Air rudder for aerospace craft, positioning tool and positioning punching method

Abstract

The invention discloses an air rudder for an aerospace craft. The air rudder comprises a rudder body and a connecting shaft part arranged on one side of the rudder body. The rudder body and the connecting shaft part are integrally formed and are both made of metal materials; the rudder body is a right-angled trapezoidal plate; the connecting shaft part comprises a cylindrical main body part and a convex ring part formed by radially protruding at least one end part of the cylindrical main body part; a through shaft hole is formed in the connecting shaft part; a positioning block is convexly arranged on the surface of the convex ring part; the two side faces of the rudder body and the peripheral face of the cylindrical main body part are all covered with ceramic matrix composite material layers. The thickness of the ceramic-based composite material layer is 1-10cm, and the length of the convex ring is 1 / 10-1 / 2 of the length of the cylindrical main body part. The invention further provides a positioning tool and a positioning and punching method for the air rudder for the aerospace craft. According to the air rudder for the aerospace craft, the requirement of the aerospace craft for force loads under the flight working condition is met, meanwhile, the excellent heat insulation performance of the ceramic matrix composite provides good protection for the metal body of the air rudder, and the high temperature resistance of the air rudder is greatly improved; and faults and failures of the air rudder caused by overheating in the long-time flight process of the aircraft are avoided.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to an air rudder, a positioning tool and a positioning punching method for a spacecraft. Background Art

[0002] The air rudder is an important component in a spacecraft. It is the executive component of the aircraft's attitude control and is distributed outside the aircraft's servo cabin to provide it with maneuverable flight control torque.

[0003] As the speed of the aircraft increases, the air rudder is required to withstand greater force loads and greater thermal loads under flight conditions. Existing air rudders cannot meet the load-bearing and heat-protection requirements. When the aircraft flies for a long time, the air rudder overheats and deforms greatly, causing the mechanical connection between the conventional air rudder shaft and the rudder surface to fail, resulting in air rudder failure. Summary of the invention

[0004] The purpose of the first aspect of the present disclosure is to provide an air rudder for a spacecraft, which is made of metal and most of its surface is covered with a ceramic-based composite material. This structure not only ensures the force load requirements of the spacecraft under flight conditions, but also the excellent thermal insulation performance of the ceramic-based composite material provides good protection for the metal body of the air rudder, greatly improves the high temperature resistance of the air rudder, and avoids malfunction and failure of the air rudder due to overheating during long-term flight of the aircraft.

[0005] The second aspect of the present disclosure aims to provide a positioning tool for the air rudder used in the above-mentioned spacecraft, which can accurately position the air rudder and improve the accuracy of subsequent hole opening processing on the surface of the air rudder.

[0006] In a first aspect, the present disclosure provides an air rudder for a spacecraft, the air rudder comprising a rudder body and a coupling portion provided at one side of the rudder body; the rudder body and the coupling portion are integrally formed and are both made of metal material; the rudder body is a right-angled trapezoidal plate; the coupling portion comprises a cylindrical main body portion and a convex ring portion formed by radially protruding at least one end of the cylindrical main body portion; a through shaft hole is provided inside the coupling portion, and a positioning block is convexly provided on the surface of the convex ring portion;

[0007] Wherein, both side surfaces of the rudder body are covered with a ceramic-based composite material layer, and the outer peripheral surface of the cylindrical main body is covered with a ceramic-based composite material layer; the thickness of the ceramic-based composite material layer is 1 to 10 cm, and the length of the convex ring portion is 1 / 10 to 1 / 2 of the length of the cylindrical main body.

[0008] Furthermore, the convex ring portion is located at one end of the columnar main body portion; and the surface of the connecting shaft portion covered with the ceramic matrix composite material layer is the first area, and the surface not covered with the ceramic matrix composite material layer is the second area.

[0009] In this embodiment, the second area not covered by the ceramic-based composite material is located at one end of the shaft connection portion, so that the positioning tool can use this area for precise positioning.

[0010] In a second aspect, the present disclosure provides a positioning tool for an air rudder for a spacecraft, the positioning tool being used to position the air rudder; the positioning tool comprising a main positioning seat, a secondary positioning seat, a first limiting end cover and a second limiting end cover;

[0011] The main positioning seat has a first end and a second end opposite to each other; a through first concave hole is formed in the main positioning seat, and the first concave hole has an inner wall surface that is gap-matched with the first area of ​​the connecting shaft portion;

[0012] The auxiliary positioning seat is locked to the first end of the main positioning seat, wherein a second concave hole is provided; the second concave hole has an inner wall surface that transitionally matches with the second area of ​​the connecting shaft portion;

[0013] The first limiting end cover is locked on the auxiliary positioning seat, and the second limiting end cover is locked on the second end of the main positioning seat; the first limiting end cover and the second limiting end cover respectively have a first boss and a second boss that are transitionally matched with the shaft hole of the connecting shaft;

[0014] Wherein, the main positioning seat is also provided with a processing hole penetrating through the hole wall of the first concave hole, which is used to open a hole in the first area of ​​the connecting shaft part.

