CN106586016A - Air rearming system - Google Patents
Air rearming system Download PDFInfo
- Publication number
- CN106586016A CN106586016A CN201610919876.5A CN201610919876A CN106586016A CN 106586016 A CN106586016 A CN 106586016A CN 201610919876 A CN201610919876 A CN 201610919876A CN 106586016 A CN106586016 A CN 106586016A
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- China
- Prior art keywords
- rope
- firing mount
- aerial
- ropes
- shengzhu
- Prior art date
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- 230000005674 electromagnetic induction Effects 0.000 claims abstract description 16
- 239000000696 magnetic material Substances 0.000 claims abstract description 11
- 238000010304 firing Methods 0.000 claims description 36
- 230000005611 electricity Effects 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 2
- 239000002828 fuel tank Substances 0.000 abstract description 5
- 238000000034 method Methods 0.000 description 7
- 230000005484 gravity Effects 0.000 description 4
- 210000001015 abdomen Anatomy 0.000 description 3
- 238000004804 winding Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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
- B64F1/36—Other airport installations
-
- 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
- B64D39/00—Refuelling during flight
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Electric Cable Installation (AREA)
- Load-Engaging Elements For Cranes (AREA)
Abstract
An air rearming system mainly comprises a bomb loading frame and a sliding track. The bomb loading frame comprises a frame body, a rope system and a circuit control system. The bomb loading frame is designed into a shape of a Delta flying wing or a triangular frame; three wheels are arranged under three corners; a bomb or a fuel tank is placed in an appropriate position on the back of the bomb loading frame so that aircrafts are convenient to be hung and buckled. Three ropes are respectively arranged above the three corners of the bomb loading frame; and by using a mode of pressing rope ends, the ropes are wound on an electric winch to be wound and unwound. Three electromagnetic induction switches are arranged in a circuit in series; magnetic material sheets arranged on the ropes are used for controlling the circuit to be connected and broken; and four rope columns are arranged on the sliding track behind the bomb loading frame to expand the ropes so that the aircrafts are convenient to be hung and buckled.
Description
Art
The invention belongs to it is a kind of also can complete in the air in the case of nonstop to hang bullet for opportunity of combat or hang fuel tank it is complete from
Dynamic operating system, can also extend the combat radius of operational aircraft in the case of without tanker aircraft or aircraft carrier.
Background technology
Current technical background, the main method for extending opportunity of combat combat radius is air refuelling, or using aircraft carrier
Open-ocean operations are carried out, both approaches technical difficulty is big, and construction cost is big, and cost of use is high, and little country has no ability at all
Purchase is built or using both armament systems.Both armament systems also have short slab, are exactly that target is big easily under attack,
Once damage, operational aircraft just again cannot fly back land.Aerial extension bullet system of the invention, can be used alone, it is also possible to make
For the stand-by equipment of tanker aircraft.
The content of the invention
In order to realize that aerial extension plays this purpose, the present invention is aerial to hang bullet system, mainly includes two big element of installation, carries bullet
Frame and dragging track.Carrying firing mount includes support body, tethered system, circuit control system, dynamical system, Remote Control Recovery System.Slide
Track includes track and a rope support.
The technical solution adopted for the present invention to solve the technical problems is：Load firing mount is designed to triangle flying wing or triangle
The shape of framework, parallel empennage is arranged on back, and vertical tail is directed downward, and top edge is put down no more than the upper of firing mount is carried
The belly of aircraft is pressed close at face, the back for carrying firing mount with blocking-proof.Before one being respectively provided with below three angles of triangle flying wing
Wheel and two trailing wheels, wheel design requires to roll in grooved tracks, is made up of metal or other hard wear-resistant materials.
