CN112945030A - Arc-shaped flexible support bracket of hypersonic cruise missile - Google Patents
Arc-shaped flexible support bracket of hypersonic cruise missile Download PDFInfo
- Publication number
- CN112945030A CN112945030A CN202110127793.3A CN202110127793A CN112945030A CN 112945030 A CN112945030 A CN 112945030A CN 202110127793 A CN202110127793 A CN 202110127793A CN 112945030 A CN112945030 A CN 112945030A
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- Prior art keywords
- missile
- air bag
- inflatable
- hypersonic
- inflation
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- 239000000463 material Substances 0.000 claims abstract description 4
- 239000002184 metal Substances 0.000 claims description 3
- 238000010276 construction Methods 0.000 claims 1
- 230000001788 irregular Effects 0.000 abstract description 6
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
- F42B39/28—Ammunition racks, e.g. in vehicles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
Abstract
An arc-shaped flexible support bracket of a hypersonic cruise missile relates to a support structure of a missile, and solves the problem of poor flexibility of the support structure of the hypersonic cruise missile with the conventional irregular appearance and brittle heat-proof structure. The invention comprises an inflatable air bag, an inflation valve and a rigid bracket; the inflatable air bag is of a hollow saccular closed structure made of rubber materials, is arc-shaped in appearance and is provided with an inflation inlet, and the inflation inlet is provided with an inflation valve; the rigid bracket is disposed at the bottom of the inflatable airbag for securing and supporting the inflatable airbag. The inflatable air bag is inflated through the inflation valve, the hypersonic velocity cruise missile is placed on the inflatable air bag, the hypersonic velocity cruise missile is supported by the flexible shape-following adjustable rigidity of the hypersonic velocity missile which is in a shape close to a circle but not in a round shape and does not allow the local support to contact too high pressure, and damage to a thermal protection structure of the hypersonic velocity missile due to too high local support pressure is avoided.
Description
Technical Field
The invention relates to a support structure of a missile, in particular to an arc-shaped flexible support bracket of a hypersonic cruise missile with a near-circular non-circular appearance.
Background
The novel hypersonic cruise missile is different from the traditional missile in the aspect of aerodynamic characteristics, and the section of the novel hypersonic cruise missile is approximately circular but not circular. On the other hand, due to the requirement of heat insulation and heat protection, the surface of the bullet body is provided with a brittle heat protection ceramic structure, and the heat protection structure is easily damaged due to overlarge local supporting pressure. The irregular shape and the brittle heat-proof structure bring new challenges to the support of the projectile body, and the support device is required to have flexibility and be capable of passively adapting to the irregular shape of the projectile body; meanwhile, the support pressure distribution is uniform, and the local contact pressure is prevented from being overlarge.
Traditionally, the missile is supported by a felt or rubber cushion on a rigid supporting ring. However, the adaptability of the supporting mode to the shape of the projectile body is extremely limited, and the supporting requirement on the irregular shape of a nearly round non-round shape is difficult to meet. Meanwhile, no matter the felt or the rubber support is adopted, the support rigidity is fixed, the flexibility is limited, and when the felt or the rubber support is used for supporting for a long time, the deformation caused by extrusion leads to hardening of the felt or the rubber support, so that the requirement for supporting the hypersonic cruise missile on flexibility and adjustable rigidity is difficult to meet.
Disclosure of Invention
Aiming at the problem of poor flexibility of a support structure of the hypersonic cruise missile with the existing irregular shape and brittle heat-proof structure, the invention provides an arc-shaped flexible support bracket of the hypersonic cruise missile.
The invention discloses an arc-shaped flexible support bracket of a hypersonic cruise missile, which comprises an inflatable air bag 1, an inflation valve 2 and a rigid bracket 3;
the inflatable air bag 1 is of a hollow saccular closed structure made of rubber materials, is arc-shaped in appearance and is provided with an inflation inlet, and the inflation inlet is provided with an inflation valve 2;
the rigid bracket 3 is provided at the bottom of the inflatable airbag 1 for fixing and supporting the inflatable airbag 1.
