阅读说明：本技术 一种面向重复使用火箭的变刚度阻尼支撑机构 (Variable-stiffness damping supporting mechanism for reusable rocket ) 是由 王辰 张宏剑 于兵 章凌 张东 王迪 乐晨 郭岳 包宇兵 张晓晖 刘观日 王婧 于 2021-08-30 设计创作，主要内容包括：本发明涉及一种面向重复使用火箭的变刚度阻尼支撑机构,包括摆臂组件、支撑杆组件、伸缩弯梁组件和安装座组件,摆臂组件包括摆臂接头和摆臂,摆臂两端与摆臂接头固连形成摆臂组件,摆臂组件一端的摆臂接头与安装座相连,另一端的摆臂接头同时连接支撑杆和伸缩弯梁；安装座组件包括安装座和弹簧片,全套支撑机构呈收缩状态时,弹簧片处于受压状态,机构需展开时,外设锁定装置对摆臂的锁定解除,摆臂在弹簧片的作用下绕安装座转动,带动弯梁收缩升高和支撑杆伸长升高。本发明在满足在重复使用火箭整流罩和舱段结构安装的几何外形尺寸和接口要求的基础上,不改变壳段或整流罩等火箭结构的原本结构形式,采用运动机构的形式增加结构整体刚度。(The invention relates to a variable-stiffness damping support mechanism facing a reusable rocket, which comprises a swing arm assembly, a support rod assembly, a telescopic curved beam assembly and a mounting seat assembly, wherein the swing arm assembly comprises a swing arm joint and a swing arm, two ends of the swing arm are fixedly connected with the swing arm joint to form the swing arm assembly, the swing arm joint at one end of the swing arm assembly is connected with the mounting seat, and the swing arm joint at the other end is simultaneously connected with a support rod and the telescopic curved beam; the mounting seat assembly comprises a mounting seat and a spring piece, when the whole set of supporting mechanism is in a contraction state, the spring piece is in a compression state, when the mechanism needs to be unfolded, the locking of the swing arm by the external locking device is released, and the swing arm rotates around the mounting seat under the action of the spring piece to drive the bent beam to contract and lift and the supporting rod to extend and lift. The invention does not change the original structural form of the shell section or the fairing and other rocket structures on the basis of meeting the requirements of geometric overall dimension and interface for repeatedly using rocket fairing and cabin section structure installation, and adopts the form of a motion mechanism to increase the overall rigidity of the structure.)

1. A variable-stiffness damping supporting mechanism facing a reusable rocket is characterized by comprising a swing arm assembly (1), a supporting rod assembly (2), a telescopic curved beam assembly (3) and a mounting seat assembly (4),

the swing arm assembly comprises a swing arm joint (1-1) and a swing arm (1-2), two ends of the swing arm are fixedly connected with the swing arm joint to form the swing arm assembly, the swing arm joint at one end of the swing arm assembly is connected with the mounting seat, and the swing arm joint at the other end is simultaneously connected with the support rod and the telescopic bent beam;

the mounting seat assembly (4) comprises a mounting seat (4-1) and a spring piece (4-2), when the whole set of supporting mechanism is in a contraction state, the spring piece is in a compression state, when the mechanism needs to be unfolded, the locking of an external locking device on the swing arm is released, the swing arm rotates around the mounting seat under the action of the spring piece, and the bent beam is driven to contract and rise and the supporting rod extends and rises;

the support rod component (2) comprises a support rod joint (2-1), a support rod inner cylinder (2-2) and a support rod outer cylinder (2-3), the support rod inner cylinder and the support rod outer cylinder are sleeved, the support rod joint at one end of the support rod component is hinged with the swing arm component, and the support rod joint at the other end of the support rod component is hinged with a mounting seat arranged in the shell section or the fairing; the swing arm rotates to drive the supporting rod to rise, the inner supporting rod cylinder and the outer supporting rod cylinder move relatively, and the supporting rod extends integrally;

the telescopic curved beam assembly (3) comprises a curved beam (3-1), a curved beam sleeve (3-2), a curved beam joint (3-3), a locking block (3-4), a spring (3-5), a lock box (3-6), a friction block (3-7) and a disc spring (3-8),

the curved beam (3-1) comprises a curved beam head part and a curved beam tail part, and a curved structural part is arranged in the middle;

the lock box is installed on the surface of the curved beam sleeve, the locking block and the spring are sequentially installed into the lock box and covered with the cover plate of the lock box, then the disc spring is sleeved on the guide post of the friction block in a group, the guide post of the friction block is inserted into the through hole in the corresponding position of the curved beam sleeve, the nut and the guide post are positioned and screwed on the other side of the outer curved beam sleeve, the curved beam joint is installed at one end of the curved beam sleeve, and the curved beam is inserted into the other end of the curved beam sleeve to form the telescopic curved beam assembly.

