CN104712459A - Solid rocket power control device and control method - Google Patents
Solid rocket power control device and control method Download PDFInfo
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- CN104712459A CN104712459A CN201310672630.9A CN201310672630A CN104712459A CN 104712459 A CN104712459 A CN 104712459A CN 201310672630 A CN201310672630 A CN 201310672630A CN 104712459 A CN104712459 A CN 104712459A
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Abstract
The invention discloses a solid rocket power control device and control method. The control device comprises an engine shell, an air spraying pipeline, a control surface and a fuel gas channel. The air spraying pipeline is arranged in the engine shell, and the control surface is connected with the engine shell through a rudder spindle; an air spraying opening is formed in the control surface; the fuel gas channel is formed in the engine shell; and one port of the fuel gas channel is connected with the air spraying pipeline, and the other port of the fuel gas channel is connected with the air spraying opening and is used for enabling the air spraying pipeline to be communicated with the air spraying opening. Through drainage of a main engine, direct side force is provided for achieving precise control over air-to-air missiles of a solid rocket and light-duty, miniaturization, and long-term effects of the solid rocket power control device, and meeting the development requirements of air defense/air-to-air missiles in the future for light weight and remote range.
Description
Technical field
The present invention relates to rocket propulsion technology field, and in particular to a kind of solid-rocket power control unit and controlling method.
Background technique
In solid-rocket technical field, solid-rocket, as air-ground/air-to-air missile, in order to reach the object of precise guidance, need, by providing accurately effective thrust to control to solid-rocket, just to need to improve solid-rocket for this reason, as guided missile, end permissible load factor, reduces overload response time.
At present, be successfully applied in air defence missile by Direct Force Control Technology abroad, wherein typical application has Aster-30, the Muscovite 9M96E2 in Europe and the PAC-3 etc. of the U.S..Wherein, Aster-30 utilizes four gas generators be arranged on immediate vicinity aerofoil to produce direct lateral force; 9M96E2 utilizes 24 the radial puffers being arranged on center of gravity place to produce direct lateral force; 180 microminiature solid pulsed motors that PAC-3 guided missile then utilizes forebody to install produce direct lateral force.And at air-to-air missile weapon field, the application of Direct Force Control Technology is still in exploratory development.
Due to air defence missile adopts more independently gas generator as the power plant of side-jet control, have that architecture quality is heavier, take up room large, the shortcoming such as the operating time is short, this and air defense in future/air-to-air missile small light, long-range development trend are runed counter to.
Thus, a kind of light is provided, the solid-rocket power control unit of miniaturization and long-actingization is the art problem demanding prompt solution.
Summary of the invention
The technical problems such as the present invention is intended to solve in existing Solid rocket propulsion control technique, and side-jet control apparatus structure that solid-rocket adopts is complicated, volume is comparatively large, heavier-weight, operating time are short.
For solving the technical problem of prior art, the invention provides a kind of solid-rocket power control unit, comprising: motor body; Jet pipe, is arranged in described motor body; Rudder face, be connected with described motor body by rudderpost, it has puff prot; Blast tube, be arranged on described motor body, one port is connected with described jet pipe, and another port is connected with described puff prot, in order to be communicated with described puff prot by described jet pipe.
Further, described rudder face also comprises: puff prot control switch, to control described puff prot switch.
Further, described rudderpost also comprises: blast tube control switch, to control described blast tube switch.
The present invention also provides a kind of solid-rocket power-control method, comprising: control engine start and combustion gas sprayed by jet pipe; By blast tube, combustion gas is drained into the puff prot ejection of rudder face.
Further, when rudder face does not rotate, control to close described blast tube; When rudder face rotates, control to open described blast tube, make combustion gas drain into the puff prot ejection of described rudder face.
Further, direction combustion gas being drained into the puff prot ejection of rudder face is along rudder face Normal direction.
In sum, solid-rocket power control unit provided by the invention and controlling method, direct lateral force is provided to realize solid-rocket as air-to-air missile by controlling master motor drainage, accurate control, achieve the effect of the light of solid-rocket power control unit, miniaturization and long-actingization, meet following air defense/air-to-air missile small light, long-range growth requirement.
