CN106005425A - Surface contact type bus device - Google Patents
Surface contact type bus device Download PDFInfo
- Publication number
- CN106005425A CN106005425A CN201610400428.4A CN201610400428A CN106005425A CN 106005425 A CN106005425 A CN 106005425A CN 201610400428 A CN201610400428 A CN 201610400428A CN 106005425 A CN106005425 A CN 106005425A
- Authority
- CN
- China
- Prior art keywords
- airborne
- missile
- bus
- contact
- borne
- 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
- 238000004891 communication Methods 0.000 claims abstract description 15
- 238000012545 processing Methods 0.000 claims abstract description 3
- 230000005540 biological transmission Effects 0.000 claims description 7
- 239000013536 elastomeric material Substances 0.000 claims description 4
- 239000000463 material Substances 0.000 claims 2
- 210000001503 joint Anatomy 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 3
- 239000002184 metal Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000008054 signal transmission Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Classifications
-
- 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
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L12/40006—Architecture of a communication node
- H04L12/40032—Details regarding a bus interface enhancer
Landscapes
- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides a surface contact type bus device. A missile-borne surface contact bus is installed on the surface of an airborne weapon. A missile-borne signal adjustment modulator is connected with the missile-borne surface contact bus. The missile-borne signal adjustment modulator is installed in the airborne weapon. Meanwhile, an airborne surface contact bus is installed in the position, in contact with the missile-borne surface contact bus correspondingly, of the surface of an aircraft. An airborne signal adjustment modulator is connected with the airborne surface contact bus. In addition, the airborne surface contact bus and the missile-borne surface contact bus are each composed of a plurality of contact plates. The contact plates are of a grid structure. The missile-mounted signal adjustment modulator is used for modulating a signal transmitted from the airborne signal adjustment modular and processing the modulated signal into a feedback signal, then the feedback signal is modulated and input into an alternating-current power supply signal provided by the airborne weapon, and therefore communication between a carrying aircraft and the airborne weapon is achieved. The butt joint mode between the carrying aircraft and the airborne weapon is substantially simplified, the integrity of an airborne weapon missile structure is maintained, and the surface contact type bus device is especially suitable for hypersonic platforms and weapons.
Description
Technical field
The present invention relates to air communications technical field, particularly relate to a kind of surface contact bus unit.
Background technology
At present, using 1553B EBI communication between the weapon of aircraft platform and institute's carry, this interface is widely used in respectively
Type weaponry, and possess perfect relevant criterion；But this interface belongs to standard type physical interface, the interface that there is complexity is fixed
Justice requirement, for adapting to this interface requirement, various weaponry must carry out adaptability design；This interface belongs to style of opening and connects simultaneously
Mouthful, certain technical problem is existed for sealing protection, short circuit is protected, solar heat protection is protected etc., thus causes environmental requirement higher or speed
Higher aircraft is difficult to apply.
Summary of the invention
Technical problem solved by the invention is to provide a kind of surface contact bus unit, to solve above-mentioned background skill
Shortcoming in art.
Technical problem solved by the invention realizes by the following technical solutions:
A kind of surface contact bus unit, adjusts including air weapon, airborne contact bus, airborne vehicle, airborne Signal Regulation
Device processed, missile-borne Signal Regulation manipulator and missile-borne face contact bus；Wherein, contact bus in missile-borne face is arranged on air weapon table
Face, missile-borne Signal Regulation manipulator contacts bus and connects with missile-borne face, and missile-borne Signal Regulation manipulator is arranged on air weapon
In；Simultaneously contact the position of the corresponding contact of bus with missile-borne face in aircraft surface to be provided with airborne and contact bus, airborne letter
Number regulation manipulator contacts bus and connects with airborne；Additionally, airborne contact bus contacts bus respectively by counting with missile-borne face
Block contact plate forms, and contact plate is grid structure；Missile-borne Signal Regulation manipulator carries Signal Regulation manipulator for demodulating machine
The signal that sends be feedback signal by the signal processing of demodulation, then will feedback signal modulate after inject the friendship that air weapon provides
In stream power supply signal, thus realize the communication of carrier aircraft and air weapon.
In the present invention, airborne contact bus contacts bus and is made up of six pieces of contact plates respectively, owing to leading with missile-borne face
Play body structure and mostly be metal structure, designed by grid structure, form the expansible contact area of surface contact bus, with
Preventing poor contact.
In the present invention, the contact surface of monolithic contact plate is 15mm × 60mm.
In the present invention, airborne contact bus is made up of elastomeric material, owing to aircraft exists bigger in flight course
Vibration, for guaranteeing work process effectively contacts, it is desirable to elastomeric material has certain springing stroke, by on-hook vibration analysis,
The stroke of elastomeric material is more than 2.5mm.
