CN114426094B - Foldable air rudder of hypersonic aircraft - Google Patents
Foldable air rudder of hypersonic aircraft Download PDFInfo
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- CN114426094B CN114426094B CN202210353024.XA CN202210353024A CN114426094B CN 114426094 B CN114426094 B CN 114426094B CN 202210353024 A CN202210353024 A CN 202210353024A CN 114426094 B CN114426094 B CN 114426094B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type 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
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Abstract
The application provides a collapsible air rudder of hypersonic aircraft, including rudder face subassembly, tiller subassembly, the fixed subassembly of rudder face. The control surface fixing assembly is rotatably connected with the control handle assembly through the transmission shaft, the control surface assembly is provided with a radial locking structure, the control surface fixing assembly is provided with an axial locking structure, and the radial locking hole and the axial locking hole on the control handle assembly are matched, so that the control surface assembly is simultaneously locked from multiple directions after being automatically unfolded, and the strength of the connection position of the control surface assembly after being unfolded is obviously improved; the air rudder adopts a modular design, is convenient to assemble, has a compact integral structure and good sealing performance due to the fact that the transmission shaft and the torsion spring are structurally designed inside the air rudder; the control surface assembly, the rudder handle assembly and the control surface fixing assembly are provided with the heat-proof layers, so that the influence of aerodynamic heat on an internal structure in the hypersonic flight process can be effectively reduced, the stability, the reliability and the track precision of the aircraft in the flight process are improved, and the requirement of hypersonic stable flight in a high-temperature large overload environment is met.
Description
Technical Field
The invention relates to the technical field of air rudders, in particular to a foldable air rudder of a hypersonic aircraft.
Background
In recent years, the hypersonic aircraft technology is paid more and more attention by countries, and the hypersonic aircraft technology is developed into engineering technology development and application stages of hypersonic missiles, hypersonic scooters, hypersonic transport planes, atmospheric aircrafts, aerospace planes and the like from a basic research and exploration stage of concept principles. With the increase of application scenes, the foldable air rudder of the hypersonic aircraft convenient to store and transport becomes a research focus.
The foldable air rudder is an important executing mechanism for realizing attitude adjustment of the hypersonic aircraft and determines the reliability, stability, maneuverability and track precision of flight. Along with the increase of the flying speed, the folding rudder faces a severe aerodynamic force thermal environment, the number of the foldable air rudders which can meet the requirement of hypersonic speed application is small at present, and the foldable air rudders are research difficulties and hot spots in the field, so that the development of the folding rudder which can be unfolded quickly and locked reliably and can bear high temperature and large overload is significant.
Disclosure of Invention
In view of the above problem, this application aims at providing a collapsible air vane of hypersonic aircraft, can realize expandes the locking function fast, connects stable reliability height, can satisfy the aircraft and stabilize the flight requirement at the big overload environment of high temperature hypersonic.
The application provides a foldable air rudder of a hypersonic flight vehicle, which comprises,
a tiller assembly having a first end connected to the aircraft and a second, relatively remote end, and a first central plane and a tiller heat shield for thermal insulation; the second end is provided with a transmission shaft, and the axis direction of the transmission shaft is a first direction;
the control surface assembly is provided with a second central surface and a control surface heat-proof layer for heat insulation, wherein the second central surface is in a folded state forming a first included angle with the first central surface and in an unfolded state forming a second included angle with the first central surface; the first included angle is larger than the second included angle;
the control surface fixing assembly comprises a control surface connecting part for connecting the control surface assembly and a heat-proof layer of the control surface fixing assembly for heat insulation; the control surface fixing assembly is rotatably connected around the transmission shaft;
the rudder face fixing assembly and the rudder handle assembly are respectively provided with an axial locking structure and an axial locking hole which are matched for use, and the axis of the axial locking hole is parallel to the first direction; the control surface assembly and the rudder handle assembly are respectively provided with a radial locking structure and a radial locking hole which are matched with each other, the radial locking hole is arranged at the second end, and the axis of the radial locking hole is vertical to the first direction;
when the control surface assembly is in an unfolded state, the axial locking structure is matched and locked with the axial locking hole, and the radial locking structure is matched and locked with the radial locking hole.
According to the technical scheme provided by the embodiment, the axial locking structure comprises:
a drum rotatably connected to the drive shaft;
the axial locking cavity is arranged on one side, adjacent to the second end, in the rotary drum along the first direction, and an axial ejection port is formed in one side, adjacent to the second end, of the axial locking cavity;
the torsion spring structure is arranged on one side, far away from the second end, in the rotary drum along the first direction; the transmission shaft penetrates through the rotary drum and is connected with the inside of the torsion spring structure in a spline fit manner; the torsion spring structure is rotatably connected with the rotary drum;
the axial pressure spring is in a compressed state when the control surface assembly is in a folded state and is positioned in the axial locking cavity; one end of the axial pressure spring is detachably connected with the inner wall of the axial locking cavity;
the axial locking pin is detachably connected with the other end of the axial pressure spring and is arranged corresponding to the axial locking hole; axial locking round pin is in when the control surface subassembly is fold condition, with axial locking hole staggers when the control surface subassembly is expansion state, follow axial ejection of compact mouth pop out with axial locking hole cooperation is connected.