Accompanying drawing explanation
Figure 1 shows that the structural representation of the solid-rocket power control unit that one embodiment of the invention provides;
Figure 2 shows that the structural representation of the solid-rocket power control unit that another embodiment of the present invention provides;
Figure 3 shows that the structural representation of the solid-rocket power control unit that another embodiment of the present invention provides;
Figure 4 shows that the method flow diagram of the solid-rocket power-control method that another embodiment of the present invention provides.
Embodiment
In view of in existing solid-rocket dynamic Control technology, in order to reach the object of precise guidance, existing solid-rocket adopt adopted side direction side-jet control device be independently power control unit, himself need possess power plant and control gear, not only has that complex structure, volume are comparatively large, a defect of heavier-weight but also have the technical problems such as the operating time is shorter.The present invention is by being drained to rudder face by the combustion gas of solid-rocket master motor, the method that direct lateral force accurately controls to realize solid-rocket is provided, the main engine power of side direction side-jet control device and solid-rocket is merged, by the mode that power is shared, achieve the object of the light of solid-rocket power control unit, miniaturization and long-actingization.
For making object of the present invention, feature becomes apparent, and is further described the specific embodiment of the present invention below in conjunction with accompanying drawing.
Incorporated by reference to see Fig. 1, it is depicted as the structural representation of the solid-rocket power control unit provided for one embodiment of the invention.
This solid-rocket power control unit, comprising: motor body 110; Jet pipe 120, is arranged in described motor body 110; Rudder face 130, be connected with described motor body 110 by rudderpost 140, it has puff prot 150; Blast tube 160, be arranged on described motor body 110, one port is connected with described jet pipe 120, and another port is connected with described puff prot 150, in order to be communicated with described puff prot 150 by described jet pipe 120.
When solid-rocket ignition trigger, the combustion gas that master motor combustion jet goes out sprays via the jet pipe 120 be arranged in the motor body 110 of solid-rocket, wherein a part of combustion gas is drained into the puff prot 150 be arranged on rudder face 130 sprayed by being arranged at blast tube 160 on described motor body 110, thus achieves the side direction side-jet control to solid-rocket.
The power adopted due to side direction side-jet control is the power of the master motor from solid-rocket, namely be that power is shared with the power of the master motor of solid-rocket, thus when side direction side-jet control, just do not need independently power supplying apparatus, and then reach the object of the light of solid-rocket power control unit, miniaturization and long-actingization.
Further, in embodiments of the present invention, refer to Fig. 2, described rudder face also comprises: puff prot control switch 210, to control the jet direction of described puff prot.By the different choice of switch, combustion gas can be controlled and eject from the upper surface of rudder face or lower surface, achieve the flexible control of solid-rocket power.
Further, in embodiments of the present invention, refer to Fig. 3, described rudderpost also comprises: blast tube control switch 310, to control described blast tube switch.
In solid-rocket flight course, when rudder face does not rotate, blast tube control switch controls blast tube and cuts out, and guided missile adopts conventional pneumatic rudder face to control; When rudder face rotates, blast tube control switch controls blast tube and opens, and combustion gas is ejected by rudder face Normal direction, for guided missile provides combustion gas control moment, thus realizes direct force/aerodynamic force complex controll.
Refer to Fig. 4, it is depicted as the method flow diagram of the solid-rocket power-control method that another embodiment of the present invention provides.
This solid-rocket power-control method, comprises the following steps:
Step 410: control engine start and combustion gas is sprayed by jet pipe;
Step 420: the puff prot ejection by blast tube, combustion gas being drained into rudder face.
By said method, when carrying out side direction side-jet control to solid-rocket, by sharing the power of the master motor of solid-rocket, the light of solid-rocket power control unit, miniaturization and long-actingization can be realized.
Further, in embodiments of the present invention, step 420 specifically comprises: when rudder face does not rotate, and controls to close described blast tube; When rudder face rotates, control to open described blast tube, make combustion gas drain into the puff prot ejection of described rudder face.
When rudder face does not deflect, blast tube is closed, and guided missile adopts conventional pneumatic rudder face to control; When control surface deflection, blast tube is opened, and combustion gas is ejected by rudder face Normal direction, for solid-rocket, as guided missile provides combustion gas control moment, thus realize direct force/aerodynamic force complex controll, while reaching precise guidance more, also save the energy, achieve the object of long-range.