[0015] Furthermore, when the positioning tool is used:

[0016] The main positioning seat is configured to be fitted into the first area of ​​the connecting part through the first recessed hole; the secondary positioning seat is configured to be fitted into the second area of ​​the connecting part through the second recessed hole, and is locked with the first end of the main positioning seat to achieve radial positioning of the first end of the main positioning seat; the first limiting end cover is configured to be inserted into the axial hole of the connecting part from the side close to the first end of the main positioning seat through the first boss, and is locked with the secondary positioning seat to achieve axial positioning of the first end of the main positioning seat; the second limiting end cover is configured to be inserted into the axial hole of the connecting part from the side close to the second end of the main positioning seat through the second boss, and is locked with the second end of the main positioning seat to achieve axial positioning and radial positioning of the second end of the main positioning seat.

[0017] In this embodiment, the first end of the main positioning seat is axially and radially positioned by the transition fit between the secondary positioning seat, the first limiting end cover and the second area of ​​the connecting shaft, and the second end of the main positioning seat is axially and radially positioned by the transition fit between the second limiting end cover and the inner wall of the shaft hole of the connecting shaft, thereby achieving precise positioning of the main positioning seat on the first area of ​​the connecting shaft, which is convenient for improving the accuracy of subsequent drilling in the first area of ​​the connecting shaft.

[0018] Furthermore, a plurality of first positioning holes are provided on the end faces of the first end and the second end of the main positioning seat, and a plurality of first positioning columns and a second positioning columns corresponding to the first positioning holes are respectively provided on the surfaces of the auxiliary positioning seat and the second limiting end cover relative to the main positioning seat; when the auxiliary positioning seat and the second limiting end cover are installed on the connecting shaft, the first positioning columns and the second positioning columns are respectively embedded in the corresponding first positioning holes on the main positioning seat.

[0019] In this embodiment, by providing the first positioning hole, the first positioning column and the second positioning column, preliminary positioning of the two ends of the main positioning seat in the radial direction can be achieved.

[0020] Furthermore, a plurality of second positioning holes are provided on the end surfaces of the first end and the second end of the main positioning seat; a plurality of first through holes and second through holes corresponding to the second positioning holes are respectively provided on the secondary positioning seat and the second limiting end cover; the positioning tooling also includes a plurality of first locking pieces and second locking pieces, the first locking piece being used to lock the secondary positioning seat to the main positioning seat through the first through hole and the second positioning hole; the second locking piece being used to lock the second limiting end cover to the main positioning seat through the second through hole and the second positioning hole.

[0021] In this embodiment, the auxiliary positioning seat and the second limiting end cover are locked on the main positioning seat by the first locking piece and the second locking piece, thereby achieving precise positioning of both ends of the main positioning seat in the radial direction.

[0022] Furthermore, the auxiliary positioning seat is also provided with a plurality of third positioning holes, and the surface of the first limiting end cover relative to the auxiliary positioning seat has a plurality of third positioning columns corresponding to the third positioning holes; when the first limiting end cover is installed on the connecting shaft, the third positioning columns are embedded in the corresponding third positioning holes on the auxiliary positioning seat.

[0023] In this embodiment, the first position-limiting end cover can be preliminarily positioned by providing the third positioning hole and the third positioning column.

[0024] Furthermore, the auxiliary positioning seat is provided with a plurality of fourth positioning holes, and the first limiting end cover is provided with a plurality of third through holes corresponding to the fourth positioning holes; the positioning tooling also includes a plurality of third locking pieces, and the third locking pieces are used to lock the first limiting end cover to the auxiliary positioning seat through the third through holes and the fourth positioning holes.

[0025] In this embodiment, the first limiting end cover is locked on the auxiliary positioning seat by the third locking piece, thereby realizing accurate axial positioning of the main positioning seat.

[0026] Furthermore, the first limiting end cover and the second limiting end cover are respectively provided with a fourth through hole and a fifth through hole penetrating the boss; the positioning tool also includes a fourth locking piece, and the fourth locking piece is used to lock the first limiting end cover and the second limiting end cover to the connecting shaft through the fourth through hole, the fifth through hole and the shaft hole.

[0027] In this embodiment, the first limiting end cover and the second limiting end cover are locked to the shaft connecting portion by a fourth locking piece, thereby further improving the stability of the positioning tool installed on the shaft connecting portion.