According to the technical scheme provided by the embodiment, the transmission shafts are respectively arranged on two sides of the second end of the tiller assembly; the control surface fixing assembly is provided with the axial locking structures corresponding to the transmission shaft, the control surface assembly is axially locked from two directions at the same time, the connection strength of the control surface assembly and the control handle assembly can be further improved, and the reliability and stability of the air rudder in the hypersonic speed flight process are guaranteed, so that the precision of the flight trajectory is guaranteed.
According to the technical scheme provided by the embodiment, the radial locking structure comprises:
the radial locking cavity is arranged on one side, adjacent to the second end, of the control surface assembly corresponding to the radial locking hole; a radial ejection port is formed in one side, adjacent to the second end, of the radial locking cavity;
the radial pressure spring is in a compressed state when the control surface assembly is in a folded state and is positioned in the radial locking cavity; one end of the radial pressure spring is detachably connected with the inner wall of the radial locking cavity;
the radial locking pin is detachably connected with the other end of the radial pressure spring and is arranged corresponding to the radial locking hole; radial locking round pin is in when the control surface subassembly is fold condition, with radial locking hole staggers when the control surface subassembly is the expansion state, follow radial ejection of compact mouth pop out with radial locking hole cooperation is connected.
According to the technical scheme provided by the embodiment, the tiller assembly is provided with a first through hole penetrating through the transmission shaft and the second end along the first direction; the control surface assembly is provided with a long pin shaft penetrating through the first through hole, the long pin shaft can ensure the coaxiality of the control surface assembly and the tiller assembly in the assembling and debugging process, and the overall connection strength of the air rudder can also be improved.
According to the technical scheme provided by the embodiment, the axial locking pin and the radial locking pin are respectively provided with an inner hole for containing the end part of the axial compression spring and an inner hole for containing the end part of the radial compression spring.
According to the technical scheme provided by the embodiment, the radial locking structure further comprises a pressure spring stop block connected with the inner wall of the radial locking cavity, one end, far away from the radial locking pin relatively, of the radial pressure spring is in butt joint with the pressure spring stop block, and the radial pressure spring is convenient to disassemble in the assembling and debugging process.
According to the technical scheme that this embodiment provided, the second end is equipped with and is used for adjusting the recess of rudder face subassembly folded state, through the adjustment as required the structure and the size of recess can make the rudder face subassembly reaches required folding angle.
According to the technical scheme provided by the embodiment, the hole wall of the inner hole is provided with a second through hole, and the second through hole is used for withdrawing the radial locking pin or the axial locking pin to the radial locking cavity or the axial locking cavity by using a tool in the assembling and debugging process.
According to the technical scheme provided by the embodiment, the control surface assembly and the control surface fixing assembly are respectively provided with the detachable radial locking cavity cover plate and the detachable axial locking cavity cover plate corresponding to the radial locking cavity and the axial locking cavity, so that the radial locking structure and the axial locking structure can be assembled, debugged and maintained conveniently.
According to the technical scheme provided by the embodiment, the rudder surface assembly further comprises a tail edge heat-proof plate and a front edge heat-proof plate for heat insulation and an anti-abrasion strip for protecting the air rudder from being collided and abraded.
In summary, the present application discloses a foldable air rudder of hypersonic aircraft, the beneficial effect that produces based on the above-mentioned scheme is, the air rudder includes rudder face subassembly, rudder stock subassembly and rudder face fixed subassembly, rudder face fixed subassembly pass through the transmission shaft on the rudder stock subassembly with rudder stock subassembly rotatable coupling, the rudder face subassembly passes through rudder face connecting portion on the rudder face fixed subassembly are connected to on the rudder stock subassembly, thereby realize the rudder face subassembly around the transmission shaft rotates foldingly, the rudder face subassembly is equipped with and is used for radial locking the radial locking structure of rudder face subassembly, rudder face fixed subassembly is equipped with and is used for axial locking the axial locking structure of rudder face subassembly, and correspond on the rudder stock subassembly be equipped with respectively with radial locking structure and axial locking structure complex radial locking hole and axial locking hole, thereby realize locking from a plurality of directions after the rudder face subassembly expandes, the connection strength and stability of the control surface assembly after being unfolded are obviously improved, and the reliability of the control surface assembly in the hypersonic flight process is guaranteed; this application adopts the modularized design, the assembly of being convenient for, and overall structure is compact, and the leakproofness is good, moreover rudder face subassembly, tiller subassembly, the fixed subassembly heat-proof layer of rudder face are equipped with rudder face heat-proof layer, tiller heat-proof layer, the fixed subassembly heat-proof layer of rudder face respectively, effectively reduce the influence of aerodynamic heat to inner structure in hypersonic flight in-process, have improved aircraft stability and reliability at flight in-process, have guaranteed the precision of flight orbit, have satisfied the aircraft and have stabilized the flight requirement at the big overload environment of high temperature hypersonic.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings.
