CN106711632A - Radio-frequency cable component for space navigation - Google Patents
Radio-frequency cable component for space navigation Download PDFInfo
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- CN106711632A CN106711632A CN201611155552.5A CN201611155552A CN106711632A CN 106711632 A CN106711632 A CN 106711632A CN 201611155552 A CN201611155552 A CN 201611155552A CN 106711632 A CN106711632 A CN 106711632A
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- insulator
- radio
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- chamber
- housing
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Classifications
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R4/00—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation
- H01R4/70—Insulation of connections
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B17/00—Insulators or insulating bodies characterised by their form
- H01B17/56—Insulating bodies
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B17/00—Insulators or insulating bodies characterised by their form
- H01B17/56—Insulating bodies
- H01B17/58—Tubes, sleeves, beads, or bobbins through which the conductor passes
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B17/00—Insulators or insulating bodies characterised by their form
- H01B17/56—Insulating bodies
- H01B17/58—Tubes, sleeves, beads, or bobbins through which the conductor passes
- H01B17/583—Grommets; Bushings
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R24/00—Two-part coupling devices, or either of their cooperating parts, characterised by their overall structure
- H01R24/38—Two-part coupling devices, or either of their cooperating parts, characterised by their overall structure having concentrically or coaxially arranged contacts
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R4/00—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation
- H01R4/70—Insulation of connections
- H01R4/72—Insulation of connections using a heat shrinking insulating sleeve
Landscapes
- Coupling Device And Connection With Printed Circuit (AREA)
Abstract
The invention discloses a radio-frequency cable component for space navigation. The radio-frequency cable component comprises a radio-frequency coaxial cable, a first radio-frequency connector and a second radio-frequency arranged at the two ends of the radio-frequency coaxial cable, and a marking shrinkable casing coating the radio-frequency coaxial cable. The first radio-frequency connector comprises a contact pin, a first insulator, a pressure sleeve, a second insulator, a welding sleeve, a fastening nut and a shell of which the center lines are in the same axis. The first insulator and the second insulator respectively sleeve the head and the tail of the contact pin. The center hole of the contact pin is in welding connection with the inner core of the radio-frequency coaxial cable. The pressure sleeve is arranged between the second insulator and the inner wall of the shell. The welding sleeve sleeves and is welded onto one end of the radio-frequency coaxial cable. The fastening nut sleeves the welding sleeve. The radio-frequency cable component for space navigation of the invention meets the use requirements for microwave signal transmission under sudden temperature change, in a high-radiation space environment or in a vacuum state, and improves the performance and reliability of the whole antenna system.
Description
Technical field
The invention belongs to microwave radio passive device technical field, more particularly to a kind of aerospace radio-frequency cable component.
Background technology
The CA cable assembly of existing K-type 2.92 due to use traditional CA cable assembly structure, not for cable under temperature alternating
Insulating barrier end face situation of change carries out spacing design, and the low physical characteristic of insulating materials more options low-k material,
Resistance to mechanical property and resistance to irradiation ability are poor, therefore, it is impossible to meet under high/low temperature mutation, radiation space environment high and vacuum state
The use requirement of microwave signal is transmitted, and showing for microwave transmission deterioration parameter is also easy to produce under dither and high/low temperature alternation
As, communication link is influenceed, reduce the reliability of whole product.Therefore, need design one kind badly and disclosure satisfy that high/low temperature is dashed forward
The CA cable assembly of the use requirement of microwave signal is transmitted under change, radiation space environment high and vacuum state, to improve whole antenna
The Performance And Reliability of system.
The content of the invention
Technology solve problem of the invention：Overcome the deficiencies in the prior art, there is provided a kind of aerospace radio-frequency cable component, it is full
The use requirement of microwave signal is transmitted under sufficient high/low temperature mutation, radiation space environment high and vacuum state, to improve whole antenna
The Performance And Reliability of system.
