Compensation-type spacecraft separation device

Abstract

The present invention provides a compensation-type spacecraft separation device, which includes a mounting base plate, a pyrotechnic actuating device, and a spring separation device. The pyrotechnic actuating device and the spring separation device are both mounted on the mounting base plate. One end of the pyrotechnic actuating device is connected to the spacecraft, and the other end passes through the mounting base plate and is connected to the launch vehicle. The spring separation devices are evenly distributed along the circumferential direction of the mounting base plate, and the spring separation devices can move along the direction of the center line connecting them to the mounting base plate. The spring separation devices are used to drive the separation of the spacecraft and the launch vehicle. By adjusting the positions of the spring separation devices, the present invention can compensate and adjust the centroid distribution of the separated spacecraft, offset the separation disturbance caused by the deviation between the measured centroid of the spacecraft and the theoretical value, and completely compensate for the separation disturbance caused by the inconsistency in spring processing. It is simple to operate and lightweight, which helps to save a large amount of manpower and material resources.

Description

Technical Field

[0001] The present invention relates to the fields related to spacecraft separation and inter-stage separation. Specifically, it relates to a compensation-type spacecraft separation device. Background Art

[0002] With the development of space technology, spacecraft such as miniaturized satellites and micro interceptors are a major trend in future development. In order to ensure that multiple satellites separated by a single rocket do not collide with each other, and interceptors have high-precision and fast-response guidance and control requirements, higher requirements are put forward for the separation attitude.

[0003] The spring separation device is an important part of the spacecraft separation system, and its performance directly affects the separation speed, separation attitude, and separation reliability. Traditional separation devices control the separation attitude by measures such as selecting and matching separation springs and strictly controlling the matching accuracy of the guiding section. Selecting and matching separation springs requires mass production of products and then adapting and selecting from them, which seriously wastes manpower and material resources and cannot ensure that the spring processing is completely consistent. If the matching size of the guiding section, such as the clearance, is too small, the frictional resistance will affect the separation speed and does not meet the separation requirements.

[0004] The Chinese patent with the publication number CN103407585A discloses a spring separation device, which includes a housing. A piston is disposed in the housing, and a compression spring is disposed in the cavity between the piston and the bottom of the housing; on the other side of the piston in contact with the compression spring, a push rod is provided, and a through hole is provided at the top of the housing. The push rod can extend out of the housing through the through hole under the action of the compression spring.

[0005] The inventor believes that the prior art can only weaken the separation disturbance caused by the separation device itself, and cannot control the separation disturbance caused by the mass characteristics of the spacecraft itself. However, such disturbances are often key factors during spacecraft separation, which puts high requirements on its center of mass. Once the measured result of the center of mass position deviates too much from the theoretical value, the separation attitude cannot meet the control requirements, and the mission of the model cannot be successfully completed. Therefore, it is necessary to provide a compensation-type spacecraft separation device that can compensate for separation disturbances caused by factors such as inconsistent spring processing and deviation between the actual center of mass and the theoretical center of mass of the spacecraft. Summary of the Invention

[0006] Aiming at the defects in the prior art, the purpose of the present invention is to provide a compensation-type spacecraft separation device.

[0007] A compensation-type spacecraft separation device provided by the present invention includes a mounting base plate, a pyrotechnic actuating device, and a spring separation device. The pyrotechnic actuating device and the spring separation device are both mounted on the mounting base plate. One end of the pyrotechnic actuating device is connected to the spacecraft, and the other end passes through the mounting base plate and is connected to the carrier. The spring separation devices are evenly distributed along the circumference of the mounting base plate, and the spring separation devices can move along the direction of the center line connecting them to the mounting base plate. The spring separation devices are used to drive the separation of the spacecraft and the carrier.

[0008] Preferably, there are 4 spring separation devices, which are evenly distributed at 90° with the center of the mounting base plate as the origin.

[0009] Preferably, by moving the position of one or more of the spring separation devices, the separation disturbance caused by the deviation between the measured centroid and the theoretical value of the spacecraft can be offset.

[0010] Preferably, the spring separation device includes a guide rod, a base, and a compression spring. The guide rod passes through the base and is tightly installed on the base by cooperating with a first nut. The compression spring is sleeved on the base, and the guide rod and the base cooperate to compress the compression spring.

[0011] Preferably, the base includes a rectangular plate, and the four corners of the base are tightly installed on the mounting base plate by cooperating with screws and second nuts.

[0012] Preferably, a concave groove is provided on the mounting base plate, and the direction of the concave groove is the same as the direction of the center line connecting the spring separation device and the mounting base plate, and the screw can move in the concave groove.

[0013] Preferably, the spring separation device is installed on the side of the mounting base plate close to the spacecraft, and the spring separation device is not fixedly connected to the spacecraft.

[0014] Preferably, the pyrotechnic actuating device and the spring separation device are arranged at the same height.

[0015] Preferably, multiple pyrotechnic actuating devices are evenly arranged on the mounting base plate.

