CN202650977U - Timing zero trigger for sequential controller of civil rocket - Google Patents
Timing zero trigger for sequential controller of civil rocket Download PDFInfo
- Publication number
- CN202650977U CN202650977U CN 201220312593 CN201220312593U CN202650977U CN 202650977 U CN202650977 U CN 202650977U CN 201220312593 CN201220312593 CN 201220312593 CN 201220312593 U CN201220312593 U CN 201220312593U CN 202650977 U CN202650977 U CN 202650977U
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- trigger
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- spring
- trigger body
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Abstract
The utility model relates to a timing zero trigger for a sequential controller of a civil rocket and belongs to the rocket technology field. The zero trigger provided by the utility model comprises a trigger body, a spring, a conductive sphere, a voltage controlled gasket and two conductive sheets. Two cavities communicated with each other are arranged in the trigger body. The two conductive sheets disconnected with each other are mounted on a connection position of the cavities and are respectively connected with two poles of a trigger circuit. The spring and the conductive sphere are disposed in the cavities. The spring tightly presses the conductive sphere to support the sphere on the voltage controlled gasket arranged in a combustion chamber of an engine. The pressure which the voltage controlled gasket can bear is greater than the detonation pressure of a flame igniter and less than the operation pressure of normal operation of the engine. The trigger provided by the utility model has the advantages of simple structure, low cost and reliable operation. The timing zero trigger for the sequential controller solves a problem that conventional zero trigger which is controlled to start by the flame igniter has safe hidden troubles in a condition of abnormal operation of the rocket engine.
Description
Technical field
The utility model relates to a kind of civil rocket time schedule controller timing trigger at zero point, belongs to play the arrow technical field.
Background technology
On the civil rocket product, be mainly used in after receiving timing triggering signal at zero point, beginning timing such as the trigger at zero point of hail-proof rain-increasing rocket front end seeding device, provide control signal in predetermined time and excite the payload carrying on mechanism to produce action.Zero point, triggering signal produced when rocket launching usually, and it is often excited by the switching line state transition of holding wire.The trigger mechanism at a kind of zero point of successfully using at present is that the wire that will consist of signal circuit in the engine ignition tool is divided into insulated from each other adjacent two sections, insulating barrier is burnt in the combustion gas that produces after the igniter effect, under the ionic state gas that in the effect of igniter gaseous-pressure and igniter, forms and the conducting effect of carbonized product, control loop by disconnected to logical generation timing triggering signal at zero point.Yet after the igniter effect, rocket engine may be because some special circumstances, normal operation, if this moment the front end seeding device begin produce action, just have and have certain potential safety hazard.
The utility model content
The purpose of this utility model is will solve tradition trigger at zero point to be started by igniter control; in the situation that working, rocket engine can not have the problem of potential safety hazard; and a kind of time schedule controller timing trigger at zero point is provided, guarantee to produce reliably for the civil rocket time schedule controller under the prerequisite that rocket engine worked the problem of timing triggering signal at zero point.
The purpose of this utility model is achieved through the following technical solutions:
A kind of time schedule controller timing trigger at zero point of the present utility model, comprise trigger body, spring, conductor ball, voltage-controlled pad and conducting strip, trigger body center is processed with two sections cavitys that are interconnected, the junction sidewall of two sections cavitys has two conducting strip installing holes, all be fixed with a conducting strip in each conducting strip installing hole, two conducting strips link to each other by wire the two poles of the earth with the time schedule controller circuits for triggering respectively in the trigger body exterior, and two conducting strips open circuit by stretch out two connecting portions formation that mutually disconnect in the trigger body interior; Place spring in one section cavity of trigger body interior, place conductor ball in another section cavity, the internal diameter of the diameter of conductor ball and place cavity is complementary, the cavity end face of placing spring one end encapsulates by setting-up piece, place the cavity end face of conductor ball one end by fixing voltage-controlled pad encapsulation, trigger body cavity inner spring after the encapsulation presses conductor ball and withstands on the voltage-controlled pad, and conductor ball two conducting strips interior with inserting cavity do not contact, on the trigger body is installed at the bottom of the connection of rocket engine front end, and voltage-controlled pad one end of trigger is put into engine chamber.
Voltage-controlled pad can bear pressure for greater than the ignition pressure of the igniter operating pressure less than engine work.
Voltage-controlled pad is fixing heat insulating mattress outward, prevents from placing voltage-controlled pad and does not break owing to ablating before reaching specified pressure.
The course of work
Igniter starts moment, because the maximum pressure that the pressure that igniter produces can bear less than voltage-controlled pad, trigger can not start because of igniting of igniter, behind engine work, the maximum pressure that the larger pressure that produces can bear greater than voltage-controlled pad, the voltage-controlled pad of trigger breaks, and conductor ball travels forward under the gases at high pressure effect that engine produces, the conducting strip of two disconnections of conductor ball front end is communicated with, and then time schedule controller meter circuits for triggering are started.
Beneficial effect
Trigger structure of the present utility model is simple, and is cheap, and reliable effect has solved traditional zero point trigger and started by igniter control, can not have the problem of potential safety hazard in the situation that rocket engine works.
Description of drawings
Fig. 1 is the structural representation of the utility model time schedule controller timing trigger at zero point;
Wherein, 1-screw; The 2-nut; The 3-conducting strip; The 4-pad; The 5-spring; 6-trigger body; The 7-heat insulating mattress; The voltage-controlled pad of 8-; The 9-conductor ball.