2. A variable stiffness damped support mechanism for a re-usable rocket as claimed in claim 1 wherein, as the swing arms rotate to raise the telescoping camber beam, the camber beam gradually moves along the camber beam sleeve and extends into the sleeve to retract the telescoping camber beam assembly.

3. A variable stiffness damping support mechanism for a re-usable rocket as claimed in claim 1 wherein the swing arm, support rod and telescoping camber beam assembly are all tightly attached to the inner surface of the cylindrical shell segment or fairing in the retracted state to reduce the space occupied inside the rocket.

4. The variable-stiffness damping support mechanism for the reusable rocket according to claim 1, wherein the support mechanism is externally constrained and contacted when the support mechanism needs to be unfolded, the swing arm assemblies on two sides rotate and unfold under the action of a driving source to drive the middle telescopic camber beam to contract and ascend, and simultaneously drive the support rod to extend and rotate and ascend, the telescopic camber beam is locked when the mechanism is unfolded in place, and a formed rod system structure can form support in the shell section and the fairing so as to improve the overall stiffness of the structure.

5. A variable stiffness damped support mechanism for a re-usable rocket as claimed in claim 1 wherein the locking blocks lock the beam so that the beam does not rebound when in position, and forward motion of the beam is resisted by the friction blocks.

6. A stiffness-variable damping support mechanism for a reusable rocket as claimed in claim 1 wherein the friction block is a rectangular block structure with three long cylindrical guide posts on the upper surface, the guide posts can be inserted into corresponding through holes on the camber beam sleeve.

7. A stiffness-variable damping support mechanism for a reusable rocket as claimed in claim 1 wherein a disc spring is mounted between the friction block and the camber beam sleeve in a group, and the friction block is pressed by the guide of the guide post and then can move relative to the camber beam sleeve.

8. A variable-stiffness damping support mechanism for a reusable rocket as claimed in claim 1, wherein when the bending beam moves forward, the inclined surface of the head of the bending beam contacts with the inclined surface of the lower surface of the friction block, the two move relatively to each other and generate sliding friction on the contact surface, the head of the bending beam is pressed by the inclined surface contact to cause the friction block to compress the disc spring and move upward, and the larger the forward movement of the bending beam is, the larger the pressing amount of the friction block and the disc spring is, the larger the generated back pressure and friction force are.

9. A variable stiffness damped support mechanism for a re-usable rocket according to claim 1 wherein the camber beam assembly is hinged at each end to a swing arm joint and a support bar joint on either side of the hull section or fairing.

10. A variable stiffness damping support mechanism for a reusable rocket according to claim 2 wherein the telescopic camber beam assembly retracts until the camber beam head touches the locking block, the camber beam head pushes the locking block open, the locking block then completes locking of the camber beam under the action of the spring and completes locking of the entire set of mechanisms at the same time, so that the entire set of mechanisms form a rod system structure to form internal support for the shell section or the fairing structure.

Technical Field

The invention relates to a variable-stiffness damping supporting mechanism for a reusable rocket, which is used for improving the structural stiffness of a reusable rocket fairing and a cabin structure in a reentry and return process, providing a damping impact reduction effect and increasing the capability of keeping the integrity of a rocket structure.

Background

The reuse of the carrier rocket is an important way for reducing the launching cost, improving the launching frequency and establishing the normalized space entering capability, the improvement of the availability of the landing zone is also an important factor for reducing the design constraint of the flight trajectory of the carrier rocket, the improvement of the safety of the landing zone can also improve the carrying capability of the carrier rocket, and the search and practice of the lossless recovery and reuse technology of the carrier rocket can drive the search and development of the aerospace technology.

The reentry process of the rocket fairing structure and part of the cabin structure can be subjected to separation, a vacuum stable section, a maximum dynamic pressure rolling deformation section, an attitude stable section and other stages. Therefore, the structure is easy to be subjected to large deformation such as separation vibration and respiration effect generated by external excitation, and the structure is easy to generate plastic deformation and fatigue fracture after repeated large deformation, so that the structure is damaged.

