CN218545464U

CN218545464U - Grid rudder of spacecraft

Info

Publication number: CN218545464U
Application number: CN202222454585.7U
Authority: CN
Inventors: 袁野; 张振涛
Original assignee: Zhejiang Landspace Technology Co Ltd
Current assignee: Zhejiang Landspace Technology Co Ltd
Priority date: 2022-09-16
Filing date: 2022-09-16
Publication date: 2023-02-28
Anticipated expiration: 2032-09-16

Abstract

The utility model provides a space carrier grid rudder, include: the grid rudder body is of a grid-shaped structure formed by a plurality of grids; the supporting unit is used for fixedly connecting the grid rudder body to the spacecraft; the locking unit is arranged on the inner side of the wall surface of the space vehicle and used for locking the grid rudder body in a folded state; the movement unit is arranged on one side, back to the grid rudder body, of the support unit and used for driving the unfolded grid rudder body to rotate around the axis direction of the grid rudder body. The grid rudder of the spacecraft realizes the reduction of the whole volume of the grid rudder through the compact and efficient layout, and saves the internal installation space of the spacecraft.

Description

Grid rudder of spacecraft

Technical Field

The utility model relates to a recovery field of space carrier, concretely relates to space carrier grid rudder.

Background

In the prior art, the grid rudder is unlocked basically in an initiating explosive device mode, a driving device for realizing folding, unfolding and rotating of the grid rudder is complex in structure, power mechanisms are needed in the folding direction and the rotating direction, and the occupied radial space is large in size. The drive mode of the actuating cylinder can also be adopted, and the mode can only output a certain linear stroke and cannot provide the functions of initial locking and in-place locking. If the stroke of the actuating cylinder is adopted to judge whether the folding angle is in place, a calibration test needs to be carried out on the ground, and the actuating cylinder cannot be powered off after being folded in place, otherwise, the actuating cylinder cannot be locked.

In view of this, it is desirable to design a grid rudder for an aerospace vehicle that has a simple structure and can satisfy a locking function.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to overcome prior art's not enough, provide a space carrier grid rudder.

The utility model provides a space carrier grid rudder, include: the grid rudder body is of a grid-shaped structure formed by a plurality of grids; the supporting unit is used for fixedly connecting the grid rudder body to the spacecraft; the locking unit is arranged on the inner side of the wall surface of the space vehicle and used for locking the grid rudder body in a folded state; the movement unit is arranged on one side, back to the grid rudder body, of the support unit and used for driving the unfolded grid rudder body to rotate around the axis direction of the grid rudder body.

According to the utility model discloses an embodiment, the supporting element includes rudder axle, outer support and inner support, the outer support is used for setting outside the spacecraft wall, the inner support is used for setting inboard in the spacecraft wall, through the rudder axle will the outer support with run through the connection in the inner support.

According to an embodiment of the utility model, the outer support comprises a pin shaft, and the grid rudder body is provided with two support lugs extending out; the grid rudder body penetrates through the two support lugs through pin shafts to be connected to the outer support.

According to the utility model discloses an embodiment, the outer support still includes ratchet, ratchet sets up in the outer support built-in groove and connect in the round pin axle, ratchet is used for the restriction grid rudder body along a rotatory direction lock of round pin axle is dead.

According to the utility model discloses an embodiment, ratchet includes ratchet, pawl, spring and toggle switch, the pawl with the spring all sets up on the inner wall of outer support built-in groove, toggle switch can be through stirring the pawl with thereby the spring control the direction of rotation of ratchet.

According to an embodiment of the present invention, the inner support comprises a nipple and an extension sleeve, the nipple and the extension sleeve being connected as a whole by means of a bolt.

According to the utility model discloses an embodiment, the locking unit is electromagnetic unlocking mechanism, set up outstanding locking pole on the grid rudder body, through electromagnetic unlocking mechanism will fold condition down locking pole locking or release on the grid rudder body.

According to the utility model discloses an embodiment, electromagnetism release mechanism includes electromagnetic switch, upper end cover, bottom end cover, hold-down pin and pressure spring, electromagnetic switch is used for control the upper end cover moves the hold-down pin compresses tightly or releases the locking pole.

According to the utility model discloses an embodiment, the motion unit includes rocking arm and servo steering wheel, the one end of rocking arm is embedded into the insertion groove of rudder axle is fixed, and the other end is connected servo steering wheel, through the power of servo steering wheel output drives the rotation of grid rudder body.