In order to solve the above-mentioned technical problem, the invention discloses a kind of aerospace radio-frequency cable component, including：Structure is identical
The first radio frequency connector (100) and the second radio frequency connector (200), and, radio frequency coaxial-cable (300) and mark Heat-Shrinkable Tubings
(400)；The two ends of the radio frequency coaxial-cable (300) are connected with first radio frequency connector (100) and the second radio frequency respectively
Device (200) is connected；Mark Heat-Shrinkable Tubings (400) is wrapped in the radio frequency coaxial-cable (300) outside；
Wherein, first radio frequency connector (100), including：Center line is located at contact pin (1), first on same axis
Insulator (2), gland (3), the second insulator (4), weldering set (5), clamp nut (6) and housing (7)；
The contact pin (1) includes：Pin head (11) and contact pin afterbody (12) that diameter increases step by step, and be arranged on slotting
Centre bore (13) on Aculeata (12)；
First insulator (2) is sleeved on pin head (11)；
Second insulator (4) is sleeved on contact pin afterbody (12)；
The centre bore (13) is welded to connect with the inner core of the radio frequency coaxial-cable (300)；
The gland (3) is arranged between second insulator (4) and the inwall of the housing (7)；
Weldering set (5) is welded with one end suit of radio frequency coaxial-cable (300)；
The clamp nut (6) is set in weldering set (5)；
The contact pin (1), the first insulator (2), gland (3), the second insulator (4), weldering set (5) and clamp nut (6)
In the inner chamber of the housing (7).
In above-mentioned aerospace radio-frequency cable component, first insulator (2) includes：The annular boss portion being linked in sequence
And flange part (23) (21)；
The clamp nut (6) includes：The nut first end portion (61) of order arrangement and nut the second end (62)；Its
In, the nut first end portion (61) is provided with external screw thread, and nut first end portion (61) inner side is provided with first step
And second step (64) (63)；
Weldering set (5) includes：The weldering of order arrangement covers first end (51) and weldering set the second end (52), and, if
Put the inner groove (53) in weldering set the second end (52)；
The housing (7) includes：Outside order arrangement, cylindrical portion (71), the first step portion that diameter gradually increases
(72) and second step portion (73), and, internal sequence arrangement, the first chamber (74), the second chamber that diameter increases successively
(75), the 3rd chamber (76) and the 4th chamber (77), and, the First terrace formed between the first chamber (74) and the second chamber (75)
(78), the second step face (79) formed between the second chamber (75) and the 3rd chamber (76), and, it is arranged on the cylindrical portion (71)
On front end face bulge loop (712).
In above-mentioned aerospace radio-frequency cable component, first insulator (2) is arranged on the first chamber of the housing (7)
(74) in；Wherein, the outer wall of first insulator (2) is contacted with the cavity wall of first chamber (74), first insulator
(2) flange part (23) abuts the First terrace (78) of the housing (7)；
The gland (3) is arranged in second chamber (75) of the housing (7)；Wherein, the outer wall of the gland (3) and institute
The cavity wall contact in the second chamber (75) is stated, the bottom of the gland (3) abuts the second step face (79) of the housing (7), described
The first air section is formed between the internal chamber wall of gland (3) and the contact pin afterbody (12)；
Second insulator (4) is arranged in second chamber (75) of the housing (7), the gland (3) is inserted with described
Between pin (1)；Wherein, the outer wall of second insulator (4) is contacted with the internal chamber wall of the gland (3)；Second insulation
The bottom of sub (4) abuts the second step face (79) of the housing (7).
In above-mentioned aerospace radio-frequency cable component, it is described weldering set (5) be arranged on the housing (7) the 3rd chamber (76) and
In 4th chamber (77)；Wherein, the second step face (79) of front end face and the housing (7) of weldering set first end (51) with
And the afterbody contact of the gland (3) is spacing；
The nut first end portion (61) of the clamp nut (6) is arranged in the 4th chamber (77) of the housing (7)；Its
In, internal thread is provided with the cavity wall of the 4th chamber (77), coordinate company with the external screw thread on the nut first end portion (61)
Connect；The nut the second end (62) is carried out spacing positioned at the 4th chamber (77) outside to the clamp nut (6)；Set
First step (63) on the inside of the nut first end portion (61) contacts limit with the rear end face of weldering set the second end (52)
Position；The second step (64) of the clamp nut (6) be arranged on it is described weldering set the second end (52) inner groove (53) between
Constitute scolding tin trickling space.
In above-mentioned aerospace radio-frequency cable component, cable core and the contact pin (1) of the radio frequency coaxial-cable (300) are welded
Connect in succession；
Wherein, the cable core of the radio frequency coaxial-cable (300) by the step of the contact pin afterbody (12) with it is described
Annular boss portion (21) contact of the first insulator (2), makes first insulator (2) convex with the front end face of the housing (7)
Ring (712) is compressed, and to the cable core front limit of radio frequency coaxial-cable (300), and forms the second air section；And, by
Two insulators (4) are compressed with the end face of radio frequency coaxial-cable (300), to spacing after the cable core of radio frequency coaxial-cable (300).