The repeated use of the rocket fairing structure and part of the cabin section structure needs to design related structures and mechanisms to improve the overall rigidity of the structure, and the method starts from two aspects, on one hand, a honeycomb sandwich/composite material skin sandwich structure can be adopted to improve the overall rigidity on the premise of ensuring light weight, and the defects of complex manufacturing process, high cost and low percent of pass are overcome; on the other hand, a supporting mechanism is added in the structure to form a box-shaped closed structure. Because enough installation space and separation safety space need to be reserved for the effective load in the fairing structure and the cabin structure in the main task stage, a deployable mechanism can be adopted, and the effective load space is made available when the main task stage is in a folded state. After the rocket sections are separated, the internal mechanism is unfolded to form a support, so that the rigidity is improved. In addition to the improvement of rigidity, the rocket fairing structure and the cabin structure can be impacted by separating devices such as a separating spring and an explosion bolt when being separated, large deformation is generated in a vacuum section, and a supporting mechanism is required to have the capacity of providing damping, reduce the impact and attenuate deformation movement.

Disclosure of Invention

The technical problem solved by the invention is as follows: the variable-rigidity damping supporting mechanism for the reusable rocket overcomes the defects of the prior art, and can be tightly attached to the inner wall of a cabin section structure to reduce the occupation of space on the basis of meeting the requirements of geometric overall dimension and interfaces for installing the reusable rocket fairing and the cabin section structure, so that the installation space and separation margin of an effective load are ensured, the rigidity/strength of structures such as the fairing and the like is improved after the mechanism is unfolded, the damping effect can be provided for the reciprocating deformation of the structure, the vibration is attenuated, and the safety and the integrity of the rocket body structure are protected.

The technical scheme of the invention is as follows:

a variable-rigidity damping support mechanism facing to a reusable rocket comprises a swing arm assembly, a support rod assembly, a telescopic curved beam assembly and a mounting seat assembly,

the swing arm assembly comprises a swing arm joint and a swing arm, two ends of the swing arm are fixedly connected with the swing arm joint to form a swing arm assembly, the swing arm joint at one end of the swing arm assembly is connected with the mounting seat, and the swing arm joint at the other end is simultaneously connected with the support rod and the telescopic bent beam;

the mounting seat assembly comprises a mounting seat and a spring piece, when the complete set of supporting mechanism is in a contraction state, the spring piece is in a compression state, when the mechanism needs to be unfolded, the locking of an external locking device on the swing arm is released, and the swing arm rotates around the mounting seat under the action of the spring piece to drive the curved beam to contract and lift and the supporting rod to extend and lift;

the support rod component comprises a support rod joint, a support rod inner cylinder and a support rod outer cylinder, the support rod inner cylinder and the support rod outer cylinder are sleeved, the support rod joint at one end of the support rod component is hinged with the swing arm component, and the support rod joint at the other end of the support rod component is hinged with a mounting seat arranged in the shell section or the fairing; the swing arm rotates to drive the supporting rod to rise, the inner supporting rod cylinder and the outer supporting rod cylinder move relatively, and the supporting rod extends integrally;

the telescopic curved beam component comprises a curved beam, a curved beam sleeve, a curved beam joint, a locking block, a spring, a lock box, a friction block and a disc spring,

the camber beam comprises a camber beam head part and a camber beam tail part, and a bent structural part is arranged in the middle of the camber beam;

the lock box is installed on the surface of the curved beam sleeve, the locking block and the spring are sequentially installed into the lock box and covered with the cover plate of the lock box, then the disc spring is sleeved on the guide post of the friction block in a group, the guide post of the friction block is inserted into the through hole in the corresponding position of the curved beam sleeve, the nut and the guide post are positioned and screwed on the other side of the outer curved beam sleeve, the curved beam joint is installed at one end of the curved beam sleeve, and the curved beam is inserted into the other end of the curved beam sleeve to form the telescopic curved beam assembly.

Furthermore, when the swing arms on the two sides rotate to drive the telescopic camber beam to rise, the camber beam gradually moves along the camber beam sleeve and extends into the sleeve, so that the telescopic camber beam assembly contracts.

Furthermore, the swing arm, the support rod and the telescopic curved beam assembly are tightly attached to the inner surface of the shell section or the inner surface of the fairing of the cylindrical shell type in the contraction state, and the occupied space of the rocket is reduced.

Furthermore, when the telescopic mechanism needs to be unfolded, external restraint contact is performed, the swing arm assemblies on two sides rotate and unfold under the action of the driving source, the middle telescopic bent beam is driven to contract and ascend, the supporting rod is driven to extend and rotate and ascend simultaneously, the telescopic bent beam is locked when the mechanism is unfolded in place, the formed rod system structure can form a support in the shell section and the fairing, and the integral rigidity of the structure is improved.

Furthermore, the locking block locks the bent beam, so that the bent beam cannot rebound after moving in place, and the forward movement of the bent beam is blocked by the friction block.