According to the utility model discloses an embodiment, the motion unit still includes the baffle, the baffle sets up the rudder axle dorsad the one end of inner support is used for spacing locking the rocking arm.

According to the utility model discloses a space carrier grid rudder passes through grid rudder body, the overall arrangement and the cooperation of supporting unit, locking unit and motion unit, has formed simple structure and can realize folding, expansion and rotatory grid rudder. The grid rudder body is stably locked in a folded state by the locking unit which is independently arranged on the inner side of the wall surface, and the locking mode realizes reduction of the whole volume of the grid rudder of the spacecraft and saves the internal installation space of the spacecraft through compact and efficient layout.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of the specification of the invention, illustrate exemplary embodiments of the invention and together with the description, serve to explain the principles of the invention.

Fig. 1 is a schematic view of an aerospace vehicle grid rudder according to an embodiment of the invention;

fig. 2 is an exploded schematic view of an aerospace vehicle grid rudder according to an embodiment of the invention;

fig. 3 is an exploded view of the outer base of the spacecraft grid rudder according to an embodiment of the present invention;

fig. 4 is an exploded schematic view of a locking unit of an aerospace vehicle grid rudder according to an embodiment of the invention.

Reference numerals are as follows:

100-grid rudder body, 101-locking rod, 200-supporting unit, 201-rudder shaft, 202-outer support, 203-inner support, 204-pin shaft, 205-inner joint, 206-extending shaft sleeve, 207-ratchet mechanism, 211-ratchet, 212-pawl, 213-ratchet spring, 214-toggle switch, 300-locking unit, 301-electromagnetic switch, 302-upper end cover, 303-lower end cover, 304-pressing pin, 305-pressing spring, 400-moving unit, 401-rocker arm and 402-servo steering engine.

Detailed Description

The features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention, for the purpose of illustrating the principles of the invention. Additionally, the components in the drawings are not necessarily to scale. For example, the dimensions of some of the structures or regions in the figures may be exaggerated relative to other structures or regions to help improve understanding of embodiments of the present invention.

The directional terms appearing in the following description are directions shown in the drawings and do not limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise stated, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood as the case may be, by those of ordinary skill in the art.

Furthermore, the terms "comprises," "comprising," "includes," "including," "has," "having" or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a structure or assembly that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such structure or assembly. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of another like element in an article or device comprising the element.

Spatially relative terms such as "under," "below," "…," "low," "above," "…," "high," and the like are used to facilitate description to explain the positioning of one element relative to a second element, indicating that these terms are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.

It will be apparent to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.

Fig. 1 is a schematic view of an aerospace vehicle grid rudder according to an embodiment of the invention; fig. 2 is an exploded schematic view of an aerospace vehicle grid rudder according to an embodiment of the invention; fig. 3 is an exploded view of the outer base of the spacecraft grid rudder according to an embodiment of the present invention; fig. 4 is an exploded schematic view of a locking unit of an aerospace vehicle grid rudder according to an embodiment of the invention.

As shown in fig. 1, the utility model provides a space carrier grid rudder, include: the grid rudder body 100 is a grid-shaped structure formed by a plurality of grids; the supporting unit 200 is used for fixedly connecting the grid rudder body 100 to the spacecraft; a locking unit 300 provided inside a wall surface of the space vehicle for locking the grid rudder body 100 in a folded state; and the moving unit 400 is arranged on the side, facing away from the grid rudder body 100, of the support unit 200 and is used for driving the grid rudder body 100 in the unfolding state to rotate around the axis direction of the grid rudder body 100.

In particular, spacecraft may create safety issues when recovering a fall to the ground, and so attitude control needs to be provided by the grid rudders. After the interstage separation of the space carrier, the grid rudder generates aerodynamic force through rotation so as to control the rolling, pitching and yawing of the space carrier, and therefore the space carrier can accurately land on the recovery platform. The grid rudder body 100 is formed of a grid-like structure formed of a plurality of grids, and the grid rudder body 100 can be fixedly attached to a wall surface of the space vehicle by the support unit 200. The grid rudder body 100 can be folded and unfolded relative to the wall surface of the spacecraft under the fixation of the support unit 200. During the takeoff phase of the spacecraft, the grid rudder body 100 is kept in a folded state, and the grid rudder body 100 is locked in the folded state through the locking unit 300. Wherein the locking unit 300 is arranged inside the wall position of the spacecraft with the grid rudder in the folded state. For example, the locking unit 300 is on the same axis as the support unit 200 on the spacecraft wall. The moving unit 400 is a set of servo mechanism, which is disposed on the side of the supporting unit 200 facing away from the grid rudder body 100, and performs rotation control of the deployed grid rudder by providing a driving force.