In above-mentioned aerospace radio-frequency cable component, the housing (7) also includes：It is arranged on the front end face bulge loop
(712) annular groove (711) on；Wherein, the inner space of the annular groove (711) and housing (7).
In above-mentioned aerospace radio-frequency cable component, first radio frequency connector (100) also includes：Attaching nut (9)
With jump ring (8)；The housing (7) also includes：It is arranged on the spring card slot (710) on the first step portion (72)；
The jump ring (8) is arranged in the spring card slot (710)；
The attaching nut (9) is connected by the jump ring (8) with the housing (7).
In above-mentioned aerospace radio-frequency cable component, first insulator (2) includes：Along first insulator (2)
The equally distributed multiple first through hole in axis；
Second insulator (4) includes：Axis equally distributed multiple second along second insulator (4) leads to
Hole.
In above-mentioned aerospace radio-frequency cable component, the cable (300) is flexible or semi-flexible radio frequency coaxial-cable；
First insulator (2) is modified polyphenyl ether material；
Second insulator (4) is polyetherimide material.
The present invention has advantages below：
(1) heretofore described aerospace radio-frequency cable component, using double insulator supported design, can bear compared with Gao Zhen
Dynamic impact and temperature alternating impact, reduce the risk of CA cable assembly microwave transmission deterioration parameter under extraneous environmental catastrophe,
The highly reliable resistance to Space environmental property of CA cable assembly is realized on the basis of excellent microwave transmission parameter is ensured.
(2) heretofore described aerospace radio-frequency cable component, using the first insulation of two sections of different materials and structure
Son and the second insulator, compared with the single insulator of traditional six hole open flume types or cylindrical band ledge structure, mechanical performance is obtained
Enhancing is arrived so that aerospace radio-frequency cable component of the present invention has highly reliable characteristic.
(3) heretofore described aerospace radio-frequency cable component, using setting insulation patch between contact pin and cable
Structure, insulation patch is spacing before and after being carried out to cable inner core, compared with traditional air gap structure, can connect ultrashort cable
(e.g., cable of the length less than 30mm), further enhancing the environment resistant of aerospace radio-frequency cable component of the present invention
Energy and mechanical performance, with highly reliable characteristic.
(4) cavity structure that clamp nut of the invention is constituted with the step and chamfering of weldering set, can make weldering cover afterbody and overflow
Go out scolding tin and form preferable rounding arc angle, compared with traditional afterbody is without chamfering weldering nested structure, improve present invention weldering set welding
When yield rate and reliability.
(5) heretofore described aerospace radio-frequency cable component is specifically as follows the CA cable assembly of K-type 2.92, due to using
Accurate microwave parameters simulation optimization designing technique, high specific strength insulator structure Compensation Design technology and the spacing knot of temperature variation resistant
Structure designing technique, and the isolator material physical property reliability for using, therefore working band is wider, power is higher, and microwave is passed
Defeated performance and resistance to Space environmental property are more preferable.The working frequency of aerospace radio-frequency cable component of the present invention can for DC~
40GHz, standing-wave ratio is less than 1.30, and operating temperature is -100 DEG C~+130 DEG C, can be worked under high vacuum environment, realizes that space is appointed
Connection between the meaning interface of position K-type 2.92.
Brief description of the drawings
Fig. 1 is a kind of attachment structure schematic diagram of aerospace radio-frequency cable component in the embodiment of the present invention；
Fig. 2 is a kind of assembling schematic diagram of radio frequency connector in the embodiment of the present invention；
Fig. 3 is the cross-sectional view of the radio frequency connector shown in Fig. 2；
Fig. 4 is the structural representation of the first insulator in the radio frequency connector shown in Fig. 2；
Fig. 5 is the structural representation of the second insulator in the radio frequency connector shown in Fig. 2；
Fig. 6 is the structural representation of the clamp nut in the radio frequency connector shown in Fig. 2；
Fig. 7 is the structural representation of the weldering set in the radio frequency connector shown in Fig. 2；
Fig. 8 is the structural representation of the housing in the radio frequency connector shown in Fig. 2.
Specific embodiment
It is public to the present invention below in conjunction with accompanying drawing to make the object, technical solutions and advantages of the present invention clearer
Implementation method is described in further detail.
