CN112591140A - Load-shedding slow-release device for aircraft drag release launching - Google Patents
Load-shedding slow-release device for aircraft drag release launching Download PDFInfo
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- CN112591140A CN112591140A CN202011205955.2A CN202011205955A CN112591140A CN 112591140 A CN112591140 A CN 112591140A CN 202011205955 A CN202011205955 A CN 202011205955A CN 112591140 A CN112591140 A CN 112591140A
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- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
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Abstract
The invention relates to a load-shedding slow-release device for aircraft drag release launching, which comprises a pull rod, a split type piston ring, a slow-release device shell, a damping oil cavity shell, damping oil and damping holes, wherein an aircraft is positioned on a launching platform, the load-shedding slow-release device is arranged below the launching platform, and the pull rod penetrates through a through hole on the launching platform and is fixedly connected with the aircraft; the split piston ring is of a two-segment structure, is arranged at the lower end of the pull rod and is arranged in the inner cavity of the slow release device shell, and is tightly attached to the inner cavity of the slow release device shell; the damping oil cavity shell is filled with damping oil, and the slow release device shell is arranged in the damping oil of the damping oil cavity shell. The aircraft structure before launching and the launching platform structure are connected and locked by the drag release device, the drag release device receives an instruction to release the drag force during launching, the aircraft is released, and the load-shedding slow release device starts to work at the same time to provide slow release resistance so as to prevent the aircraft from being subjected to overlarge impact force.
Description
Technical Field
The invention relates to a load-shedding slow-release device for aircraft drag release launching, and belongs to the technical field of vertical launching of aerospace aircrafts.
Background
The containment release launching device is used for fixing the aircraft on the launching platform before vertical launching and after ignition for a plurality of seconds. After the ignition works normally and the thrust of the engine reaches the takeoff rated value, the drag release device releases the aircraft, and the aircraft departs from the drag force to normally take off. The launching mode of firstly igniting the engine and establishing the thrust and then releasing the aircraft can stop launching under the abnormal condition of the aircraft after ignition, so that the reliability of vertical launching is improved, but additional releasing load impact is increased when the aircraft is suddenly released from the drag force. In order to reduce the impact to which the aircraft is subjected, impact relief is generally achieved by providing a special slow-release scheme.
The load-shedding slow-release schemes adopted by various foreign models are classified into the following three types: (1) a sleeve pull rod type slow release mechanism; (2) a broken pull rod type slow release mechanism; (3) a friction lever-reed type slow release mechanism. The three load-reducing slow-release schemes are all slow-release of impact by means of structural plastic deformation and friction force, and have the common defect that accurate slow-release force control cannot be achieved in the design stage. The research and accumulation of the domestic load-reducing slow-release scheme technology are weak, and no practical engineering application case exists.
With the improvement of the vertical launching reliability requirement of aircrafts such as a carrier rocket and the like, the demand of the contained release launching technology adopting a slow release scheme in China is more and more urgent.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, and the load-shedding slow-release device for the aircraft drag release launching is provided, so that slow-release resistance is provided to prevent the aircraft from being subjected to excessive impact.
The technical scheme of the invention is as follows:
an unloading and slow-releasing device for aircraft drag release launching comprises a pull rod, a split piston ring, a slow-releasing device shell, a damping oil cavity shell, damping oil and damping holes,
the aircraft is positioned on the launching platform, the load-shedding slow-release device is arranged below the launching platform, and the pull rod penetrates through a through hole on the launching platform to be fixedly connected with the aircraft
The split piston ring is of a two-segment structure, is arranged at the lower end of the pull rod and is arranged in the inner cavity of the slow release device shell, and is tightly attached to the inner cavity of the slow release device shell;
damping oil is contained in the damping oil cavity shell, and the slow release device shell is arranged in the damping oil of the damping oil cavity shell;
the slow release device shell is a cavity with a blind hole at one end, and a damping hole communicated with the outside is formed at the bottom of the slow release device shell;
when the aircraft is released, the pull rod moves upwards along with the aircraft, and in the process, the pull rod drives the split piston ring to move upwards along the cylindrical inner cavity of the shell of the slow release device to form a closed cavity with gradually increased volume; the volume of the closed cavity is increased, and the oil in the damping oil cavity is sucked into the closed cavity through the damping hole by negative pressure formed inside the closed cavity; the damping force generated when the oil passes through the damping holes forms the slow release resistance which is exerted by the slow release device.
Furthermore, when the split piston ring moves to the separation groove, the damping oil at least fills the inner cavity of the slow release device shell.
Furthermore, the damping force is adjusted by adjusting the number and the size of the damping holes.
Furthermore, a separation groove is arranged on the shell of the slow release device, and the distance between the separation groove and the shell of the slow release device is ensured to meet the slow release requirement.
Furthermore, when the split piston ring moves to the separation groove on the shell of the slow release device, the split piston ring slides into the separation groove under the action of the radial force of the conical contact surface of the pull rod, the pull rod is separated from the slow release device, and the slow release device finishes working.
Furthermore, after the pull rod is separated from the slow release device, the aircraft continues to drive the connecting rod to walk.
Furthermore, the distance between the separating groove and the upper end of the shell of the sustained-release device is 1/5-1/3 of the height of the shell of the sustained-release device.
Furthermore, the damping holes are uniformly distributed at the bottom of the shell of the slow release device.
Compared with the prior art, the invention has the beneficial effects that:
(1) the structure of the aircraft before launching and the structure of the launching platform are connected and locked by the drag release device, the drag release device receives an instruction to release the drag force during launching, the aircraft is released, and the load-shedding slow release device starts to work at the same time to provide slow release resistance so as to prevent the aircraft from being subjected to overlarge impact force;
(2) the damping force generated when oil passes through the damping holes is the slow-release resistance exerted by the slow-release device, and the magnitude of the damping force can be accurately designed by adjusting the number and the magnitude of the damping holes in the design stage;
(3) when the split piston ring moves to the position of the separation groove structure on the shell of the slow release device, the split piston ring slides into the separation groove under the action of the radial force of the conical contact surface of the pull rod, the pull rod is separated from the slow release device, and the slow release device finishes the work.
Drawings
FIG. 1 is a schematic view of an application of a sustained release apparatus of the present invention, wherein 1-a pull rod, 2-an unloading sustained release apparatus, 3-an aircraft, 4-a launch pad, 5-a drag release apparatus;
FIG. 2 is a schematic diagram of the working principle and the components of the load-shedding slow-release device, wherein 6 is a split piston ring, 7 is a slow-release device shell, 8 is a damping oil cavity shell, 9 is damping oil and 10 is a damping hole.
Detailed Description
The invention is further illustrated by the following examples.
A load-reducing slow-release device for aircraft drag release launching, as shown in figures 1 and 2, comprises a pull rod, a split type piston ring, a slow-release device shell, a damping oil cavity shell, damping oil and a damping hole,
the aircraft is positioned on the launching platform, the load-shedding slow-release device is arranged below the launching platform, and the pull rod penetrates through a through hole on the launching platform to be fixedly connected with the aircraft
The split piston ring is of a two-segment structure, is arranged at the lower end of the pull rod and is arranged in the inner cavity of the slow release device shell, and is tightly attached to the inner cavity of the slow release device shell;
damping oil is contained in the damping oil cavity shell, and the slow release device shell is arranged in the damping oil of the damping oil cavity shell;
the slow release device shell is a cavity with a blind hole at one end, and a damping hole communicated with the outside is formed at the bottom of the slow release device shell;
when the aircraft is released, the pull rod moves upwards along with the aircraft, and the pull rod drives the split piston ring to move upwards along the cylindrical inner cavity of the shell of the slow release device in the process to form a closed cavity with gradually increased volume. The volume of the closed cavity is increased, and oil in the damping oil cavity is sucked into the closed cavity through the damping hole by negative pressure formed inside the closed cavity. The damping force generated when the oil passes through the damping holes is the slow-release resistance exerted by the slow-release device, and the magnitude of the damping force can be accurately designed by adjusting the number and the magnitude of the damping holes in the design stage.
When the split piston ring moves to the position of the separation groove structure on the shell of the slow release device, the split piston ring slides into the separation groove under the action of the radial force of the conical contact surface of the pull rod, the pull rod is separated from the slow release device, and the slow release device finishes working.
The aircraft structure before launching and the launching platform structure are connected and locked by the drag release device, the drag release device receives an instruction to release the drag force during launching, the aircraft is released, and the load-shedding slow release device starts to work at the same time to provide slow release resistance so as to prevent the aircraft from being subjected to overlarge impact force.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (8)
1. A load-shedding slow-release device for aircraft drag release launching is characterized by comprising a pull rod, a split type piston ring, a slow-release device shell, a damping oil cavity shell, damping oil and damping holes,
the aircraft is positioned on the launching platform, the load-shedding slow-release device is arranged below the launching platform, and the pull rod penetrates through a through hole on the launching platform to be fixedly connected with the aircraft
The split piston ring is of a two-segment structure, is arranged at the lower end of the pull rod and is arranged in the inner cavity of the slow release device shell, and is tightly attached to the inner cavity of the slow release device shell;
damping oil is contained in the damping oil cavity shell, and the slow release device shell is arranged in the damping oil of the damping oil cavity shell;
the slow release device shell is a cavity with a blind hole at one end, and a damping hole communicated with the outside is formed at the bottom of the slow release device shell;
when the aircraft is released, the pull rod moves upwards along with the aircraft, and in the process, the pull rod drives the split piston ring to move upwards along the cylindrical inner cavity of the shell of the slow release device to form a closed cavity with gradually increased volume; the volume of the closed cavity is increased, and the oil in the damping oil cavity is sucked into the closed cavity through the damping hole by negative pressure formed inside the closed cavity; the damping force generated when the oil passes through the damping holes forms the slow release resistance which is exerted by the slow release device.
