CN113460319A - Tandem booster fireless separation structure and aircraft with same - Google Patents
Tandem booster fireless separation structure and aircraft with same Download PDFInfo
- Publication number
- CN113460319A CN113460319A CN202010241702.4A CN202010241702A CN113460319A CN 113460319 A CN113460319 A CN 113460319A CN 202010241702 A CN202010241702 A CN 202010241702A CN 113460319 A CN113460319 A CN 113460319A
- Authority
- CN
- China
- Prior art keywords
- booster
- assembly
- separation
- limiting
- base body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000926 separation method Methods 0.000 title claims abstract description 129
- 238000010008 shearing Methods 0.000 claims abstract description 28
- 230000000694 effects Effects 0.000 claims description 3
- 238000010276 construction Methods 0.000 claims 2
- 239000002360 explosive Substances 0.000 abstract description 9
- 230000000977 initiatory effect Effects 0.000 abstract description 6
- 238000006073 displacement reaction Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 6
- 230000008878 coupling Effects 0.000 description 5
- 238000010168 coupling process Methods 0.000 description 5
- 238000005859 coupling reaction Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000012466 permeate Substances 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Braking Systems And Boosters (AREA)
- Manipulator (AREA)
Abstract
The invention provides a tandem booster fireless separation structure and an aircraft with the same, wherein the tandem booster fireless separation structure comprises a body separation part, a booster separation part, a shearing connection assembly, a limiting groove assembly and a limiting protrusion assembly, the body separation part comprises a body separation base body and a first connecting lifting lug assembly, the first connecting lifting lug assembly is fixedly arranged on the body separation base body, the booster separation part comprises a booster separation base body and a second connecting lifting lug assembly, the second connecting lifting lug assembly is fixedly arranged on the booster separation base body, the first connecting lifting lug assembly is connected with the second connecting lifting lug assembly through the shearing connection assembly, the limiting groove assembly is arranged on the body separation base body and/or the booster separation base body, and the limiting protrusion assembly is arranged on the body separation base body and/or the booster separation base body. By applying the technical scheme of the invention, the technical problems of inconvenience in transportation and high cost when initiating explosive devices are adopted for separating the booster in the prior art are solved.
Description
Technical Field
The invention relates to the technical field of booster separation structure design, in particular to a tandem booster fireless separation structure and an aircraft with the same.
Background
The release mechanism of traditional series boosting launching unmanned aerial vehicle generally adopts initiating explosive devices such as explosive bolts, and its shortcoming lies in that the transportation storage is inconvenient to its price is higher. And as the unmanned aerial vehicle technique permeates to all walks of life, have the application that the firer separation structure influences unmanned aerial vehicle more and more.
Disclosure of Invention
The invention provides a tandem booster fireless separation structure and an aircraft with the tandem booster fireless separation structure, and can solve the technical problems that in the prior art, when an initiating explosive device is adopted for separating a booster, the booster is inconvenient to transport and high in cost.
According to an aspect of the present invention, there is provided a tandem type booster fireless separation structure, the tandem type booster fireless separation structure comprising: the machine body separating piece comprises a machine body separating base body and a first connecting lifting lug assembly, the first connecting lifting lug assembly is fixedly arranged on the machine body separating base body, and the machine body separating base body is fixedly arranged on the machine body; the booster separating piece comprises a booster separating base body and a second connecting lifting lug assembly, the second connecting lifting lug assembly is fixedly arranged on the booster separating base body, and the booster separating base body is fixedly arranged on the booster; the first connecting lifting lug assembly is connected with the second connecting lifting lug assembly through the shearing connecting assembly, and the shearing connecting assembly can be disconnected when external force with set magnitude is applied to separate the first connecting lifting lug assembly from the second connecting lifting lug assembly; the device comprises a limiting groove component and a limiting protrusion component, wherein the limiting groove component is arranged on the fuselage separation base body and/or the booster separation base body, and the limiting protrusion component is arranged on the fuselage separation base body and/or the booster separation base body; when the aircraft is in a transportation state, the aircraft body separating piece is connected with the booster separating piece through the shearing connecting assembly; when the booster is in a working state, the shearing connecting assembly is disconnected under stress, and the machine body separating part and the booster separating part are matched with each other through the limiting groove assembly and the limiting protrusion assembly to limit the relative movement between the booster and the machine body; when the work of the booster is finished, the limiting convex assembly is separated from the limiting groove assembly so as to realize the separation of the booster and the machine body.
