction module. The design of two-stage pneumatic separation is adopted, the fairing one-stage resistance reducing module is firstly opened only by small pneumatic downward pressure, and the profile of the fairing one-stage resistance reducing module after being opened at a certain angle can further generate larger pneumatic downward pressure to drive the fairing two-stage resistance reducing module to be opened together, so that the whole fairing is finally separated smoothly. The method solves the contradiction between the self pneumatic separating force requirement of the fairing and the resistance reduction and weight reduction of the shrouded state, and can meet the design requirement of the complicated-structure three-dimensional compression hypersonic inlet duct fairing, so that the fairing is more flexible and diversified in design.
Description
Technical Field
The invention relates to the technical field of aircraft air inlet passages, in particular to a two-stage pneumatic separation type hypersonic air inlet passage fairing.
Background
Fairings were originally proposed for rocket-transported payloads to protect the payload from the external harmful environment of aerodynamic forces, aerodynamic heat, and vibration. The common structure is a clamshell type (two halves) which comprises an end head, a front conical section, a cylindrical section, an inverted conical section, a longitudinal and transverse separating mechanism and the like.
For an air-breathing hypersonic aircraft, in order to ensure that a hypersonic air inlet channel normally works, other flight platforms such as a mounted aircraft and a boosting rocket are often needed. The hypersonic flight vehicle is sent to a designated flight altitude by the flight platform and reaches a designated initial flight speed. In the process from zero speed to the appointed flight Mach number, the air inlet channel of the hypersonic aircraft is completely exposed in the incoming flow of high total temperature air, so that on one hand, the flight resistance is increased, and meanwhile, parts such as the air inlet channel, a combustion chamber, a spray pipe and the like are easily damaged.
In order to solve the above problems, there are some existing solutions, for example, an air inlet lip of an aircraft is designed to be rotatable, the lip is closed in a boosting phase to prevent high total temperature air flow from entering the inside of an engine, and the lip is unscrewed after the boosting phase is finished. Except for the scheme of a rotary lip, most air-breathing hypersonic aircrafts adopt special separable fairing parts, and are mainly divided into a large-fairing scheme and a small-fairing scheme, wherein the large-fairing scheme adopts the mode that the whole aircraft or the head of the aircraft is completely shrouded, the volume and the weight are large, the shape is regular, and most of the air-breathing hypersonic aircrafts are spinning bodies; the small cover scheme only covers the air inlet channel to prevent air flow entering the air inlet channel, the volume and the weight are small, and the shape is irregular.
Among the above-mentioned prior art, the rotary lip scheme needs to actuate the mechanism specially, and the structure is complicated and can not separate to increase the structure weight of cruising aircraft. And the large cover scheme for wrapping the whole aircraft or the head of the aircraft has larger volume and structural weight of the fairing, and larger aerodynamic resistance in the boosting process. The increase in aerodynamic drag and the greater structural weight result in an increase in the scale of the booster, as well as the greater manufacturing costs of the cowling. The small cap solution requires an integrated design with the projectile and the inlet channel. The existing small cover scheme is designed with a large pneumatic compression surface in order to ensure that enough separated pneumatic force and moment are generated, and the shock waves generated by the compression surface are incident on the wall surface of an elastomer to generate serious shock wave/boundary layer interference, so that the flight resistance and the thermal protection difficulty of the elastomer and a fairing are increased.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the two-stage pneumatic separation type hypersonic inlet duct fairing, solves the contradiction between the self pneumatic separation force requirement of the fairing and the resistance reduction and weight reduction of the shrouded state, can meet the design requirement of a complicated-configuration three-dimensional compression hypersonic inlet duct fairing, and enables the fairing design to be more flexible and diversified.
