CN113700576A - Visual detection method for rocket tail tank engine swing clearance - Google Patents
Visual detection method for rocket tail tank engine swing clearance Download PDFInfo
- Publication number
- CN113700576A CN113700576A CN202110972809.0A CN202110972809A CN113700576A CN 113700576 A CN113700576 A CN 113700576A CN 202110972809 A CN202110972809 A CN 202110972809A CN 113700576 A CN113700576 A CN 113700576A
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- China
- Prior art keywords
- engine
- rocket
- gap
- clearance
- swinging
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Classifications
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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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N7/00—Television systems
- H04N7/18—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
Abstract
The invention discloses a visual detection method for a rocket tail cabin engine swinging gap, which comprises the step 1 of searching a smaller rocket tail cabin gap. According to a rocket assembly model, a position with a small gap is searched around the engine; and 2, final assembly of the tail cabin. According to the rocket assembly requirement, the engine, the servo mechanism and the single machine product in the cabin are completed; and 3, arranging a camera and an interpretation mark. Arranging a camera at the position with a small gap, transmitting a monitoring signal to the ground, and displaying the monitoring signal on an interpretation monitor; the interpretation mark thickness is a required value of the safety clearance; and 4, connecting the servo intermediate frequency power supply and the controller. Connecting a ground medium-frequency power supply process cable, a controller cable and a cable of the rocket servo mechanism in a plugging manner; and 5, swinging the engine, and observing the gap. And swinging the engine according to a set program, and observing whether the interpretation mark at the position with smaller clearance generates interference clearance in the swinging process, thereby ensuring that the requirement of safety clearance is met.
Description
Technical Field
The invention relates to the field of carrier rocket assembly and servo systems, in particular to a visual detection method for a rocket tail cabin engine swinging gap.
Background
During the rocket flying process, the engine needs to be swung to ensure the stable posture of the rocket and fly according to the set orbit. In order to ensure the safety of the swing of the engine, whether the engine has enough safety clearance with other equipment in the process of the engine or not needs to be ensured.
The swing clearance inspection of the engine of the tail cabin of the rocket in active service in China adopts a method of manually pushing an engine spray pipe, and in the process, personnel inspect the swing clearance in the cabin.
Disclosure of Invention
The invention aims to provide a visual detection method for a rocket tail tank engine swinging gap, which ensures that the engine has enough safety gap with other equipment in the swinging process.
In order to achieve the purpose, the invention provides a visual detection method for a rocket tail tank engine rocking gap, which comprises the following steps:
step one, finding a smaller gap of a rocket tail cabin: according to a rocket assembly model, a position with a small gap is searched around the engine;
step two, final assembly of the tail cabin: according to the rocket final assembly requirement, the installation of the engine, the servo mechanism and the single machine products in the cabin is finished;
step three, arranging a camera and an interpretation mark: arranging a camera at the position with a small gap, transmitting a monitoring signal to the ground, and displaying the monitoring signal on an interpretation monitor; the interpretation mark thickness is the required value of the safety gap.
Step four, connecting the servo intermediate frequency power supply and the controller: and the cable connecting the ground medium-frequency power supply process cable, the controller cable and the arrow servo mechanism is inserted and connected.
Step five, swinging the engine, observing the clearance: and swinging the engine according to a set program, and observing whether the interpretation mark at the position with smaller clearance generates interference clearance in the swinging process, thereby ensuring that the requirement of safety clearance is met.
In the third step, a camera and a precast block are arranged: the thickness of the precast block is a required value of the safety clearance.
Compared with the prior art, the invention has the technical beneficial effects that:
according to the novel visual detection method for the gap between the rocket tail cabin equipment, due to the adoption of the technical scheme, the enough safety gap between the engine and other equipment in the swinging process can be detected, and the normal flight of the rocket is ensured.
Drawings
The invention provides a visual detection method for a rocket tail tank engine rocking gap, which is provided by the following embodiments and attached drawings.
FIG. 1 is a schematic diagram of a swing angle testing system.
Detailed Description
The following describes a rocket tail tank engine rocking gap visualization detection method in detail with reference to the accompanying drawings.
Step 1, finding a smaller gap of the rocket tail cabin. And according to a rocket assembly model, finding a position with a small gap around the engine.
And 2, final assembly of the tail cabin. And finishing the engine, the servo mechanism and the single machine product in the cabin according to the general assembly requirement of the rocket.
And 3, arranging a camera and an interpretation mark. Arranging a camera at the position with a small gap, transmitting a monitoring signal to the ground, and displaying the monitoring signal on an interpretation monitor; the interpretation mark thickness is the required value of the safety gap.
And 4, connecting the servo intermediate frequency power supply and the controller. And the cable connecting the ground medium-frequency power supply process cable, the controller cable and the arrow servo mechanism is inserted and connected.
And 5, swinging the engine, and observing the gap. And swinging the engine according to a set program, and observing whether the interpretation mark at the position with smaller clearance generates interference clearance in the swinging process, thereby ensuring that the requirement of safety clearance is met.
According to the novel visual detection method for the gap between the rocket tail cabin equipment, due to the adoption of the technical scheme, the enough safety gap between the engine and other equipment in the swinging process can be detected, and the normal flight of the rocket is ensured.
The above-described embodiments are intended to illustrate the present invention, and any modifications and variations of the present invention are within the spirit of the present invention and the scope of the claims.
Claims (2)
1. A visual detection method for a rocket tail tank engine swing gap is characterized by comprising the following steps:
step one, finding a smaller gap of a rocket tail cabin: according to a rocket assembly model, a position with a small gap is searched around the engine;
step two, final assembly of the tail cabin: according to the rocket final assembly requirement, the installation of the engine, the servo mechanism and the single machine products in the cabin is finished;
step three, arranging a camera and an interpretation mark: arranging a camera at the position with a small gap, transmitting a monitoring signal to the ground, and displaying the monitoring signal on an interpretation monitor; the interpretation mark thickness is the required value of the safety gap.
Step four, connecting the servo intermediate frequency power supply and the controller: and the cable connecting the ground medium-frequency power supply process cable, the controller cable and the arrow servo mechanism is inserted and connected.
Step five, swinging the engine, observing the clearance: and swinging the engine according to a set program, and observing whether the interpretation mark at the position with smaller clearance generates interference clearance in the swinging process, thereby ensuring that the requirement of safety clearance is met.
2. The visual detection method for the swaying gap of the rocket tail capsule engine as recited in claim 1, wherein in said third step, a camera and a prefabricated block are arranged: the thickness of the precast block is a required value of the safety clearance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110972809.0A CN113700576B (en) | 2021-08-24 | 2021-08-24 | Visual detection method for rocket tail tank engine swing clearance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110972809.0A CN113700576B (en) | 2021-08-24 | 2021-08-24 | Visual detection method for rocket tail tank engine swing clearance |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113700576A true CN113700576A (en) | 2021-11-26 |
| CN113700576B CN113700576B (en) | 2022-08-26 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110972809.0A Active CN113700576B (en) | 2021-08-24 | 2021-08-24 | Visual detection method for rocket tail tank engine swing clearance |
Country Status (1)
| Country | Link |
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| CN (1) | CN113700576B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3979086A (en) * | 1974-11-08 | 1976-09-07 | The United States Of America As Represented By The Secretary Of The Army | Rocketed data communication system |
| JPH0350500A (en) * | 1989-07-17 | 1991-03-05 | Nissan Motor Co Ltd | Tester for missile |
| CN111947523A (en) * | 2020-07-08 | 2020-11-17 | 一重集团(黑龙江)专项装备科技有限公司 | Control system and control method for full-automatic adjustment of rocket perpendicularity |
-
2021
- 2021-08-24 CN CN202110972809.0A patent/CN113700576B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3979086A (en) * | 1974-11-08 | 1976-09-07 | The United States Of America As Represented By The Secretary Of The Army | Rocketed data communication system |
| JPH0350500A (en) * | 1989-07-17 | 1991-03-05 | Nissan Motor Co Ltd | Tester for missile |
| CN111947523A (en) * | 2020-07-08 | 2020-11-17 | 一重集团(黑龙江)专项装备科技有限公司 | Control system and control method for full-automatic adjustment of rocket perpendicularity |
Non-Patent Citations (2)
| Title |
|---|
| 刘博等: ""火箭喷管运动视觉测试精度的校准与实验"", 《光学精密工程》 * |
| 邝奇等: ""发动机地面试验摇摆测控系统设计与实现"", 《火箭推进》 * |
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| CN113700576B (en) | 2022-08-26 |
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