[0028] In a third aspect, the present disclosure provides a method for positioning and punching holes for an air rudder for a spacecraft, using the aforementioned air rudder positioning tool for a spacecraft, and comprising the following steps:

[0029] S1. The main positioning seat is fitted into the first area of ​​the connecting shaft portion through the first recessed hole;

[0030] S2. The auxiliary positioning seat is fitted into the second region of the connecting shaft portion through the second recessed hole, and the first positioning column on the auxiliary positioning seat is fitted into the first positioning hole on the main positioning seat; then the main positioning seat and the auxiliary positioning seat are locked by the first locking member;

[0031] S3. Insert the first limit end cover into the shaft hole of the connecting shaft portion from the side close to the auxiliary positioning seat through the first boss, and make the third positioning column on the first limit end cover fit into the third positioning hole on the auxiliary positioning seat; then lock the first limit end cover and the auxiliary positioning seat by the third locking piece;

[0032] S4. Insert the second limiting end cover into the shaft hole of the connecting shaft portion from the side close to the main positioning seat through the second boss, and make the second positioning column on the second limiting end cover fit into the first positioning hole on the main positioning seat; then lock the main positioning seat and the second limiting end cover seat by the second locking piece;

[0033] S5. The first limiting end cover and the second limiting end cover are locked on the shaft coupling portion by a fourth locking member;

[0034] S6. Use a punching device to drill a hole in the first area of ​​the coupling portion through the processed hole on the main positioning seat.

[0035] The present disclosure can at least achieve the following technical effects:

[0036] 1. The air rudder for a spacecraft provided by the present invention is made of metal, and most of its surface is covered with ceramic-based composite materials. This structure not only ensures the force load requirements of the spacecraft under flight conditions, but also the excellent thermal insulation performance of the ceramic-based composite materials provides good protection for the metal body of the air rudder, greatly improves the high temperature resistance of the air rudder, and avoids malfunction and failure of the air rudder due to overheating during long-term flight of the aircraft.

[0037] 2. Since the surface of the ceramic-based composite material is relatively rough and the size is irregular, when the existing positioning tooling is used to fix and punch the air rudder made of metal and ceramic-based composite materials, the ceramic-based composite material cannot be accurately positioned, resulting in poor accuracy of punching on the surface of the coupling. If the machine tool tooling is used for positioning, not only is the investment in equipment large and the cost high, but there is also the problem of low punching efficiency. The positioning tooling for the air rudder for aerospace vehicles provided by the present disclosure radially positions the first end of the main positioning seat through the transition fit between the secondary positioning seat and the second area of ​​the coupling, axially positions the first end of the main positioning seat through the first limiting end cover, and axially and radially positions the second end of the main positioning seat through the transition fit between the second boss in the second limiting end cover and the shaft hole, thereby achieving precise positioning of the main positioning seat on the coupling, and improving the accuracy and efficiency of subsequent hole opening processing in the ceramic-based composite material covering area of ​​the coupling. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 It is a schematic diagram of the structure of the air rudder for the aerospace vehicle disclosed in the present invention;

[0039] Figure 2 It is a schematic structural diagram of an air rudder for a spacecraft disclosed in the present invention (without the ceramic-based composite material);

[0040] Figure 3 It is an exploded schematic diagram of the positioning tool in the present disclosure;

[0041] Figure 4 An exploded schematic diagram of another perspective of the positioning tooling disclosed in the present invention;

[0042] Figure 5 It is a schematic diagram of the positioning tooling after assembly in the present disclosure;

[0043] Figure 6 It is a structural schematic diagram of the positioning tooling disclosed in the present invention installed on the air rudder;

[0044] Explanation of reference numerals in the figure: 100, air rudder; 110, rudder body; 120, connecting shaft; 121, cylindrical main body; 122, convex ring; 1221, positioning block; 123, shaft hole; 124, first area; 125, second area; 126, process hole; 130, ceramic matrix composite material layer; 200, positioning tool; 210, main positioning seat; 211, first concave hole; 212, first positioning hole; 213, second positioning hole; 214, processing hole; 220, auxiliary positioning seat; 221, second concave hole; 22 2. First positioning column; 223. First through hole; 224. Third positioning hole; 225. Fourth positioning hole; 230. First limiting end cover; 231. First boss; 232. Third positioning column; 233. Third through hole; 234. Fourth through hole; 240. Second limiting end cover; 241. Second boss; 242. Second positioning column; 243. Second through hole; 244. Fifth through hole; 251. First locking piece; 252. Second locking piece; 253. Third locking piece; 254. Fourth locking piece. DETAILED DESCRIPTION

[0045] The technical solution of the present disclosure will be described clearly and completely below in conjunction with the accompanying drawings and specific implementation methods. Obviously, the described embodiments are only part of the embodiments of the present disclosure, rather than all of the embodiments. Based on the embodiments in the present disclosure, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present disclosure.

[0046] As attached Figure 1-2 As shown, the present disclosure provides an air rudder 100 for a spacecraft, which includes a rudder body 110 and a connecting shaft portion 120 disposed on one side of the rudder body 110. The rudder body 110 is a right-angled trapezoidal plate, and both sides of the rudder body 110 are covered with a ceramic matrix composite material layer 130.