Furthermore, the friction block is of a cuboid block structure, the upper surface of the friction block is provided with three long cylindrical guide columns, and the guide columns can be inserted into through holes in corresponding positions on the camber beam sleeve.

Furthermore, disc springs are arranged between the friction blocks and the camber beam sleeves in groups, and the friction blocks can move relative to the camber beam sleeves after being pressed under the guiding action of the guide columns.

Furthermore, when the bending beam moves forwards, the inclined surface of the head of the bending beam is in contact with the inclined surface of the lower surface of the friction block, the inclined surface and the inclined surface generate relative movement and sliding friction on the contact surface, the head of the bending beam is extruded under the contact action of the inclined surfaces to enable the friction block to compress the disc spring and move upwards, the more the forward movement of the bending beam is, the larger the extrusion amount of the friction block and the disc spring is, and the larger the formed reverse pressure and friction force is.

Furthermore, two ends of the camber beam assembly are respectively hinged with a swing arm joint and a support rod joint on two sides of the shell section or the fairing.

Furthermore, when the telescopic curved beam assembly contracts until the head of the curved beam touches the locking block, the head of the curved beam pushes the locking block open, then the locking block completes locking of the curved beam under the action of the spring and simultaneously completes locking of the whole set of mechanism, so that the whole set of mechanism forms a rod system structure to form internal support for the shell section or the fairing structure.

Compared with the prior art, the invention has the beneficial effects that:

(1) the folded state of the invention can cling to the inner wall of the cabin structure to reduce the space occupation and ensure the installation space and the separation margin of the effective load. After the telescopic;

(2) on the basis of meeting the requirements of geometric overall dimension and interface for mounting the rocket fairing and cabin section structures which are repeatedly used, the original structural form of the rocket structures such as the shell section or the fairing is not changed, and the overall rigidity of the structure is increased by adopting a movement mechanism;

(3) the reciprocating deformation of the rocket shell section or the fairing of the invention causes repeated frictional contact and separation between the curved beam and the friction block, and generates frictional damping to the vibration of the rocket shell section or the fairing structure through the friction action, thereby dissipating the vibration energy, reducing the vibration magnitude and protecting the safety of the rocket structure.

Drawings

FIG. 1 is a schematic view of the mechanism in a assembled-contracted state;

the device comprises a swing arm assembly, a support rod assembly, a telescopic bent beam assembly and a mounting seat assembly, wherein the swing arm assembly is 1, the support rod assembly is 2, the telescopic bent beam assembly is 3, and the mounting seat assembly is 4;

FIG. 2 is a schematic view of the mechanism in an assembled-expanded state;

FIG. 3 is a schematic view of the mechanism mounted in the cowl in a retracted state;

FIG. 4 is a schematic view of the mechanism mounted in the cowling in an unfolded state;

FIG. 5 is a schematic view of the swing arm assembly;

wherein, 1-1 swing arm joint and 1-2 swing arm;

FIG. 6 is a schematic view of a mount assembly;

wherein, 4-1 mounting seat and 4-2 spring leaf;

FIG. 7 is a schematic view of a support rod assembly;

wherein, the joint of the 2-1 support rod, the inner cylinder of the 2-2 support rod and the outer cylinder of the 2-3 support rod;

FIG. 8 is a schematic view of the telescoping camber beam assembly in an extended state;

wherein, 3-1 curved beam, 3-2 curved beam sleeve, 3-3 curved beam joint, 3-4 locking block, 3-5 spring, 3-6 lock box, 3-7 friction block, 3-8 disc spring;

fig. 9 is a schematic view of the telescopic beam assembly in a contracted state.

Detailed Description

The invention is further illustrated by the following examples.

A variable-stiffness damping support mechanism facing a reusable rocket comprises a swing arm assembly 1, a support rod assembly 2, a telescopic curved beam assembly 3 and a mounting seat assembly 4, wherein the telescopic curved beam assembly is in a contracted state as shown in figure 1, and the mounting seat assembly is in an expanded state as shown in figure 2. The swing arm, the support rod and the telescopic curved beam assembly are tightly attached to the inner surface of the shell section or the inner surface of the fairing of the cylindrical shell type in a contraction state, and the occupied space of the rocket is reduced. When the telescopic bent beam needs to be unfolded, the outside is restrained and contacted, the swing arm assemblies on the two sides rotate and unfold under the action of the driving source, the middle telescopic bent beam is driven to contract and ascend, and meanwhile, the supporting rod is driven to extend and rotate to ascend. When the mechanism is unfolded in place, the telescopic bent beam is locked, and the formed rod system structure can form support in the shell section and the fairing, so that the integral rigidity of the structure is improved.

