CN106224127A - A kind of solid rocket ramjet gas flow adjusting means - Google Patents
A kind of solid rocket ramjet gas flow adjusting means Download PDFInfo
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- CN106224127A CN106224127A CN201610813742.5A CN201610813742A CN106224127A CN 106224127 A CN106224127 A CN 106224127A CN 201610813742 A CN201610813742 A CN 201610813742A CN 106224127 A CN106224127 A CN 106224127A
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- Prior art keywords
- guiding valve
- opening
- solid rocket
- adjusting means
- power unit
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Mechanically-Actuated Valves (AREA)
Abstract
nullThe present invention relates to solid rocket ramjet technical field，Particularly relate to a kind of solid rocket ramjet gas flow adjusting means，The sleeve closed including one end、Combustion gas venturi and flow control device，Combustion gas venturi and flow control device are all located in sleeve，And combustion gas throat is perpendicular to the end face setting of sleeve，The end face of sleeve is provided with the first opening connected with combustion gas venturi，Governor motion includes guiding valve and power unit，Guiding valve is rotating to be sheathed in combustion gas venturi，And the end face of the open at one end other end of guiding valve is provided with the second opening，The end face of guiding valve is arranged with the end face laminating of sleeve，Power unit is connected with guiding valve，Band movable pulley rotates，Guiding valve is during rotating，First opening completely closes by being completely open to，Achieve the descending adjustment of the first opening，And it is shallower to adjust process ratio，The rotation of guiding valve is realized by controlling the action of power unit，And then realize adjusting the effect of the first openings of sizes.
Description
Technical field
The present invention relates to solid rocket ramjet technical field, particularly relate to a kind of solid rocket ramjet gas flow and adjust
Regulating device.
Background technology
Due to solid rocket ramjet have than leaping high, light weight, volume are little, can omnidistance active attack, reliable operation, make
By the advantage such as easy to maintenance, the most increasingly paid attention to by countries in the world.
The performance parameter of solid rocket ramjet is closely related with suction engine air capacity, and air mass flow is to starting
The performance impact of machine is mainly reflected in air-fuel ratio (i.e. air mass flow and the ratio of gas flow).Therefore, solid punching press is started
Machine typically should be operated near design air-fuel ratio, and guarantee electromotor has good performance.Send out yet with solid punching press
The air mass flow that motivation sucks is to be determined by state of flights such as the flight speed of guided missile, height and attitudes (angle of attack and yaw angle)
, therefore the gas flow of solid rocket ramjet must be adjusted, so when missile flight shape with the flow sucking air
When state changes, the performance of electromotor just can be fully played.The combustion gas stream of the most conventional solid rocket ramjet
Quantity regulating device commonly used electrodynamic type slide-valve plunger or pneumatic pin valve device, the most pneumatic needle valve adjusting means is being fired
Need to use air machinery during throughput regulation, take up an area space relatively greatly, leakage easily occurs, at adjustment of combustion gas flow due to gas
During, it is not easy to reach accurately to control.
Summary of the invention
(1) to solve the technical problem that
The technical problem to be solved in the present invention is to solve pneumatic needle valve adjusting means floor space greatly, gas easily occurs
The problem of leakage.
(2) technical scheme
In order to solve above-mentioned technical problem, the invention provides a kind of solid rocket ramjet gas flow adjusting means,
Sleeve, combustion gas venturi and the flow control device closed including one end, described combustion gas venturi and described flow control device are all provided with
In described sleeve, and described combustion gas venturi is perpendicular to the end face setting of described sleeve, and the end face of described sleeve is provided with and institute
State the first opening of combustion gas venturi connection；Described flow control device includes guiding valve and power unit, and described guiding valve is rotating
It is sheathed in described combustion gas venturi, and the end face of the open at one end other end of described guiding valve is provided with the second opening, described guiding valve
The end face laminating of end face and described sleeve arrange；Described power unit is connected with described guiding valve, is used for driving described guiding valve to turn.
Wherein, the shape of described first opening and described second opening is semicircle, and described first opening is with described
The radius of the second opening is equal.
Wherein, described flow control device also include gear unit, described gear unit include shell and be located at described outside
Screw mandrel in shell and nut, described screw mandrel is connected with described power unit, and described nut is located on described screw mandrel, and described nut
On be arranged with bearing, described bearing is provided with the sliding part with slide valve parallel；Described shell is provided with the first chute, described slip
Part is along described first slide, and described sliding part is connected with described guiding valve by fork.
Wherein, one end of described fork is provided with two symmetrically arranged claws, and described claw is arranged in outside described guiding valve
On wall, the other end of described fork is provided with the second chute, and described second chute is perpendicular to described first chute and arranges, and described cunning
Moving part is located in described second chute.