Further, spacing recess subassembly includes at least three spacing recess, and spacing protruding subassembly includes at least three spacing arch, and at least three spacing recess interval sets up on fuselage separation base member, and at least three spacing protruding interval sets up on booster separation base member, and at least three spacing recess sets up with at least three spacing protruding one-to-one.
Furthermore, the first connecting lifting lug assembly comprises at least three first lifting lugs, the at least three first lifting lugs are arranged on the body separating base body at intervals, and one first lifting lug is arranged between any two adjacent limiting grooves; the second connecting lifting lug assembly comprises at least three second lifting lugs, the at least three second lifting lugs are arranged on the separation base body of the booster at intervals, and one second lifting lug is arranged between any two adjacent limiting bulges; the shearing connecting assembly comprises at least three shearing connecting pieces, and the at least three shearing connecting pieces, the at least three first lifting lugs and the at least three second lifting lugs are arranged in a one-to-one correspondence mode.
Further, at least three first lugs and at least three spacing recess are evenly spaced and are set up on fuselage separation base member, and at least three second lug and at least three spacing protruding even interval set up on booster separation base member.
Furthermore, at least three first lifting lugs are arranged on the end face of the separation base body of the machine body at uniform intervals, and at least three second lifting lugs are arranged on the outer wall face of the separation base body of the booster at uniform intervals.
Further, the shear connection assembly includes a shear pin or a shear rivet.
Furthermore, the groove wall surface of the limiting groove component comprises a conical surface or a spherical surface, and the structural profile of the limiting protrusion component comprises a conical surface or a spherical surface.
Further, spacing recess subassembly includes a plurality of first spacing recesses and a plurality of second spacing recesses, spacing protruding subassembly includes a plurality of first spacing archs and a plurality of second spacing archs, a plurality of first spacing recesses and a plurality of first spacing archs alternate interval in proper order and set up on fuselage separation base member, a plurality of second spacing recesses and a plurality of second spacing archs alternate interval in proper order and set up on boost separation base member, a plurality of first spacing recesses and a plurality of second spacing protruding one-to-one set up, a plurality of second spacing recesses and a plurality of first spacing protruding one-to-one set up.
Further, the fuselage separation base member and the first connecting lug assembly are integrally manufactured, and the booster separation base member, the second connecting lug assembly and the limiting protrusion assembly are integrally manufactured.
According to another aspect of the invention, there is provided an aircraft comprising a fuselage, thrusters and tandem-thruster fireless separation structures, the tandem-thruster fireless separation structures being as described above, the fuselage being connected to the thrusters by the tandem-thruster fireless separation structures.
Compared with the prior art, the tandem booster fireless separation structure does not relate to firer during the separation process of the booster and the booster body, is convenient to store and transport and has low cost; in addition, after the shearing connection assembly is sheared, the aircraft body and the booster can be matched with the limiting groove assembly through the limiting convex assembly under the condition of pressure so as to provide restraint, and after the booster is flamed out, the booster is separated from the aircraft body without structural jamming, and the booster can be smoothly separated from the aircraft body.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 illustrates a front view of a tandem booster fireless disconnect configuration provided in accordance with a specific embodiment of the present invention;
FIG. 2 shows a cross-sectional view A-A of the tandem booster fireless disconnect structure provided in FIG. 1;
FIG. 3 illustrates a side view of the tandem booster fireless disconnect configuration provided in FIG. 1;
FIG. 4 illustrates a front view of a fuselage splitter provided in accordance with an exemplary embodiment of the present invention;
FIG. 5 shows a cross-sectional view at A-A of the fuselage separator provided in FIG. 4;
FIG. 6 illustrates a side view of the fuselage separator provided in FIG. 4;
FIG. 7 illustrates a front view of a booster release provided in accordance with a specific embodiment of the present invention;
FIG. 8 shows a cross-sectional view at A-A of the booster release member provided in FIG. 7;
fig. 9 shows a side view of the booster release member provided in fig. 7.