In order to achieve the aim, the invention provides a two-stage pneumatic separation type hypersonic air inlet duct fairing which comprises a resistance reducing unit and a plugging unit, wherein a plugging structure capable of plugging an inlet of an air inlet duct is arranged on the plugging unit;
the head of each drag reduction unit is folded at one point, the tail of each drag reduction unit is connected with the head of each plugging unit, the drag reduction units are gradually widened and thickened along the direction from the heads to the tails, and the tails of the plugging units are detachably and fixedly connected with the outer wall surface of the bottom of the air inlet channel through first connecting structures;
the drag reduction unit comprises a first-stage drag reduction module and a second-stage drag reduction module which are in contact connection, the bottoms of two matching surfaces between the first-stage drag reduction module and the second-stage drag reduction module are hinged through a hinge, the first-stage drag reduction module and the second-stage drag reduction module are connected with the outer wall surface of an aircraft through a second connecting structure, the head of the drag reduction unit faces the head of the aircraft and is positioned on the first-stage drag reduction module, and the tail of the drag reduction unit faces the tail of the aircraft and is positioned on the second-stage drag reduction module;
the lift force borne by the drag reduction units is greater than the resistance borne by the drag reduction units, and the lift force borne by the first-level drag reduction module is less than the resistance borne by the first-level drag reduction module.
In one embodiment, an angle fixing structure is arranged between the first-stage drag reduction module and the second-stage drag reduction module to fix an included angle between two matching surfaces between the first-stage drag reduction module and the second-stage drag reduction module.
In one embodiment, the drag reduction unit comprises a windward bottom surface, a windward side surface and a connecting top surface;
the number of the windward side surfaces is two, the windward bottom surface is connected with the two sides of the connecting top surface through the windward side surfaces, and the top of one windward side surface inclines towards the direction of the other windward side surface;
one part of the windward bottom surface, the windward side surface and the connecting top surface is positioned on the first-stage drag reduction module, and the other part of the windward bottom surface, the windward side surface and the connecting top surface is positioned on the second-stage drag reduction module;
the hinge is arranged on the windward bottom surface, and the second connecting structure is arranged on the connecting top surface.
In one embodiment, the windward bottom surface is a cambered surface structure which gradually widens and is convex downwards along the head part to the tail part.
In one embodiment, the windward side surface is a plane structure which gradually widens from the head to the tail.
In one embodiment, the plugging unit comprises a connecting bottom surface and a plugging surface as the plugging structure;
the plugging surface is respectively connected with the tail part of the windward bottom surface, the tail part of the windward side surface and the tail part of the connecting top surface, the head part of the connecting bottom surface is connected with the tail part of the windward bottom surface, and the second connecting structure is arranged at the tail part of the connecting bottom surface.
In one embodiment, the first connecting structure comprises a first connecting part and a second connecting part, the first connecting part is fixedly arranged at the tail part of the connecting bottom surface, and the second connecting part is fixedly arranged on the outer wall surface of the bottom of the air inlet channel;
the first connecting part is provided with a first embedding part and a first embedding groove at intervals along the direction from the head part to the tail part, the second connecting part is provided with a second embedding groove and a second embedding part at intervals along the direction from the head part to the tail part, the first embedding part is embedded and connected on the first embedding groove, and the second embedding part is embedded and connected on the second embedding groove;
the first embedding part and the matching surface between the first embedding grooves and the matching surface between the second embedding parts and the second embedding grooves are cambered surfaces, so that the first connecting part can rotate around the second connecting part under the driving of external moment and is separated from the second connecting part after rotating for a certain angle.
In one embodiment, the second connecting structure is an explosive bolt.