[0047] The coupling part 120 includes a cylindrical main body part 121 and a convex ring part 122 formed by radially extending at least one end of the cylindrical main body part 121, wherein a through shaft hole 123 is provided inside the coupling part 129, and a positioning block 1221 is convexly provided on the surface of the convex ring part 122. The purpose of the positioning block 1221 is to facilitate the positioning of the positioning tooling so as to perform subsequent punching processing. In some preferred embodiments, the positioning block 1221 is a right-angle positioning block, that is, the two adjacent surfaces of the positioning block 1221 are at right angles.

[0048] In the present disclosure, the number of the coupling part 120 can be one or more, preferably two. The convex ring part 122 is preferably located at one end of the cylindrical main body part 121. The coupling part 120 and the rudder body 110 are preferably integrally formed; similarly, the positioning block 1221 is preferably integrally formed with the coupling part 120, which is convenient for processing and forming.

[0049] In the present disclosure, the rudder body 110 and the connecting shaft portion 120 are both made of metal, and the two side surfaces of the rudder body 110 and the surface of the cylindrical body portion 121 are covered with a ceramic matrix composite material layer 130. Preferably, after the surface of the cylindrical body portion 121 is covered with the ceramic matrix composite material layer 130, its surface is flush with the convex ring portion 122.

[0050] Metal materials have good processing properties and are easy to process into the rudder body 110 and the connecting shaft 120; at the same time, metal materials have good strength and toughness, ensuring the force load requirements of the aerospace vehicle under flight conditions. Ceramic-based composite materials have the advantages of light weight, good heat resistance and corrosion resistance. Covering the surface of the rudder body 110 and the cylindrical main body 121 with ceramic-based composite materials can not only play a lightweight role, but also play a good protective role for metal parts; due to the excellent thermal insulation performance of ceramic-based composite materials, it can avoid the problems of overheating and thermal failure of metal parts caused by high temperature generated by friction when the spacecraft is flying at high speed for a long time.

[0051] In the present disclosure, the thickness of the ceramic-based composite material layer is preferably 1 to 10 cm, for example, 1 cm, 2 cm, 3 cm, 4 cm, 5 cm, 6 cm, 8 cm, 10 cm, etc.; sufficient thickness can ensure good thermal insulation effect.

[0052] In the present disclosure, the convex ring portion 122 in the coupling portion 120 is not covered by the ceramic-based composite material. Since the air rudder used in the aerospace vehicle in the present disclosure needs to be processed by drilling in the area covered by the ceramic-based composite material during the processing. Since the surface of the ceramic-based composite material is not smooth, but rough, the size is irregular, and the positioning accuracy is poor, it is difficult to accurately clamp and position the coupling portion 120, which makes it difficult to perform subsequent drilling processing on the coupling portion 120. Therefore, in the present disclosure, by making a partial area of ​​the coupling portion 129 not covered by the ceramic-based composite material and exposing the metal surface, the positioning device can accurately clamp and position through this area, which is beneficial to improve the accuracy of the drilling processing.

[0053] In the present disclosure, the length of the convex ring portion 122 is preferably 1 / 10 to 1 / 2 of the length of the cylindrical body portion 121, for example, it can be 1 / 10, 1 / 8, 1 / 6, 1 / 5, 1 / 3, 1 / 2, etc. of the length of the cylindrical body portion 121. If the length of the convex ring portion 122 is too short, it is difficult for the positioning tool to accurately and stably clamp and position the coupling portion 129 through this area. It should be pointed out that the length here refers to the projected length of the convex ring portion 122 and the cylindrical body portion 121 along the axis of the shaft hole 123.

[0054] For the convenience of description, the area on the shaft coupling 120 covered by the ceramic matrix composite material is defined as the first area 124 ( Figure 1 The dark area in FIG. 1 is the dark area in FIG. 1 , and the area not covered by the ceramic matrix composite material is the second area 125 ( Figure 1 ).

[0055] As mentioned above, during the processing of the air rudder 100, it is necessary to punch holes (i.e. Figure 1-2 Since the surface of the first region 124 is covered with a ceramic matrix composite material, and the surface of the ceramic matrix composite material is relatively rough, irregular in size, and poor in positioning accuracy, the precision of drilling holes on the surface of the first region 124 of the coupling 120 is poor. If the positioning is performed using a machine tool, not only is the efficiency low, but the processing accuracy is also low.

[0056] In view of this technical problem, the present disclosure provides a positioning tool 200 for an air rudder for a spacecraft, which is used to position the air rudder 100 mentioned above. Figure 5-6 The positioning fixture 200 includes a first limiting end cover 230 , a secondary positioning seat 220 , a main positioning seat 210 and a second limiting end cover 240 .