Put guided missile or fuel tank to facilitate aircraft to buckle in the suitable position of back of triangle flying wing.In the upper of three angles of triangle flying wing
Face arranges three ropes, in case aircraft hangs up rope and slings bomb rack, respectively arranges above two angles of the back of flying wing
One pulley is used for wire rope handling, and at the rear portion of flying wing an electric capstan is provided with, and is introduced through from two pulleys with folding and unfolding for laying in
The rope for coming, arranges an electric capstan, for laying in that root arranged above with folding and unfolding anterior angle above flying wing front portion
Rope, two electric capstans withdrawal rope that can be in due course makes bomb rack press close to the belly of aircraft to hang bullet.Two electricity
There is certain frictional force during dynamic capstan winch rope stretching, can tighten during rope rope to open below.Carry firing mount below equipped with one to
Two rocket propulsions, for mitigating the downward gravity of bomb rack with the thrust of rocket propulsion when hanging and snapping into row.Circuit
Control system：After the wire drawn from battery anode electric capstan respectively through two pulleys below and above, then connect
To the positive pole and the positive pole of two rocket propulsion electric controllers of two electric capstan motors.On this root wire, near below
Where where the rope that two pulleys are drawn is passed through and above electric capstan rope is passed through, three electromagnetic induction are arranged in series
Switch.Magnetic material sheets being is wrapped in the appropriate position of three ropes front end, for closed electromagnetic inductive switch, at the end of rope
Magnetic material sheets being is wrapped in the appropriate position in end, for opening electromagnetic induction switch at the end of electric capstan rope closing.Motor
The negative pole of negative pole and rocket propulsion electric controller is connected to the negative pole of battery pack.When magnetic material sheets being is through electromagnetic induction switch,
After three electromagnetic switch are all closed, could power to motor and rocket propulsion electric controller.
Track is made up of three groove type parallel orbits, and three wheels for being respectively supplied to carry firing mount are used.The length of slideway
Degree is determined by different use platform and concrete condition.The certain length of one section of the beginning of slideway, is designed with certain friction system
Number, and appropriate frictional force can be produced, aircraft is suspended to after three ropes, rope can be tightened together.In the initial bit of track
Put four vertical Zhang Shengzhu of equidistant setting on the direction vertical with track, both sides two Zhang Shengzhu upper end and under
End is respectively respectively provided with one rope clamp, and in the top and bottom of Zhong Jian two Zhang Shengzhu two rope clamps are respectively respectively provided with.
Rope clamp opening has appropriate grip force towards load firing mount, can make rope tension, can not come off easily again, and aircraft can be made again
Rope can be pulled off from a rope clamp when being suspended to rope.Open a rope method of rope support：Three spaces are formed by four rope posts, two
The corresponding rope drawn from two pulleys is opened respectively in two spaces on side, and a middle space is used for opening above electric mincing
The rope that disk is drawn.The rope that one pulley is drawn is under a rope clamp of a Zhang Shengzhu bottom of corresponding space
Face upwards through that guides to this root Zhang Shengzhu tops opens rope clamp, also passes through from bottom to top, then rope is guided to this space opposite
A piece Zhang Shengzhu, is passed down through rope from above the rope clamp on this root Zhang Shengzhu tops, then rope from this root Zhang Shengzhu
It is passed down through above a rope clamp of bottom, the end of this root rope is arranged one and crosses becket bridle, this ring set in this root rope
On the rope of the first rope clamp bottom that rope is passed through.Thus rope is opened on this space the square of a closing
Propped up by four rope clamps that this root rope is passed through at shape, four angles of this rectangle.Remaining two rope takes same
Method is opened on its corresponding space, so that aircraft is buckled.
Three are respectively provided with the front portion of aircraft and the corresponding position of both wings and stretch the hook that has certain length downwards, work as aircraft
Along the direction of track, that middle root track is directed at, by certain altitude, hook will respectively tangle three for opening
Rope, rope is pulled from a rope support, and due to there is certain frictional force during electric capstan rope stretching, track has certain frictional force,
At this moment three ropes will be tightened up exceptionally straight, carry firing mount and slide in orbit, and capstan winch continues rope stretching, when three front end magnetic on rope
Property piece respectively through three electromagnetic induction switch when, three switches are respectively closed, and motor and rocket propulsion electric controller are supplied simultaneously
Electricity, electric capstan stops rope stretching, and starts rope closing, rocket propulsion ignition operation, when the thrust of rocket propulsion is load firing mount
Gravity mitigate to a certain extent after, carrying firing mount will be hung to aerial by aircraft, and electric capstan winch continues rope closing, press close to winged when firing mount is carried
When ventral portion is to certain position, the magnetic material sheets being of rope end is switched off through electromagnetic induction switch, and electric capstan breaks
Electricity, stalling are simultaneously locked, and at this moment guided missile or fuel tank have been sent to the position that aircraft is capable of carry automatically, after the automatic carry of aircraft,
Release carries firing mount, carries firing mount remote control and reclaims.