Fig. 1 is a schematic structural diagram of a foldable air rudder of a hypersonic aircraft provided by the present application.
FIG. 2 is a schematic structural diagram of a control surface assembly of a foldable air rudder of a hypersonic aircraft according to an embodiment of the present application.
FIG. 3 is a schematic structural diagram of a control surface fixing assembly of a foldable air rudder of a hypersonic aircraft according to an embodiment of the present application.
FIG. 4 is a schematic structural diagram of a tiller assembly of a foldable air rudder of a hypersonic aircraft according to an embodiment of the application.
FIG. 5 is a schematic diagram of an unfolded state of a foldable air rudder of a hypersonic flight vehicle according to an embodiment of the present application.
FIG. 6 is a schematic view of a foldable air rudder of the hypersonic flight vehicle in a folded state according to the embodiment of the application.
FIG. 7 is a schematic side view of a control surface assembly and a tiller assembly of a foldable air rudder of a hypersonic aircraft according to an embodiment of the present application.
FIG. 8 is a schematic cross-sectional view of a first axial locking structure according to an embodiment of the present application.
In the figure, 1, a control surface assembly; 2. a long pin shaft; 3. a first rotating part; 4. a first rotating drum; 41. a first axial locking cavity cover plate; 42. a first axial locking cavity; 421. a first axial compression spring; 422. a first axial locking pin; 43. a first torsion spring structure; 44. a first splint; 45. a second splint; 46. a first torsion spring; 5. a radial locking cavity heat protection layer; 6. a first end; 7. a second end; 71. a first drive shaft; 72. a second transmission shaft; 73. a radial locking hole; 74. a tiller heat-proof layer; 8. a second rotating drum; 81. a second axial locking cavity cover plate; 82. a second axial locking cavity; 821. a second axial compression spring; 822. a second axial locking pin; 84. a third splint; 85. a fourth splint; 86. a second axial bore; 9. a second rotating part; 10. a leading edge thermal shield; 11. an anti-wear strip; 12. a first connecting plate; 13. a radial locking cavity cover plate; 14. a radial locking structure; 141. a radial locking pin; 142. a radial pressure spring; 15. a radial locking cavity; 16. a second connecting plate; 17. a control surface framework; 18. a trailing edge heat shield; 19. a pressure spring stop block; 20. a control surface heat-proof layer; 21. a heat-proof layer of the control surface fixing assembly; 22. a first central plane; 23. a second central plane.
Detailed Description
The present application will be described in further detail with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings. The present application will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
The foldable air rudder of the hypersonic aircraft as shown in the figures 1-8 comprises a control surface assembly 1, a rudder handle assembly and a control surface fixing assembly.
A tiller assembly having a first end 6 for connection to an aircraft and a second, relatively remote end 7, and a first central plane 22 and a tiller thermal protection layer 74 for thermal insulation; a transmission shaft is arranged on the second end 7, and the axis direction of the transmission shaft is a first direction; specifically, the thermal protection layer 74 wraps the exposed portion of the second end 7 and the exposed portion of the first end 6.
The control surface assembly 1 is provided with a second central surface 23 and a control surface heat protection layer 20 for heat insulation, the second central surface 23 is in a folded state and forms a first included angle with the first central surface 22, the second central surface 23 is in an unfolded state and forms a second included angle with the first central surface 22, when the control surface assembly 1 is in the unfolded state, the first central surface 22 and the second central surface 23 are overlapped, and as shown in fig. 7, the angle of the second included angle is set to be 0 degree; when the control surface assembly 1 is in a folded state, the first central surface 22 and the second central surface 23 form a first included angle α, and an angle of the first included angle α is greater than 0 °.
The control surface fixing assembly comprises a control surface connecting part for connecting the control surface assembly 1 and a heat-proof layer 21 of the control surface fixing assembly for heat insulation; the control surface fixing assembly is rotatably connected around the transmission shaft;
the rudder surface fixing assembly and the rudder handle assembly are respectively provided with an axial locking structure and an axial locking hole which are matched with each other, and the axis of the axial locking hole is parallel to the first direction; the rudder surface assembly 1 and the tiller assembly are respectively provided with a radial locking structure 14 and a radial locking hole 73 which are matched with each other, the radial locking hole 73 is arranged at the second end, and the axis of the radial locking hole 73 is perpendicular to the first direction.
When the control surface assembly 1 is in an unfolded state, the axial locking structure and the axial locking hole are locked in a matching manner, and the radial locking structure 14 and the radial locking hole 73 are locked in a matching manner.