Compared with the prior art, the two-stage pneumatic separation type hypersonic air inlet duct fairing provided by the invention has the following beneficial technical effects:
1. a complex mechanical actuating mechanism is not needed, separation is realized only by pneumatic force, and the structure is simple;
2. by adopting the two-stage separation design idea, compared with a single-stage separation scheme which needs to separate the whole fairing, the required pneumatic separation force is reduced only by firstly separating the fairing at one stage, so that the pneumatic pressing surface is reduced, the fairing profile design is more flexible, and the pneumatic resistance caused by the fairing can be greatly reduced;
3. by adopting the two-stage separation design concept, compared with a single-stage separation scheme, the size of the fairing is shortened, the structural strength requirement is lower, and therefore the weight of the fairing is lighter.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is an isometric view of a fairing in an embodiment of the invention;
FIG. 2 is a top view of a fairing in an embodiment of the invention;
FIG. 3 is a bottom view of a fairing in an embodiment of the invention;
FIG. 4 is an exploded view of a first connection structure in accordance with an embodiment of the present invention;
FIG. 5 is a cross-sectional view of a first coupling structure in an embodiment of the present invention;
FIG. 6 is an isometric view of an aircraft in a boosting phase in an embodiment of the present invention;
FIG. 7 is a bottom view of the aircraft in a boost phase in an embodiment of the present invention;
FIG. 8 is an isometric view of an aircraft in an embodiment of the invention with the primary and secondary drag reduction modules separated;
FIG. 9 is an isometric view of an aircraft fairing in an embodiment of the invention about to be removed;
FIG. 10 is an isometric view of an aircraft with a fairing detached employing an embodiment of the invention.
The reference numbers illustrate:
the device comprises a first-stage drag reduction module 10, a first windward bottom plate 101, a first windward side plate 102 and a first connecting top plate 103;
the second-stage drag reduction module 20, a second windward bottom plate 201, a second windward side plate 202 and a second connecting top plate 203;
a first connecting plate 301, a second connecting plate 302 and a hinge 303;
the sealing unit 40, the connecting bottom surface 401 and the sealing surface 402;
the first connecting structure 50, the first connecting portion 501, the second connecting portion 502, the first insertion portion 503, the first insertion groove 504, the second insertion groove 505, and the second insertion portion 506;
a second connecting structure 60;
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes 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 at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
Fig. 1 to 10 show a two-stage pneumatic separation type hypersonic air inlet duct fairing disclosed in this embodiment, which mainly includes a drag reduction unit and a plugging unit 40, where the plugging unit 40 is provided with a plugging structure capable of plugging an inlet of an air inlet duct 701. The head parts of the resistance reducing units are gathered at one point, the tail parts of the resistance reducing units are connected with the head parts of the plugging units 40, and the resistance reducing units are gradually widened and thickened along the direction from the head parts to the tail parts, namely the whole resistance reducing units are of a conical structure. The tail part of the plugging unit 40 is detachably and fixedly connected with the bottom outer wall surface of the air inlet passage 701 through the first connecting structure 50.
In this embodiment, the drag reduction unit includes the first-order drag reduction module 10 and the second-order drag reduction module 20 that contact is continuous, the bottom of two fitting surfaces between the first-order drag reduction module 10 and the second-order drag reduction module 20 is articulated through hinge 303, and the first-order drag reduction module 10, the second-order drag reduction module 20 all links to each other with the outer wall of aircraft 70 through second connection structure 60, the head of drag reduction unit faces the head of aircraft 70 and is located first-order drag reduction module 10, the afterbody of drag reduction unit faces the afterbody of aircraft 70 and is located second-order drag reduction module 20, and first-order drag reduction module 10, the in-process of second-order drag reduction module 20 connecting on the outer wall of aircraft 70 through second connection structure 60, the top of first-order drag reduction module 10, the top of second-order drag reduction module 20 all pastes with the outer wall of aircraft 70. In the same hypersonic incoming flow, the lift force borne by the drag reduction unit is greater than the resistance borne by the drag reduction unit, and the lift force borne by the first-stage drag reduction module 10 is less than the resistance borne by the drag reduction unit.
In this embodiment, an angle fixing structure is disposed between the first-stage drag reduction module 10 and the second-stage drag reduction module 20 to fix an included angle between two mating surfaces of the first-stage drag reduction module 10 and the second-stage drag reduction module 20, which can prevent the first-stage drag reduction module 10 and the second-stage drag reduction module 20 from being opened at too large angles, and can also keep the position between the first-stage drag reduction module 10 and the second-stage drag reduction module 20 relatively fixed, thereby preventing the first-stage drag reduction module 10 and the second-stage drag reduction module 20 from being attached again. In the specific implementation process, the angle fixing structure can adopt a common car door opening stopper in the market, and therefore the details are not repeated in the embodiment.