Wherein the figures include the following reference numerals:
10. a fuselage disconnect; 11. a fuselage separation matrix; 12. a first connecting lug assembly; 20. a booster release member; 21. separating the matrix by the booster; 22. a second connecting lug assembly; 30. shearing the connecting assembly; 40. a limiting groove component; 50. spacing protruding subassembly.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. 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. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. 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 is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
As shown in fig. 1 to 9, according to an embodiment of the present invention, there is provided a tandem booster fireless separation structure, the tandem booster fireless separation structure comprising a fuselage separator 10, a booster separator 20, a shear coupling assembly 30, a limit groove assembly 40, and a limit protrusion assembly 50, the fuselage separator 10 comprising a fuselage separator base 11 and a first connecting lug assembly 12, the first connecting lug assembly 12 being fixedly disposed on the fuselage separator base 11, the fuselage separator base 11 being fixedly disposed on the fuselage, the booster separator 20 comprising a booster separator base 21 and a second connecting lug assembly 22, the second connecting lug assembly 22 being fixedly disposed on the booster separator base 21, the booster separator base 21 being fixedly disposed on the booster, the first connecting lug assembly 12 being connected to the second connecting lug assembly 22 through the shear coupling assembly 30, the shear connection assembly 30 can be disconnected when external force with a set magnitude is applied to separate the first connection lifting lug assembly 12 from the second connection lifting lug assembly 22, the limiting groove assembly 40 is arranged on the fuselage separation base body 11 and/or the booster separation base body 21, and the limiting protrusion assembly 50 is arranged on the fuselage separation base body 11 and/or the booster separation base body 21; wherein the fuselage splitter 10 is connected to the booster splitter 20 by a shear connection assembly 30 when the aircraft is in a transport state; when the booster is in a working state, the shear connection assembly 30 is disconnected under force, and the body separating component 10 and the booster separating component 20 are matched through the limiting groove assembly 40 and the limiting protrusion assembly 50 to limit the relative movement between the booster and the body; when the booster is finished working, the limiting protrusion assembly 50 is separated from the limiting groove assembly 40 to realize the separation of the booster from the fuselage.
By applying the configuration mode, the tandem type booster fireless separation structure is provided, the tandem type booster fireless separation structure is characterized in that a first connecting lifting lug assembly is arranged on a fuselage separation base body, a second connecting lifting lug assembly is arranged on the booster separation base body, the first connecting lifting lug assembly and the second connecting lifting lug assembly are connected through a shearing connection assembly, the fuselage separation base body and the booster separation base body are provided with limiting groove assemblies and limiting protrusion assemblies which correspond to each other one by one, and when an aircraft is in a transportation state, the booster is fixed on the fuselage through the shearing connection assembly; when the aircraft is in a launching state, the shear connection assembly is sheared through the thrust of the booster, and the limiting convex assembly slides into the limiting groove assembly to limit the relative displacement between the aircraft body and the booster in the radial direction and the thrust direction; after the booster stops working, the thrust disappears, the pressure between the limiting convex assembly and the limiting groove assembly disappears, and the booster is separated from the aircraft body. Compared with the prior art, the mode does not involve initiating explosive devices in the process of separating the booster from the machine body, is convenient to store and transport and has low cost; in addition, after the shearing connection assembly is sheared, the aircraft body and the booster can be matched with the limiting groove assembly through the limiting convex assembly under the condition of pressure so as to provide restraint, and after the booster is flamed out, the booster is separated from the aircraft body without structural jamming, and the booster can be smoothly separated from the aircraft body.
As a first embodiment of the present invention, as shown in fig. 4 to 9, in order to provide reliable restraint between the body and the booster after the shear connection assembly is cut off, the limit groove assembly 40 may be configured to include at least three limit grooves, the limit projection assembly 50 includes at least three limit projections, the at least three limit grooves are arranged on the body separating base 11 at intervals, the at least three limit projections are arranged on the booster separating base 21 at intervals, and the at least three limit grooves and the at least three limit projections are arranged in one-to-one correspondence.
Under this kind of configuration, through setting up at least three spacing recess on fuselage separation base member 11, set up at least three spacing arch on boost motor separation base member, after the shearing coupling assembling is cut off, under the thrust effect of boost motor, at least three spacing arch one-to-one slips into at least three spacing recess, cooperatees with reliable restraint the relative displacement of radial and thrust direction between unmanned aerial vehicle fuselage and the boost motor through spacing recess.