Further, in embodiments of the present invention, direction combustion gas being drained into the puff prot ejection of rudder face is along rudder face Normal direction, accurately controls for solid-rocket provides combustion gas control moment thus realizes lateral force.
In sum, the solid-rocket power control unit that the embodiment of the present invention provides and controlling method, direct lateral force is provided to realize solid-rocket as air-to-air missile by controlling master motor drainage, accurate control, achieve the effect of the light of solid-rocket power control unit, miniaturization and long-actingization, meet following air defense/air-to-air missile small light, long-range growth requirement.
Although the present invention discloses as above with preferred embodiment; so itself and be not used to limit the present invention; have in any art and usually know the knowledgeable; without departing from the spirit and scope of the present invention; when being used for a variety of modifications and variations, therefore protection scope of the present invention is when being as the criterion depending on those as defined in claim.
Claims (6)
1. a solid-rocket power control unit, is characterized in that, comprising:
Motor body;
Jet pipe, is arranged in described motor body;
Rudder face, be connected with described motor body by rudderpost, it has puff prot;
Blast tube, be arranged on described motor body, one port is connected with described jet pipe, and another port is connected with described puff prot, in order to be communicated with described puff prot by described jet pipe.
2. solid-rocket power control unit according to claim 1, is characterized in that, described rudder face also comprises: puff prot control switch, to control described puff prot switch.
3. solid-rocket power control unit according to claim 1, is characterized in that, described rudderpost also comprises: blast tube control switch, to control described blast tube switch.
4. a solid-rocket power-control method, is characterized in that, comprises the following steps:
Control engine start combustion gas is sprayed by jet pipe;
By blast tube, combustion gas is drained into the puff prot ejection of rudder face.
5. solid-rocket power-control method according to claim 4, is characterized in that, also comprise:
When rudder face does not rotate, control to close described blast tube;
When rudder face rotates, control to open described blast tube, make combustion gas drain into the puff prot ejection of described rudder face.
6. solid-rocket power-control method according to claim 4, is characterized in that, direction combustion gas being drained into the puff prot ejection of rudder face is along rudder face Normal direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310672630.9A CN104712459A (en) | 2013-12-12 | 2013-12-12 | Solid rocket power control device and control method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310672630.9A CN104712459A (en) | 2013-12-12 | 2013-12-12 | Solid rocket power control device and control method |
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| CN104712459A true CN104712459A (en) | 2015-06-17 |
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| CN201310672630.9A Pending CN104712459A (en) | 2013-12-12 | 2013-12-12 | Solid rocket power control device and control method |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106568356A (en) * | 2016-10-27 | 2017-04-19 | 浙江理工大学 | Missile rudder surface control mechanism |
| CN106643340A (en) * | 2016-10-27 | 2017-05-10 | 浙江理工大学 | Missile control surface space linkage type control mechanism |
| CN109238634A (en) * | 2018-09-12 | 2019-01-18 | 北京空天技术研究所 | Hypersonic aircraft model in wind tunnel rudder-face device |
| CN110095990A (en) * | 2019-06-10 | 2019-08-06 | 西北工业大学 | A kind of aircraft end direct force pulse duration modulation method |
| CN112197655A (en) * | 2020-09-25 | 2021-01-08 | 中国航天空气动力技术研究院 | Rolling control method and control device for rotating missile |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106568356A (en) * | 2016-10-27 | 2017-04-19 | 浙江理工大学 | Missile rudder surface control mechanism |
| CN106643340A (en) * | 2016-10-27 | 2017-05-10 | 浙江理工大学 | Missile control surface space linkage type control mechanism |
| CN109238634A (en) * | 2018-09-12 | 2019-01-18 | 北京空天技术研究所 | Hypersonic aircraft model in wind tunnel rudder-face device |
| CN110095990A (en) * | 2019-06-10 | 2019-08-06 | 西北工业大学 | A kind of aircraft end direct force pulse duration modulation method |
| CN112197655A (en) * | 2020-09-25 | 2021-01-08 | 中国航天空气动力技术研究院 | Rolling control method and control device for rotating missile |
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Application publication date: 20150617 |