阅读说明：本技术 用于航天器防隔热及分离试验的压紧释放机构 (A compress tightly release mechanism for spacecraft is prevented insulating against heat and separation test ) 是由 李民民 李广会 寇鑫 王朋军 周献齐 何小军 王宏亮 王岳 赵政社 赵飞 张建明 于 2019-10-25 设计创作，主要内容包括：本发明涉及一种用于航天器防隔热及分离试验的压紧释放机构,目的是为了解决现有技术中存在的发动机点火过程中试验产品无法牢靠的固定,分离前又不能可靠打开的问题。本发明包括固定支架、多套压紧释放装置、承力凸台、控制系统；固定支架包括支持框架以及固定在支撑框架上的上面板；压紧释放装置包括液压缸、压板；压板为L型,其拐角处与固定支架的一侧框架铰接,其上端用于将下底板压紧在上面板上,其下端与液压缸的活塞杆铰接；压板上端位于最高位置时其边缘位于航天器L型安装架下底板的外侧；液压缸的缸体与固定支架另一侧框架铰接；承力凸台设置在固定支架的上面板上,用于与下底板上的承力卡槽配合；控制系统用于控制液压缸运动。(The invention relates to a compression release mechanism for a spacecraft heat insulation and separation test, and aims to solve the problems that a test product cannot be firmly fixed in the ignition process of an engine and cannot be reliably opened before separation in the prior art. The invention comprises a fixed support, a plurality of sets of compression release devices, a force bearing boss and a control system; the fixed bracket comprises a supporting frame and an upper panel fixed on the supporting frame; the pressing release device comprises a hydraulic cylinder and a pressing plate; the pressing plate is L-shaped, the corner of the pressing plate is hinged with a side frame of the fixed support, the upper end of the pressing plate is used for pressing the lower bottom plate on the upper panel, and the lower end of the pressing plate is hinged with a piston rod of the hydraulic cylinder; when the upper end of the pressure plate is positioned at the highest position, the edge of the pressure plate is positioned at the outer side of the lower bottom plate of the L-shaped mounting rack of the spacecraft; the cylinder body of the hydraulic cylinder is hinged with the frame at the other side of the fixed bracket; the bearing boss is arranged on the upper panel of the fixed support and is used for being matched with the bearing clamping groove on the lower bottom plate; the control system is used for controlling the movement of the hydraulic cylinder.)

1. A compress tightly release mechanism for spacecraft is prevented insulating against heat and separation test, its characterized in that: comprises a fixed support (1), a plurality of sets of pressing and releasing devices (2), a force bearing boss (3) and a control system;

the fixed bracket (1) comprises a supporting frame and an upper panel (11) fixed on the supporting frame; the bottom of the supporting frame is provided with a plurality of threaded holes;

the pressing and releasing device (2) comprises a hydraulic cylinder (21) and a pressing plate (22);

the pressing plate (22) is L-shaped, the corner of the pressing plate is hinged with a frame on one side of the fixed support (1) through a pressing plate rotating shaft (23), the upper end of the pressing plate is used for pressing a lower bottom plate (4) of the L-shaped mounting rack of the spacecraft onto the upper panel (11), and the lower end of the pressing plate is hinged with a piston rod (211) of a hydraulic cylinder; the edge of the upper end of the pressure plate (22) is positioned at the outer side of the lower bottom plate (4) of the L-shaped mounting rack of the spacecraft when the upper end is positioned at the highest position;

the cylinder body (212) of the hydraulic cylinder (21) is hinged with the other side frame of the fixed support (1); the bearing capacity of the hydraulic cylinder (21) is more than 24 kN;

the bearing boss (3) is arranged on an upper panel (11) of the fixed support (1) and is used for being matched with a bearing clamping groove (41) on a lower bottom plate (4) of the L-shaped mounting rack of the spacecraft;

the control system is used for controlling the movement of the hydraulic cylinder (21).

2. The compression and release mechanism for spacecraft insulation and separation tests of claim 1, wherein: four sets of the compaction and release devices (2) are arranged;

four sets of pressing and releasing devices (2) are uniformly arranged along the length direction of the upper panel (11).

3. The compression and release mechanism for spacecraft insulation and separation tests according to claim 1 or 2, wherein: the size of the bearing boss (3) is smaller than that of the bearing clamping groove (41).

4. The compression and release mechanism for spacecraft insulation and separation tests of claim 3, wherein: and reinforcing ribs (221) are arranged on the pressing plate (22).

5. The compression and release mechanism for spacecraft insulation and separation tests of claim 4, wherein: the material of the pressing plate (22) is 40Cr, the maximum stress is 63.7MPa, and the maximum deformation is 0.19 mm.

6. The compression and release mechanism for spacecraft insulation and separation tests of claim 5, wherein: the number of the bearing bosses (3) is two.

7. The compression and release mechanism for spacecraft insulation and separation tests of claim 6, wherein: the hydraulic cylinder (21) is an electric hydraulic cylinder.

Technical Field

The invention relates to an anti-heat insulation and separation test, in particular to a compressing and releasing mechanism for an anti-heat insulation and separation test of a spacecraft.