In addition, as a second embodiment of the present invention, the limiting groove assembly 40 may also be configured to include at least three limiting grooves, the limiting protrusion assembly 50 includes at least three limiting protrusions, the at least three limiting grooves are arranged on the booster separating base 21 at intervals, the at least three limiting protrusions are arranged on the fuselage separating base 11 at intervals, and the at least three limiting grooves and the at least three limiting protrusions are arranged in a one-to-one correspondence. This kind of mode only lies in the difference that spacing recess and spacing protruding set up the position with first embodiment, after the shearing coupling assembling is cut off, under the thrust effect of boost ware, at least three spacing protruding one-to-one slips into at least three spacing recess, cooperates with the relative displacement of radial and thrust direction between reliable restraint unmanned aerial vehicle fuselage and the boost ware through spacing recess and spacing protruding.
Alternatively, as a third embodiment of the present invention, the limiting groove assembly 40 may also be configured to include a plurality of first limiting grooves and a plurality of second limiting grooves, the limiting protrusion assembly 50 includes a plurality of first limiting protrusions and a plurality of second limiting protrusions, the plurality of first limiting grooves and the plurality of first limiting protrusions are sequentially and alternately arranged on the fuselage separation base 11 at intervals, the plurality of second limiting grooves and the plurality of second limiting protrusions are sequentially and alternately arranged on the booster separation base 21 at intervals, the plurality of first limiting grooves and the plurality of second limiting protrusions are arranged in a one-to-one correspondence manner, and the plurality of second limiting grooves and the plurality of first limiting protrusions are arranged in a one-to-one correspondence manner.
For example, the limiting groove assembly comprises two first limiting grooves and two second limiting grooves, the limiting protrusion assembly 50 comprises two first limiting protrusions and two second limiting protrusions, the two first limiting grooves and the two first limiting protrusions are sequentially arranged on the body separating base body 11 at intervals according to the sequence of the first limiting grooves, the first limiting protrusions, the first limiting grooves and the first limiting protrusions, the two second limiting grooves and the two second limiting protrusions are sequentially arranged on the booster separating base body 21 at intervals according to the sequence of the second limiting protrusions, the second limiting grooves, the second limiting protrusions and the second limiting grooves, the mode is different from the first embodiment and the second embodiment only in the arrangement positions of the limiting grooves and the limiting protrusions, after the shearing connecting assembly is cut off, under the thrust action of the booster, the two first limiting protrusions correspondingly slide into the two second limiting grooves respectively, the two second limiting protrusions correspondingly slide into the two first limiting grooves respectively, and are matched with the limiting protrusions through the limiting grooves to reliably restrain radial and thrust direction relative displacement between the unmanned aerial vehicle body and the booster.
Further, in the invention, in order to ensure reliable connection of the unmanned aerial vehicle during transportation, the first connecting lug assembly 12 may be configured to include at least three first lugs, the at least three first lugs are arranged on the fuselage separation base body 11 at intervals, and a first lug is arranged between any two adjacent limiting grooves; the second connecting lifting lug assembly 22 comprises at least three second lifting lugs, the at least three second lifting lugs are arranged on the booster separating base body 21 at intervals, and one second lifting lug is arranged between any two adjacent limiting protrusions; the shearing connecting assembly 30 comprises at least three shearing connecting pieces, and the at least three shearing connecting pieces, the at least three first lifting lugs and the at least three second lifting lugs are arranged in a one-to-one correspondence manner.
In addition, in the present invention, in order to improve the uniformity of the distribution of the coupling force and the restraining force between the body separating member and the booster separating member, at least three first lifting lugs and at least three limiting grooves may be configured to be uniformly spaced on the body separating base 11, and at least three second lifting lugs and at least three limiting protrusions may be uniformly spaced on the booster separating base 21.