Further, the two sides of the second end 7 of the tiller assembly are respectively provided with the transmission shafts, the transmission shafts on the control surface fixing assembly corresponding to the two sides of the second end 7 are respectively provided with the axial locking structures, specifically, the transmission shafts arranged on the two sides of the second end 7 are respectively a first transmission shaft 71 and a second transmission shaft 72, the first transmission shaft 71 and the second transmission shaft 72 are coaxial, and the end parts of the first transmission shaft 71 and the second transmission shaft 72 are respectively provided with a key groove; the axial locking structure comprises a first axial locking structure and a second axial locking structure which are arranged on the control surface fixing component corresponding to the first transmission shaft 71 and the second transmission shaft 72, the axial locking hole comprises a first axial locking hole and a second axial locking hole which are respectively arranged at two sides of the second end 7 of the tiller component corresponding to the first axial locking structure and the second axial locking structure, the first axial locking hole is parallel to the axial direction of the second axial locking hole and is parallel to the first direction, for more clearly describing the scheme, as shown in figures 1, 3 and 4,
the first axial locking structure comprises:
a first rotary drum 4, which is provided with a first axial hole along the first direction, and the first transmission shaft 71 passes through the first axial hole and is rotatably connected with the first rotary drum 4;
a first axial locking cavity 42 arranged in the first direction on the side of the first rotary drum 4 adjacent to the second end 7, wherein a first axial ejection outlet is arranged on the side of the first axial locking cavity 42 adjacent to the second end 7;
a first torsion spring structure 43 disposed in the first direction on a side of the first rotary cylinder 4 away from the second end 7 and having a key therein for key-way engagement with the first transmission shaft 71; the key groove and the key form a spline structure; the first transmission shaft 71 passes through the first axial hole to be in fit connection with the inside of the first torsion spring structure 43 through a spline structure, so that the first torsion spring structure 43 is fixedly connected with the first transmission shaft 71; as shown in fig. 8, the first torsion spring structure 43 includes a first torsion spring 46, one end of the first torsion spring 46 is fixedly connected with the inside of the first rotary cylinder 4, and the other end is fixedly connected with the inside of the first torsion spring structure, when the first rotary cylinder 4 rotates around the first transmission shaft 71 to make the control surface assembly 1 in the folded state, the first torsion spring 46 will generate a torque to make the control surface assembly 1 unfold, thereby ensuring that the control surface assembly 1 can be unfolded automatically in time when the air rudder is in use;
a first axial compression spring 421, which is in a compressed state when the control surface assembly 1 is in a folded state and is located in the first axial locking cavity 42; one end of the first axial pressure spring 421 is detachably connected to the inner wall of the first axial locking cavity 42;
the first axial locking pin 422 is detachably connected with the other end of the first axial compression spring 421 and is arranged corresponding to the first axial locking hole; first axial locking round pin 422 is in when rudder face subassembly 1 is fold condition, with first axial locking hole staggers when rudder face subassembly 1 is the expansion state, follow first axial catapult mouth pop out with first axial locking hole cooperation is connected, realizes rudder face subassembly 1 axial locking.
Further, as shown in fig. 3, the first axial locking structure is provided with two sets of the first axial locking cavity 42, the first axial pressure spring 421 and the first axial locking pin 422 which are parallel to each other, and correspondingly, the second end 7 of the tiller assembly is provided with two first axial locking holes which are matched with the first axial locking pin 422.
The second axial locking structure includes:
a second drum 8 having a second axial hole 86 along the first direction, as shown in fig. 8, wherein the second transmission shaft 72 is rotatably connected to the second drum 8 through the second axial hole 86;
a second axial locking chamber 82, arranged in said first direction on a side of said second drum 8 adjacent to said second end 7, said second axial locking chamber 82 being provided with a second axial ejection opening on a side adjacent to said second end 7;
the second torsion spring structure is arranged on one side, far away from the second end 7, in the second rotary drum 8 along the first direction, and a key matched with the key groove of the second transmission shaft 72 is arranged in the second torsion spring structure; the key groove and the key form a spline structure; the second transmission shaft 72 penetrates through the second axial hole 86 to be in fit connection with the inside of the second torsion spring structure through a spline structure, so that the second torsion spring structure is fixedly connected with the second transmission shaft 72; the second torsion spring structure comprises a second torsion spring, one end of the second torsion spring is fixedly connected with the inside of the second rotary drum 8, the other end of the second torsion spring is fixedly connected with the inside of the second torsion spring structure, when the second rotary drum 8 rotates around the second transmission shaft 72 to enable the control surface assembly 1 to be in a folded state, the second torsion spring can generate a torque enabling the control surface assembly 1 to be unfolded, and therefore the control surface assembly 1 can be automatically unfolded in time when the air rudder is used; when the control surface assembly 1 is in a folded state, the first torsion spring 46 and the second torsion spring act together to provide sufficient force for the control surface assembly 1 to be automatically unfolded in time;
a second axial compression spring 821 which is in a compressed state when the control surface assembly 1 is in a folded state and is positioned in the second axial locking cavity 82; one end of the second axial pressure spring 821 is detachably connected with the inner wall of the second axial locking cavity 82;
a second axial locking pin 822 detachably connected to the other end of the second axial compression spring 821 and disposed corresponding to the second axial locking hole; second axial locking pin 822 is in when control surface subassembly 1 is fold condition, with second axial locking hole staggers control surface subassembly 1 is when the expansion state, follows second axial ejection opening pop out with second axial locking hole cooperation is connected, realizes control surface subassembly 1 axial locking.
