CN202511719U - Gas actuating cylinder for expansion mechanism - Google Patents
Gas actuating cylinder for expansion mechanism Download PDFInfo
- Publication number
- CN202511719U CN202511719U CN2012201428713U CN201220142871U CN202511719U CN 202511719 U CN202511719 U CN 202511719U CN 2012201428713 U CN2012201428713 U CN 2012201428713U CN 201220142871 U CN201220142871 U CN 201220142871U CN 202511719 U CN202511719 U CN 202511719U
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- CN
- China
- Prior art keywords
- combustion chamber
- igniter
- propellant
- cylindrical shell
- push rod
- 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.)
- Expired - Lifetime
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Abstract
The utility model relates to a gas actuating cylinder for an expansion mechanism, which is applied into the expansion mechanism with folding wings. The gas actuating cylinder consists of an igniter, an ignition medicine box, a propellant, a combustion chamber, a push rod, a cylinder and the like. The igniter, the ignition medicine box and the propellant are assembled in sequence; and the igniter is arranged at one end of the combustion chamber and is hermetically connected with the combustion chamber. The ignition medicine box and the propellant are arranged in the combustion chamber. A heat insulation layer is arranged on the inner wall of the combustion chamber. One end of the cylinder is hermetically connected with the other end of the combustion chamber. The combustion chamber is communicated with the cylinder. The push rod can be movably arranged in the cylinder. The gas actuating cylinder has the beneficial effects that when the gas actuating cylinder works, both the igniter and the ignition medicine box are ignited, and further, the propellant is ignited; and along with the sharp increasing of intensity of pressure in the combustion chamber, the push rod is pushed to move outwards to generate the variable thrust and reduce the impact after the expansion is in place.
Description
Technical field
The utility model relates to a kind of development mechanism combustion gas pressurized strut, is 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.
The utility model content
The purpose of the utility model is that output becomes thrust, the impact after reducing to launch to put in place in the development mechanism expansion process.
The main design of the utility model: 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 utility model 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 utility model 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 the structural representation of the utility model.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 cushioning members, 9 is a guide ring.
The specific embodiment
Below in conjunction with accompanying drawing the utility model 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 utility model is done any restriction, and every any simple modification, change and equivalent structure of being done according to the utility model technical spirit changes, and all still belongs in the protection domain of the utility model technical scheme.
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 |
|---|---|---|---|
| CN2012201428713U CN202511719U (en) | 2012-03-30 | 2012-03-30 | Gas actuating cylinder for expansion mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012201428713U CN202511719U (en) | 2012-03-30 | 2012-03-30 | Gas actuating cylinder for expansion mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202511719U true CN202511719U (en) | 2012-10-31 |
Family
ID=47064199
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012201428713U Expired - Lifetime CN202511719U (en) | 2012-03-30 | 2012-03-30 | Gas actuating cylinder for expansion mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202511719U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102645137A (en) * | 2012-03-30 | 2012-08-22 | 中国航天科工集团第六研究院四十一所 | Gas actuator cylinder of unfolding mechanism |
| CN109696088A (en) * | 2018-12-07 | 2019-04-30 | 上海机电工程研究所 | Close-coupled missile wing companding mechanism and guided missile |
-
2012
- 2012-03-30 CN CN2012201428713U patent/CN202511719U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102645137A (en) * | 2012-03-30 | 2012-08-22 | 中国航天科工集团第六研究院四十一所 | Gas actuator cylinder of unfolding mechanism |
| CN109696088A (en) * | 2018-12-07 | 2019-04-30 | 上海机电工程研究所 | Close-coupled missile wing companding mechanism and guided missile |
| CN109696088B (en) * | 2018-12-07 | 2021-06-08 | 上海机电工程研究所 | Compact missile wing contraction and expansion mechanism and missile |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121031 |