CN102645137A - Gas actuator cylinder of unfolding mechanism - Google Patents
Gas actuator cylinder of unfolding mechanism Download PDFInfo
- Publication number
- CN102645137A CN102645137A CN2012101036590A CN201210103659A CN102645137A CN 102645137 A CN102645137 A CN 102645137A CN 2012101036590 A CN2012101036590 A CN 2012101036590A CN 201210103659 A CN201210103659 A CN 201210103659A CN 102645137 A CN102645137 A CN 102645137A
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- combustion chamber
- igniter
- propellant
- cylindrical shell
- development mechanism
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Abstract
The invention relates to a gas actuator cylinder which is used for an unfolding mechanism with folded wings. The gas actuator cylinder comprises an igniter, an ignition charge basket, propellant, a combustion chamber, a pushrod, a cylinder and the like, wherein the igniter, the ignition charge basket and the propellant are sequentially assembled, the igniter is arranged at one end of the combustion chamber and is hermetically connected with the combustion chamber, the ignition charge basket and the propellant are arranged in the combustion chamber, the inner wall of the combustion chamber is provided with a heat insulating layer, one end of the cylinder is hermetically connected with the other end of the combustion chamber, the combustion chamber is communicated with the cylinder and the pushrod can be movably arranged in the cylinder. During working, the igniter ignites the ignition charge basket, the propellant is ignited, the pushrod is pushed to move outwards with the sudden increase of pressure in the combustion chamber, controllable thrust is produced and the impact after the unfolding mechanism is unfolded in place is reduced.
Description
Technical field
The present invention relates to a kind of development mechanism combustion gas pressurized strut, be applied to the development mechanism of folding wings.
Background technology
Folding wings is widely used in the tactical missile, is in folded state at the transporting procedures wing centre section and is contracted in the guided missile bomb body, in flight course, folding wings is launched, and it has the advantage that remarkable minimizing guided missile takes up room.Because missile wing is generally bigger; Suffered aerodynamic lift and aerodynamic drag are bigger during expansion; Therefore as the power source of development mechanism; The combustion gas pressurized strut must make the development mechanism normal reliable launch under different flight attitudes, and output adapts to the change thrust of varying duty, and the back of launching to put in place is little to the impact of development mechanism.
Summary of the invention
The objective of the invention is output change thrust in the development mechanism expansion process, the impact after reducing to launch to put in place.
Main design of the present invention: the change thrust that expansion process is required, the design through propellant and ignition charge realizes.In combustion gas pressurized strut when work,, minimum thrust is created under the situation that development mechanism combustion gas pressurized strut push rod stretches out fully, and maximum thrust produces development mechanism and begins to launch constantly.In order to reduce the impact after launching to put in place, reduce the explosive payload of propellant as far as possible, with the foundation of minimum thrust as calculating propellant loading amount.After the explosive payload of having confirmed propellant, confirm to produce the time of maximum thrust, prevent in official hour, can't reliably launch.Before producing maximum thrust, the propellant part of only having burnt can't produce maximum thrust, relies on ignition charge to compensate the generation maximum thrust.
The technical scheme that the present invention adopts is: a kind of development mechanism combustion gas pressurized strut comprises igniter, igniter cartridge, propellant, combustion chamber, cylindrical shell and push rod.Igniter, igniter cartridge, propellant assemble successively, and igniter is arranged on combustion chamber one end, and are connected with combustion chamber sealing.Igniter cartridge and propellant are arranged in the combustion chamber.The combustion chamber inwall is provided with heat insulation layer.Cylindrical shell one end and the combustion chamber other end are tightly connected.Communicate between combustion chamber and the cylindrical shell.Push rod is arranged in the cylindrical shell movably.Firing point firearm during work, the igniter cartridge that ignites, and then propellant is lighted, and along with combustion chamber pressure increases severely, promote push rod and move outward, produce change thrust.
Adopt between combustion chamber and the cylindrical shell to be threaded, between combustion chamber and cylindrical shell sealing ring is arranged, form confined space.
This development mechanism combustion gas pressurized strut also comprises guide ring, is positioned at cylindrical shell bottom gathering sill.
Push rod simultaneously is provided with heat insulation layer towards that of combustion chamber.
Igniter is the insensitiveness electric initiator.
This development mechanism combustion gas pressurized strut also comprises cushioning members, is positioned at cylindrical shell other end bottom.
Push rod flexibly connects near combustion chamber one end and cylindrical shell, and is provided with containment member.
The present invention is applied to have the development mechanism of folding wings, can be implemented in the technique effect of output change thrust in the development mechanism expansion process, and the impact after reducing to launch to put in place.
Description of drawings
Fig. 1 is a structural representation of the present invention.Wherein: 1 is that igniter, 2 is that igniter cartridge, 3 is that propellant, 4 is that combustion chamber, 5 is that heat insulation layer, 6 is that push rod, 7 is that cylindrical shell, 8 is that damping pad, 9 is a guide ring.