In this embodiment, when the aircraft 70 with the fairings is in the boosting stage shown in fig. 6 to 7, the resistance reducing units are in the first state, that is, two matching surfaces between the first-stage resistance reducing module 10 and the second-stage resistance reducing module 20 are mutually attached, and the top of the first-stage resistance reducing module 10 and the top of the second-stage resistance reducing module 20 are both attached to the outer wall surface of the aircraft 70, so that the lift force applied to the resistance reducing units is greater than the resistance applied to the resistance reducing units, and it is further ensured that the fairings are integrally fixed relative to the aircraft 70, and the blocking structures on the blocking units 40 cover the inlets of the air inlets 701. When the cowling needs to be separated after the boosting stage, the second connecting structure 60 on the first-stage drag reduction module 10 is controlled to fail, so that the first-stage drag reduction module 10 is separated from the outer wall surface of the aircraft 70, the first-stage drag reduction module 10 rotates downwards at the position of the hinge 303, the first-stage drag reduction module 10 and the second-stage drag reduction module 20 keep a certain included angle and are relatively fixed under the action of the angle fixing structure, and meanwhile, a gap exists between the first-stage drag reduction module 10 and the outer wall surface of the aircraft 70, namely, as shown in fig. 8. The hypersonic incoming flow stagnates in the gap, the pressure rises, and the downward resistance of the first-stage resistance reducing module 10 is further increased, so that the lift force borne by the resistance reducing units is smaller than the resistance borne by the resistance reducing units at the moment. Subsequently, the second connecting structure 60 on the secondary drag reduction module 20 is controlled to be disabled, so that the secondary drag reduction module 20 is separated from the outer wall surface of the aircraft 70, and at this time, under the action of the resistance, the whole fairing rotates downwards by taking the first connecting structure 50 as an axis, which is shown in fig. 9; when the rotation reaches a certain angle, the first connecting structure 50 fails, and the cowling assembly is thrown away in a six-degree-of-freedom motion, completing the separation from the aircraft 70, as shown in fig. 10.
In this embodiment, the drag reduction unit includes a windward bottom surface, a windward side surface, and a connection top surface. Specifically, the number of the windward side surfaces is two and is mutually symmetrical, and the windward bottom surface and the two sides of the connecting top surface are connected through one windward side surface. The windward side is a plane structure gradually widening from the head to the tail, and the top of one windward side inclines towards the direction of the other windward side so as to provide downward resistance for the resistance reducing unit. The windward bottom surface is of a cambered surface structure which is gradually widened and is downward convex from the head to the tail so as to provide upward lift force for the drag reduction unit. If the specific size and the curved surface configuration of the windward bottom surface, the specific size and the inclination angle of the windward side surface are designed, and how to divide the first-stage drag reduction module 10 and the second-stage drag reduction module 20, the effect that the lift force borne by the drag reduction unit is larger than the resistance borne by the drag reduction unit and the lift force borne by the first-stage drag reduction module 10 is smaller than the resistance borne by the drag reduction unit in the same hypersonic incoming flow is achieved. On the premise of the connection structure of each component, the conventional technical means in the technical field of pneumatic layout are adopted, and therefore details of the connection structure are not repeated in this embodiment.
In a specific implementation process, the windward bottom surface includes a first windward bottom plate 101 and a second windward bottom plate 201, the windward side surface includes a first windward side plate 102 and a second windward side plate 202, and the connection top surface includes a first connection top plate 103 and a second connection top plate 203. The first windward bottom plate 101, the first windward side plate 102 and the first connecting top plate 103 are all located on the first-stage drag reduction module 10, and the second windward bottom plate 201, the second windward side plate 202 and the second connecting top plate 203 are all located on the second-stage drag reduction module 20. The head of the first windward base plate 101, the head of the first windward side plate 102 and the head of the first connecting top plate 103 are all folded at the head of the drag reduction unit, the tail of the first windward base plate 101, the tail of the first windward side plate 102 and the tail of the first connecting top plate 103 are respectively connected with the head of the second windward base plate 201, the head of the second windward side plate 202 and the head of the second connecting top plate 203, and the tail of the second windward base plate 201, the tail of the second windward side plate 202 and the tail of the second connecting top plate 203 are all fixedly connected with the plugging unit 40. The hinge 303 is connected between the tail of the first windward base plate 101 and the head of the second windward base plate 201. The second connecting structures 60 are explosion bolts and are two in number, one of which is provided on the first connecting top plate 103 and the other of which is provided on the second connecting top plate 203.
As a preferred embodiment, the drag reduction unit further comprises a first connecting plate 301 and a second connecting plate 302, wherein the tail of the first windward base plate 101, the tail of the first windward side plate 102 and the tail of the first connecting top plate 103 are all connected with the first connecting plate 301, and a first cavity is enclosed among the first windward base plate 101, the first windward side plate 102, the first connecting top plate 103 and the first connecting plate 301; the head of the second windward bottom plate 201, the head of the second windward side plate 202 and the head of the second connecting top plate 203 are all connected with the second connecting plate 302, and a second cavity is defined by the second windward bottom plate 201, the second windward side plate 202, the second connecting top plate 203, the second connecting plate 302 and the blocking unit 40. And then can also ensure the stability of the configuration of the drag reduction unit while effectively reducing the quality of the drag reduction unit.
In the present embodiment, the plugging unit 40 includes a connection bottom surface 401 and a plugging surface 402 as a plugging structure. It should be noted that when the air inlet 701 has a V-lip configuration, the bottom connecting surface 401 also belongs to a blocking structure, i.e., the blocking surface 402 is used for blocking the inlet in front of the air inlet 701, and the bottom connecting surface 401 is used for blocking the inlet at the bottom of the air inlet 701. The plugging surface 402 is connected with the tail part of the second windward bottom plate 201, the tail part of the second windward side plate 202 and the tail part of the second connecting top plate 203 respectively so as to form the second cavity, the head part of the connecting bottom surface 401 is connected with the tail part of the windward bottom surface, and the second connecting structure 60 is arranged at the tail part of the connecting bottom surface 401.
In this embodiment, the first connecting structure 50 includes a first connecting portion 501 and a second connecting portion 502, the first connecting portion 501 is fixedly disposed at the tail portion of the connecting bottom surface 401, and the second connecting portion 502 is fixedly disposed on the outer wall surface of the bottom of the air inlet channel 701. The first connecting portion 501 is provided with a first embedded portion 503 and a first embedded groove 504 at intervals along the direction from the head portion to the tail portion, the second connecting portion 502 is provided with a second embedded groove 505 and a second embedded portion 506 at intervals along the direction from the head portion to the tail portion, the first embedded portion 503 is embedded and connected to the first embedded groove 504, and the second embedded portion 506 is embedded and connected to the second embedded groove 505. The mating surfaces between the first insertion portion 503 and the first insertion groove 504 and between the second insertion portion 506 and the second insertion groove 505 are arc surfaces, so that the first connection portion 501 can rotate around the second connection portion 502 under the driving of an external moment and is separated from the second connection portion 502 after rotating a certain angle.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (5)
1. A two-stage pneumatic separation type hypersonic air inlet duct fairing is characterized by comprising a resistance reducing unit and a plugging unit, wherein a plugging structure capable of plugging an inlet of an air inlet duct is arranged on the plugging unit;