Preferably, the inflatable air bag 1 and the rigid bracket 3 are of an integrated structure, the diameter of the rigid bracket 3 is larger than the outer diameter of the supported missile, and the inner diameter of the inflated inflatable air bag 1 is smaller than the outer diameter of the supported missile.
Preferably, the inflation valve 2 is a one-way valve.
Preferably, the support bracket further comprises an inflator, an air outlet of the inflator is communicated with the inflatable airbag 1 through an inflation valve to inflate the inflatable airbag 1, and the air pressure in the inflatable airbag 1 can be detected.
Preferably, the rigid carrier 3 is a metal carrier.
Preferably, the supporting bracket further comprises a supporting base 4, the supporting base 4 is a V-shaped block, and the rigid bracket 3 is mounted in a V-shaped recess on the supporting base 4.
The invention has the beneficial effects that: the invention adopts the rigid arc-shaped bracket to be embedded with the flexible inflatable air bag to realize flexible shape-following adjustable rigidity support for products such as novel hypersonic missile which have a near-circular but non-circular appearance and do not allow local support and contact pressure to be overlarge, thereby avoiding the damage of the hypersonic missile thermal protection structure caused by overlarge local support pressure.
Drawings
FIG. 1 is a schematic structural view of the arcuate flexible support bracket of the present invention.
FIG. 2 is a side view of FIG. 1;
FIG. 3 is a schematic three-dimensional view of the arcuate flexible support bracket illustrated in FIGS. 1 and 2;
FIG. 4 is a schematic view of a particular application of the arcuate flexible support bracket of the present invention;
FIG. 5 is a side view of FIG. 4;
fig. 6 is a three-dimensional schematic view of a specific application of the curved flexible support bracket illustrated in fig. 4 and 5.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The invention is further described with reference to the following drawings and specific examples, which are not intended to be limiting.
Aiming at the flexible shape-following adjustable rigidity support requirements of products such as supersonic cruise missiles and the like which have a near-circular but non-circular irregular shape and are sensitive to contact stress during support, the embodiment provides the arc-shaped flexible support bracket, and shape-following flexible adjustable rigidity support of the near-circular non-circular hypersonic cruise missiles can be realized. As shown in fig. 1 to 3, the curved flexible support bracket of the hypersonic cruise missile of the present embodiment includes an inflatable airbag 1, an inflation valve 2 and a rigid bracket 3;
the inflatable air bag 1 is of a hollow saccular closed structure made of rubber materials, is arc-shaped in appearance and is provided with an inflation inlet, and the inflation inlet is provided with an inflation valve 2; compressed air can be charged through the charging valve 2, and different contact support rigidity can be realized by adjusting charging pressure;
the rigid bracket 3 is provided at the bottom of the inflatable airbag 1 for fixing and supporting the inflatable airbag 1.
The wall thickness of the inflatable air bag is designed according to the weight of a supported missile, firstly, the inflation pressure is designed to ensure that the upper wall and the lower wall of the air bag are not attached after the weight of the missile is borne; then the wall thickness of the air bag is designed to ensure that the air bag can bear the inflation pressure and has enough strength allowance.
The inflatable air bag comprises an inflatable air bag 1, an inflation valve 2 and a rigid bracket 3 from top to bottom in sequence; compressed air is filled into the inflatable air bag 1 through the inflation valve 2, different contact support rigidity can be realized when the internal air pressure is different, and meanwhile, the shape can adapt to the shape of the supported missile in a certain range. The inflatable air bag of the embodiment can adapt to the shape of the supported missile, and the arc-shaped bracket does not need to be accurately processed according to the near-circle non-circular shape of the missile; the supporting rigidity can be adjusted through inflation pressure, and damage to a missile thermal protection structure caused by overlarge local contact pressure is avoided.