As an embodiment of the present invention, as shown in fig. 1 to 9, the first connecting shackle assembly 12 is configured to include three first shackles, the second connecting shackle assembly 22 includes three second shackles, the limiting groove assembly 40 includes three limiting grooves, the limiting projection assembly 50 includes three limiting protrusions, the three limiting grooves are disposed on the fuselage separation base body 11 at intervals, the three limiting protrusions are disposed on the booster separation base body 21 at intervals, the three first shackles are disposed along radial directions of 0 °, 120 ° and 240 ° of the fuselage separation base body 11, the three limiting grooves are disposed along radial directions of 60 °, 180 ° and 300 ° of the fuselage separation base body 11, the three second shackles are disposed along radial directions of 0 °, 120 ° and 240 ° of the booster separation base body 21, and the three limiting protrusions are disposed along radial directions of 60 °, 180 ° and 180 ° of the booster separation base body 21, respectively, And 300 degrees of azimuth setting.
Further, in the present invention, in order to reduce the length of the fuselage separator and the booster separator in the axial direction, at least three first lifting lugs may be disposed to be evenly spaced on the end surface of the fuselage separator base body 11, and at least three second lifting lugs may be disposed to be evenly spaced on the outer wall surface of the booster separator base body 21.
Further, in the present invention, in order to achieve reliable connection and disconnection between the booster and the fuselage, the shear connection assembly 30 may be configured to include a shear pin or a shear rivet. Wherein, shear pin or shear rivet need satisfy not destroyed under unmanned aerial vehicle storage and transportation operating mode loaded condition on the one hand when material and size are selected, on the other hand need satisfy the booster and need be cut off under the thrust overload condition. In the present invention, other elements may be adopted as the shear connection assembly as long as the requirements in the above two aspects can be met, and the present invention is not limited herein.
Further, in the present invention, in order to reliably restrain the relative displacement between the drone and the booster in the radial direction and the thrust direction when the drone is launched, the groove wall surface of the limiting groove assembly 40 may be configured to include a conical surface or a spherical surface, and the structural profile of the limiting protrusion assembly 50 includes a conical surface or a spherical surface. As other embodiments of the present invention, the groove wall surface of the limiting groove component and the structural profile of the limiting protrusion component may be configured in other shapes as long as the matching between the limiting protrusion component and the limiting groove component can be realized.
In addition, in the present invention, in order to improve the integrity and the force-bearing performance of the fuselage split part and the booster split part, the fuselage split base body 11 and the first connecting lug assembly 12 may be configured to be integrally formed, and the booster split base body 21, the second connecting lug assembly 22 and the limit projection assembly 50 may be integrally formed.
According to another aspect of the invention, an aircraft is provided, the aircraft comprising a fuselage, thrusters, and tandem-thruster fireless separation structures, the tandem-thruster fireless separation structures being tandem-thruster fireless separation structures as described above, the fuselage being connected to the thrusters via the tandem-thruster fireless separation structures.
By applying the configuration mode, the aircraft is improved, and as the tandem booster non-explosive work separation structure provided by the invention does not relate to explosive work in the process of separating the booster from the aircraft body, the tandem booster is convenient to store and transport and has low cost; in addition, after the shearing connection assembly is sheared, the aircraft body and the booster can be matched with the limiting groove assembly through the limiting convex assembly under the condition of pressure so as to provide restraint, and after the booster is flamed out, the booster is separated from the aircraft body without structural jamming, and the booster can be smoothly separated from the aircraft body. Therefore, the tandem booster fireless separation structure provided by the invention is used for realizing the separation between the booster and the aircraft body, and the working performance of the aircraft is greatly improved.
For further understanding of the present invention, the tandem booster fireless separation structure provided by the present invention is described in detail below with reference to fig. 1 to 9.
As shown in fig. 1 to 9, according to a specific embodiment of the present invention, there is provided a tandem type booster fireless separation structure, the tandem type booster fireless separation structure includes a body separation member 10, a booster separation member 20, a shear connection assembly 30, a limit groove assembly 40, and a limit protrusion assembly 50, the body separation member 10 includes a body separation base 11 and three first lifting lugs, the three first lifting lugs are fixedly disposed on the body separation base 11, the three first lifting lugs are respectively provided with pin holes, the body separation base 11 is fixedly disposed on the body, the booster separation member 20 includes a booster separation base 21 and three second lifting lugs, the three second lifting lugs are fixedly disposed on the booster separation base 21, the three second lifting lugs are respectively provided with pin holes, the booster separation base 21 is fixedly disposed on the booster, the shear connection assembly 30 includes three shear pins, the three first lifting lugs are connected with the three second lifting lugs through three shearing pins respectively, and the three shearing pins can be disconnected when external force with set magnitude is applied to the three first lifting lugs so as to separate the first lifting lugs from the second lifting lugs.