Reference picture 1, shows a kind of attachment structure schematic diagram of aerospace radio-frequency cable component in the embodiment of the present invention.Its
In, the aerospace is included with radio-frequency cable component：Structure identical the first radio frequency connector 100 and the second radio frequency connector 200,
And, radio frequency coaxial-cable 300 and mark Heat-Shrinkable Tubings 400.
In the present embodiment, the two ends of the radio frequency coaxial-cable 300 respectively with first radio frequency connector 100 and
Two radio frequency connectors 200 are connected；The mark Heat-Shrinkable Tubings 400 are wrapped in the outside of the radio frequency coaxial-cable 300.Wherein, it is described
Cable 300 can be flexible or semi-flexible radio frequency coaxial-cable；The length of the cable 300 can be pressed before assembly as needed
Need to cut, and bent before assembly as needed or bent when in use.
Reference picture 2, shows a kind of assembling schematic diagram of radio frequency connector in the embodiment of the present invention；Reference picture 3, is Fig. 2
The cross-sectional view of shown radio frequency connector.As previously described, because the first radio frequency connector 100 and the connection of the second radio frequency
The physical dimension of device 200 is completely the same, therefore, in the present embodiment, illustrated by taking the first radio frequency connector 100 as an example, second
The concrete structure of radio frequency connector 200 is referred to the structure description of first radio frequency connector 100.
In the present embodiment, with reference to Fig. 2 and Fig. 3, first radio frequency connector 100 can specifically include：Center line position
In the contact pin 1 on same axis, the first insulator 2, gland 3, the second insulator 4, weldering set 5, clamp nut 6 and housing 7.Its
In, the contact pin 1 includes：Pin head 11 and contact pin afterbody 12 that diameter gradually increases, and be arranged on contact pin afterbody 12
Centre bore 13.
In the present embodiment, the first insulator 2 is sleeved on pin head 11；Second insulator 4 is sleeved on contact pin afterbody
On 12；The inner core of the radio frequency coaxial-cable 300 stretches into the centre bore 13, and by way of welding with the centre bore 13
Connection.Gland 3 is arranged between second insulator 4 and the inwall of the housing 7；The weldering set 5 and radio frequency coaxial-cable
300 one end suit welding.Clamp nut 6 is set on weldering set 5.The contact pin 1, the first insulator 2, gland 3, second insulate
Son 4, weldering set 5 and clamp nut 6 are located in the inner chamber of the housing 7.
It is right with reference to the concrete structure of each parts in the aerospace radio-frequency cable component described in the embodiment of the present invention
The specific annexation between each parts in the aerospace radio-frequency cable component is described in detail.
Reference picture 4, is the structural representation of the first insulator in the radio frequency connector shown in Fig. 2.Such as Fig. 4, described the
One insulator 2 can specifically include：The annular boss portion 21 being linked in sequence and flange part 23, and, along first insulator 2
The equally distributed multiple first through hole (first through hole as shown in Figure 4 22 in axis.Preferably, in the present embodiment, institute
The quantity for stating first through hole can be 6, and 6 first through hole reduce the comprehensive dielectric coefficient of the first insulator 2, favorably
In impedance matching.
Reference picture 5, is the structural representation of the second insulator in the radio frequency connector shown in Fig. 2.Such as Fig. 5, described the
Two insulators 4 can specifically include：Along equally distributed multiple second through holes in the axis of second insulator 4 (in such as Fig. 5
The second shown through hole 41).Preferably, in the present embodiment, the quantity of second through hole can be 6, described 6 second
The effect of through hole and the type of action of above-mentioned 6 first through hole, can reduce the comprehensive dielectric coefficient of the second insulator 4, favorably
In impedance matching.
Reference picture 6, is the structural representation of the clamp nut in the radio frequency connector shown in Fig. 2.Such as Fig. 6, the fastening
Nut 6 can specifically include：The nut first end portion 61 of order arrangement and nut the second end 62.Wherein, the nut first
End 61 is provided with external screw thread, and the inner side of the nut first end portion 61 is provided with first step 63 and second step 64.
Reference picture 7, is the structural representation of the weldering set in the radio frequency connector shown in Fig. 2.Such as Fig. 7, it is specific that the weldering covers 5
Can include：The weldering set first end 51 and weldering set the second end 52 of order arrangement, and, it is arranged on the weldering set the second end
52 inner groove 53.