The design requirement of electric capstan：Being powered before starting can reverse free rope stretching, will be with certain during electric capstan winch rope stretching
Frictional force, can so tighten rope and be avoided that disorder cable (just as a kind of water droplet wheel and drum of Lu Yayong, typically takes electromagnetism again
The form of brake is avoiding random line), locking state is reversed into after power failure, it is impossible to rope stretching again.Afterwards electric capstan can be a strand
Disk separates into two parts, and the rope for being introduced through is wound from two pulleys respectively, during rope stretching, can with a partial turn rope stretching,
Another part does not rotate not rope stretching, while rope closing during rope closing.The rope-winding method of electric capstan is：Rope should not be fastened dead strand
On disk, fag end is pressed on capstan winch, compresses tightly wrap from level to level, so, three ropes do not hang up if one, just have
One magnetic switch can not be closed, because three magnetic switch are used in series, circuit would not be powered, and electric capstan would not work
Make, two for hanging up piece rope continues rope stretching on capstan winch, until rope has gone out, depart from capstan winch, be unlikely in load firing mount oblique pull
My god, there is accident.
The invention has the beneficial effects as follows：Aerial to hang bullet system, low cost can be placed on many platforms and use, such as vapour
On Che Shang, steamer, on submarine, the back of aircraft etc., use disguised strong, can remotely be attacked suddenly, it is also possible to make
For the stand-by equipment of tanker aircraft, little money is spent, can be achieved with some operation effects that astronomical fund could be realized
Really, and it is also equipped with oneself exclusive advantage.Therefore the present invention can play a significant role in national defense construction, in international munitions city
Also extensive market prospects are had on field.
Description of the drawings
Below in conjunction with the accompanying drawings the present invention is further described.
Fig. 1 is the schematic diagram of the present invention.
In Fig. 1,1, dragging track, 2, wheel, 3, carry firing mount, 4, anterior electric capstan, 5, electromagnetic induction switch, 6, front end
Magnetic material sheets being, 7, guided missile, 8, rear portion electric capstan, 9, battery pack, 10, wire, 11, rope, 12, pulley, 13, parallel tail
The wing, 14, vertical tail, 15, rocket propulsion, 16, cross becket bridle, 17, end magnetic material sheets being, 18, Zhang Shengzhu, 19, a rope clamp.
Specific embodiment
In FIG, carry in triangle and respectively arrange below three angles of firing mount (3) wheel (2), three wheels can
Have at three respectively on the parallel dragging track (1) of certain length and roll.Slideway starts one section of certain length, is designed with certain
Coefficient of friction, and produce appropriate frictional force, so that aircraft is suspended to after three ropes, can rope is taut neat.In triangle
Shape to be carried and be provided with parallel empennage (13) and vertical tail (14) behind firing mount, and to hang bullet rear remote control distributor recovery is terminated.In triangle
Shape carries firing mount back and puts guided missile (7) in case aircraft is buckled.Piece rope of each setting above three angles of firing mount is carried in triangle
Rope (11), for hanging load firing mount.Carry in triangle and respectively arrange above two angles at firing mount rear portion a pulley (12), rope
Be wrapped on the rear portion electric capstan (8) at rear portion through pulley, before be separately provided an anterior electric capstan (4) for winding
A rope above.The design requirement of electric capstan, being powered before starting can reverse free rope stretching, will band during electric capstan winch rope stretching
Certain frictional force, can so tighten rope and be avoided that disorder cable again, locking state be reversed into after power failure, it is impossible to rope stretching again.Electricity
The rope-winding method of dynamic capstan winch is：Rope should not be fastened extremely on capstan winch, fag end is pressed on capstan winch, be compressed tightly wrap from level to level,
When so rope has gone out, rope will depart from capstan winch.On positive pole from battery pack (9) draw a wire (10) respectively through
Two pulleys below, and electric capstan above, three are arranged in series on this root wire where three ropes processes
Individual electromagnetic induction switch (5), is connected to again two electric capstan motors and rocket propulsion after three electromagnetic induction switch
(15) on the positive pole of electric controller, the negative pole of two electric capstan motors and the electric controller of rocket propulsion is connected on battery pack
On negative pole.Front end magnetic material sheets being (6) is wrapped in three ropes front end appropriate location, as three front end magnetic material sheets being difference Jing
When crossing three electromagnetic induction switch, three electromagnetic induction switch are closed successively, and two electric capstans and two rocket propulsions are same