Spacing recess subassembly 40 includes three spacing recess, the recess wall of three spacing recess is the conical surface, spacing protruding subassembly 50 includes three spacing arch, three spacing bellied profile is the conical surface, three spacing recess interval sets up on fuselage separation base member 11, three spacing protruding interval sets up on boost motor separation base member 21, three first lug is respectively along fuselage separation base member 11 radial 0 °, 120 °, 240 azimuth setting, three spacing recess is respectively along fuselage separation base member 11 radial 60 °, 180 °, 300 azimuth setting, three second lug is respectively along boost motor separation base member 21 radial 0 °, 120 °, 240 azimuth setting, three spacing arch is respectively along boost motor separation base member 21 radial 60 °, 180 °, 300 azimuth setting.
In the embodiment, when the unmanned aerial vehicle and the booster are in the storage and transportation states, the booster is fixed on the body through three shear pins; when the unmanned aerial vehicle is in a launching state, the three shear pins are sheared by the thrust of the booster, the three conical limiting protrusions on the booster separating base body 21 correspondingly slide into the three conical limiting grooves on the fuselage separating base body 11 one by one, and the radial displacement and the thrust direction relative displacement between the fuselage and the booster are restrained by the limiting protrusions and the limiting grooves; after the booster stops working, thrust disappears, and the pressure between spacing arch and the spacing recess disappears, and the booster separates from unmanned aerial vehicle's fuselage.
In conclusion, the invention provides a tandem booster without an initiating explosive device separating structure, and the separating structure does not relate to initiating explosive devices in the process of separating the booster from a machine body, is convenient to store and transport and has low cost; in addition, after the shearing connection assembly is sheared, the aircraft body and the booster can be matched with the limiting groove assembly through the limiting convex assembly under the condition of pressure so as to provide restraint, and after the booster is flamed out, the booster is separated from the aircraft body without structural jamming, and the booster can be smoothly separated from the aircraft body. Therefore, the tandem booster fireless separation structure provided by the invention can meet the boosting and post-flameout separation functions of the booster on the premise of ensuring the booster to be effectively fixed in the unmanned aerial vehicle transportation and storage stage.
In the description of the present invention, it is to be understood that the orientation or positional relationship indicated by the orientation words such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc. are usually based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplicity of description, and in the case of not making a reverse description, these orientation words do not indicate and imply that the device or element being referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore, should not be considered as limiting the scope of the present invention; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides a tandem type booster does not have firework isolating construction which characterized in that, tandem type booster does not have firework isolating construction includes:
the fuselage separation piece (10), the fuselage separation piece (10) comprises a fuselage separation base body (11) and a first connecting lifting lug assembly (12), the first connecting lifting lug assembly (12) is fixedly arranged on the fuselage separation base body (11), and the fuselage separation base body (11) is fixedly arranged on the fuselage;
the booster separating piece (20), the booster separating piece (20) comprises a booster separating base body (21) and a second connecting lifting lug assembly (22), the second connecting lifting lug assembly (22) is fixedly arranged on the booster separating base body (21), and the booster separating base body (21) is fixedly arranged on the booster;
a shear connection assembly (30), the first connecting lug assembly (12) being connected to the second connecting lug assembly (22) via the shear connection assembly (30), the shear connection assembly (30) being disconnectable upon application of a predetermined force to effect separation of the first connecting lug assembly (12) from the second connecting lug assembly (22);
the limiting groove assembly (40) and the limiting protrusion assembly (50), the limiting groove assembly (40) is arranged on the fuselage separation base body (11) and/or the booster separation base body (21), and the limiting protrusion assembly (50) is arranged on the fuselage separation base body (11) and/or the booster separation base body (21);
wherein the fuselage splitter (10) is connected to the booster splitter (20) by the shear connection assembly (30) when the aircraft is in a transport state; when the booster is in a working state, the shearing connecting assembly (30) is disconnected under stress, and the machine body separating part (10) and the booster separating part (20) are matched with each other through the limiting groove assembly (40) and the limiting protrusion assembly (50) to limit the relative movement between the booster and the machine body; when the work of the booster is finished, the limiting convex assembly (50) is separated from the limiting groove assembly (40) so as to realize the separation of the booster and the machine body.