The specific embodiment
Below in conjunction with accompanying drawing the present invention is described further.
As shown in Figure 1; A kind of development mechanism combustion gas pressurized strut comprises igniter 1 (as incendiary source; Light igniter cartridge), igniter cartridge 2 (light propellant and produce maximum thrust with compensation), propellant 3 (produce lasting thrust when development mechanism work; For producing minimum thrust power source is provided), (igniter, igniter cartridge and propellant burn within it in combustion chamber 4; Its volume size has determined upbuild voltage capacity), push rod 6 (the power executive component of combustion gas pressurized strut links to each other with development mechanism) and cylindrical shell 7 (be threaded with combustion chamber 4, and settle push rod 6).Combustion chamber 4 inwalls are provided with heat insulation layer 5 (during combustion gas pressurized strut work, playing the effect that prevents that energy outwards runs off).Igniter 1 connects outside igniting holding wire.Igniter 1, igniter cartridge 2, propellant 3, push rod 6 connect successively.Propellant 3 is contained in the combustion chamber 4.Cushioning members 8 is damping pads of being processed by polytetrafluoroethylene (PTFE), is positioned at cylindrical shell 7 bottoms.Guide ring 9 (polytetrafluoroethylene (PTFE) material) is positioned at cylindrical shell 7 gathering sills.Combustion chamber 4 is threaded with cylindrical shell 7, and 7 of combustion chamber 4 and cylindrical shells have sealing ring, forms confined space.Push rod 6 flexibly connects near an end and the cylindrical shell 7 of combustion chamber 4, and is provided with sealing ring.
During development mechanism combustion gas pressurized strut work, at first the firing point firearm 1, and igniter 1 is lighted igniter cartridge 2; And then light propellant 3, along with the burning of propellant 3 and the burning of igniter cartridge 2, combustion chamber 4 pressure increase sharply; Promote push rod 6 and produce thrust, when producing maximum thrust, igniter cartridge 2 completing combustions; After this promote push rod 6 by propellant 3 burnings, along with the volume change of combustion chamber 4 is big, push rod 6 thrusts begin to diminish; When combustion gas pressurized strut push rod 6 stretches out fully, propellant 3 completing combustions, the thrust of this moment is minimum thrust.
Introduce in the face of the design of propellant and ignition charge down.
1) propellant confirms
Calculate the propellant loading amount according to the equation of gas state:
PV＝nRT (1)
In the formula: P-is a chamber pressure, Pa;
V-is a container volume, m
3
R-is a gas constant, R=8.31Nm/ (molk);
T-is an ignition temperature, K;
N-is the combustion gas molal quantity.
Calculate combustion gas molal quantity n.Development mechanism combustion gas pressurized strut propellant design dose (g): m=nMg.MG is the molal weight of powder column in the formula.
2) ignition charge confirms
Carry out the calculation level powder volume by following formula:
In the formula: W
Ig-igniter quantity, g;
T
gFuel gas temperature during the constant volume burning of-ignition charge, k;
R
0-universal gas constant 8.31Nm/ (molk);
V
0-combustion chamber initial free volume m
3, m
3
The percetage by weight of ε-ignition charge burning condensed phase product;
M-ignition charge gas-phase product molecular weight, g/mol;
k
Ig-igniter quantity correction factor.
P
Ig-igniting pressure, Pa;
Igniting pressure is calculated as follows P
Ig=P
Max-P
1-P
2, P
MaxCombustion chamber pressure during for the generation maximum thrust; P
1The pressure that igniter produces during for the generation maximum thrust, P
2The pressure that propellant produces during for the generation maximum thrust.
The above is not that the present invention is done any restriction, and every any simple modification that technical spirit is done according to the present invention, change and equivalent structure change, and all still belong in the protection domain of technical scheme of the present invention.
Claims (7)
1. development mechanism combustion gas pressurized strut; It is characterized in that: comprise igniter (1), igniter cartridge (2), propellant (3), combustion chamber (4), cylindrical shell (7) and push rod (6), igniter (1), igniter cartridge (2), propellant (3) assemble successively, and igniter (1) is arranged on combustion chamber (4) one ends; And be tightly connected with combustion chamber (4); Igniter cartridge (2) and propellant (3) are arranged in the combustion chamber (4), and combustion chamber (4) inwall is provided with heat insulation layer (5), and cylindrical shell (7) one ends and combustion chamber (4) other end are tightly connected; Communicate between combustion chamber (4) and the cylindrical shell (7), push rod (6) is arranged in the cylindrical shell (7) movably.
2. development mechanism combustion gas pressurized strut according to claim 1 is characterized in that: adopt between combustion chamber (4) and the cylindrical shell (7) to be threaded, between combustion chamber (4) and cylindrical shell (7) sealing ring is arranged, form confined space.