[0057] See also Figure 3-4 The main positioning seat 210 is a square block as a whole, and has a first end and a second end opposite to each other. A through first concave hole 211 is provided in the main positioning seat 210, and the first concave hole 211 has a shape that matches the shaft connecting portion 120, so that it can be mounted on the shaft connecting portion 120. In addition, the length of the main positioning seat 210 is consistent with the length of the first area 124 of the shaft connecting portion 120. The "length" here refers to the projected length along the axis of the shaft hole 123. When the main positioning seat 210 is mounted on the first area 124 of the shaft connecting portion 120, the inner wall surface of the first concave hole 211 is gap-matched with the first area 124 of the shaft connecting portion 120. A processing hole 214 that passes through the hole wall of the first concave hole 211 is also provided on the main positioning seat 210. When the main positioning seat 210 is installed on the shaft connecting portion 120, a hole can be opened in the first area 124 of the shaft connecting portion 120 through the processing hole 214. In this embodiment, there are two processed holes 214 , which are respectively disposed on the hole walls on both sides of the first concave hole 211 .

[0058] See also Figure 3-4The auxiliary positioning seat 220 is locked to the first end of the main positioning seat 210, and a through second concave hole 221 is provided therein. Similarly, the second concave hole 221 has a shape that matches the connecting shaft portion 120, so that it can be sleeved on the connecting shaft portion 120. In addition, the length of the auxiliary positioning seat 220 is consistent with the length of the second area 125 of the connecting shaft portion 120. When the auxiliary positioning seat 220 is sleeved on the second area 125 of the connecting shaft portion 120, the inner wall surface of the second concave hole 221 transitionally matches with the second area 125 of the connecting shaft portion 120.

[0059] See also Figure 3-4 The first position-limiting end cover 230 is locked on the auxiliary positioning seat 220, and the first position-limiting end cover 230 has a first convex column 231 on a side facing the auxiliary positioning seat 220. The first convex column 231 and the first position-limiting end cover 230 are preferably integrally formed. When the first position-limiting end cover 230 is locked on the auxiliary positioning seat 220, the first convex column 231 is inserted into the shaft hole 123 of the connecting shaft portion 120, and transitionally matches with the shaft hole 123 of the connecting shaft portion 120.

[0060] See also Figure 2-3 The second position-limiting end cover 240 is locked to the second end of the main positioning seat 210, and the second position-limiting end cover 240 has a second convex column 241 on a side facing the main positioning seat 210. The second convex column 241 and the second position-limiting end cover 240 are preferably integrally formed. When the second position-limiting end cover 240 is locked on the main positioning seat 210, the second convex column 241 is inserted into the shaft hole 123 of the connecting shaft portion 120, and transitionally matches with the shaft hole 123 of the connecting shaft portion 120.

[0061] In some embodiments of the present disclosure, a plurality of first positioning holes 212 are provided on the end surfaces of the first end and the second end of the main positioning seat 210; and a plurality of first positioning columns 222 and second positioning columns 242 corresponding to the first positioning holes 212 are provided on the surfaces of the auxiliary positioning seat 220 and the second limiting end cover 240 relative to the main positioning seat 210. Therefore, when the auxiliary positioning seat 220 and the second limiting end cover 240 are installed to the corresponding positions of the shaft connecting portion 120, the first positioning columns 222 and the second positioning columns 242 are respectively embedded in the corresponding first positioning holes 212 on the main positioning seat 210, thereby realizing the preliminary positioning of the two ends of the main positioning seat 210 in the radial direction.

[0062] In this embodiment, the number of the first positioning holes 212 on both end surfaces of the main positioning seat 210 is two, and the two first positioning holes 212 are preferably arranged on the hole walls on both sides of the first concave hole 211, so as to improve the stability of the initial positioning of the main positioning seat 210. Of course, in other embodiments, the number of the first positioning holes 212 can be more than two, and the present disclosure is not limited to this.

[0063] In some embodiments of the present disclosure, a plurality of second positioning holes 213 are further provided on the end surfaces of the first end and the second end of the main positioning seat 210; a plurality of first through holes 223 and second through holes 243 corresponding to the second positioning holes 213 are respectively provided on the auxiliary positioning seat 220 and the second limiting end cover 240. In addition, the positioning fixture 200 further includes a plurality of first locking members 251 and second locking members 252. The first locking members 251 can lock the auxiliary positioning seat 220 on the main positioning seat 210 through the first through holes 223 and the second positioning holes 213, and the second locking members 252 can lock the second limiting end cover 240 on the main positioning seat 210 through the second through holes 243 and the second positioning holes 213, thereby realizing the positioning of the two ends of the main positioning seat 210 in the radial direction.

[0064] In this embodiment, the number of the second positioning holes 213 on the end surface of the first end of the main positioning seat 210 is four, and preferably distributed at the four corners of the end surface, so that the stability of the locking between the auxiliary positioning seat 220 and the main positioning seat 210 can be improved. The first locking member 251 and the second locking member 252 can be various types of fixing members that can play a locking function, preferably screws. The number of the second positioning holes 213 on the end surface of the second end of the main positioning seat 210 is two, and preferably distributed at the two lower bottom corners of the end surface. Of course, in other embodiments, the number of the second positioning holes 213 on the end surface of the second end of the main positioning seat 210 can be more than two, and the present disclosure does not limit this.

[0065] In some embodiments of the present disclosure, a plurality of third positioning holes 224 are further provided on the auxiliary positioning seat 220, and a plurality of third positioning posts 232 corresponding to the third positioning holes 224 are provided on the surface of the first limiting end cover 230 relative to the auxiliary positioning seat 220. Therefore, when the first limiting end cover 230 is installed on the shaft connecting portion 120, the third positioning posts 232 are engaged in the corresponding third positioning holes 224 on the auxiliary positioning seat 220, thereby playing a role in preliminarily positioning the first limiting end cover 230.

[0066] In this embodiment, the number of the third positioning holes 224 on the auxiliary positioning seat 220 is two, and the two third positioning holes 224 are preferably arranged on the hole walls on both sides of the second recessed hole 221. Of course, in other embodiments, the number of the third positioning holes 224 can be more than two, and the present disclosure does not limit this.

[0067] In some embodiments of the present disclosure, a plurality of fourth positioning holes 225 are further provided on the secondary positioning seat 220, and a plurality of third through holes 233 corresponding to the fourth positioning holes 225 are provided on the first limiting end cover 230. In addition, the positioning fixture 200 further includes a plurality of third locking members 253, which lock the first limiting end cover 230 to the secondary positioning seat 220 through the third through holes 233 and the fourth positioning holes 225, thereby realizing the axial positioning of the main positioning seat 210. The third locking member 253 can be any type of fixing member that can play a locking function, preferably a screw.

[0068] In this embodiment, the number of the fourth positioning holes 225 on the auxiliary positioning seat 220 is two. Of course, in other embodiments, the number of the fourth positioning holes 225 can be more than two, and the present disclosure does not limit this.

[0069] In some embodiments of the present disclosure, the first limiting end cover 230 is further provided with a fourth through hole 234 penetrating the first boss 231, and the second limiting end cover 240 is further provided with a fifth through hole 244 penetrating the second boss 241; and the positioning tool 200 also includes a fourth locking member 254, which locks the first limiting end cover 230 and the second limiting end cover 240 on the connecting shaft 120 via the fourth through hole 234, the fifth through hole 244 and the shaft hole 123, thereby further improving the stability of the positioning tool 200 installed on the connecting shaft 120.

[0070] In addition, the present disclosure also provides a method for positioning and punching holes for an air rudder for a spacecraft, which uses the above-mentioned air rudder positioning tool 200 for a spacecraft and includes the following steps:

[0071] S1. The main positioning seat 210 is fitted into the first region 124 of the connecting shaft portion 120 through the first recessed hole 211;

[0072] S2. The auxiliary positioning seat 220 is fitted into the second region 125 of the connecting shaft portion 120 through the second recessed hole 221, and the first positioning column 222 on the auxiliary positioning seat 220 is engaged with the first positioning hole 212 on the main positioning seat 210; and then the main positioning seat 210 and the auxiliary positioning seat 220 are locked by the first locking member 251;

[0073] S3. The first limiting end cover 230 is inserted into the shaft hole 123 of the connecting shaft portion 120 through the first boss 231 from the side close to the auxiliary positioning seat 220, and the third positioning column 232 on the first limiting end cover 230 is embedded in the third positioning hole 224 on the auxiliary positioning seat 220; then the first limiting end cover 230 is locked with the auxiliary positioning seat 220 by the third locking member 253;

[0074] S4. The second limiting end cover 240 is inserted into the shaft hole 123 of the connecting shaft portion 120 through the second boss 241 from the side close to the main positioning seat 210, and the second positioning column 242 on the second limiting end cover 240 is embedded in the first positioning hole 212 on the main positioning seat 210; then the main positioning seat 210 and the second limiting end cover 240 are locked by the second locking member 252;

[0075] S5. The first limiting end cover 230 and the second limiting end cover 240 are locked on the connecting shaft portion 120 by the fourth locking member 254;

[0076] S6. Use a punching device to drill a hole in the first area 124 of the coupling portion 120 through the processed hole 214 on the main positioning seat 210 .

[0077] In the above step S1, since the surface of the ceramic-based composite material in the first region 124 is rough and uneven, it is necessary to ensure that there is a certain gap margin between the main positioning seat 210 and the shaft connecting portion 120 when installing the main positioning seat 210. The gap margin can be determined according to the tolerance of the surface of the ceramic-based composite material, for example, it can be 0.1 to 1 mm. In the present disclosure, the inner wall surface of the first concave hole 211 of the main positioning seat 210 is gap-matched with the first region 124 of the shaft connecting portion 120, so that the main positioning seat 210 can be smoothly installed on the first region 124 of the shaft connecting portion 120.