2. The tandem booster fireless separation structure of claim 1, wherein the limiting groove component (40) comprises at least three limiting grooves, the limiting protrusion component (50) comprises at least three limiting protrusions, the at least three limiting grooves are arranged on the body separation base body (11) at intervals, the at least three limiting protrusions are arranged on the booster separation base body (21) at intervals, and the at least three limiting grooves and the at least three limiting protrusions are arranged in a one-to-one correspondence manner.
3. The tandem booster fireless separation structure of claim 2, wherein the first connecting lug assembly (12) comprises at least three first lugs, the at least three first lugs are arranged on the fuselage separation base body (11) at intervals, and one first lug is arranged between any two adjacent limiting grooves; the second connecting lifting lug assembly (22) comprises at least three second lifting lugs, the at least three second lifting lugs are arranged on the booster separating base body (21) at intervals, and one second lifting lug is arranged between any two adjacent limiting protrusions; the shearing connecting assembly (30) comprises at least three shearing connecting pieces, and the at least three shearing connecting pieces, the at least three first lifting lugs and the at least three second lifting lugs are arranged in a one-to-one correspondence mode.
4. The tandem booster fireless separation structure of claim 3, wherein at least three first lifting lugs and at least three limiting grooves are uniformly spaced on the body separation base body (11), and at least three second lifting lugs and at least three limiting protrusions are uniformly spaced on the booster separation base body (21).
5. The tandem booster fireless separation structure of claim 3, wherein at least three first lifting lugs are uniformly spaced on the end surface of the fuselage separation base body (11), and at least three second lifting lugs are uniformly spaced on the outer wall surface of the booster separation base body (21).
6. The in-line booster fireless separation structure of any one of claims 1 to 5, wherein the shear connection assembly (30) comprises a shear pin or a shear rivet.
7. The tandem booster fireless separation structure of claim 6, wherein the groove wall surface of the limiting groove component (40) comprises a conical surface or a spherical surface, and the structural profile of the limiting protrusion component (50) comprises a conical surface or a spherical surface.
8. The tandem booster fireless separation structure of claim 1, wherein the limiting groove component (40) comprises a plurality of first limiting grooves and a plurality of second limiting grooves, the limiting protrusion component (50) comprises a plurality of first limiting protrusions and a plurality of second limiting protrusions, the first limiting grooves and the first limiting protrusions are sequentially and alternately arranged on the body separation base body (11) at intervals, the second limiting grooves and the second limiting protrusions are sequentially and alternately arranged on the booster separation base body (21) at intervals, the first limiting grooves and the second limiting protrusions are arranged in a one-to-one correspondence manner, and the second limiting grooves and the first limiting protrusions are arranged in a one-to-one correspondence manner.
9. The tandem booster fireless separation structure of claim 2, wherein the body separating base body (11) and the first connecting lug assembly (12) are integrally formed, and the booster separating base body (21), the second connecting lug assembly (22) and the limit projection assembly (50) are integrally formed.