The first axial locking pin 422 and the second axial locking pin 822 axially lock the control surface assembly 1 together, so that the strength of the control surface assembly 1 and the tiller assembly can be obviously improved, and the reliability and stability of the air rudder are improved.
Further, as shown in fig. 3, the second axial locking structure is provided with two sets of the second axial locking cavity 82, the second axial compression spring 821 and the second axial locking pin 822 which are arranged side by side, and correspondingly, the second end 7 of the tiller assembly is provided with two second axial locking holes which are matched with the second axial locking pin 822.
As shown in fig. 2, the radial locking structure 14 includes:
a radial locking cavity 15 which is arranged on one side of the control surface assembly 1 adjacent to the second end 7 corresponding to the radial locking hole 73; a radial ejection port is formed in one side, adjacent to the second end 7, of the radial locking cavity 15;
the radial pressure spring 142 is in a compressed state when the control surface assembly 1 is in a folded state and is positioned in the radial locking cavity 15; one end of the radial pressure spring 142 is detachably connected with the inner wall of the radial locking cavity 15;
the radial locking pin 141 is detachably connected with the other end of the radial pressure spring 142 and is arranged corresponding to the radial locking hole 73; radial locking pin 141 is in when control surface subassembly 1 is fold condition, with radial locking hole 73 staggers when control surface subassembly 1 is expansion condition, follow radial ejection of compact mouth pop out with radial locking hole 73 cooperation is connected, realizes control surface subassembly 1's radial locking.
Further, the control surface assembly 1 further comprises a control surface framework 17, and the control surface heat-proof layer 20 is arranged on the outer side of the control surface framework 17; a radial locking cavity 15 is formed in one side, adjacent to the second end 7, of the control surface framework 17; five groups of radial compression springs 142 and radial locking pins 141 which are arranged in parallel are arranged in the radial locking cavity 15, and correspondingly, as shown in fig. 6, five groups of radial locking holes 73 matched with the radial locking pins 141 are arranged at the second end 7 of the tiller assembly;
because hypersonic aircraft speed is high, the dynamic pressure is big, lead to the rudder face load big, only still can not provide sufficient intensity from radial locking rudder face subassembly 1, can not guarantee the stability and the reliability of air rudder hypersonic flight process, so this application is through the rational design and the overall arrangement to transmission shaft and torsional spring structure, design axial locking structure on the fixed subassembly of rudder face, design radial locking structure 14 on rudder face subassembly 1, realize locking rudder face subassembly 1 jointly from radial and a plurality of directions of axial, thereby provide sufficient joint strength, guarantee the holistic stability of air rudder and reliability.
Further, as shown in fig. 1, 2, 3, and 4, the control surface frame 17 further includes a first rotating portion 3 and a second rotating portion 9; first rotation portion 3 is followed first direction is equipped with the third through-hole, second rotation portion 9 be equipped with the coaxial fourth hole of third through-hole, the fourth hole is equipped with the internal thread. The tiller assembly is provided with a first through hole penetrating through the first transmission shaft 71, the second end 7 and the second transmission shaft 72 along the first direction; the long pin shaft 2 penetrates through the third through hole, the first through hole and the fourth through hole in threaded connection, so that the overall connection strength and reliability of the air rudder are further improved, the coaxiality among the control surface assembly 1, the control surface fixing assembly and the rudder handle assembly is guaranteed, and the phenomenon that the coaxiality changes in the folding process of the control surface assembly to influence the stability and the track precision of a later-stage aircraft during hypersonic flight is prevented.
Further, the axial locking pin and the radial locking pin are respectively provided with an inner hole for accommodating an end portion of the axial compression spring and an inner hole for accommodating an end portion of the radial compression spring, specifically, the axial locking pin includes a first axial locking pin 422 and a second axial locking pin 822, as shown in fig. 3, one end of the first axial locking pin 422 connected with the first axial compression spring 421 is provided with an inner hole for accommodating an end portion of the first axial compression spring 421, so that the first axial compression spring 421 is assembled and fixed conveniently; an inner hole for accommodating the end part of the second axial compression spring 821 is formed at one end of the second axial locking pin 822 connected with the second axial compression spring 821, so that the second axial compression spring 821 is convenient to assemble and fix; an inner hole for accommodating the end of the radial pressure spring 142 is formed at one end of the radial locking pin 141 connected with the radial pressure spring 142, so that the radial pressure spring 142 can be assembled and fixed conveniently.
Furthermore, the first axial locking pin, the second axial locking pin and the radial locking pin are circumferentially provided with 4 second through holes, so that the first axial locking pin 422, the second axial locking pin 822 and the radial locking pin 141 are respectively withdrawn to the first axial locking cavity 42, the second axial locking cavity 82 and the radial locking cavity 15 by using tools in the assembling and test debugging processes.