In a preferred embodiment, the inflatable airbag 1 and the rigid bracket 3 of the present embodiment are of an integrated structure, that is, the inflatable airbag 1 is directly embedded on the rigid bracket 3, the diameter of the rigid bracket 3 is slightly larger than the outer diameter of the supported missile, and the inner diameter of the inflated inflatable airbag 1 is slightly smaller than the outer diameter of the supported missile;
in the preferred embodiment, the inflation valve 2 is a one-way valve. When the inflatable air bag is externally connected with an inflating device, the inflatable air bag 1 can be inflated, and when the inflating device is not connected, the inflatable air bag 1 can be sealed to prevent air leakage;
in a preferred embodiment, the support bracket further comprises an inflation device, the outlet of which communicates with the inflatable bladder 1 via an inflation valve, inflates the inflatable bladder 1, and detects the air pressure within said inflatable bladder 1. The supporting contact rigidity of the supported missile is adjusted by controlling the air pressure of the inflatable air bag 1, and the damage of the surface heat-proof structure of the missile caused by overlarge local contact pressure is avoided. Different inflation pressures can change the support rigidity, so that the appearance of the inflatable air bag 1 is influenced, the contact area with the missile is changed, and different support contact pressures on the missile are realized. Therefore, the support contact pressure can be adjusted by adjusting the inflation pressure. Meanwhile, when the missile is supported for a long time, the supporting rigidity and the supporting contact pressure of the missile can be detected by detecting the pressure, so that the hardening of the felt or the rubber pad along with the time during the supporting is avoided.
The inflatable air bag is inflated through the inflation valve 2 until the rigidity meets the requirement of supporting the missile 5, the inflation device can use air sources such as a high-pressure air bottle and an air compressor, and the corresponding relation between the inflation pressure and the supporting rigidity of the air bag to the product can be measured and calibrated in advance. In the inflation process, the inflation pressure is monitored through a pressure gauge and the like, so that whether the requirement of supporting rigidity is met or not is obtained. When the inflation pressure reaches a set value, the inflation is stopped, and the missile 5 can be placed on the inflatable air bag, so that the flexible support of the product is realized.
In the preferred embodiment, the rigid bracket 3 is made of metal, and may be of a circular arc shape to secure and support the inflatable airbag 1 for ease of manufacture and cost savings. Because the inflatable air bag 1 has the adaptability to the shape of the missile, the rigid bracket 3 does not need to be consistent with the shape of the missile, and can adopt an arc-shaped structure which is easy to produce and process, and meanwhile, the diameter has no clear tolerance requirement, thereby reducing the cost.
In the preferred embodiment, the support bracket further comprises a support base 4, the rigid bracket 3 being mounted on the support base 4.
In use, the rigid carrier is mounted on a support base 4 which may be suitably configured as required, this embodiment being illustrated by a V-block. The inner diameter of the air bag can be designed according to the outer diameter of the product supporting position; the width of the air bag can be designed according to the requirement of the missile on the contact pressure during supporting and the number of supporting points. The number of support points can be designed according to the length, the gravity center position, the support width and the like of the product, and the support with two arc-shaped flexible support brackets is illustrated in figures 4, 5 and 6.
Although the invention herein has been described with reference to particular embodiments, it is to be understood that these embodiments are merely illustrative of the principles and applications of the present invention. It is therefore to be understood that numerous modifications may be made to the illustrative embodiments and that other arrangements may be devised without departing from the spirit and scope of the present invention as defined by the appended claims. It should be understood that features described in different dependent claims and herein may be combined in ways different from those described in the original claims. It is also to be understood that features described in connection with individual embodiments may be used in other described embodiments.
Claims (6)
1. An arc-shaped flexible support bracket of a hypersonic cruise missile is characterized by comprising an inflatable air bag (1), an inflation valve (2) and a rigid bracket (3);
the inflatable air bag (1) is of a hollow bag-shaped closed structure made of rubber materials, is arc-shaped in appearance and is provided with an inflation inlet, and the inflation inlet is provided with an inflation valve (2);
the rigid bracket (3) is arranged at the bottom of the inflatable air bag (1) and is used for fixing and supporting the inflatable air bag (1).
2. The curved flexible support cradle of a hypersonic cruise missile according to claim 1, characterised in that the inflatable air bag (1) is of integral construction with the rigid cradle (3), the rigid cradle (3) having a diameter greater than the external diameter of the missile to be supported and the inflatable air bag (1) having an inflated internal diameter less than the external diameter of the missile to be supported.
3. The curved flexible support bracket of a hypersonic cruise missile according to claim 2, characterised in that the inflation valve (2) is a one-way valve.