Wherein, the outer wall of described guiding valve is provided with annular groove, and described claw is provided with the key matched with annular groove,
And described claw is connected by securing member with described guiding valve.
Wherein, the first helical gear and the second helical gear engaged with described first helical gear, described first helical teeth are also included
Wheel is sheathed on one end of described screw mandrel, and described second helical gear axis is vertical and described with described first helical gear axis
Second helical gear diameter is less than the first helical gear diameter, and described second helical gear is connected with described power unit.
Wherein, described power unit is motor, and described second helical gear is located on the output shaft of described motor.
Wherein, also include that controlling organization, described controlling organization are connected with described power unit, be used for controlling described power list
The action of unit.
Wherein, described sliding part is provided with linear potentiometers, and described linear potentiometers is connected with described controlling organization, is used for
The straight-line displacement of sliding part described in Real-time Feedback, described controlling organization controls described power according to the straight-line displacement of described sliding part
The action of unit.
(3) beneficial effect
The technique scheme of the present invention has the advantage that a kind of solid rocket ramjet combustion gas stream that the present invention provides
Quantity regulating device, sleeve, combustion gas venturi and the flow control device closed including one end, combustion gas venturi and flow control device are equal
Being located in sleeve, and combustion gas throat is perpendicular to the end face of sleeve and arranges, the end face of sleeve is provided with the connected with combustion gas venturi
One opening, governor motion includes guiding valve and power unit, and guiding valve is rotating to be sheathed in combustion gas venturi, and one end of guiding valve opens
The end face of the mouth other end is provided with the second opening, and the end face of guiding valve is arranged with the end face laminating of sleeve, and power unit connects with guiding valve
Connect, band movable pulley rotate, when guiding valve turn to the second opening and the first opening relative to time, the first opening of combustion gas venturi is by completely
Open；When guiding valve turns to the second opening and the first opening staggers completely, the first opening is closed；Guiding valve is in the process rotated
In, the first opening completely closes by being completely open to, it is achieved that the descending adjustment of the first opening, and adjustment process compares
Gently, realize the rotation of guiding valve by controlling the action of power unit, and then realize adjusting the effect of the first openings of sizes.Should
Apparatus structure is simple, floor space is less, does not use air machinery to be controlled, it is to avoid the problem that gas leaks occur.
Except the technical characteristic of technical scheme that described above present invention solves the technical problem that, constitute and there is this
Outside the advantage that the technical characteristic of a little technical schemes is brought, the other technologies feature of the present invention and these technical characteristics bring
Advantage, will further illustrate in conjunction with accompanying drawing.
Accompanying drawing explanation
Fig. 1 is the structural representation of the solid rocket ramjet gas flow adjusting means that the embodiment of the present invention provides；
Fig. 2 is the sleeve annexation figure with combustion gas venturi of embodiment of the present invention offer；
Fig. 3 is the power unit annexation figure with gear unit of embodiment of the present invention offer；
Fig. 4 is that the A-A of Fig. 3 is to sectional view；
Fig. 5 is the external structure schematic diagram of the gear unit that the embodiment of the present invention provides；
Fig. 6 is the structural representation of the fork that the embodiment of the present invention provides；
Fig. 7 is external agency's schematic diagram of the combustion gas venturi that the embodiment of the present invention provides；
Fig. 8 is the fork annexation figure with combustion gas venturi of embodiment of the present invention offer.
In figure: 1: sleeve；2: combustion gas venturi；3: fork；4: gear unit；5: power unit；6: the second helical gears；7: the
One helical gear；8: screw；101: the first openings；201: the second openings；202: annular groove；203: vertical slot；204: screwed hole；
301: claw；302: vertical key；303: cross key；304: through hole；305: the second chutes；401: shell；402: screw mandrel；403: spiral shell
Female；404: bearing；405: linear potentiometers；406: sliding part；407: steel sleeve.
Detailed description of the invention
For making the purpose of the embodiment of the present invention, technical scheme and advantage clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
A part of embodiment of the present invention rather than whole embodiments.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained on the premise of not making creative work, broadly falls into the scope of protection of the invention.
In describing the invention, it should be noted that unless otherwise clearly defined and limited, term " is installed ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be fixing connection, it is also possible to be to removably connect, or be integrally connected；Can
To be mechanical connection, it is also possible to be electrical connection；Can be to be joined directly together, it is also possible to be indirectly connected to by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, can understand that above-mentioned term is at this with concrete condition
Concrete meaning in invention.