2. The slow release device for aircraft drag release launching as claimed in claim 1, wherein the damping fluid at least fills the interior cavity of the slow release housing when the split piston ring is moved into the separator tank.
3. A load shedding and release device for aircraft drag release launching as claimed in claim 1, wherein the magnitude of the damping force is adjusted by adjusting the number and size of the damping holes.
4. A load shedding and release device for aircraft drag release launching as claimed in claim 1, wherein the release device housing is provided with a separation groove, the separation groove being located at a distance from the release device housing to ensure sustained release.
5. The load shedding and release device for aircraft drag release launching of claim 4, wherein when the split piston ring moves to the separation groove on the release device housing, the split piston ring slides into the separation groove under the radial force of the tapered contact surface with the pull rod, the pull rod disengages from the release device, and the release device is finished.
6. The load shedding and release device for aircraft drag release launching as claimed in claim 5, wherein the aircraft continues to drive the linkage to travel after the pull rod disengages from the release device.
7. The load relief slow release device for aircraft contained release launching as claimed in claim 4, wherein the separation groove is located at a distance 1/5-1/3 from the upper end of the slow release housing at the height of the slow release housing.
8. A load shedding sustained release apparatus for aircraft drag release launching as claimed in claim 3, wherein the damping holes are evenly distributed at the bottom of the sustained release apparatus housing.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011205955.2A CN112591140B (en) | 2020-11-02 | 2020-11-02 | Load-shedding slow-release device for aircraft drag release launching |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011205955.2A CN112591140B (en) | 2020-11-02 | 2020-11-02 | Load-shedding slow-release device for aircraft drag release launching |
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| CN112591140A true CN112591140A (en) | 2021-04-02 |
| CN112591140B CN112591140B (en) | 2022-10-21 |
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| CN202011205955.2A Active CN112591140B (en) | 2020-11-02 | 2020-11-02 | Load-shedding slow-release device for aircraft drag release launching |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113739634A (en) * | 2021-08-11 | 2021-12-03 | 浙江蓝箭航天空间科技有限公司 | Drag slow release device and launching pad of carrier rocket |
| CN113800012A (en) * | 2021-09-30 | 2021-12-17 | 北京中科宇航技术有限公司 | Drag release device and system thereof |
Citations (4)
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|---|---|---|---|---|
| GB8800513D0 (en) * | 1988-01-11 | 1988-06-02 | British Aerospace | Load coupling/uncoupling mechanism |
| CN1554875A (en) * | 2003-12-29 | 2004-12-15 | 杰 陆 | Damper after changing damp |
| JP2007321864A (en) * | 2006-05-31 | 2007-12-13 | Hitachi Ltd | Damping force adjustment type hydraulic shock absorber |
| US20200189771A1 (en) * | 2017-09-01 | 2020-06-18 | Ruag Space Ab | Separation device for spacecraft and a method for separation |
-
2020
- 2020-11-02 CN CN202011205955.2A patent/CN112591140B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB8800513D0 (en) * | 1988-01-11 | 1988-06-02 | British Aerospace | Load coupling/uncoupling mechanism |
| CN1554875A (en) * | 2003-12-29 | 2004-12-15 | 杰 陆 | Damper after changing damp |
| JP2007321864A (en) * | 2006-05-31 | 2007-12-13 | Hitachi Ltd | Damping force adjustment type hydraulic shock absorber |
| US20200189771A1 (en) * | 2017-09-01 | 2020-06-18 | Ruag Space Ab | Separation device for spacecraft and a method for separation |
Non-Patent Citations (2)
| Title |
|---|
| 万军等: "国外牵制释放发射技术研究现状", 《导弹与航天运载技术》 * |
| 安军等: "牵制缓释放过程中火箭动力响应特性分析", 《航空工程进展》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113739634A (en) * | 2021-08-11 | 2021-12-03 | 浙江蓝箭航天空间科技有限公司 | Drag slow release device and launching pad of carrier rocket |
| CN113800012A (en) * | 2021-09-30 | 2021-12-17 | 北京中科宇航技术有限公司 | Drag release device and system thereof |
| CN113800012B (en) * | 2021-09-30 | 2023-09-19 | 北京中科宇航技术有限公司 | Drag release device and system thereof |
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| Publication number | Publication date |
|---|---|
| CN112591140B (en) | 2022-10-21 |
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