The locking device of the grid rudder of the spacecraft in the embodiment is simple in structure and reliable in connection, and the grid rudder body 100 can be stably locked in a folded state in the takeoff stage of the spacecraft through the locking unit 300 which is independently arranged on the inner side of the wall surface. According to the locking mode, the whole volume of the grid rudder of the spacecraft is reduced through the compact and efficient layout, the radial mounting space inside the spacecraft is saved, in addition, the structure of the locking mode is compact, the light weight of the locking structure is realized, and the grid rudder body 100 capable of adapting to large loads can be folded and unfolded.

As shown in fig. 2, according to an embodiment of the present invention, the support unit 200 includes a rudder shaft 201, an outer bracket 202, and an inner bracket 203. Outer support 202 is used for being arranged on the outer side of the wall surface of the space carrier, inner support 203 is used for being arranged on the inner side of the wall surface of the space carrier, and the outer support 202 and the inner support 203 are connected in a penetrating mode through rudder shafts 201.

According to an embodiment of the present invention, the outer base 202 includes a pin 204, two support lugs extending from the grid rudder body 100; the grid rudder body 100 is connected to the outer base 202 through two lugs by pins 204.

According to an embodiment of the present invention, the inner support 203 comprises an inner joint 205 and an extension sleeve 206, the inner joint 205 and the extension sleeve 206 being connected as a whole by a bolt.

Specifically, the rudder shaft 201 in the support unit 200 sequentially penetrates through the outer support 202, the wall surface, and the inner support 203, and both ends of the rudder shaft 201 can penetrate through the inner support 203 and the outer support 202, thereby connecting the outer support 202 on the outer side of the wall surface and the inner support 203 on the inner side of the wall surface. Further, in order to connect the grid rudder body 100 to the support unit 200, two support lugs need to be extended from both sides of the grid rudder body 100, and the grid rudder body 100 is fixed to the outer support 202 by two pins 204 of the outer support 202 passing through the two support lugs, so that the grid rudder body 100 is fixed to the wall surface of the space vehicle. In addition, the outer base 202 needs to be provided with an internal groove for accommodating the pin 204 to fix the lug of the grid rudder. The inner support 203 includes an inner joint 205 and an extension bushing 206, and the inner joint 205 and the extension bushing 206 are connected as a whole by bolts, wherein the rudder shaft 201 is connected to the outer support 202 and penetrates the inner joint 205 and the extension bushing 206.

As shown in fig. 3, according to an embodiment of the present invention, the outer base 202 further includes a ratchet mechanism 207, the ratchet mechanism 207 is disposed in the built-in groove of the outer base 202 and connected to the pin 204, and the ratchet mechanism 207 is used to limit the grid rudder body 100 to be locked along one direction of the rotation of the pin 204.

According to an embodiment of the present invention, the ratchet mechanism 207 comprises a ratchet 211, a pawl 212, a ratchet spring 213 and a toggle switch 214. Pawl 212 and ratchet spring 213 are both disposed on the inner wall of the built-in slot of outer support 202, and toggle switch 214 is capable of controlling the rotation direction of ratchet 211 by toggling pawl 212 and ratchet spring 213.

Specifically, the deployed grid rudder body 100 needs to be provided with a ratchet mechanism 207 for position locking. Ratchet mechanism 207 is mounted in an internal slot of outer housing 202. The two ratchet mechanisms 207 are provided inside the pin shaft 204 in the built-in grooves, enabling the locking force of the ratchet mechanisms 207 to be stronger. In one embodiment, the ratchet wheel 211 of the ratchet mechanism 207 is sleeved on the pin 204, and the two pawls 212 and the two ratchet springs 213 are both disposed on the inner wall of the built-in groove of the outer support 202. A ratchet spring 213 is fixedly connected below each pawl 212, the toggle switch 214 can toggle one pawl 212 and press the ratchet spring 213 below the pawl 212, and the corresponding ratchet spring 213 of the other pawl 212 releases elastic force to be in an elastic state, so that the ratchet 211 can only rotate in one direction of clockwise or counterclockwise under the influence of the position of the other pawl 212.