Further, as shown in fig. 2 and fig. 5, the radial locking structure 14 further includes five pressure spring stoppers 19 detachably connected to the threads on the inner wall of the radial locking cavity 15, the pressure spring stoppers 19 correspond to five radial pressure springs 142 respectively, the radial pressure springs 142 are relatively far away from one ends of the radial locking pins 141 and the pressure spring stoppers 19 are tightly connected, the pressure spring stoppers 19 are provided with protrusions inserted into the inner portions of the radial pressure springs 142 to prevent the radial pressure springs 142 from displacing to affect the radial locking function, and are detachable from the pressure spring stoppers 19, so that the radial pressure springs 142 can be assembled, disassembled and adjusted.
Further, as shown in fig. 7, the second end 7 is provided with a groove for adjusting the folding angle of the rudder surface assembly, and the specific size and structure of the groove can be adjusted as required under the condition of meeting the strength of the rudder handle assembly, so that the folding angle is maximized, and the maximum folding angle can be greater than 110 degrees, so as to reduce the assembly volume of the aircraft and facilitate the loading and transportation of the aircraft.
Further, the axial locking chamber cover plates include a first axial locking chamber cover plate 41 and a second axial locking chamber cover plate 81, and particularly, as shown in fig. 3, a pair of detachable first axial locking cavity cover plates 41 are arranged on the front and back sides of the first rotary drum 4, so as to facilitate the assembly, debugging, replacement and maintenance of two sets of the first axial locking pins 422 and the first axial compression springs 421, a pair of detachable second axial locking cavity cover plates 81 are arranged at the front side and the rear side of the second rotary drum 8, so that the assembly, debugging, replacement and maintenance of two groups of second axial locking pins 822 and second axial compression springs 821 are facilitated, the first axial locking cavity cover plate 41 and the second axial locking cavity cover plate 81 are both made of heat-proof material, can carry out heat protection to inner structure at the super flight in-process, prevent that inside metal from receiving intensity reduction after the pneumatic heat, influencing locking function and effect.
Further, as shown in fig. 3, a control surface fixing component heat shielding layer 21 is disposed outside the control surface fixing component, so that the strength of the metal structures of the first axial locking structure 42, the second axial locking structure 82, the first rotary drum 4 and the second rotary drum 8 is prevented from being reduced after being subjected to aerodynamic heat, and the locking function and effect are prevented from being affected.
Further, as shown in fig. 2, the control surface framework 17 further includes a radial locking cavity cover plate 13 for sealing the radial locking cavity 15 and being detachable, and a radial locking cavity heat-proof layer 5 is arranged on the outer surface of the radial locking cavity cover plate 13, so that five groups of radial locking pins 141 and radial pressure springs and pressure spring stoppers 19 are convenient to assemble, debug, replace and maintain, and meanwhile, the radial locking structure 14 is prevented from being reduced in strength after being heated pneumatically, and the automatic locking function and effect are prevented from being affected.
Further, as shown in fig. 2, the control surface assembly 1 further includes a tail edge heat-proof plate 18, a front edge heat-proof plate 10, and an abrasion-proof strip 11, wherein the tail edge heat-proof plate 18 is fixedly connected with the tail of the control surface framework 17 through a high-strength bolt, so as to prevent aerodynamic heat from entering the interior of the air rudder from the tail of the control surface; the front edge heat-proof plate 10 is fixedly connected with the front end of the rudder surface framework 17 through a high-strength bolt and is used for bearing high-temperature heating and scouring of shock waves to the front end of the rudder surface in the high-speed flight process and improving the high-temperature resistance and deformation resistance of the front end; the abrasion-proof strip 11 is connected with the top of the control surface framework 17, and the abrasion-proof strip 11 has certain flexibility and is used for protecting the air rudder from being collided and abraded in the processes of cylinder discharging, loading and transporting.
Further, as shown in fig. 2 and 3, the control surface connection part includes a first control surface connection part disposed on the first drum 4 and a second control surface connection part disposed on the second drum 8; the control surface framework 17 is provided with a first connecting plate 12 connected with the first control surface connecting part and a second connecting plate 16 connected with the second control surface connecting part.
The first control surface connecting part comprises a first clamping plate 44 and a second clamping plate 45 which are connected with the top of the first rotary drum 4, and the first clamping plate 44 and the second clamping plate 45 form a space for accommodating the first connecting plate 12; the second rudder surface connection comprises a third clamping plate 84 and a fourth clamping plate 85 connected to the top of the second drum 8, the third clamping plate 84 and the fourth clamping plate 85 forming a space for accommodating the second connecting plate 16. The first connecting plate 12 is fixedly connected with the first clamping plate 44 and the second clamping plate 45 through bolts, so that the connection strength and reliability of the control surface framework 17 and the first rotary drum 4 are improved, and the second connecting plate 16 is fixedly connected with the third clamping plate 84 and the fourth clamping plate 85 through bolts, so that the connection strength of the control surface framework 17 and the second rotary drum 8 is improved, and the overall connection strength and reliability of the air rudder are improved.
Further, the control surface framework 17 is made of high-strength light metal materials such as titanium alloy and the like; the tiller component is made of high-temperature-resistant and high-strength metal materials such as nickel-based alloy and the like; the control surface heat-proof layer 20, the control surface fixing component heat-proof layer 21 and the tiller heat-proof layer 74 are made of high-temperature-resistant and scouring-resistant materials; the trailing edge thermal shield 18 and the leading edge thermal shield 10 are made of quartz material.
In view of the above embodiments, the present application provides a foldable air rudder for hypersonic aircraft, the air rudder comprises a rudder surface assembly 1, a rudder handle assembly, and a rudder surface fixing assembly, wherein a first rotating drum 4 and a second rotating drum 8 in the rudder surface fixing assembly are rotatably connected to the rudder handle assembly through a first transmission shaft 71 and a second transmission shaft 72 respectively, a first torsion spring structure 43 and a second torsion spring structure are respectively disposed in the first rotating drum 4 and the second rotating drum 8 and are respectively connected and fixed to the rudder handle assembly through a spline structure and a first transmission shaft 71 and a second transmission shaft 72 respectively, the rudder surface assembly 1 is connected to the rudder handle assembly through a first rudder surface connecting portion and a second rudder surface connecting portion on the rudder surface fixing assembly, so that the rudder surface assembly 1 can be folded around the first transmission shaft 71 and the second transmission shaft 72, when the control surface component 1 is folded, the first axial pressure spring 421, the second axial pressure spring 821 and the radial pressure spring 142 are all in a compressed state, when the control surface component 1 is unfolded, the first axial pressure spring 421, the second axial pressure spring 821 and the radial pressure spring 142 respectively press the first axial locking pin 422, the second axial locking pin 822 and the radial locking pin 141 into the corresponding first axial locking hole, second axial locking hole and radial locking hole, so that the control surface component 1 is locked from 3 directions simultaneously, the connection strength between the unfolded control surface component 1 and the control handle component is obviously improved, the control surface component 1, the control surface fixing component and the control handle component are connected through the long pin shaft 2, the overall connection strength of the air rudder is further improved, and the stability and reliability of the aircraft in the hypersonic flight process are further improved, and this application is through modular design, with first torsion spring structure 43 and second torsion spring machine structural design inside the air vane, overall structure is compact, and the leakproofness is good, the assembly of being convenient for. The control surface component 1, the rudder handle component and the control surface fixing component are respectively provided with a control surface heat-proof layer 20, a rudder handle heat-proof layer 74 and a control surface fixing component heat-proof layer 21, wherein the control surface component 1 is also provided with a tail edge heat-proof plate 18 and a front edge heat-proof plate 10, so that the influence of aerodynamic heat on an internal structure of the aircraft in the hypersonic flight process is effectively reduced, the stability, the reliability and the track precision of the flight process are improved, and the requirement of hypersonic stable flight in a high-temperature large overload environment is met.
The above examples are given for the purpose of illustrating the present invention clearly and not for the purpose of limiting the same, and it will be apparent to those skilled in the art that various changes and modifications can be made in the above examples without departing from the scope of the invention.
Claims (9)
1. A foldable air rudder of a hypersonic aerocraft, characterized in that the air rudder comprises,
a tiller assembly having a first end connected to the aircraft and a second, relatively remote end, and a first central plane and a tiller heat shield for thermal insulation; the second end is provided with a transmission shaft, and the axis direction of the transmission shaft is a first direction;
the control surface assembly is provided with a second central surface and a control surface heat-proof layer for heat insulation, and the second central surface is provided with a folded state forming a first included angle with the first central surface and an unfolded state forming a second included angle with the first central surface; the first included angle is larger than the second included angle;
the control surface fixing assembly comprises a control surface connecting part for connecting the control surface assembly and a heat-proof layer of the control surface fixing assembly for heat insulation; the control surface fixing assembly is rotatably connected around the transmission shaft;
the rudder surface fixing assembly and the rudder handle assembly are respectively provided with an axial locking structure and an axial locking hole which are matched with each other, and the axis of the axial locking hole is parallel to the first direction; the control surface assembly and the rudder handle assembly are respectively provided with a radial locking structure and a radial locking hole which are matched with each other, the radial locking hole is arranged at the second end, and the axis of the radial locking hole is vertical to the first direction;
when the control surface assembly is in an unfolded state, the axial locking structure is matched and locked with the axial locking hole, and the radial locking structure is matched and locked with the radial locking hole;
the axial locking structure includes:
a drum rotatably connected to the drive shaft;
the axial locking cavity is arranged on one side, adjacent to the second end, in the rotary drum along the first direction, and an axial ejection port is formed in one side, adjacent to the second end, of the axial locking cavity;
the torsion spring structure is arranged on one side, far away from the second end, in the rotary drum along the first direction; the transmission shaft penetrates through the rotary drum and is connected with the inside of the torsion spring structure in a spline fit manner; the torsion spring structure is rotatably connected with the rotary drum;
the axial pressure spring is in a compressed state when the control surface assembly is in a folded state and is positioned in the axial locking cavity; one end of the axial pressure spring is detachably connected with the inner wall of the axial locking cavity;
the axial locking pin is detachably connected with the other end of the axial pressure spring and is arranged corresponding to the axial locking hole; the axial locking pin is in when the control surface subassembly is fold condition, with the axial locking hole staggers when the control surface subassembly is the expansion state, follow the axial ejection opening pop out with the axial locking hole cooperation is connected.