3. development mechanism combustion gas pressurized strut according to claim 1 is characterized in that: also comprise guide ring, be positioned at cylindrical shell (7) bottom gathering sill.
4. development mechanism combustion gas pressurized strut according to claim 1 is characterized in that: that of (4) simultaneously is provided with heat insulation layer to said push rod (6) towards the combustion chamber.
5. development mechanism combustion gas pressurized strut according to claim 1 is characterized in that: said igniter (1) is the insensitiveness electric initiator.
6. development mechanism combustion gas pressurized strut according to claim 1 is characterized in that: also comprise cushioning members (8), be positioned at cylindrical shell other end bottom.
7. development mechanism combustion gas pressurized strut according to claim 1 is characterized in that: said push rod (6) flexibly connects near combustion chamber (4) one ends and cylindrical shell (7), and is provided with containment member.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012101036590A CN102645137A (en) | 2012-03-30 | 2012-03-30 | Gas actuator cylinder of unfolding mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012101036590A CN102645137A (en) | 2012-03-30 | 2012-03-30 | Gas actuator cylinder of unfolding mechanism |
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|---|---|
| CN102645137A true CN102645137A (en) | 2012-08-22 |
Family
ID=46658116
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012101036590A Pending CN102645137A (en) | 2012-03-30 | 2012-03-30 | Gas actuator cylinder of unfolding mechanism |
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| CN (1) | CN102645137A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104142099A (en) * | 2013-05-09 | 2014-11-12 | 中国航天科工集团第六研究院四十一所 | Gas actuating cylinder |
| CN105784447A (en) * | 2016-04-07 | 2016-07-20 | 西北工业大学 | Pressure intensity automatically balanced condensed-phase combustion product pollution-free collecting device |
| CN107436113A (en) * | 2017-03-30 | 2017-12-05 | 内蒙动力机械研究所 | A kind of combustion gas pressurized strut of gas buffer |
| CN113237391A (en) * | 2021-04-27 | 2021-08-10 | 西安北方庆华机电有限公司 | Small-size long-stroke actuating mechanism for unfolding missile wing |
| CN114165816A (en) * | 2022-02-09 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Engine hydraulic actuator cylinder mounting device |
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| BE552288A (en) * | 1953-10-20 | |||
| US5035378A (en) * | 1990-05-07 | 1991-07-30 | Spanovich Joseph P | Variable alignment mechanism |
| RU2338663C1 (en) * | 2007-07-05 | 2008-11-20 | Открытое Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Folded aerodynamic surface |
| CN102003276A (en) * | 2010-10-15 | 2011-04-06 | 北京机械设备研究所 | Piston movement and ignition separated gas power device |
| CN201925048U (en) * | 2010-10-09 | 2011-08-10 | 南京理工大学 | Multi-powder-chamber variable thruster |
| CN202126218U (en) * | 2011-05-26 | 2012-01-25 | 浙江理工大学 | Directly-connected lengthways unfolding mechanism for folding wings |
| CN202511719U (en) * | 2012-03-30 | 2012-10-31 | 中国航天科工集团第六研究院四十一所 | Gas actuating cylinder for expansion mechanism |
-
2012
- 2012-03-30 CN CN2012101036590A patent/CN102645137A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| BE552288A (en) * | 1953-10-20 | |||
| US5035378A (en) * | 1990-05-07 | 1991-07-30 | Spanovich Joseph P | Variable alignment mechanism |
| RU2338663C1 (en) * | 2007-07-05 | 2008-11-20 | Открытое Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Folded aerodynamic surface |
| CN201925048U (en) * | 2010-10-09 | 2011-08-10 | 南京理工大学 | Multi-powder-chamber variable thruster |
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Non-Patent Citations (1)
| Title |
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| 郭晨俊: "动力装置的动力学分析和受力计算的研究", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》, no. 11, 15 November 2008 (2008-11-15) * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104142099A (en) * | 2013-05-09 | 2014-11-12 | 中国航天科工集团第六研究院四十一所 | Gas actuating cylinder |
| CN105784447A (en) * | 2016-04-07 | 2016-07-20 | 西北工业大学 | Pressure intensity automatically balanced condensed-phase combustion product pollution-free collecting device |
| CN107436113A (en) * | 2017-03-30 | 2017-12-05 | 内蒙动力机械研究所 | A kind of combustion gas pressurized strut of gas buffer |
| CN113237391A (en) * | 2021-04-27 | 2021-08-10 | 西安北方庆华机电有限公司 | Small-size long-stroke actuating mechanism for unfolding missile wing |
| CN114165816A (en) * | 2022-02-09 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Engine hydraulic actuator cylinder mounting device |
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Application publication date: 20120822 |