When work, when carrying the downward gravity of firing mount and being offset to a certain extent by the thrust of rocket propulsion, carry firing mount and be lifted.Series connection sets
Putting the purpose of three electromagnetic induction switch is：If a rope is not suspended pulling, just have an electromagnetic induction and open
Pass can not close, motor cannot work, and two for hanging piece rope has gone out, and finally departs from electric capstan, be unlikely to carry firing mount with
Incorrect attitude pulls on sky, causes the accident.Four Zhang Shengzhu are vertically arranged the initial position of dragging track is equidistant
(18), three spaces are formed.One rope clamp (19) is respectively set in the top and bottom of outmost two Zhang Shengzhu, inside
The top and bottom of two Zhang Shengzhu two rope clamps are respectively set.The rope that latter one pulley is drawn is from corresponding
Be upward through below the rope clamp of a piece Zhang Shengzhu bottom of space, guide to a rope clamp on this root Zhang Shengzhu tops also from it is lower to
On through, rope is guided to the Zhang Shengzhu on this space opposite, rope from above the rope clamp on this root Zhang Shengzhu tops downwards
Pass through, then rope is passed down through from above a rope clamp of this root Zhang Shengzhu bottoms, the end of this root rope is arranged one
Becket bridle (16) is crossed, on the rope of the first rope clamp bottom that this ring set is passed through in this root rope.Thus rope is existed
A rectangle is opened on this space, so that aircraft is buckled.Remaining two rope takes same method corresponding
Open on space.
It is respectively provided with three in the front portion of aircraft and the corresponding position of both wings and stretches the hook for having certain length, when aircraft edge
The direction of track, that middle root track is directed at, by certain altitude, hook will respectively tangle three ropes, rope
Rope is pulled from a rope support, and due to there is certain frictional force during electric capstan rope stretching, track has certain frictional force, at this moment three
Rope will be tightened up it is exceptionally straight, carry firing mount slide forward on dragging track, capstan winch continue rope stretching, when three front end magnetic on rope
Property piece respectively through three electromagnetic induction switch when, three switch closure, electric capstan motor and rocket propulsion electric controller it is same
When power, electric capstan stops rope stretching, and starts rope closing, rocket propulsion ignition operation simultaneously, when the thrust of rocket propulsion
After the downward gravity of load firing mount is offset to a certain extent, carrying firing mount will be hung to aerial, electric capstan winch continuation rope closing by aircraft, when
When load firing mount presses close to aircraft belly to certain position, the end magnetic material sheets being (17) of rope is through electromagnetic induction switch, switch
Disconnect, electric capstan stalling is locked, it is impossible to rope stretching again, at this moment guided missile or fuel tank have been sent to the position that aircraft is capable of carry automatically
Put, after the automatic carry of aircraft, release carries firing mount, carry firing mount remote control and reclaim.
Claims (4)
1. a kind of aerial extension bullet system, is characterized in that：The aerial load firing mount design triangularity flying wing for hanging bullet system or triangle
The shape of shape framework, the vertical tail (14) at rear portion is directed downward, and its top edge is no more than the upper plane for carrying firing mount；Carrying
Respectively being respectively provided with one below three angles of firing mount can roll by metal or other hard wear-resistant material systems in grooved tracks
Into wheel (2).
2. the aerial extension bullet system according to right 1, is characterized in that：The aerial tethered system for hanging bullet system, carries in triangle
Three ropes (11) are set above three angles of firing mount, in case aircraft hangs up rope and slings bomb rack；Carrying two behind firing mount
It is each above angle that a pulley (12) for being used for connecting two ropes below is set, firing mount rear portion is carried, one rear portion electricity is set
Dynamic capstan winch (8), for carrying out the rope that folding and unfolding is connected from two pulleys, before an anterior electric capstan (4) be set be
A rope above carries out folding and unfolding.
3. the aerial extension bullet system according to the right 2 of right 1, is characterized in that：The aerial circuit control system for hanging bullet system, from
After the wire (10) that battery anode is drawn is respectively through two pulleys below and anterior electric capstan, then connect electrical appliance just
Pole, on this root wire, where the rope drawn near two pulleys below is passed through and above rope Jing on electric capstan
Where crossing, three electromagnetic induction switch (5) are arranged in series；Wrap front end magnetic in the appropriate position of three ropes front end respectively
Property material piece (6), in the end of rope, end magnetic material sheets being (17) is wrapped in appropriate position, for control circuit closure and
Disconnect.