In the present invention, air weapon provides 115v alternating current power supply, by airborne Signal Regulation manipulator by communication data
Injecting Alternating Current Power Supply signal with the modulation of carrier frequency form, the signal that missile-borne Signal Regulation manipulator demodulation carrier aircraft sends, simultaneously by anti-
Inject Alternating Current Power Supply signal after feedback signal modulation, thus realize the effective communication of carrier aircraft and air weapon.
In the present invention, airborne Signal Regulation manipulator is more than with the transmission communication transmission rate of missile-borne Signal Regulation manipulator
1Mbps。
Beneficial effect: the present invention uses the direct way of contact in surface, it is to avoid physical interface, significantly simplifies carrier aircraft and airborne force
The docking mode of device, thus keep the integrity of air weapon body structure, it is especially suitable for hypersonic speed platform and weapon uses；
While realizing air weapon structural intergrity, it is achieved signal transmission and guided missile are powered, for improving body intensity, reducing and lead
Play weight, raising thermal protection ability has important function.
Accompanying drawing explanation
Fig. 1 is the front view of presently preferred embodiments of the present invention.
Fig. 2 is the sectional view of presently preferred embodiments of the present invention.
Detailed description of the invention
For the technological means making the present invention realize, creation characteristic, reach purpose and be easy to understand with effect, below in conjunction with tool
Body illustrates, and the present invention is expanded on further.
See a kind of surface contact bus unit of Fig. 1 ~ Fig. 2, including guided missile 1, airborne contact bus 2, wing 3,
Airborne Signal Regulation manipulator 4, missile-borne Signal Regulation manipulator 5 and missile-borne face contact bus 6.
In the present embodiment, contact bus 6 in missile-borne face is arranged on guided missile 1 surface, missile-borne Signal Regulation manipulator 5 and missile-borne
Face contact bus 6 connects, and is arranged in guided missile 1；Airborne contact bus 2 is arranged on wing 3, and contacts always with missile-borne face
Line 6 contacts layout in correspondence, and airborne Signal Regulation manipulator 4 contacts bus 2 with airborne and connects；Additionally, airborne contact is total
Line 2 contacts bus 6 and is made up of six pieces of contact plates respectively with missile-borne face, and contact plate is grid structure simultaneously, due to guided missile 1 body
Structure mostly is metal structure, is designed by grid structure, forms the expansible contact area of surface contact bus, to prevent from connecing
Touch bad.
In the present embodiment, for guaranteeing that guided missile 1 and wing 3 contact surface have good contact performance, it is desirable to its area is full
The certain requirement of foot, the contact surface of monolithic contact plate is 15mm × 60mm.
In the present embodiment, airborne contact bus 2 is made up of flexure strip, owing to aircraft exists bigger in flight course
Vibration, for guaranteeing effectively to contact in work process, it is desirable to flexure strip has certain springing stroke, by on-hook vibration analysis, bullet
Property sheet stroke more than 2.5mm.
In the present embodiment, guided missile 1 provides 115v alternating current power supply, by airborne Signal Regulation manipulator 4 by communication data
Injecting Alternating Current Power Supply signal with the modulation of carrier frequency form, missile-borne Signal Regulation manipulator 5 demodulates the signal that carrier aircraft sends, simultaneously will be anti-
Inject Alternating Current Power Supply signal after feedback signal modulation, thus realize the effective communication of carrier aircraft and guided missile 1.
In the present embodiment, airborne Signal Regulation manipulator 4 is big with the transmission communication transmission rate of missile-borne Signal Regulation manipulator 5
In 1Mbps.
In the present embodiment, carrier aircraft and guided missile 1 are based on RS422 communication bus technology, by complete to original simulation and discrete communication
Portion is converted into digital communication, and 422 buses is combined with aircraft 115v Alternating Current Power Supply, uses frequency modulated mode numeral to be believed
Number transmission to guided missile, simultaneously use the direct way of contact in surface, it is to avoid physical interface, to keep the complete of guided missile 1 body structure
Property；While realizing guided missile structure integrity, it is achieved signal transmission and guided missile are powered, for improving body intensity, reducing and lead
Play weight, raising thermal protection ability has important function.
The ultimate principle of the present invention and principal character and advantages of the present invention have more than been shown and described.The technology of the industry
Personnel, it should be appreciated that the present invention is not restricted to the described embodiments, simply illustrating this described in above-described embodiment and description
The principle of invention, without departing from the spirit and scope of the present invention, the present invention also has various changes and modifications, and these become
Change and improvement both falls within scope of the claimed invention.Claimed scope by appending claims and
Equivalent defines.