Additionally, in describing the invention, except as otherwise noted, " multiple ", " many ", " many groups " be meant that two or
Two or more, " several ", " some ", " some groups " are meant that one or more.
As shown in Figures 1 to 8, a kind of solid rocket ramjet gas flow adjusting means that the embodiment of the present invention provides,
Sleeve 1, the combustion gas venturi 102 being located in sleeve 1 and the flow control device closed including one end, combustion gas venturi 102 is perpendicular to
The end face of sleeve 1 is arranged, and the end face of sleeve 1 is provided with the first opening 101 connected with combustion gas venturi 102；Flow-rate adjustment machine
Structure includes guiding valve 2 and power unit 4, and guiding valve 2 is rotating to be sheathed in combustion gas venturi 102, and the open at one end of guiding valve 2 another
The end face of end is provided with the second opening 201, and the end face of guiding valve 2 is arranged with the end face laminating of sleeve 1；Power unit 5 is with guiding valve 2 even
Connect, rotate for band movable pulley 2.When guiding valve 2 turn to the second opening 201 relative with the first opening 101 time, combustion gas venturi 102
The first opening 101 be fully opened；When guiding valve 2 turns to the second opening 201 and the first opening 101 staggers completely, first
Opening 101 is closed；Guiding valve 2 is during rotating, and the first opening 101 completely closes by being completely open to, it is achieved that first
The descending adjustment of opening 101, and the adjustment that gas flow is from large to small, and it is shallower to adjust process ratio, by controlling
The action of power unit 5 realizes the rotation of guiding valve 2, and then realizes adjusting the effect of the first opening 101 size.This apparatus structure
Simply, floor space is less, do not use air machinery to be controlled, it is to avoid the problem that gas leaks occur.
Further, the shape of the first opening 101 and the second opening 201 is semicircle, and the first opening 101 and second
The radius of opening 201 is equal.I.e. first opening 101 is identical with the form and dimension of the second opening 201, it is possible to realize first
Opening 101 fully open and fully closed.
Further, flow control device also includes gear unit 4, and as shown in Figures 3 to 5, gear unit 4 includes shell
401, shell 401 is provided with the first chute, is provided with screw mandrel 402 and nut 403 in shell 401, and screw mandrel 401 is with power unit 5 even
Connecing, nut 403 is located on screw mandrel 402, and is arranged with bearing 404 on nut 403, and bearing 404 is provided with the cunning parallel with guiding valve 2
Moving part 406, sliding part 406 is connected with guiding valve 2 along the first slide, sliding part 406 by fork 3, and fork 3 is perpendicular to guiding valve
2 and sliding part 406, guiding valve 2 and sliding part 406 are connected, power unit 5 drives screw mandrel 402 to rotate, thus drives screw mandrel 402
On nut 403 move along a straight line along screw mandrel 402, bearing 404 on nut 403 and sliding part 406 with nut 403 at screw mandrel
402 slide, owing to guiding valve 2 is connected with sliding part 406 by fork 3, so the process that sliding part 406 slides in the first chute
In, fork 3 band movable pulley 2 rotates, and then realizes adjusting the effect of the first opening 101 size.In the present embodiment by sliding part
The Cross-section Design of 406 is square, increases sliding part 406 and the contact area of the first chute, prevents local stress excessive, and
Seamed edge at sliding part 406 designs fillet, prevents wedge angle stuck, and sliding bearing selected by bearing 404, and sliding bearing uses beryllium blue or green
Copper, beryllium-bronze has self-lubricating function, reduces bearing inner race and the bearing outer ring frictional force when mutually rotating.Housing uses aluminum
Making, arrange steel sleeve at the first chute, steel sleeve is arranged on housing by screw, prevents housing local by sliding part pressure
Burst.Dramatically reduce the weight of mechanism simultaneously.
Further, as shown in Figure 6 and Figure 7, one end of fork 3 is provided with two symmetrically arranged claws 301, claw 301
Being arranged on the outer wall of guiding valve 2, the other end of fork 301 is provided with the second chute 305, and the second chute 305 is along the length side of fork 3
To setting, and sliding part is located in the second chute 305.Ensure that, when sliding part linearly slides in the first chute, drive is pulled out
Fork 3 rotation.