Reference picture 8, is the structural representation of the housing in the radio frequency connector shown in Fig. 2.Such as Fig. 8, the housing 7 is specific
Can include：Outside order arrangement, the first step portion 72 of cylindrical portion 71 and second step portion 73 that diameter gradually increases, with
And, internal sequence is arranged, the first chamber 74 that diameter increases successively, the second chamber 75, the 3rd chamber 76 and the 4th chamber 77, and, the
The First terrace 78 formed between one chamber 74 and the second chamber 75, the second step face formed between the second chamber 75 and the 3rd chamber 76
79, and, it is arranged on the front end face bulge loop 712 in the cylindrical portion 71.
Understood with reference to above-mentioned Fig. 2-8：
First insulator 2 is arranged in the first chamber 74 of the housing 7.Wherein, the outer wall of first insulator 2 and institute
The cavity wall contact in the first chamber 74 is stated, the flange part 23 of first insulator 2 abuts the First terrace 78 of the housing 7.
Gland 3 is arranged in the second chamber 75 of the housing 7.Wherein, the outer wall of the gland 3 and second chamber 75
Cavity wall is contacted, and the bottom of the gland 3 abuts the second step face 79 of the housing 7, and the internal chamber wall of the gland 3 is inserted with described
The first air section is formed between Aculeata 12.Wherein, first is formed between the internal chamber wall of the gland 3 and the contact pin afterbody 12
Air section is conducive to impedance matching.
Second insulator 4 is arranged in the second chamber 75 of the housing 7, between the gland 3 and the contact pin 1.Wherein,
The outer wall of second insulator 4 is contacted with the internal chamber wall of the gland 3；The bottom of second insulator 4 abuts the shell
The second step face 79 of body 7.
Weldering set 5 is arranged in the 3rd chamber 76 and the 4th chamber 77 of the housing 7；Wherein, the weldering covers first end 51
Front end face contacts spacing with the second step face 79 of the housing 7 and the afterbody of the gland 3.
The nut first end portion 61 of clamp nut 6 is arranged in the 4th chamber 77 of the housing 7.Wherein, the 4th chamber
Internal thread is provided with 77 cavity wall, is connected with the external screw thread in the nut first end portion 61；The end of the nut second
Portion 62 is located at the outside of the 4th chamber 77, the clamp nut 6 is carried out spacing；It is arranged on the inner side of the nut first end portion 61
First step 63 with it is described weldering set the second end 52 rear end face contact spacing；The second step 64 of the clamp nut 6 with
It is arranged on composition scolding tin trickling space between the inner groove 53 of the weldering set the second end 52.
The cable core of radio frequency coaxial-cable 300 is welded to connect with contact pin 1.Wherein, the electricity of the radio frequency coaxial-cable 300
Cable core is contacted by the step of the contact pin afterbody 12 with the annular boss portion 21 of first insulator 2, makes described first
Insulator 2 is compressed with the front end face bulge loop 712 of the housing 7, to the cable core front limit of radio frequency coaxial-cable 300, and shape
Into the second air section；And, compressed with the end face of radio frequency coaxial-cable 300 by the second insulator 4, to radio frequency coaxial-cable
It is spacing after 300 cable core., wherein it is desired to explanation, in the present embodiment, before the first insulator 2 and the housing 7
The second air section that end face bulge loop 712 is formed is conducive to impedance-compensated；Secondly, the insulator 4 of first insulator 2 and second is total to
It is same to realize that, to the spacing of the inner core of radio frequency coaxial-cable 300, two insulators are respectively provided with precise impedance compensation performance and ratio high by force
Degree, housing 7 is isolated entirely from contact pin 1 and cable inner core, enhances the aerospace radio-frequency cable described in the embodiment of the present invention
The anti-vacuum micro discharge ability of component；Additionally, double insulating supporting structures that 2 and second insulator of the first insulator 4 is constituted
Mechanical Reliability is high, improves reliability of the aerospace radio-frequency cable component under aerospace environment.
In the preferred embodiment of the present invention, as shown in figure 8, the housing 7 also includes：It is arranged on the front end face convex
Annular groove 711 on ring 712, wherein, the inner space of the annular groove 711 and housing 7 is conducive to the inner chamber of housing 7
Air is discharged rapidly in the environment that air pressure is reduced, and improves the aerospace radio-frequency cable component under high/low temperature alternation environment
Anti- vacuum micro discharge and anti-low pressure discharge ability so that the aerospace described in the embodiment of the present invention has with radio-frequency cable component
Good resistance to Space environmental property.