10. An aircraft, characterized in that the aircraft comprises a fuselage, a booster and a tandem booster fireless separation structure, the tandem booster fireless separation structure being the tandem booster fireless separation structure of any one of claims 1 to 9, the fuselage being connected with the booster through the tandem booster fireless separation structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010241702.4A CN113460319B (en) | 2020-03-31 | 2020-03-31 | Tandem booster fireless separation structure and aircraft with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010241702.4A CN113460319B (en) | 2020-03-31 | 2020-03-31 | Tandem booster fireless separation structure and aircraft with same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113460319A true CN113460319A (en) | 2021-10-01 |
| CN113460319B CN113460319B (en) | 2023-03-14 |
Family
ID=77865217
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010241702.4A Active CN113460319B (en) | 2020-03-31 | 2020-03-31 | Tandem booster fireless separation structure and aircraft with same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113460319B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0557907A1 (en) * | 1992-02-24 | 1993-09-01 | Hercules Incorporated | Assembly and method for attaching a pressure vessel to another object |
| DE4340002C1 (en) * | 1993-11-24 | 1995-05-11 | Deutsche Aerospace | Attachment of a thermal insulation structure |
| CN107097980A (en) * | 2017-03-30 | 2017-08-29 | 北京临近空间飞行器系统工程研究所 | A kind of non-firer's stage separation structure |
| CN107792403A (en) * | 2017-09-07 | 2018-03-13 | 湖北航天技术研究院总体设计所 | A kind of satellite separator |
| CN108177800A (en) * | 2017-12-27 | 2018-06-19 | 哈尔滨工业大学深圳研究生院 | A kind of cradle head locked based on marmem with discharging |
| CN109703773A (en) * | 2018-12-28 | 2019-05-03 | 西北工业大学 | It is a kind of to positive unmanned plane rocket thrust transferring structure |
| CN208847042U (en) * | 2018-04-26 | 2019-05-10 | 湖南宏大日晟航天动力技术有限公司 | A kind of novel boost motor of supersonic cruising guided missile |
-
2020
- 2020-03-31 CN CN202010241702.4A patent/CN113460319B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0557907A1 (en) * | 1992-02-24 | 1993-09-01 | Hercules Incorporated | Assembly and method for attaching a pressure vessel to another object |
| DE4340002C1 (en) * | 1993-11-24 | 1995-05-11 | Deutsche Aerospace | Attachment of a thermal insulation structure |
| CN107097980A (en) * | 2017-03-30 | 2017-08-29 | 北京临近空间飞行器系统工程研究所 | A kind of non-firer's stage separation structure |
| CN107792403A (en) * | 2017-09-07 | 2018-03-13 | 湖北航天技术研究院总体设计所 | A kind of satellite separator |
| CN108177800A (en) * | 2017-12-27 | 2018-06-19 | 哈尔滨工业大学深圳研究生院 | A kind of cradle head locked based on marmem with discharging |
| CN208847042U (en) * | 2018-04-26 | 2019-05-10 | 湖南宏大日晟航天动力技术有限公司 | A kind of novel boost motor of supersonic cruising guided missile |
| CN109703773A (en) * | 2018-12-28 | 2019-05-03 | 西北工业大学 | It is a kind of to positive unmanned plane rocket thrust transferring structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113460319B (en) | 2023-03-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9796488B2 (en) | Dual port payload attach ring compatible satellite | |
| US10494123B2 (en) | Systems for interconnecting dual manifested spacecraft | |
| CN103166049A (en) | Multi-latching mechanisms and related methods | |
| CN104890902A (en) | Fusing type compression release mechanism and release method thereof | |
| CN112373734B (en) | Low-orbit satellite group emission satellite-arrow separation unlocking module and satellite-arrow separation method | |
| CN204775993U (en) | Wing device is folded to aircraft | |
| CN113460319B (en) | Tandem booster fireless separation structure and aircraft with same | |
| CN105539886B (en) | A kind of spring control separates unlocking mechanism | |
| US2889746A (en) | Explosive bolt type store suspension system for aircraft | |
| US10150556B2 (en) | Low-profile wing hinge mechanism | |
| EP0185852A1 (en) | Pilotless missile | |
| CN108615654A (en) | A kind of memorial alloy and inertial confinement multi-channel switch | |
| US20150153135A1 (en) | Umbilical cable disconnect | |
| EP4253227A1 (en) | Quick-release wing structure and an unmanned aerial vehicle using the same | |
| CN209126975U (en) | The separator and unmanned plane of unmanned plane recorery parachute | |
| CN108820188B (en) | Quick detach subassembly and unmanned aerial vehicle | |
| CN212530085U (en) | Quick separation mechanism for parachute at tail of aircraft and aircraft | |
| CN210258808U (en) | Quick detach horn of unmanned aerial vehicle | |
| CN205499341U (en) | Undercarriage for unmanned aerial vehicle | |
| US2892210A (en) | Release mechanism | |
| CN113460337A (en) | Separation wing device of multi-stage cabin and multi-stage cabin structure | |
| RU2500591C1 (en) | Aircraft compartment separation system | |
| US20130315686A1 (en) | Retention, release, and separation device, system, and method | |
| CN105667769A (en) | Undercarriage for unmanned aerial vehicle | |
| CN113460320B (en) | Booster separating mechanism for unmanned aerial vehicle and method using booster separating mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |