CN111924089A - Rudder shaft heat-proof structure with separated heat-proof and force-bearing functions - Google Patents
Rudder shaft heat-proof structure with separated heat-proof and force-bearing functions Download PDFInfo
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- CN111924089A CN111924089A CN202010600411.XA CN202010600411A CN111924089A CN 111924089 A CN111924089 A CN 111924089A CN 202010600411 A CN202010600411 A CN 202010600411A CN 111924089 A CN111924089 A CN 111924089A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/32—Air braking surfaces
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Abstract
A rudder shaft heat-proof structure with separated heat-proof and force-bearing functions comprises: brush type heat seal ring and heat-proof ring; the heat-proof ring is fixedly arranged on the surface of the cabin body, a boss is arranged on the upper surface of the heat-proof ring, and a through hole is formed in the center of the heat-proof ring; the rudder shaft penetrates through a through hole in the center of the heat-proof ring to be respectively connected with the cabin body and the rudder; the rudder shaft is not contacted with the central through hole of the heat-proof ring; and a clearance between the heat-proof ring and the rudder shaft is thermally sealed by a brush type thermal sealing ring. One side of the rudder facing the surface of the cabin body is provided with a groove structure matched with the boss structure of the heat-proof ring in shape; the total height of the heat-proof ring is larger than the gap between the cabin body and the rudder; there is no contact between the rudder and the heat shield ring. The invention realizes the separation of the bearing and heat-proof functions of the rudder shaft part and solves the problem of uncertain rigidity and strength reliability of the rudder shaft caused by the severe pneumatic heating of the rudder shaft part.
Description
Technical Field
The invention relates to a rudder shaft heat-proof structure with separated heat-proof and force-bearing functions, and belongs to the technical field of rudder shaft heat-proof.
Background
The air rudder of the aircraft is an important part for controlling the flight attitude of the aircraft, and the air rudder needs to rotate ceaselessly in the flight attitude control process to control the flight attitude of the aircraft, so the rigidity and the strength of the rudder shaft are important technical indexes for stably controlling the aircraft. In the military field or the civil field, the development direction of the aircraft is faster in the future, but after the speed of the aircraft reaches a certain speed, the aerodynamic heat environment borne by each part of the aircraft is more and more serious along with the increase of the speed, the rudder shaft part is subjected to aerodynamic interference, the aerodynamic heat is more serious, the rigidity and the strength of the rudder shaft are reduced due to the fact that the rudder shaft is partially ablated or excessively high in temperature, and the problem of heat sealing of high-speed airflow at the rudder shaft part is also difficult due to the rotation of the rudder shaft.
The traditional heat-proof measure for the rudder shaft part is to adopt a composite material rudder shaft design with ablation resistance or adopt a measure of designing a composite material heat-proof cup outside a metal rudder shaft. The traditional heat-proof measures have the defects that the calculation of the thermal environment of the rudder shaft part is complex, accurate simulation is difficult, and great uncertainty exists, so that the rigidity and the strength of the rudder shaft under the actual working condition are difficult to predict even if the composite material rudder shaft or heat-proof cup measures are adopted, and the reliability of the rudder shaft is uncertain.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the rudder shaft heat-proof structure overcomes the defects of the prior art, the rudder shaft heat-proof structure with separated heat-proof and force-bearing functions is provided, the force-bearing and heat-proof functions of the rudder shaft part are separated by the design scheme that a circle of heat-proof rings protruding out of the outer surface of a cabin body is arranged around the rudder shaft, and the problem that the rigidity and the strength reliability of the rudder shaft are uncertain due to the fact that the rudder shaft part bears severe pneumatic heating is solved.
The technical scheme of the invention is as follows:
a rudder shaft heat-proof structure with separated heat-proof and force-bearing functions comprises: brush type heat seal ring and heat-proof ring;
the heat-proof ring is fixedly arranged on the surface of the cabin body;
the upper surface of the heat-proof ring is provided with a boss, and the center of the heat-proof ring is provided with a through hole;
the rudder shaft penetrates through a through hole in the center of the heat-proof ring to be respectively connected with the cabin body and the rudder; the rudder shaft is not contacted with the central through hole of the heat-proof ring; a clearance between the heat-proof ring and the rudder shaft is thermally sealed by a brush type thermal sealing ring;
one side of the rudder facing the surface of the cabin body is provided with a groove structure, and the groove structure is matched with the boss structure of the heat-proof ring in shape;
the total height of the heat-proof ring is larger than the gap between the cabin body and the rudder;
the rudder is not contacted with the heat-proof ring, and a gap between the rudder and the heat-proof ring is equal to a gap between the cabin body and the rudder;
the rudder shaft and the heat-proof ring can rotate relatively.
The unilateral clearance between the side wall of the rudder shaft and the inner wall of the central through hole of the heat-proof ring is 2 mm.
The inner wall of the central through hole of the heat-proof ring is provided with a brush type heat seal ring.
The brush type heat seal ring sequentially comprises the following components from outside to inside along the radial direction: a metal loop area, a fiber woven area and a fiber fluffed area.
The metal ring area of the brush type heat seal ring is fixedly connected with the inner wall of the central through hole of the heat-proof ring.
The material of the metal ring area is as follows: stainless steel.
The materials of the fiber weaving area are as follows: a quartz fiber.
The material of the fiber fluffing area is as follows: a quartz fiber.
Compared with the prior art, the invention has the beneficial effects that:
1) compared with the existing rudder shaft self passive thermal protection technology, the invention transfers the high heat flow of the rudder shaft to the heat-proof ring, greatly reduces the aerodynamic heat load of the rudder shaft, and reduces the heat-proof pressure of the rudder shaft;
2) compared with the traditional rudder shaft heat-proof technology, the invention separates the functions of the bearing force and the heat load of the rudder shaft and reduces the difficulty of material selection of the rudder shaft. The heat-proof ring has no bearing force, and can be made of heat-proof material with good temperature resistance. The rudder shaft basically does not bear thermal load, and materials with good mechanical property can be selected.
Drawings
FIG. 1 is a schematic view of the heat shield ring of the present invention;
FIG. 2(a) is an axial view of a flexible brush type heat seal ring of the present invention;
FIG. 2(b) is a radial schematic view of the flexible brush heat seal ring of the present invention;
FIG. 3 is a schematic view of the heat shroud mounting structure of the present invention;
fig. 4 is a cross-sectional view of the present invention.
1-rudder; 2-heat-proof ring; 3-a cabin body; 4-rudder shaft; 5-brush type sealing ring
Detailed Description
The invention is described in further detail below with reference to the figures and the detailed description.
The invention separates the heat-proof function and the force-bearing function of the rudder shaft, adds a circle of heat-proof ring around the rudder shaft for bearing the action of aerodynamic heat, and the heat-proof ring only bears the thermal load but not the force load, thereby greatly reducing the influence of the aerodynamic thermal load on the rudder shaft, and ensuring the reliability of the rudder shaft.
The design content is as follows:
1. scheme for determining heat-proof ring structure material
And aiming at the requirement of the flight working condition, carrying out calculation and analysis on the thermal environment of the thermal-protection ring area, and making a thermal-protection ring material scheme according to the size of the thermal environment and comprehensively considering the factors of cost and production cycle.
2. Heat-proof ring structure installation
The heat-proof ring mounting structure is shown in fig. 3. The heat-proof ring 2 is connected with the cabin body 3 through four screws, the heat-proof ring 2 protrudes out of the surface of the cabin body 3, the height of the heat-proof ring 2 protruding out of the cabin body 3 is larger than the gap between the cabin body 3 and the rudder 1, a groove is processed at the position where the lower end surface of the rudder 1 coincides with the heat-proof ring 2, and the gap between the bottom end surface of the groove at the lower end surface of the rudder 1 and the top end surface of the heat-proof ring 2 is generally consistent with the gap between the rudder 1 and the cabin body 3. A2 mm gap is reserved between the central hole of the heat-proof ring 2 and the rudder shaft 4, and the gap between the heat-proof ring 2 and the rudder shaft 4 is thermally sealed by adopting a scheme of a brush type thermal sealing ring 5.
3. Key technology and solution of heat-proof and force-bearing function separation structure
3.1 structural design of thermal-protective ring for bearing pneumatic heat
The clearance between the rudder and the cabin body ensures that the rudder can smoothly rotate, and in order to reduce the impact of high-temperature hot air flow on the rudder shaft, as shown in fig. 4, the heat-proof ring needs to protrude out of the surface of the cabin body, a wall is formed between the rudder shaft and the high-temperature air flow, but the heat-proof ring protrudes out of the surface of the cabin body to influence the rotation of the rudder. The annular groove with a certain depth is processed at the corresponding position of the bottom end face of the rudder, so that the contradiction between the increase of the heat-proof ring and the rotation of the rudder can be solved.