the head of the drag reduction unit is folded at one point, the tail of the drag reduction unit is connected with the head of the plugging unit, the drag reduction unit is gradually widened and thickened along the direction from the head to the tail, and the tail of the plugging unit is detachably and fixedly connected with the outer wall surface of the bottom of the air inlet channel through a first connecting structure;
the drag reduction unit comprises a first-stage drag reduction module and a second-stage drag reduction module which are in contact connection, the bottoms of two matching surfaces between the first-stage drag reduction module and the second-stage drag reduction module are hinged through a hinge, the first-stage drag reduction module and the second-stage drag reduction module are connected with the outer wall surface of an aircraft through a second connecting structure, the head of the drag reduction unit faces the head of the aircraft and is positioned on the first-stage drag reduction module, and the tail of the drag reduction unit faces the tail of the aircraft and is positioned on the second-stage drag reduction module;
the lift force borne by the drag reduction units is greater than the resistance borne by the drag reduction units, and the lift force borne by the first-level drag reduction module is less than the resistance borne by the first-level drag reduction module;
the resistance reducing unit comprises a windward bottom surface, a windward side surface and a connecting top surface;
the number of the windward side surfaces is two, the windward bottom surface is connected with the two sides of the connecting top surface through the windward side surfaces, and the top of one windward side surface inclines towards the direction of the other windward side surface;
one part of the windward bottom surface, the windward side surface and the connecting top surface is positioned on the first-stage drag reduction module, and the other part is positioned on the second-stage drag reduction module;
the hinge is arranged on the windward bottom surface, and the second connecting structure is arranged on the connecting top surface;
the plugging unit comprises a connecting bottom surface and a plugging surface serving as the plugging structure;
the plugging surface is respectively connected with the tail part of the windward bottom surface, the tail part of the windward side surface and the tail part of the connecting top surface, the head part of the connecting bottom surface is connected with the tail part of the windward bottom surface, and the first connecting structure is arranged at the tail part of the connecting bottom surface;
the first connecting structure comprises a first connecting part and a second connecting part, the first connecting part is fixedly arranged at the tail part of the connecting bottom surface, and the second connecting part is fixedly arranged on the outer wall surface of the bottom of the air inlet channel;
the first connecting part is provided with a first embedding part and a first embedding groove at intervals along the direction from the head part to the tail part, the second connecting part is provided with a second embedding groove and a second embedding part at intervals along the direction from the head part to the tail part, the first embedding part is embedded and connected on the first embedding groove, and the second embedding part is embedded and connected on the second embedding groove;
the first embedding part and the matching surface between the first embedding grooves and the matching surface between the second embedding parts and the second embedding grooves are cambered surfaces, so that the first connecting part can rotate around the second connecting part under the driving of external moment and is separated from the second connecting part after rotating for a certain angle.
2. The two-stage pneumatic separation type hypersonic air inlet duct fairing according to claim 1, characterized in that an angle fixing structure is arranged between the first-stage drag reduction module and the second-stage drag reduction module to fix an included angle between two matching surfaces between the first-stage drag reduction module and the second-stage drag reduction module.
3. The two-stage aerodynamic separation type hypersonic air inlet duct fairing according to claim 1 or 2, characterized in that the windward bottom surface is a cambered surface structure which is gradually widened and is downward convex from the head to the tail.
4. The two-stage aerodynamic separation type hypersonic inlet duct fairing according to claim 1 or 2, characterized in that the windward side is a plane structure which gradually widens from head to tail.
5. The two-stage aerodynamic separation hypersonic inlet duct fairing according to claim 1 or 2, characterized in that said second attachment structure is an explosion bolt.
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| CN202110735606.XA CN113247276B (en) | 2021-06-30 | 2021-06-30 | Two-stage pneumatic separation type hypersonic air inlet duct fairing |
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| CN202110735606.XA CN113247276B (en) | 2021-06-30 | 2021-06-30 | Two-stage pneumatic separation type hypersonic air inlet duct fairing |
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| CN114753928B (en) * | 2022-05-18 | 2023-08-18 | 华中科技大学 | Novel air inlet channel protective cover |
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| CN113247276A (en) | 2021-08-13 |
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