In another preferred embodiment of the invention, with reference to Fig. 2 and 3, first radio frequency connector 100 can also be wrapped
Include：Attaching nut 9 and jump ring 8；Further, such as Fig. 8, the housing 7 can also include：It is arranged in the first step portion 72
Spring card slot 710.Wherein, the jump ring 8 is arranged in the spring card slot 710；The attaching nut 9 passes through the jump ring
8 are connected with the housing 7.
It should be noted that in aerospace component, conventional insulating materials has four kinds：Polytetrafluoroethylene (PTFE), modified polyphenyl
Ether, PEI and polyether-ether-ketone.Any one insulating materials can be selected to process and to obtain first insulator 2 and institute
State the second insulator 4, it is preferred that in the present embodiment, first insulator 2 can be modified polyphenyl ether material, described the
Two insulators 4 can be polyetherimide material.
In sum, heretofore described aerospace radio-frequency cable component, using double insulator supported design, can bear
Compared with high vibration impact and temperature alternating impact, CA cable assembly microwave transmission deterioration parameter under extraneous environmental catastrophe is reduced
Risk, realizes the highly reliable resistance to Space environmental property of CA cable assembly on the basis of excellent microwave transmission parameter is ensured.
Secondly, first insulator and the second insulator of two sections of different materials and structure, with traditional six hole open flume types or
The single insulator of cylindrical band ledge structure is compared, and mechanical performance is strengthened so that aerospace radio frequency of the present invention
CA cable assembly has highly reliable characteristic.
Again, using the structure that insulation patch is set between contact pin and cable, before insulation patch can be carried out to cable inner core
It is spacing afterwards, compared with traditional air gap structure, ultrashort cable (e.g., cable of the length less than 30mm) can be connected, further
The environmental resistance and mechanical performance of aerospace radio-frequency cable component of the present invention are enhanced, with highly reliable characteristic.
Further, the cavity structure that clamp nut of the invention is constituted with the step and chamfering of weldering set, can cover weldering
Afterbody overflows scolding tin and forms preferable rounding arc angle, compared with traditional afterbody is without chamfering weldering nested structure, improves weldering of the present invention
Yield rate and reliability during set welding.
Additionally, heretofore described aerospace radio-frequency cable component is specifically as follows the CA cable assembly of K-type 2.92, due to adopting
It is spacing with accurate microwave parameters simulation optimization designing technique, high specific strength insulator structure Compensation Design technology and temperature variation resistant
Structure-design technique, and the isolator material physical property reliability for using, therefore working band is wider, power is higher, microwave
Transmission performance and resistance to Space environmental property are more preferable.The working frequency of aerospace radio-frequency cable component of the present invention can be DC
~40GHz, standing-wave ratio is less than 1.30, and operating temperature is -100 DEG C~+130 DEG C, can be worked under high vacuum environment, realizes space
Connection between the interface of optional position K-type 2.92.
The above, optimal specific embodiment only of the invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can be readily occurred in,
Should all be included within the scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (9)
1. a kind of aerospace radio-frequency cable component, it is characterised in that including：The radio frequency connector of structure identical first (100) and
Second radio frequency connector (200), and, radio frequency coaxial-cable (300) and mark Heat-Shrinkable Tubings (400)；The radio frequency coaxial-cable
(300) two ends are connected with first radio frequency connector (100) and the second radio frequency connector (200) respectively；The mark contracting
Sleeve pipe (400) is wrapped in the radio frequency coaxial-cable (300) outside；
Wherein, first radio frequency connector (100), including：Center line is located at contact pin (1), the first insulation on same axis
Sub (2), gland (3), the second insulator (4), weldering set (5), clamp nut (6) and housing (7)；
The contact pin (1) includes：Pin head (11) and contact pin afterbody (12) that diameter increases step by step, and it is arranged on contact pin tail
Centre bore (13) in portion (12)；
First insulator (2) is sleeved on pin head (11)；
Second insulator (4) is sleeved on contact pin afterbody (12)；
The centre bore (13) is welded to connect with the inner core of the radio frequency coaxial-cable (300)；
The gland (3) is arranged between second insulator (4) and the inwall of the housing (7)；
Weldering set (5) is welded with one end suit of radio frequency coaxial-cable (300)；
The clamp nut (6) is set in weldering set (5)；
The contact pin (1), the first insulator (2), gland (3), the second insulator (4), weldering set (5) and clamp nut (6) are located at
In the inner chamber of the housing (7).