Further, the outer wall of guiding valve 2 is provided with annular groove 202, and claw 301 is provided with and matches with annular groove 202
The key closed, and claw 301 is connected by securing member with guiding valve 2.Concrete, the medial surface at claw 301 is provided with 3 and is uniformly distributed
Key, one of them key is axially arranged along fork 3 of vertical key 302, annular groove 202 be provided with a vertical slot 203,
Vertical key 302 coordinates with vertical slot 203, is arranged in vertical slot 203；Two other key is cross key 303, is respectively arranged on vertical
The both sides of key 302, cross key 303 coordinates with annular groove 202, is arranged in annular groove 202, and the two ends of claw 301 are divided
Not being provided with a through hole 304, the relative position of guiding valve is provided with screwed hole 204, and screw 8 is through the screwed hole 204 of 304 with guiding valve 2
Coordinate, it is achieved fork 3 is completely fixed with guiding valve 2, it is to avoid occur to loosen.
Further, also including gear drive, gear drive includes the first helical gear 7 and the second helical gear 6,
First helical gear 7 is sheathed on one end of screw mandrel 401, and the axis of the second helical gear 6 is vertical with the axis of the first helical gear 7, and the
Two helical gears 6 engage with the first helical gear 7, and power unit 5 is connected with the second helical gear 6, and power unit 5 is motor, and second is oblique
Gear 6 is located on the output shaft of motor.In the present embodiment, power unit 5 is DC brushless motor, the first helical gear 7 straight
Footpath, less than the diameter of the second helical gear 6, on the one hand can form deceleration, on the other hand utilizes spiral gear drive mechanism to change power
Transmission direction, the requirement meeting sleeve 1 installing space is so set so that compact conformation, take up an area space little.
Further, also include that controlling organization, controlling organization are connected with power unit 5, for controlling the dynamic of power unit 5
Make.Sliding part 406 is provided with linear potentiometers 405, and linear potentiometers 405 is connected with controlling organization, slides for Real-time Feedback
The real-time straight-line displacement of part, controlling organization controls the action of power unit according to the straight-line displacement of sliding part.
During use, the shape of the first opening and the second opening is not limited to semicircle, it is also possible to be other shapes, as long as can
Realize the shape that when guiding valve rotates, the size of the first opening can regulate all to be possible.
In sum, a kind of solid rocket ramjet gas flow adjusting means that the present invention provides, by the first helical teeth
The gear pair of wheel and the second helical gear composition changes the transmission direction of power, and rotation is changed into by the cooperation of feed screw nut
Linear motion, is rotated by the sliding part being located on nut and the fork band movable pulley being connected with guiding valve by sliding part, thus carries
Movable pulley rotates, it is achieved adjusts the effect of the first openings of sizes, and then causes the change of gas flow.
Last it is noted that above example is only in order to illustrate technical scheme, it is not intended to limit；Although
With reference to previous embodiment, the present invention is described in detail, it will be understood by those within the art that: it still may be used
So that the technical scheme described in foregoing embodiments to be modified, or wherein portion of techniques feature is carried out equivalent；
And these amendment or replace, do not make appropriate technical solution essence depart from various embodiments of the present invention technical scheme spirit and
Scope.
Claims (9)
1. a solid rocket ramjet gas flow adjusting means, it is characterised in that: include sleeve, the combustion gas larynx closed one end
Road and flow control device, described combustion gas venturi and described flow control device are all located in described sleeve, and described combustion gas larynx
Road is perpendicular to the end face of described sleeve and arranges, and the end face of described sleeve is provided with the first opening connected with described combustion gas venturi；
Described flow control device includes guiding valve and power unit, and described guiding valve is rotating to be sheathed in described combustion gas venturi, and institute
The end face of the open at one end other end stating guiding valve is provided with the end face laminating of the second opening, the end face of described guiding valve and described sleeve
Arrange；Described power unit is connected with described guiding valve, is used for driving described guiding valve to rotate.
Solid rocket ramjet gas flow adjusting means the most according to claim 1, it is characterised in that: described first opens
The shape of mouth and described second opening is semicircle, and described first opening is equal with the radius of described second opening.
Solid rocket ramjet gas flow adjusting means the most according to claim 1, it is characterised in that: described flow is adjusted
Joint mechanism also includes that gear unit, described gear unit include shell and the screw mandrel being located in described shell and nut, described silk
Bar is connected with described power unit, and described nut is located on described screw mandrel, and is arranged with bearing on described nut, on described bearing
It is provided with the sliding part with slide valve parallel；Described shell is provided with the first chute, described sliding part along described first slide, and
Described sliding part is connected with described guiding valve by fork.
Solid rocket ramjet gas flow adjusting means the most according to claim 3, it is characterised in that: described fork
One end is provided with two symmetrically arranged claws, and described claw is arranged on the outer wall of described guiding valve, and the other end of described fork sets
Having the second chute, described second chute is arranged along the length direction of fork, and described sliding part is located in described second chute.