4. the aerial extension bullet system according to right 1, is characterized in that：The aerial dragging track for hanging bullet system, dragging track (1)
It is made up of three groove parallel orbits；It is equidistant on the initial position of the track direction vertical with track to arrange four vertically
Zhang Shengzhu (18), rope clamp (19) is respectively respectively provided with the top and bottom of two Zhang Shengzhu on both sides, middle
The top and bottom of two Zhang Shengzhu are respectively respectively provided with two rope clamps.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610919876.5A CN106586016B (en) | 2016-10-16 | 2016-10-16 | It is aerial to hang bullet system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610919876.5A CN106586016B (en) | 2016-10-16 | 2016-10-16 | It is aerial to hang bullet system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106586016A true CN106586016A (en) | 2017-04-26 |
| CN106586016B CN106586016B (en) | 2018-11-09 |
Family
ID=58555709
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610919876.5A Active CN106586016B (en) | 2016-10-16 | 2016-10-16 | It is aerial to hang bullet system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106586016B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108750025A (en) * | 2018-05-30 | 2018-11-06 | 中船黄埔文冲船舶有限公司 | A kind of stinger angle regulator and method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2005102906A (en) * | 2005-02-08 | 2006-07-20 | Алексей Николаевич Кочетков (RU) | HORIZONTAL TAKE-OFF Rocket Launcher WITHOUT ANTIME WITH LOW-TEMPERATURE PLANNING IN THE ATMOSPHERE WITH SOFT GROUNDING OF THE VITYAZ RGV |
| CN201338735Y (en) * | 2009-01-16 | 2009-11-04 | 中国人民解放军空军航空大学 | Large-sized integrated ammunition carrier for carrying and loading air ammunitions |
| US7950607B1 (en) * | 2006-04-10 | 2011-05-31 | Carleton Technologies, Inc. | Small munitions adaptor rack for releasing small munitions from an aircraft |
| CN202180934U (en) * | 2011-07-20 | 2012-04-04 | 西安理工大学 | Missile hanging device of four-degree-of-freedom mechanical arm |
| CN103274288A (en) * | 2013-06-05 | 2013-09-04 | 北京空间飞行器总体设计部 | Suspending and releasing system used for impact test of lander |
| CN103434646A (en) * | 2013-05-24 | 2013-12-11 | 北京航空航天大学 | Ammunition supply device, system and method |
| CN105151311A (en) * | 2015-03-31 | 2015-12-16 | 北京道永科技有限公司 | Catapult-assisted take-off device of aircraft and aircraft carrier |
-
2016
- 2016-10-16 CN CN201610919876.5A patent/CN106586016B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2005102906A (en) * | 2005-02-08 | 2006-07-20 | Алексей Николаевич Кочетков (RU) | HORIZONTAL TAKE-OFF Rocket Launcher WITHOUT ANTIME WITH LOW-TEMPERATURE PLANNING IN THE ATMOSPHERE WITH SOFT GROUNDING OF THE VITYAZ RGV |
| US7950607B1 (en) * | 2006-04-10 | 2011-05-31 | Carleton Technologies, Inc. | Small munitions adaptor rack for releasing small munitions from an aircraft |
| CN201338735Y (en) * | 2009-01-16 | 2009-11-04 | 中国人民解放军空军航空大学 | Large-sized integrated ammunition carrier for carrying and loading air ammunitions |
| CN202180934U (en) * | 2011-07-20 | 2012-04-04 | 西安理工大学 | Missile hanging device of four-degree-of-freedom mechanical arm |
| CN103434646A (en) * | 2013-05-24 | 2013-12-11 | 北京航空航天大学 | Ammunition supply device, system and method |
| CN103274288A (en) * | 2013-06-05 | 2013-09-04 | 北京空间飞行器总体设计部 | Suspending and releasing system used for impact test of lander |
| CN105151311A (en) * | 2015-03-31 | 2015-12-16 | 北京道永科技有限公司 | Catapult-assisted take-off device of aircraft and aircraft carrier |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108750025A (en) * | 2018-05-30 | 2018-11-06 | 中船黄埔文冲船舶有限公司 | A kind of stinger angle regulator and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106586016B (en) | 2018-11-09 |
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