2. radio-frequency cable component according to claim 1, it is characterised in that
First insulator (2) includes：The annular boss portion (21) being linked in sequence and flange part (23)；
The clamp nut (6) includes：The nut first end portion (61) of order arrangement and nut the second end (62)；Wherein, institute
State nut first end portion (61) and be provided with external screw thread, nut first end portion (61) inner side be provided with first step (63) and
Second step (64)；
Weldering set (5) includes：The weldering of order arrangement covers first end (51) and weldering set the second end (52), and, it is arranged on
The inner groove (53) of weldering set the second end (52)；
The housing (7) includes：Outside order arrangement, the cylindrical portion (71) that diameter gradually increases, first step portion (72) with
And second step portion (73), and, internal sequence is arranged, the first chamber (74) that diameter increases successively, the second chamber (75), the 3rd
Chamber (76) and the 4th chamber (77), and, First terrace (78), the second chamber formed between the first chamber (74) and the second chamber (75)
(75) the second step face (79) formed and the 3rd chamber (76) between, and, it is arranged on the front end face in the cylindrical portion (71)
Bulge loop (712).
3. radio-frequency cable component according to claim 2, it is characterised in that
First insulator (2) is arranged in first chamber (74) of the housing (7)；Wherein, first insulator (2)
Outer wall is contacted with the cavity wall of first chamber (74), and the flange part (23) of first insulator (2) abuts the housing (7)
First terrace (78)；
The gland (3) is arranged in second chamber (75) of the housing (7)；Wherein, the outer wall of the gland (3) and described
The cavity wall contact in two chambers (75), the bottom of the gland (3) abuts the second step face (79) of the housing (7), the gland
(3) the first air section is formed between internal chamber wall and the contact pin afterbody (12)；
Second insulator (4) is arranged in second chamber (75) of the housing (7), the gland (3) and the contact pin (1)
Between；Wherein, the outer wall of second insulator (4) is contacted with the internal chamber wall of the gland (3)；Second insulator (4)
Bottom abut the second step face (79) of the housing (7).
4. radio-frequency cable component according to claim 2, it is characterised in that
Weldering set (5) is arranged in the 3rd chamber (76) and the 4th chamber (77) of the housing (7)；Wherein, the weldering set first
The front end face of end (51) contacts spacing with the second step face (79) of the housing (7) and the afterbody of the gland (3)；
The nut first end portion (61) of the clamp nut (6) is arranged in the 4th chamber (77) of the housing (7)；Wherein, institute
Internal thread is provided with the cavity wall for stating the 4th chamber (77), is connected with the external screw thread on the nut first end portion (61)；Institute
Nut the second end (62) is stated positioned at the 4th chamber (77) outside, the clamp nut (6) is carried out spacing；It is arranged on described
First step (63) on the inside of nut first end portion (61) contacts spacing with the rear end face of weldering set the second end (52)；It is described
The second step (64) of clamp nut (6) be arranged on it is described weldering set the second end (52) inner groove (53) between constitute scolding tin
Trickling space.
5. radio-frequency cable component according to claim 2, it is characterised in that the cable of the radio frequency coaxial-cable (300)
Core is welded to connect with contact pin (1)；
Wherein, the step and described first that the cable core of the radio frequency coaxial-cable (300) passes through the contact pin afterbody (12)
Annular boss portion (21) contact of insulator (2), makes the front end face bulge loop of first insulator (2) and the housing (7)
(712) compress, to the cable core front limit of radio frequency coaxial-cable (300), and form the second air section；And, by second
Insulator (4) is compressed with the end face of radio frequency coaxial-cable (300), to spacing after the cable core of radio frequency coaxial-cable (300).
6. radio-frequency cable component according to claim 2, it is characterised in that the housing (7) also includes：It is arranged on described
Annular groove (711) on front end face bulge loop (712)；Wherein, the inner space of the annular groove (711) and housing (7).
7. radio-frequency cable component according to claim 2, it is characterised in that first radio frequency connector (100) is also wrapped
Include：Attaching nut (9) and jump ring (8)；The housing (7) also includes：It is arranged on the Spring Card on the first step portion (72)
Groove (710)；
The jump ring (8) is arranged in the spring card slot (710)；
The attaching nut (9) is connected by the jump ring (8) with the housing (7).