[0078] In the above step S2, since the second area 125 of the coupling part 120 is a metal surface with a smooth surface and high dimensional accuracy, the secondary positioning seat 220 can be radially positioned through the second area 125; and the presence of the positioning block 1221 on the coupling part 120 limits the rotation of the secondary positioning seat 220. In the present disclosure, the secondary positioning seat 220 is sleeved in the second area 125 of the coupling part 120 through the second concave hole 221, and the inner wall surface of the second concave hole 221 is transitionally matched with the second area 125 of the coupling part 120, thereby realizing the radial positioning of the secondary positioning seat 220 on the coupling part 120. Then, the main positioning seat 210 and the secondary positioning seat 220 are locked by the first locking piece 251, so as to realize the radial positioning of the first end of the main positioning seat 210.

[0079] In the above step S3, the auxiliary positioning seat 220 can be limited in the axial direction by the first limiting end cover 230. Specifically, the first protrusion 231 on the first limiting end cover 230 is inserted into the shaft hole 123 of the connecting shaft 120, and then the first limiting end cover 230 and the auxiliary positioning seat 220 are locked by the third locking piece 253, thereby limiting the axial movement of the auxiliary positioning seat 220, that is, the axial positioning of the first end of the main positioning seat 210 is achieved.

[0080] In the above step S4, since the shaft hole 123 of the shaft coupling 120 is a metal surface with high dimensional accuracy, the second end of the main positioning seat 210 can be radially positioned through the shaft hole 123 of the shaft coupling 120. In the present disclosure, the second boss 241 on the second limit end cover 240 is transitionally matched with the shaft hole 123 of the shaft coupling 120, so that the second boss 241 on the second limit end cover 240 is inserted into the shaft hole 123 of the shaft coupling 120, and then the second limit end cover 240 is locked with the main positioning seat 210 through the second locking piece 252, so that the axial and radial movements of the main positioning seat 210 can be limited at the same time, that is, the second limit end cover 240 realizes the axial positioning and radial positioning of the second end of the main positioning seat 210 at the same time.

[0081] In the above step S5 , the first limiting end cover 230 and the second limiting end cover 240 are locked on the shaft connecting portion 120 by the fourth locking member 254 , so as to further improve the stability of the positioning tool 200 installed on the shaft connecting portion 120 .

[0082] Through the above steps, the main positioning seat 210 installed on the first area 124 of the connecting shaft 120 is accurately positioned in the axial and radial directions, so that the first area 124 of the connecting shaft 120 can be punched later through the processing hole 214 on the main positioning seat 210. When the positioning tool 200 of the present disclosure is used, a handheld punching device can be used for punching, which not only reduces the equipment investment, but also has high efficiency and high hole punching accuracy.

[0083] In summary, although the present disclosure has been disclosed as above in terms of preferred embodiments, the above preferred embodiments are not intended to limit the present disclosure. A person skilled in the art may make various changes and modifications without departing from the spirit and scope of the present disclosure. Therefore, the scope of protection of the present disclosure shall be based on the scope defined in the claims.

Claims

1. An air rudder for a spacecraft, characterized in that: The air rudder comprises a rudder body and a connecting shaft portion arranged at one side of the rudder body; the rudder body and the connecting shaft portion are integrally formed and are both made of metal material; the rudder body is a right-angle trapezoidal plate; the connecting shaft portion comprises a cylindrical main body portion and a convex ring portion formed by radially protruding at least one end of the cylindrical main body portion; a through shaft hole is opened inside the connecting shaft portion, and a positioning block is convexly provided on the surface of the convex ring portion; Wherein, both side surfaces of the rudder body are covered with a ceramic-based composite material layer, and the outer peripheral surface of the cylindrical main body is covered with a ceramic-based composite material layer; the thickness of the ceramic-based composite material layer is 1 to 10 cm, and the length of the convex ring portion is 1 / 10 to 1 / 2 of the length of the cylindrical main body.

2. An air rudder for a spacecraft as claimed in claim 1, characterized in that: The convex ring portion is located at one end of the columnar main body portion; and the surface of the connecting shaft portion covered with the ceramic matrix composite material layer is the first area, and the surface not covered with the ceramic matrix composite material layer is the second area.

3. A positioning tool for an air rudder for a spacecraft, characterized in that: The positioning fixture is used to position the aerospace air rudder according to claim 2; the positioning fixture comprises a main positioning seat, a secondary positioning seat, a first limiting end cover and a second limiting end cover; The main positioning seat has a first end and a second end opposite to each other; a through first concave hole is formed in the main positioning seat, and the first concave hole has an inner wall surface that is gap-matched with the first area of ​​the connecting shaft portion; The auxiliary positioning seat is locked to the first end of the main positioning seat, wherein a second concave hole is provided; the second concave hole has an inner wall surface that transitionally matches with the second area of ​​the connecting shaft portion; The first limiting end cover is locked on the auxiliary positioning seat, and the second limiting end cover is locked on the second end of the main positioning seat; the first limiting end cover and the second limiting end cover respectively have a first boss and a second boss that are transitionally matched with the shaft hole of the connecting shaft; Wherein, the main positioning seat is also provided with a processing hole penetrating through the hole wall of the first concave hole, which is used to open a hole in the first area of ​​the connecting shaft part.