Background

With the progress and development of science and technology, higher requirements are put forward on the high-speed maneuvering performance and accuracy of the aircraft model. In order to verify the reliability of a power system of an aircraft of a certain model and the correctness and harmony of a separation time sequence, heat insulation prevention and separation tests simulating real use conditions and environments need to be developed. In the heat insulation prevention test process, a test product needs to be fixed, and after the heat insulation prevention test is finished, the hoisting buffer system is started to hoist the test product, so that a separation test is carried out.

As the engine needs to be subjected to an ignition test in the ground thermal environment assessment process of the test product, the thrust generated by the engine needs to be transferred to the mobile test platform by a special mechanism. After the ground ignition test is finished, the special mechanism is opened through the remote control system, and when the hoisting system hoists the test product, the special mechanism can not influence the direct hoisting of the product. The ground and the separation test do not allow the operator to operate on the foreground, so the structure, the precision and the control requirements of the special clamp are higher, and the prior art can not achieve the purpose.

Disclosure of Invention

The invention aims to solve the problems that a test product cannot be firmly fixed and cannot be reliably opened before separation in the ignition process of an engine in the prior art, and provides a compression release mechanism for a spacecraft heat insulation prevention and separation test.

The invention discloses a compressing and releasing mechanism for a spacecraft heat insulation and separation test, which is characterized in that: comprises a fixed support, a plurality of sets of compression release devices, a force bearing boss and a control system;

the fixed bracket comprises a supporting frame and an upper panel fixed on the supporting frame; the bottom of the supporting frame is provided with a plurality of threaded holes;

the pressing release device comprises a hydraulic cylinder and a pressing plate;

the pressure plate is L-shaped, the corner of the pressure plate is hinged with a side frame of the fixed support through a pressure plate rotating shaft, the upper end of the pressure plate is used for pressing a lower bottom plate of the L-shaped mounting rack of the spacecraft onto the upper panel, and the lower end of the pressure plate is hinged with a piston rod of the hydraulic cylinder; the edge of the upper end of the pressure plate is positioned on the outer side of the lower bottom plate of the L-shaped mounting rack of the spacecraft when the upper end of the pressure plate is positioned at the highest position;

the cylinder body of the hydraulic cylinder is hinged with the frame on the other side of the fixed support; the bearing capacity of the hydraulic cylinder is more than 24 kN;

the force bearing boss is arranged on the upper panel of the fixed support and is used for being matched with a force bearing clamping groove on the lower bottom plate of the L-shaped mounting frame of the spacecraft;

the control system is used for controlling the hydraulic cylinder to move.

Further, in order to enhance the compression effect, the compression release device is provided with four sets;

four sets of pressing and releasing devices are uniformly arranged along the length direction of the upper panel.

Furthermore, in order to enable the bearing clamping groove on the lower base plate of the L-shaped mounting frame to be smoothly matched with and quickly separated from the bearing boss, the size of the bearing boss is smaller than that of the bearing clamping groove.

Further, in order to reinforce the pressure plate, reinforcing ribs are arranged on the pressure plate.

Further, the pressing plate is made of 40Cr, the maximum stress is 63.7MPa, and the maximum deformation is 0.19 mm.

Furthermore, the number of the bearing bosses is two.

Further, the hydraulic cylinder is an electric hydraulic cylinder.

The invention has the beneficial effects that:

1. the invention adopts the compressing and releasing device to compress or release the L-shaped mounting rack of the spacecraft, controls the hydraulic cylinder to operate through the control system, and drives the pressing plate to compress or open through the piston rod on the hydraulic cylinder, so that the structure has the advantages of small impact force, large pressing force, stable state and reliable operation of compressing or opening.

2. According to the invention, when the pressing plate is pressed, the two force bearing bosses on the upper panel are matched with the force bearing clamping grooves on the lower bottom plate of the L-shaped mounting frame of the spacecraft, so that the relative position of the L-shaped mounting frame and the upper panel of the fixed support is guided, and the thrust from an engine to the L-shaped mounting frame is borne, so that the movement of the L-shaped mounting frame of the spacecraft is limited, the spacecraft is more reliably fixed, and the requirement of quick and smooth separation before hoisting is met.

3. The pressure plate is provided with the reinforcing ribs, so that the strength of the pressure plate is more reliable, and the pressing reliability is enhanced.

Drawings

FIG. 1 is a schematic structural diagram of a compression release mechanism for a spacecraft insulation and separation test according to the present invention;

FIG. 2 is a schematic view of the construction of the present invention in which the press plate presses against the lower base plate;

FIG. 3 is a schematic view of the construction of the hold-down release lower base of the present invention.

In the figure, 1-a fixed support, 11-an upper panel, 2-a compaction release device, 21-a hydraulic cylinder, 211-a piston rod, 212-a cylinder body, 22-a pressing plate, 221-a reinforcing rib, 23-a pressing plate rotating shaft, 3-a bearing boss, 4-a lower bottom plate and 41-a bearing clamping groove.

Detailed Description

To make the objects, advantages and features of the present invention more apparent, the following detailed description of the present invention will be made with reference to the accompanying drawings and specific embodiments. The advantages and features of the present invention will become more apparent from the following detailed description. It should be noted that: the drawings are in simplified form and are not to precise scale, the intention being solely for the convenience and clarity of illustrating embodiments of the invention; second, the structures shown in the drawings are often part of actual structures.