3.2 Rudder shaft rotation heat sealing technology
The thermal environment on the rudder shaft can be greatly reduced by the heat-proof ring, but because the rudder needs to rotate, 2mm of clearance is left between the rudder shaft and the central hole of the heat-proof ring, hot air flow can enter the cabin through the clearance, and temperature rise is caused to instruments and equipment in the cabin. The scheme of adopting the flexible brush type heat sealing ring on the rudder shaft can solve the heat sealing problem caused by the rotation of the rudder shaft under the condition of not influencing the rotation of the rudder.
The invention relates to a rudder shaft heat-proof structure with separated heat-proof and force-bearing functions, which comprises: brush heat seal 5 and heat shield ring 2. The heat-proof ring 2 is fixedly arranged on the surface of the cabin body 3; as shown in fig. 1, a boss is arranged on the upper surface of the heat-proof ring 2, and a through hole is formed in the center of the heat-proof ring 2; the rudder shaft 4 penetrates through a through hole in the center of the heat-proof ring 2 and is respectively connected with the cabin body 3 and the rudder 1; the rudder shaft 4 is not contacted with the central through hole of the heat-proof ring 2; the clearance between the heat-proof ring 2 and the rudder shaft 4 is thermally sealed by a brush type thermal sealing ring 5.
One side of the rudder 1, which faces the surface of the cabin body 3, is provided with a groove structure, and the groove structure is matched with the boss structure of the heat-proof ring 2 in shape; the total height of the heat-proof ring 2 is larger than the gap between the cabin body 3 and the rudder 1; the rudder 1 is not contacted with the heat-proof ring 2, and the gap between the rudder 1 and the heat-proof ring 2 is equal to the gap between the cabin body 3 and the rudder 1; the rudder shaft 4 and the heat shield ring 2 can rotate relatively.
The unilateral clearance between the side wall of the rudder shaft 4 and the inner wall of the central through hole of the heat-proof ring 2 is 2 mm.
The inner wall of the central through hole of the heat-proof ring 2 is provided with a brush type heat seal ring 5.
As shown in fig. 2(a) and 2(b), the brush type heat seal ring 5 comprises, in order from outside to inside in the radial direction: a metal loop area, a fiber woven area and a fiber fluffed area. The metal ring area of the brush type heat seal ring 5 is fixedly connected with the inner wall of the central through hole of the heat-proof ring 2. The material of the metal ring area is as follows: stainless steel. The materials of the fiber weaving area are as follows: a quartz fiber. The material of the fiber fluffing area is as follows: a quartz fiber.
Those skilled in the art will appreciate that the details of the invention not described in detail in the specification are within the skill of those skilled in the art.
Claims (8)
1. The utility model provides a rudder axle heat-proof structure of heat protection, load-carrying function separation which characterized in that includes: a brush type heat seal ring (5) and a heat-proof ring (2);
the heat-proof ring (2) is fixedly arranged on the surface of the cabin body (3);
the upper surface of the heat-proof ring (2) is provided with a boss, and the center of the heat-proof ring (2) is provided with a through hole;
the rudder shaft (4) passes through a through hole in the center of the heat-proof ring (2) and is respectively connected with the cabin body (3) and the rudder (1); the rudder shaft (4) is not contacted with the central through hole of the heat-proof ring (2); a clearance between the heat-proof ring (2) and the rudder shaft (4) is thermally sealed by a brush type thermal sealing ring (5);
one side of the rudder (1) facing the surface of the cabin body (3) is provided with a groove structure, and the groove structure is matched with the boss structure of the heat-proof ring (2) in shape;
the total height of the heat-proof ring (2) is larger than the gap between the cabin body (3) and the rudder (1);
the rudder (1) is not in contact with the heat-proof ring (2), and the gap between the rudder (1) and the heat-proof ring (2) is equal to the gap between the cabin body (3) and the rudder (1);
the rudder shaft (4) and the heat-proof ring (2) can rotate relatively.