In this embodiment, the rotation of the lattice rudder body 100 drives the ratchet 211 to rotate, and the rotation direction of the ratchet 211 is locked by the toggle switch 214, so as to prevent the lattice rudder body 100 from returning to the folded state, and keep the lattice rudder body 100 in the unfolded state. In order to increase the reliability of the ratchet mechanism 207, it is necessary to debug the rotation of the ratchet 211 and the locking performance after the entire ratchet mechanism 207 is mounted.

It is understood that the deployed grid rudder body 100 may have a bi-directional ratchet mechanism 207. The ratchet mechanism 207 is simple and reliable in structure, the locking force meets the design requirements of the conventional space carrier, meanwhile, the operation of reverse folding and recovery is convenient, and only the toggle switch 214 of the ratchet mechanism 207 needs to be manually turned to the other side.

In the return phase of the spacecraft, firstly, the electromagnetic switch 301 is unlocked, the grid rudder body 100 is bounced off by the hold-down pin 304 through the hold-down spring 305, and the grid rudder body 100 is unfolded. The hinge moment then pushes the lattice rudder body 100 to a position 90 ° to the wall surface. The grid rudder body 100 is provided with a limiting rod which can be pressed against the outer seat 202 when the grid rudder body 100 rotates to 90 degrees, and meanwhile, the ratchet mechanism 207 is in a locking state in the reverse direction, so that the grid rudder body 100 is ensured to be locked. The grid rudder body 100 unfolded in the embodiment adopts a ratchet wheel 211 locking mode, has a reliable structure and long service life, and is convenient to recover and fold.

As shown in fig. 4, according to an embodiment of the present invention, the locking unit 300 is an electromagnetic unlocking mechanism. The grid rudder body 100 is provided with a protruding lock lever 101, and the lock lever 101 of the grid rudder body 100 in a folded state is locked or released by an electromagnetic unlocking mechanism.

According to the utility model discloses an embodiment, electromagnetism release mechanism includes electromagnetic switch 301, upper end cover 302, lower end cover 303, compresses tightly round pin 304 and compression spring 305, and electromagnetic switch 301 is used for controlling upper end cover 302 to drive and compress tightly round pin 304 and compress tightly or release locking pole 101.

Specifically, the locking mode of the locking unit 300 adopts an electromagnetic switch 301, and the electromagnetic unlocking mechanism electromagnetically locks or releases the locking rod 101 protruding from the grid rudder body 100, so as to unlock the grid rudder. The locking and releasing process is simple and quick, and the response time is short. Due to the fact that the size of the electromagnetic unlocking structure is small, the integral impact force on the grid rudder is small.

The electromagnetic unlocking mechanism is composed of an electromagnetic switch 301, an upper end cover 302, a lower end cover 303, a pressing pin 304 and a pressing spring 305. In some specific examples, the compression of the detent lever 101 is as follows: the locking rod 101 can be inserted into a space formed by the upper end cover 302 and the lower end cover 303 in a pressing state in the folding process of the grid rudder body 100, and the electromagnetic switch 301 drives the pressing pin 304 to press the locking rod 101 by controlling the upper end cover 302. Wherein the hold-down pin 304 can pass through the through-hole of the lock lever 101, improving the hold-down effect. Further, the release process of the lock lever 101 is as follows: the electromagnetic switch 301 drives the pressing pin 304 to leave the through hole of the locking rod 101 by controlling the upper end cover 302, so that the pressing spring 305 located at the end of the space where the lower end cover 303 accommodates the locking rod 101 releases the pressing force, and the pressing spring 305 pushes the locking rod 101 and the grid rudder body 100 away from the wall surface of the space vehicle, so that the grid rudder body 100 is ejected to be in the unfolded state. In order to prevent the interference between the upper end cap 302 and the lower end cap 303 in the electromagnetic unlocking mechanism during the rotation of the lock lever 101, the upper end cap 302 and the lower end cap 303 are subjected to a film removing process on the surface of the lock lever 101 that is in contact with each other.

It should be noted that the lattice rudder body 100 in the folded state can be passively opened using a hinge moment. The electromagnetic switch 301 is used to lock the grid rudder body 100 before deployment. The electromagnetic unlocking mode is quick in response, small in size and small in impact force on the structure.

As shown in fig. 2, according to an embodiment of the present invention, the motion unit 400 includes a rocker arm 401 and a servo steering engine 402. One end of the rocker 401 is embedded into an insertion groove of the rudder shaft 201 and fixed, the other end of the rocker is connected with the servo steering engine 402, and the grid rudder body 100 is driven to rotate by power output by the servo steering engine 402.