Fig. 3 shows the mechanism in the retracted state when mounted in the cowl, and fig. 4 shows the mechanism in the extended state when mounted in the cowl.

Fig. 5 is a swing arm assembly, which is composed of a swing arm joint 1-1 and a swing arm 1-2. The two ends of the swing arm are fixedly connected with the swing arm joint to form a swing arm assembly, one end of the swing arm assembly is connected with the mounting seat, and the other end of the swing arm assembly is simultaneously connected with the support rod and the telescopic bent beam.

FIG. 6 is a mounting seat assembly, which is composed of a mounting seat 4-1 and a spring leaf 4-2, wherein the spring leaf is in a compressed state when the whole set of support mechanism is in a contracted state. When the mechanism needs to be unfolded, the locking of the swing arm by the external locking device is released, the swing arm rotates around the mounting seat under the action of the spring piece to drive the curved beam to contract and lift and the supporting rod to extend and lift, and the mechanism is a driving part of the whole mechanism.

FIG. 7 is a supporting rod assembly, which is composed of a supporting rod joint 2-1, a supporting rod inner cylinder 2-2 and a supporting rod outer cylinder 2-3. The inner and outer cylinders of the supporting rod assembly are sleeved, one end of the supporting rod assembly is hinged with the swing arm assembly, and the other end of the supporting rod assembly is hinged with a mounting seat mounted in the shell section or the fairing. The rotation of the swing arm can drive the supporting rod to rise, the inner barrel and the outer barrel of the supporting rod move relatively, and the supporting rod extends integrally.

Fig. 8 shows a telescopic camber beam assembly-in an extended state, which is composed of a camber beam 3-1, a camber beam sleeve 3-2, a camber beam joint 3-3, a locking block 3-4, a spring 3-5, a lock box 3-6, a friction block 3-7, a disc spring 3-8 and the like. When the swing arms on the two sides rotate to drive the telescopic curved beam to rise, the curved beam gradually moves along the curved beam sleeve and extends into the sleeve, so that the curved beam assembly contracts. When the camber beam assembly contracts to the point that the head of the camber beam touches the locking block, the head of the camber beam pushes the locking block open, the locking block completes locking of the camber beam under the action of the spring and also completes locking of the whole set of mechanism, so that the whole set of mechanism forms a rod system structure to form internal support for the shell section or the fairing structure, and the overall rigidity is improved.

The locking block locks the bent beam, so that the bent beam cannot rebound after moving in place, and the forward movement of the bent beam is blocked by the friction block. The friction block is a cuboid block-shaped structure, the upper surface of the friction block is provided with three long cylindrical guide columns, the guide columns can be inserted into through holes in corresponding positions on the camber beam sleeve, disc springs are installed between the friction block and the camber beam sleeve in groups, and the friction block can move relative to the camber beam sleeve after being pressed under the action of the guide columns.

As shown in fig. 9, when the bending beam moves forward, the inclined surface of the head of the bending beam contacts with the inclined surface of the lower surface of the friction block, the two parts move relatively to each other and generate sliding friction on the contact surface, the head of the bending beam is pressed by the inclined surface contact to enable the friction block to compress the disc spring and move upwards, the more the forward movement of the bending beam is, the larger the pressing amount of the friction block and the disc spring is, and the larger the formed back pressure and friction force are.

The effect of this design is that elastic deformation and vibration that produce to rocket shell section or radome fairing structure play the modulus dissipation effect after complete set of supporting mechanism accomplishes the locking, the elastic deformation that rocket shell section or radome fairing structure produced can drive and produce relative motion between camber beam and the camber beam sleeve, the reverse motion of camber beam is blockked by the locking piece, its forward motion can make and produce relative friction between camber beam head inclined plane and the clutch blocks inclined plane, and the bigger frictional force of the forward motion volume of camber beam is also bigger, the reciprocal deformation of rocket shell section or radome fairing makes and produces repeated frictional contact and break away from between camber beam and the clutch blocks, produce frictional damping to the vibration of rocket shell section or radome fairing structure through the friction, make the vibration energy dissipate, reduce the vibration magnitude, thereby the safety of rocket structure is protected.

The invention has the advantages that: on the basis of meeting the requirements of geometric overall dimension and interface for mounting the repeatedly used rocket fairing and cabin section structure, the original structural form of the rocket structure such as a shell section or the fairing is not changed, and the overall rigidity of the structure is increased by adopting a movement mechanism. The folded state can be tightly attached to the inner wall of the cabin section structure, so that the occupation of space is reduced, and the installation space and the separation margin of the effective load are ensured. After the telescopic.

Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.