2. The foldable air rudder of hypersonic aircraft according to claim 1, wherein the transmission shafts are respectively arranged on two sides of the second end of the rudder stock assembly; the control surface fixing assembly is provided with the axial locking structure corresponding to the transmission shaft.
3. The hypersonic aircraft foldable air rudder of claim 1, wherein the radial locking structure comprises:
the radial locking cavity is arranged on one side, adjacent to the second end, of the control surface assembly corresponding to the radial locking hole; a radial ejection port is formed in one side, adjacent to the second end, of the radial locking cavity;
the radial pressure spring is in a compressed state when the control surface assembly is in a folded state and is positioned in the radial locking cavity; one end of the radial pressure spring is detachably connected with the inner wall of the radial locking cavity;
the radial locking pin is detachably connected with the other end of the radial pressure spring and is arranged corresponding to the radial locking hole; radial locking round pin is in when the control surface subassembly is fold condition, with radial locking hole staggers when the control surface subassembly is the expansion state, follow radial ejection of compact mouth pop out with radial locking hole cooperation is connected.
4. The foldable air rudder of hypersonic aircraft according to claim 1, wherein the rudder stock assembly is provided with a first through hole extending through the transmission shaft and the second end in the first direction; the control surface assembly is provided with a long pin shaft penetrating through the first through hole.
5. The foldable air rudder of hypersonic aircraft according to claim 3, wherein the axial locking pin and the radial locking pin are respectively provided with inner holes for accommodating the ends of the axial compression spring and the ends of the radial compression spring.
6. The foldable air rudder of the hypersonic aircraft according to claim 3, wherein the radial locking structure further comprises a compressed spring stopper connected with the inner wall of the radial locking cavity, and one end of the radial compressed spring, which is relatively far away from the radial locking pin, is abutted against the compressed spring stopper.
7. The foldable air rudder of hypersonic aircraft according to claim 1, wherein the second end is provided with a groove for adjusting the folded state of the control surface assembly.
8. The foldable air rudder of hypersonic vehicle as claimed in claim 5, wherein the hole wall of the inner hole is provided with a second through hole.
9. The foldable air rudder of a hypersonic aircraft according to claim 3, characterized in that the control surface component and the control surface fixing component are respectively provided with a detachable radial locking cavity cover plate and an detachable axial locking cavity cover plate corresponding to the radial locking cavity and the axial locking cavity.
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| CN202210353024.XA CN114426094B (en) | 2022-04-06 | 2022-04-06 | Foldable air rudder of hypersonic aircraft |
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| CN115057000B (en) * | 2022-08-16 | 2022-11-01 | 中国空气动力研究与发展中心空天技术研究所 | Zero calibration device and calibration method for hypersonic aircraft air rudder system |
| CN115289918B (en) * | 2022-09-05 | 2024-02-13 | 北京凌空天行科技有限责任公司 | Wing rudder fusion structure |
| CN117470036B (en) * | 2023-09-25 | 2025-01-10 | 西安现代控制技术研究所 | A foldable rudder torque transmission structure |
| CN117053635A (en) * | 2023-10-11 | 2023-11-14 | 西安现代控制技术研究所 | High-bearing hypersonic folding rudder adapting to thermal deformation |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102774494A (en) * | 2012-07-06 | 2012-11-14 | 北京林业大学 | Aircraft folding rudder capable of stretching automatically |
| CN111099011A (en) * | 2018-10-25 | 2020-05-05 | 酷黑科技（北京）有限公司 | Aircraft |
| RU2730903C1 (en) * | 2019-09-10 | 2020-08-26 | Акционерное общество "Машиностроительное конструкторское бюро "Факел" имени Академика П.Д. Грушина" | Opening and locking mechanism of aerodynamic rudder with two axes of folding |
| CN114136157A (en) * | 2020-09-04 | 2022-03-04 | 北京恒星箭翔科技有限公司 | Guidance projectile body that 40mm rocket tube sought with general strapdown |
| CN113108652B (en) * | 2021-04-13 | 2022-09-27 | 哈尔滨工程大学 | Missile rudder surface rotary folding and retracting structure |
| CN113720217B (en) * | 2021-07-23 | 2023-04-14 | 河北汉光重工有限责任公司 | Be applied to thermal-insulated folding rudder of hypersonic flight |
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