8. radio-frequency cable component according to claim 1, it is characterised in that
First insulator (2) includes：Along the equally distributed multiple first through hole in axis of first insulator (2)；
Second insulator (4) includes：Along equally distributed multiple second through holes in the axis of second insulator (4).
9. the radio-frequency cable component according to claim any one of 1-8, it is characterised in that
The cable (300) is flexible or semi-flexible radio frequency coaxial-cable；
First insulator (2) is modified polyphenyl ether material；
Second insulator (4) is polyetherimide material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611155552.5A CN106711632A (en) | 2016-12-14 | 2016-12-14 | Radio-frequency cable component for space navigation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611155552.5A CN106711632A (en) | 2016-12-14 | 2016-12-14 | Radio-frequency cable component for space navigation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106711632A true CN106711632A (en) | 2017-05-24 |
Family
ID=58937667
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611155552.5A Pending CN106711632A (en) | 2016-12-14 | 2016-12-14 | Radio-frequency cable component for space navigation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106711632A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110514283A (en) * | 2019-08-02 | 2019-11-29 | 闫志伟 | A kind of floated weighing sensor |
| CN112563841A (en) * | 2020-11-11 | 2021-03-26 | 中国航天时代电子有限公司 | 6.25Gbps coaxial structure differential data cable assembly for aerospace |
| CN112636279A (en) * | 2020-12-17 | 2021-04-09 | 贵州航天电子科技有限公司 | Connecting method and connecting mechanism for stainless steel hose and radio frequency connector |
| CN114665343A (en) * | 2022-03-22 | 2022-06-24 | 中航光电科技股份有限公司 | Radio frequency coaxial socket and vehicle-mounted radio frequency coaxial connector |
| CN114678671A (en) * | 2022-03-10 | 2022-06-28 | 中国航天时代电子有限公司 | High-power resistant TNC radio frequency cable subassembly of radiation outside cabin for aerospace |
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| CN102437466A (en) * | 2011-08-17 | 2012-05-02 | 镇江华坚电子有限公司 | Spiral connector with opposite poles |
| CN104377480A (en) * | 2014-10-30 | 2015-02-25 | 中国航天时代电子公司 | Outside-cabin high-power TNC cable assembly for astronavigation |
| CN105957599A (en) * | 2016-07-09 | 2016-09-21 | 中国电子科技集团公司第四十研究所 | High-power radio frequency coaxial cable component for aerospace |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102437466A (en) * | 2011-08-17 | 2012-05-02 | 镇江华坚电子有限公司 | Spiral connector with opposite poles |
| CN104377480A (en) * | 2014-10-30 | 2015-02-25 | 中国航天时代电子公司 | Outside-cabin high-power TNC cable assembly for astronavigation |
| CN105957599A (en) * | 2016-07-09 | 2016-09-21 | 中国电子科技集团公司第四十研究所 | High-power radio frequency coaxial cable component for aerospace |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110514283A (en) * | 2019-08-02 | 2019-11-29 | 闫志伟 | A kind of floated weighing sensor |
| CN112563841A (en) * | 2020-11-11 | 2021-03-26 | 中国航天时代电子有限公司 | 6.25Gbps coaxial structure differential data cable assembly for aerospace |
| CN112563841B (en) * | 2020-11-11 | 2022-06-28 | 中国航天时代电子有限公司 | 6.25Gbps coaxial structure differential data cable assembly for aerospace |
| CN112636279A (en) * | 2020-12-17 | 2021-04-09 | 贵州航天电子科技有限公司 | Connecting method and connecting mechanism for stainless steel hose and radio frequency connector |
| CN112636279B (en) * | 2020-12-17 | 2022-02-22 | 贵州航天电子科技有限公司 | Connecting method and connecting mechanism for stainless steel hose and radio frequency connector |
| CN114678671A (en) * | 2022-03-10 | 2022-06-28 | 中国航天时代电子有限公司 | High-power resistant TNC radio frequency cable subassembly of radiation outside cabin for aerospace |
| CN114665343A (en) * | 2022-03-22 | 2022-06-24 | 中航光电科技股份有限公司 | Radio frequency coaxial socket and vehicle-mounted radio frequency coaxial connector |
| CN114665343B (en) * | 2022-03-22 | 2024-04-05 | 中航光电科技股份有限公司 | Radio frequency coaxial socket and vehicle-mounted radio frequency coaxial connector |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170524 |
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| RJ01 | Rejection of invention patent application after publication |