2. The rudder shaft heat-proof structure with the separated heat-proof and force-bearing functions as claimed in claim 1, wherein the unilateral gap between the side wall of the rudder shaft (4) and the inner wall of the central through hole of the heat-proof ring (2) is 2 mm.
3. The rudder shaft heat-proof structure with separated heat-proof and force-bearing functions as claimed in claim 1, wherein the inner wall of the central through hole of the heat-proof ring (2) is provided with a brush type heat sealing ring (5).
4. The rudder shaft heat-proof structure with separated heat-proof and force-bearing functions as claimed in any one of claims 1 to 3, wherein the brush type heat seal ring (5) comprises, from outside to inside in the radial direction: a metal loop area, a fiber woven area and a fiber fluffed area.
5. The rudder shaft heat-proof structure with separated heat-proof and force-bearing functions as claimed in claim 4, wherein the metal ring area of the brush type heat seal ring (5) is fixedly connected with the inner wall of the central through hole of the heat-proof ring (2).
6. The rudder shaft heat-proof structure with separated heat-proof and force-bearing functions as claimed in claim 5, wherein the material of the metal ring area is: stainless steel.
7. The rudder shaft heat-proof structure with separated heat-proof and force-bearing functions as claimed in claim 5, wherein the material of the fiber weaving area is: a quartz fiber.
8. The rudder shaft heat-proof structure with separated heat-proof and force-bearing functions as claimed in claim 5, wherein the fiber fluff area is made of: a quartz fiber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010600411.XA CN111924089B (en) | 2020-06-28 | 2020-06-28 | Rudder shaft heat-proof structure with separated heat-proof and force-bearing functions |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010600411.XA CN111924089B (en) | 2020-06-28 | 2020-06-28 | Rudder shaft heat-proof structure with separated heat-proof and force-bearing functions |
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| Publication Number | Publication Date |
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| CN111924089A true CN111924089A (en) | 2020-11-13 |
| CN111924089B CN111924089B (en) | 2021-09-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010600411.XA Active CN111924089B (en) | 2020-06-28 | 2020-06-28 | Rudder shaft heat-proof structure with separated heat-proof and force-bearing functions |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113665850A (en) * | 2021-08-02 | 2021-11-19 | 湖北航天技术研究院总体设计所 | Phase-change type heat-proof structure of rudder shaft and aircraft |
| CN114275145A (en) * | 2021-12-30 | 2022-04-05 | 湖北三江航天红阳机电有限公司 | Hot air flow blocking structure |
Citations (4)
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| EP3069841A1 (en) * | 2015-03-18 | 2016-09-21 | BAE Systems PLC | Thermally insulating cover |
| CN106809375A (en) * | 2016-12-19 | 2017-06-09 | 中国航天空气动力技术研究院 | A kind of hypersonic aircraft leading-type rudderpost thermal protection struc ture |
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2020
- 2020-06-28 CN CN202010600411.XA patent/CN111924089B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3069841A1 (en) * | 2015-03-18 | 2016-09-21 | BAE Systems PLC | Thermally insulating cover |
| CN106809375A (en) * | 2016-12-19 | 2017-06-09 | 中国航天空气动力技术研究院 | A kind of hypersonic aircraft leading-type rudderpost thermal protection struc ture |
| CN108007280A (en) * | 2017-12-28 | 2018-05-08 | 北京威标至远科技发展有限公司 | A kind of steering engine thermal protection struc ture |
| CN110901885A (en) * | 2019-12-23 | 2020-03-24 | 湖北航天技术研究院总体设计所 | Thermal protection system of aircraft |
Non-Patent Citations (1)
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113665850A (en) * | 2021-08-02 | 2021-11-19 | 湖北航天技术研究院总体设计所 | Phase-change type heat-proof structure of rudder shaft and aircraft |
| CN113665850B (en) * | 2021-08-02 | 2023-06-13 | 湖北航天技术研究院总体设计所 | Phase-change heat-proof structure of rudder shaft and aircraft |
| CN114275145A (en) * | 2021-12-30 | 2022-04-05 | 湖北三江航天红阳机电有限公司 | Hot air flow blocking structure |
| CN114275145B (en) * | 2021-12-30 | 2023-10-20 | 湖北三江航天红阳机电有限公司 | Hot air flow blocking structure |
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| CN111924089B (en) | 2021-09-07 |
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