4. The arcuate flexible support bracket of a hypersonic cruise missile according to claim 3, wherein the support bracket further comprises an inflation device, the outlet of which communicates with the inflatable bladder (1) through an inflation valve, inflates the inflatable bladder (1), and can detect the air pressure within the inflatable bladder (1).
5. The curved flexible support cradle of a hypersonic cruise missile according to claim 4, characterised in that the rigid cradle (3) is a metal cradle, of curved configuration.
6. The curved, flexible support bracket of a hypersonic cruise missile according to claim 4, characterised in that it further comprises a support base (4), the rigid bracket (3) being mounted on the support base (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110127793.3A CN112945030B (en) | 2021-01-29 | 2021-01-29 | Arc-shaped flexible support bracket of hypersonic cruise missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110127793.3A CN112945030B (en) | 2021-01-29 | 2021-01-29 | Arc-shaped flexible support bracket of hypersonic cruise missile |
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| Publication Number | Publication Date |
|---|---|
| CN112945030A true CN112945030A (en) | 2021-06-11 |
| CN112945030B CN112945030B (en) | 2024-04-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110127793.3A Active CN112945030B (en) | 2021-01-29 | 2021-01-29 | Arc-shaped flexible support bracket of hypersonic cruise missile |
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| CN (1) | CN112945030B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114537616A (en) * | 2022-03-10 | 2022-05-27 | 中国舰船研究设计中心 | Suspension pier seat structure of aboveground cabin section |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2664373A1 (en) * | 1990-07-09 | 1992-01-10 | Matra Defense | Missile launcher with ejection shoe |
| US20030226771A1 (en) * | 2002-06-06 | 2003-12-11 | Corboy Grant W. | Inflatable restraint for missiles and missile canisters |
| CN201516131U (en) * | 2009-07-26 | 2010-06-30 | 万绪明 | Inflatable ophthalmic surgery head position U-shaped fixing frame |
| CN204142100U (en) * | 2013-12-09 | 2015-02-04 | 北京特种机械研究所 | A kind of can the gasbag-type self adaptation base of compatible cold and hot radiation pattern |
| CN106556290A (en) * | 2015-09-25 | 2017-04-05 | 蒙德-英格公司 | Bomb with back protector disposes suit |
| CN108844703A (en) * | 2018-04-08 | 2018-11-20 | 北京强度环境研究所 | Support device and TT&C system |
| CN110541969A (en) * | 2018-05-28 | 2019-12-06 | 宿迁市现代化工有限公司 | chemical industry equipment pipeline support frame |
| CN212227887U (en) * | 2020-04-08 | 2020-12-25 | 陕西英拓机电科技股份有限公司 | Support for simulating attack hot target in missile test |
-
2021
- 2021-01-29 CN CN202110127793.3A patent/CN112945030B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2664373A1 (en) * | 1990-07-09 | 1992-01-10 | Matra Defense | Missile launcher with ejection shoe |
| US20030226771A1 (en) * | 2002-06-06 | 2003-12-11 | Corboy Grant W. | Inflatable restraint for missiles and missile canisters |
| CN201516131U (en) * | 2009-07-26 | 2010-06-30 | 万绪明 | Inflatable ophthalmic surgery head position U-shaped fixing frame |
| CN204142100U (en) * | 2013-12-09 | 2015-02-04 | 北京特种机械研究所 | A kind of can the gasbag-type self adaptation base of compatible cold and hot radiation pattern |
| CN106556290A (en) * | 2015-09-25 | 2017-04-05 | 蒙德-英格公司 | Bomb with back protector disposes suit |
| CN108844703A (en) * | 2018-04-08 | 2018-11-20 | 北京强度环境研究所 | Support device and TT&C system |
| CN110541969A (en) * | 2018-05-28 | 2019-12-06 | 宿迁市现代化工有限公司 | chemical industry equipment pipeline support frame |
| CN212227887U (en) * | 2020-04-08 | 2020-12-25 | 陕西英拓机电科技股份有限公司 | Support for simulating attack hot target in missile test |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114537616A (en) * | 2022-03-10 | 2022-05-27 | 中国舰船研究设计中心 | Suspension pier seat structure of aboveground cabin section |
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| Publication number | Publication date |
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| CN112945030B (en) | 2024-04-05 |
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