Embodiment
Below in conjunction with drawings and Examples content of the present utility model is further described:
Embodiment
A kind of time schedule controller timing trigger at zero point of the present utility model, as shown in Figure 1, comprise trigger body 6, spring 5, conductor ball 9, voltage-controlled pad 8 and conducting strip 3, trigger body 6 centers are processed with two sections cavitys that are interconnected, the junction sidewall of two sections cavitys has two conducting strip installing holes, all be fixed with a conducting strip in each conducting strip installing hole, two conducting strips link to each other by wire the two poles of the earth with the time schedule controller circuits for triggering respectively in trigger body 6 outsides, and two conducting strips open circuit by stretch out two connecting portions formation that mutually disconnect in trigger body 6 inside; Place spring 5 in one section cavity of trigger body 6 inside, place conductor ball 9 in another section cavity, the internal diameter of the diameter of conductor ball and place cavity is complementary, place the cavity end face of spring one end by setting-up piece 4 rear encapsulation, place the cavity end face of conductor ball one end by fixing voltage-controlled pad 8 encapsulation, cavity inner spring 5 after the encapsulation presses conductor ball 9 and withstands on the voltage-controlled pad 8, and conductor ball 9 two conducting strips interior with inserting cavity do not contact, on trigger body 6 is installed at the bottom of the connection of rocket engine front end, and voltage-controlled pad one end of trigger is put into engine chamber.
Voltage-controlled pad 8 can bear pressure for greater than the ignition pressure of the igniter operating pressure less than engine work.
Voltage-controlled pad 8 outer fixedly heat insulating mattress 7 prevent that voltage-controlled pad 8 from not breaking owing to ablating before reaching specified pressure.
The course of work
Igniter starts moment, because the maximum pressure that the pressure that igniter produces can bear less than voltage-controlled pad 8, trigger can not start because of igniting of igniter, behind engine work, the maximum pressure that the larger pressure that produces can bear greater than voltage-controlled pad 8, the voltage-controlled pad 8 of trigger breaks, and conductor ball 9 travels forward under the gases at high pressure effect that engine produces, the conducting strip of two disconnections of conductor ball 9 front ends is communicated with, and then time schedule controller meter circuits for triggering are started.
Claims (2)
1. time schedule controller timing trigger at zero point, it is characterized in that: comprise trigger body, spring, conductor ball, voltage-controlled pad and conducting strip, trigger body center is processed with two sections cavitys that are interconnected, the junction sidewall of two sections cavitys has two conducting strip installing holes, all be fixed with a conducting strip in each conducting strip installing hole, two conducting strips link to each other by wire the two poles of the earth with the time schedule controller circuits for triggering respectively in the trigger body exterior, and two conducting strips open circuit by stretch out two connecting portions formation that mutually disconnect in the trigger body interior; Place spring in one section cavity of trigger body interior, place conductor ball in another section cavity, the internal diameter of the diameter of conductor ball and place cavity is complementary, the cavity end face of placing spring one end encapsulates by setting-up piece, place the cavity end face of conductor ball one end by fixing voltage-controlled pad encapsulation, trigger body cavity inner spring after the encapsulation presses conductor ball and withstands on the voltage-controlled pad, and conductor ball two conducting strips interior with inserting cavity do not contact, on the trigger body is installed at the bottom of the connection of rocket engine front end, and voltage-controlled pad one end of trigger is put into engine chamber;
Wherein, voltage-controlled pad can bear pressure for greater than the ignition pressure of the igniter operating pressure less than engine work.
2. a kind of time schedule controller timing trigger at zero point as claimed in claim 1 is characterized in that: voltage-controlled pad is fixing heat insulating mattress outward.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220312593 CN202650977U (en) | 2012-06-27 | 2012-06-27 | Timing zero trigger for sequential controller of civil rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220312593 CN202650977U (en) | 2012-06-27 | 2012-06-27 | Timing zero trigger for sequential controller of civil rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202650977U true CN202650977U (en) | 2013-01-02 |
Family
ID=47420044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220312593 Expired - Fee Related CN202650977U (en) | 2012-06-27 | 2012-06-27 | Timing zero trigger for sequential controller of civil rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202650977U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102723233A (en) * | 2012-06-27 | 2012-10-10 | 晋西工业集团有限责任公司 | Timing zero trigger for civil rocket time schedule controller |
| CN111025351A (en) * | 2019-12-05 | 2020-04-17 | 中国人民解放军63620部队 | Real-time estimation method for time zero difference of carrier rocket navigation calculation and external measurement system |
-
2012
- 2012-06-27 CN CN 201220312593 patent/CN202650977U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102723233A (en) * | 2012-06-27 | 2012-10-10 | 晋西工业集团有限责任公司 | Timing zero trigger for civil rocket time schedule controller |
| CN111025351A (en) * | 2019-12-05 | 2020-04-17 | 中国人民解放军63620部队 | Real-time estimation method for time zero difference of carrier rocket navigation calculation and external measurement system |
| CN111025351B (en) * | 2019-12-05 | 2021-11-30 | 中国人民解放军63620部队 | Real-time estimation method for time zero difference of carrier rocket navigation calculation and external measurement system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130102 Termination date: 20150627 |
|
| EXPY | Termination of patent right or utility model |