Solid rocket ramjet gas flow adjusting means the most according to claim 4, it is characterised in that: described guiding valve
Outer wall is provided with annular groove, and described claw is provided with the key matched with annular groove, and described claw leads to described guiding valve
Cross securing member to connect.
6. according to the solid rocket ramjet gas flow adjusting means described in any one of claim 3-5, it is characterised in that: also
Including the first helical gear and the second helical gear of engaging with described first helical gear, described first helical gear is sheathed on described screw mandrel
One end, described second helical gear axis is vertical with described first helical gear axis, and described second helical gear diameter
Less than the first helical gear diameter, described second helical gear is connected with described power unit.
Solid rocket ramjet gas flow adjusting means the most according to claim 6, it is characterised in that: described power list
Unit is motor, and described second helical gear is located on the output shaft of described motor.
8. according to the solid rocket ramjet gas flow adjusting means described in any one of claim 3-5, it is characterised in that: also
Including controlling organization, described controlling organization is connected with described power unit, for controlling the action of described power unit.
Solid rocket ramjet gas flow adjusting means the most according to claim 8, it is characterised in that: described sliding part
Being provided with linear potentiometers, described linear potentiometers is connected with described controlling organization, straight for sliding part described in Real-time Feedback
Displacement of the lines, described controlling organization controls the action of described power unit according to the straight-line displacement of described sliding part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610813742.5A CN106224127B (en) | 2016-09-09 | 2016-09-09 | A kind of solid rocket ramjet gas flow regulating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610813742.5A CN106224127B (en) | 2016-09-09 | 2016-09-09 | A kind of solid rocket ramjet gas flow regulating device |
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| Publication Number | Publication Date |
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| CN106224127A true CN106224127A (en) | 2016-12-14 |
| CN106224127B CN106224127B (en) | 2018-06-29 |
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| CN201610813742.5A Active CN106224127B (en) | 2016-09-09 | 2016-09-09 | A kind of solid rocket ramjet gas flow regulating device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108871784A (en) * | 2018-04-27 | 2018-11-23 | 北京航天动力研究所 | A kind of fixation device for the test of liquid rocket engine thrust chamber air-flow |
| CN109944713A (en) * | 2019-03-20 | 2019-06-28 | 中国人民解放军国防科技大学 | Gas flow regulating device and gas generator of solid rocket ramjet |
| CN114251190A (en) * | 2021-11-09 | 2022-03-29 | 北京动力机械研究所 | Low-cost solid-impact engine control method |
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| CN104500270A (en) * | 2014-12-09 | 2015-04-08 | 南京理工大学 | Electric rotary sliding-plate valve-type rocket ramjet engine gas flow-rate adjusting device |
| CN105201687A (en) * | 2015-09-02 | 2015-12-30 | 南京理工大学 | Electric sliding discal valve type gas flow regulating device for solid rocket propellant ramjet |
| CN105545524A (en) * | 2014-10-31 | 2016-05-04 | 北京精密机电控制设备研究所 | Electromechanical servo type engine flow adjusting mechanism |
| CN206071751U (en) * | 2016-09-09 | 2017-04-05 | 北京精密机电控制设备研究所 | A kind of solid rocket ramjet gas flow adjusting means |
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| GB2092271A (en) * | 1981-01-29 | 1982-08-11 | Secr Defence | Liquid Propellant Delivery Systems |
| CN105545524A (en) * | 2014-10-31 | 2016-05-04 | 北京精密机电控制设备研究所 | Electromechanical servo type engine flow adjusting mechanism |
| CN104500270A (en) * | 2014-12-09 | 2015-04-08 | 南京理工大学 | Electric rotary sliding-plate valve-type rocket ramjet engine gas flow-rate adjusting device |
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| CN206071751U (en) * | 2016-09-09 | 2017-04-05 | 北京精密机电控制设备研究所 | A kind of solid rocket ramjet gas flow adjusting means |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108871784A (en) * | 2018-04-27 | 2018-11-23 | 北京航天动力研究所 | A kind of fixation device for the test of liquid rocket engine thrust chamber air-flow |
| CN109944713A (en) * | 2019-03-20 | 2019-06-28 | 中国人民解放军国防科技大学 | Gas flow regulating device and gas generator of solid rocket ramjet |
| CN109944713B (en) * | 2019-03-20 | 2020-01-24 | 中国人民解放军国防科技大学 | Gas flow regulating device and gas generator of solid rocket ramjet |
| CN114251190A (en) * | 2021-11-09 | 2022-03-29 | 北京动力机械研究所 | Low-cost solid-impact engine control method |
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| Publication number | Publication date |
|---|---|
| CN106224127B (en) | 2018-06-29 |
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