4. A positioning fixture for an air rudder for a spacecraft as claimed in claim 3, characterized in that: When using the positioning fixture: The main positioning seat is configured to be sleeved on the first area of ​​the shaft connecting portion through the first concave hole; The secondary positioning seat is configured to be sleeved on the second area of ​​the connecting shaft portion through the second concave hole, and locked with the first end of the main positioning seat to achieve radial positioning of the first end of the main positioning seat; The first limiting end cover is configured to be inserted into the shaft hole of the connecting shaft portion from the side close to the first end of the main positioning seat through the first protrusion, and locked with the auxiliary positioning seat to achieve axial positioning of the first end of the main positioning seat; The second limiting end cover is configured to be inserted into the axial hole of the connecting shaft from the side close to the second end of the main positioning seat through the second boss, and locked with the second end of the main positioning seat to achieve axial positioning and radial positioning of the second end of the main positioning seat.

5. The positioning fixture for an air rudder for a spacecraft as claimed in claim 3, characterized in that: A plurality of first positioning holes are provided on the end surfaces of the first end and the second end of the main positioning seat, and a plurality of first positioning posts and second positioning posts corresponding to the first positioning holes are respectively provided on the surfaces of the auxiliary positioning seat and the second limiting end cover opposite to the main positioning seat; When the auxiliary positioning seat and the second limiting end cover are installed on the connecting shaft, the first positioning column and the second positioning column are respectively embedded in the corresponding first positioning holes on the main positioning seat.

6. A positioning fixture for an air rudder for a spacecraft as claimed in claim 5, characterized in that: A plurality of second positioning holes are also provided on the end surfaces of the first end and the second end of the main positioning seat; a plurality of first through holes and second through holes corresponding to the second positioning holes are respectively provided on the auxiliary positioning seat and the second limiting end cover; The positioning tool also includes a plurality of first locking pieces and second locking pieces, the first locking pieces are used to lock the secondary positioning seat to the main positioning seat through the first through hole and the second positioning hole; the second locking pieces are used to lock the second limiting end cover to the main positioning seat through the second through hole and the second positioning hole.

7. A positioning fixture for an air rudder for a spacecraft as claimed in claim 6, characterized in that: The auxiliary positioning seat is also provided with a plurality of third positioning holes, and the surface of the first limiting end cover opposite to the auxiliary positioning seat is provided with a plurality of third positioning columns corresponding to the third positioning holes; When the first limiting end cover is installed on the connecting shaft portion, the third positioning column is embedded in the corresponding third positioning hole on the auxiliary positioning seat.

8. The air rudder positioning tool for a spacecraft as claimed in claim 7, characterized in that: The auxiliary positioning seat is also provided with a plurality of fourth positioning holes, and the first limiting end cover is provided with a plurality of third through holes corresponding to the fourth positioning holes; The positioning fixture further includes a plurality of third locking pieces, and the third locking pieces are used to lock the first limiting end cover onto the auxiliary positioning seat through the third through hole and the fourth positioning hole.

9. The air rudder positioning tool for a spacecraft as claimed in claim 8, characterized in that: The first limiting end cover and the second limiting end cover are respectively provided with a fourth through hole and a fifth through hole penetrating the convex column; The positioning fixture also includes a fourth locking piece, and the fourth locking piece is used to lock the first limiting end cover and the second limiting end cover on the connecting shaft portion through the fourth through hole, the fifth through hole and the shaft hole.

10. A method for positioning and drilling holes for an air rudder for a spacecraft, characterized in that: The air rudder positioning tool for aerospace vehicle according to claim 9 is used, and includes the following steps: S1. The main positioning seat is fitted into the first area of ​​the connecting shaft portion through the first recessed hole; S2. The auxiliary positioning seat is fitted into the second region of the connecting shaft portion through the second recessed hole, and the first positioning column on the auxiliary positioning seat is fitted into the first positioning hole on the main positioning seat; then the main positioning seat and the auxiliary positioning seat are locked by the first locking member; S3. Insert the first limit end cover into the shaft hole of the connecting shaft portion from the side close to the auxiliary positioning seat through the first boss, and make the third positioning column on the first limit end cover fit into the third positioning hole on the auxiliary positioning seat; then lock the first limit end cover and the auxiliary positioning seat by the third locking piece; S4. Insert the second limiting end cover into the shaft hole of the connecting shaft portion from the side close to the main positioning seat through the second boss, and make the second positioning column on the second limiting end cover fit into the first positioning hole on the main positioning seat; then lock the main positioning seat and the second limiting end cover seat by the second locking piece; S5. The first limiting end cover and the second limiting end cover are locked on the shaft coupling portion by a fourth locking member; S6. Use a punching device to drill a hole in the first area of ​​the coupling portion through the processed hole on the main positioning seat.

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