Claims (6)
1. a surface contact bus unit, including air weapon, airborne contact bus, airborne vehicle, airborne Signal Regulation
Manipulator, missile-borne Signal Regulation manipulator and missile-borne face contact bus；It is characterized in that, missile-borne face contact bus is arranged on airborne
Weapon surface, missile-borne Signal Regulation manipulator contacts bus and connects with missile-borne face, and missile-borne Signal Regulation manipulator is arranged on machine
In load weapon；Simultaneously contact the position of the corresponding contact of bus with missile-borne face in aircraft surface to be provided with airborne and contact bus,
Airborne Signal Regulation manipulator contacts bus and connects with airborne；Additionally, airborne contact bus contacts bus with missile-borne face and divides
Not being made up of several piece contact plate, contact plate is grid structure；Missile-borne Signal Regulation manipulator carries Signal Regulation for demodulating machine
Signal that manipulator sends be feedback signal by the signal processing of demodulation, then inject air weapon after feedback signal being modulated and carry
In the Alternating Current Power Supply signal of confession, thus realize the communication of carrier aircraft and air weapon.
A kind of surface contact bus unit the most according to claim 1, it is characterised in that airborne contact bus and bullet
Section contact bus is made up of six pieces of contact plates respectively.
A kind of surface contact bus unit the most according to claim 2, it is characterised in that the contact surface of monolithic contact plate
For 15mm × 60mm.
A kind of surface contact bus unit the most according to claim 1, it is characterised in that airborne contact bus is by bullet
Property material make, and the stroke of elastomeric material is more than 2.5mm.
A kind of surface contact bus unit the most according to claim 4, it is characterised in that the bullet of airborne contact bus
Property material includes flexure strip.
A kind of surface contact bus unit the most according to claim 1, it is characterised in that airborne Signal Regulation manipulator
It is more than 1Mbps with the transmission communication transmission rate of missile-borne Signal Regulation manipulator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610400428.4A CN106005425B (en) | 2016-06-08 | 2016-06-08 | A kind of surface contact bus unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610400428.4A CN106005425B (en) | 2016-06-08 | 2016-06-08 | A kind of surface contact bus unit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106005425A true CN106005425A (en) | 2016-10-12 |
| CN106005425B CN106005425B (en) | 2018-01-30 |
Family
ID=57089936
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610400428.4A Active CN106005425B (en) | 2016-06-08 | 2016-06-08 | A kind of surface contact bus unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106005425B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110165240A (en) * | 2019-05-23 | 2019-08-23 | 北京机电工程研究所 | A kind of airborne missile zinc-silver reserve battery group heating, temperature keeping method and circuit |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0533581A1 (en) * | 1991-09-20 | 1993-03-24 | Thomson-Brandt Armements | Bidirectional communication apparatus between two objects and weapons system, comprising a vehicle and at least one carried load of this vehicle, equipped with such apparatus |
| FR2856209B1 (en) * | 2003-06-13 | 2005-08-05 | Thales Sa | COMMUNICATION SYSTEM BETWEEN TWO EMPLOYMENT POINTS OF AN AIRCRAFT |
| US7137599B1 (en) * | 2004-04-26 | 2006-11-21 | Raytheon Company | Launcher with dual mode electronics |
| US20120097795A1 (en) * | 2009-04-23 | 2012-04-26 | Saab Ab | Countermeasure arrangement |
| CN104236403A (en) * | 2008-09-30 | 2014-12-24 | 通用电气公司 | Store management system and method of operating the same |
-
2016
- 2016-06-08 CN CN201610400428.4A patent/CN106005425B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0533581A1 (en) * | 1991-09-20 | 1993-03-24 | Thomson-Brandt Armements | Bidirectional communication apparatus between two objects and weapons system, comprising a vehicle and at least one carried load of this vehicle, equipped with such apparatus |
| FR2856209B1 (en) * | 2003-06-13 | 2005-08-05 | Thales Sa | COMMUNICATION SYSTEM BETWEEN TWO EMPLOYMENT POINTS OF AN AIRCRAFT |
| US7137599B1 (en) * | 2004-04-26 | 2006-11-21 | Raytheon Company | Launcher with dual mode electronics |
| CN104236403A (en) * | 2008-09-30 | 2014-12-24 | 通用电气公司 | Store management system and method of operating the same |
| US20120097795A1 (en) * | 2009-04-23 | 2012-04-26 | Saab Ab | Countermeasure arrangement |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110165240A (en) * | 2019-05-23 | 2019-08-23 | 北京机电工程研究所 | A kind of airborne missile zinc-silver reserve battery group heating, temperature keeping method and circuit |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106005425B (en) | 2018-01-30 |
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