According to an embodiment of the present invention, the movement unit 400 further comprises a baffle 403, the baffle 403 is disposed at an end of the rudder shaft 201 facing away from the inner support 203 and is used for limiting the locking rocker 401.

Specifically, the rocker 401 of the motion unit 400 can provide a moment for the servo steering engine 402, an insertion groove is formed in the position where the rudder shaft 201 penetrates through the extension shaft sleeve 206, and one end of the rocker 401 is inserted into the insertion groove in a mortise and tenon structure mode. The other end of the rocker 401 is connected to a servo steering engine 402, and the servo steering engine 402 transmits power to the rudder shaft 201 through the rocker 401. The rolling control of the grid rudder body 100 is realized while the rudder shaft 201 is rotated. In this embodiment, since the connection mode between the rocker 401 and the rudder shaft 201 is a mortise and tenon structure, a baffle 403 needs to be disposed on the joint surface between the rocker 401 and the rudder shaft 201, so that the limit locking rocker 401 cannot fall off from the insertion slot of the rudder shaft 201.

In this application, the grid rudder of the spacecraft only needs to be provided with one set of linear servo mechanism, namely the motion unit 400, so that the cost and the structural complexity are all optimized, the connection reliability is high, the deployment speed is high, and the occupied internal space is small. In the grid rudder of this application, adopted the grid rudder body 100 that more compact efficient mechanism mode control was expanded to rotate, the wall of grid rudder body 100 and space carrier is passed through outer support 202 and rudder axle 201 and is connected, and rudder axle 201 and rocking arm 401 adopt tenon fourth of the twelve earthly branches structure, make grid rudder overall structure simple, connect reliably.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be construed as limiting the scope of the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the present invention.

Claims

1. An aerospace vehicle grid rudder, comprising:

the grid rudder body is of a grid-shaped structure formed by a plurality of grids;

the supporting unit is used for fixedly connecting the grid rudder body to the spacecraft;

the locking unit is arranged on the inner side of the wall surface of the spacecraft and used for locking the grid rudder body in a folded state;

the movement unit is arranged on one side, back to the grid rudder body, of the support unit and used for driving the unfolded grid rudder body to rotate around the axis direction of the grid rudder body.

2. An spacecraft grid rudder according to claim 1, characterised in that the support unit comprises a rudder shaft, an outer support for being arranged outside a spacecraft wall, and an inner support for being arranged inside a spacecraft wall, the outer support and the inner support being connected through the rudder shaft.

3. The spacecraft grid rudder of claim 2, wherein the outer mount includes a pin, two lugs extending from the grid rudder body; the grid rudder body penetrates through the two support lugs through pin shafts to be connected to the outer support.

4. The spacecraft carrier grid rudder of claim 3, wherein the outer mount further comprises a ratchet mechanism disposed in the outer mount inner slot and connected to the pin, the ratchet mechanism for limiting the grid rudder body from locking in one direction of rotation of the pin.

5. The spacecraft carrier grid rudder of claim 4, wherein the ratchet mechanism comprises a ratchet, a pawl, a spring, and a toggle switch, the pawl and the spring are disposed on an inner wall of the outer seat built-in slot, and the toggle switch is capable of controlling a rotation direction of the ratchet by toggling the pawl and the spring.

6. The spacecraft grid rudder of claim 2, wherein the inner mount comprises an inner nipple and an extension boss, the inner nipple and the extension boss being integrally connected by a bolt.

7. The spacecraft grid rudder of claim 2, wherein the locking unit is an electromagnetic unlocking mechanism, and a protruding locking rod is arranged on the grid rudder body, and the locking rod on the grid rudder body in a folded state is locked or released by the electromagnetic unlocking mechanism.

8. An aerospace vehicle grid rudder as claimed in claim 7, wherein the electromagnetic unlocking mechanism comprises an electromagnetic switch, an upper end cap, a lower end cap, a hold down pin and a hold down spring, the electromagnetic switch being configured to control the upper end cap to actuate the hold down pin to hold down or release the lock bar.

9. The grid rudder of a spacecraft of claim 2, wherein the motion unit comprises a rocker arm and a servo steering engine, one end of the rocker arm is embedded into and fixed to an insertion groove of the rudder shaft, the other end of the rocker arm is connected with the servo steering engine, and the grid rudder body is driven to rotate by power output by the servo steering engine.

10. The space vehicle grid rudder according to claim 9, characterised in that the kinematic unit further comprises a stop plate arranged at the end of the rudder shaft facing away from the inner bearing for positive locking of the rocker arm.