[0016] Preferably, an explosive bolt for pyrotechnics and a honeycomb buffer box are arranged inside the pyrotechnic actuating device. The explosive bolt for pyrotechnics is used to disconnect the connection between the spacecraft and the carrier, and the honeycomb buffer box is used to reduce the impact of the pyrotechnics on the spacecraft.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. By adjusting the position of the spring separation device, the present invention can compensate and adjust the centroid distribution of the separated spacecraft, offset the separation disturbance caused by the deviation between the measured centroid and the theoretical value of the spacecraft, and completely compensate for the separation disturbance caused by the inconsistent spring processing. It can ensure that the separation attitude disturbance of the spacecraft is within 1° / s, with simple operation and light weight, which helps to save a large amount of manpower and material resources.

[0019] 2. The present invention realizes the stage connection and unlocking through the pyrotechnic actuating device, and provides the separation power of the spacecraft through the spring separation device. The structure is simple and the installation is convenient, which helps to meet the separation attitude control requirements during separation and is applicable to various small spacecraft.

[0020] 3. The cooperation between the concave groove on the installation base plate and the spring separation device of the present invention helps to simplify the operation of adjusting the position of the spring separation device, and can select the appropriate number of pyrotechnic actuating devices and spring separation devices for installation according to the actual use situation. The structure is simple and the installation is convenient, which helps to improve the scope of application. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Other features, objects, and advantages of the present invention will become more apparent by reading the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0022] Figure 1 It is the top view mainly showing the compensation-type spacecraft separation device of the present invention;

[0023] Figure 2 It is the front view mainly showing the compensation-type spacecraft separation device of the present invention;

[0024] Figure 3 It is the cross-sectional schematic diagram mainly showing the spring separation device of the present invention;

[0025] Figure 4 It is mainly showing Figure 2 The enlarged view of the partial A of the present invention;

[0026] Figure 5 It is mainly showing Figure 1 The enlarged view of the partial B of the present invention;

[0027] Figure 6 It is the schematic diagram mainly showing the moving compensation principle of the spring separation device of the present invention.

[0028] As shown in the figure: installation base plate 1; pyrotechnic actuating device 2; spring separation device 3; base 4; guide rod 5; compression spring 6; first nut 7; screw 11; second nut 12; concave groove 13; first spring 31; second spring 32; third spring 33; fourth spring 34. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0029] The present invention will be described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several changes and improvements can still be made. These all belong to the protection scope of the present invention.

[0030] As Figure 1 and 2 shown, a compensation type spacecraft separation device provided by the present invention includes: a mounting base plate 1, a pyro-actuator 2, and a spring separation device 3. The pyro-actuator 2 and the spring separation device 3 are both mounted on the mounting base plate 1; one end of the pyro-actuator 2 is connected to the spacecraft, and the other end passes through the mounting base plate 1 and is connected to the launch vehicle; the spring separation devices 3 are evenly distributed along the circumference of the mounting base plate 1, and the spring separation devices 3 can move along the direction of the center connection line between them and the mounting base plate 1; the spring separation devices 3 are used to drive the separation of the spacecraft and the launch vehicle.

[0031] This application has the advantages of simple operation, light weight, etc., and conforms to the development direction of lightweight and miniaturization of spacecraft. Moreover, it can effectively solve the problems of excessive separation disturbance of the spacecraft and difficult attitude correction, and can ensure that the spacecraft meets the guidance and control requirements for rapid attitude correction. Compared with traditional separation devices, this application has the advantages of adjustable separation attitude, simple structure, easy installation, etc., and can effectively solve the problem that the separation attitude of small spacecraft is difficult to meet the control requirements during separation.

[0032] The pyro-actuator 2 follows the traditional multi-point inter-stage connection device, which is used to realize inter-stage connection and unlocking. The upper end is connected to the spacecraft, and the lower end is connected to the launch vehicle. The interior of the pyro-actuator 2 is provided with a pyrotechnic explosive bolt, which is fixed by a loading nut and can withstand various flight loads during flight. When the pyrotechnic device receives the separation signal, the explosive bolt disconnects, the spacecraft and the launch vehicle are unlocked, and reliable separation of the spacecraft is achieved under the action of the spring force. The interior of the pyro-actuator 2 is also provided with a honeycomb buffer box to reduce the impact of the pyrotechnic device on the spacecraft.

[0033] A plurality of pyro-actuators 2 are evenly arranged on the mounting base plate 1. The number of pyro-actuators 2 depends on the magnitude of the flight loads received by the spacecraft and the load-bearing capacity of the pyrotechnic devices used. If the flight loads are small and the selected pyrotechnic devices have a strong load-bearing capacity, the number of pyro-actuators 2 required is small; otherwise, a larger number is needed.

[0034] The pyro-actuator 2 and the spring separation device 3 are arranged at the same height to determine the compression spring distance.

[0035] The number of the spring separation devices 3 depends on the requirement for the relative separation speed of the spacecraft and the magnitude of the selected spring force. If the required relative separation speed is greater and the selected working load of the spring is smaller, the number of the spring separation devices 3 needed is more; otherwise, a smaller number is required. If it is necessary to compensate for the separation attitude with multiple degrees of freedom, at least 3 spring separation devices 3 are required, which are evenly distributed at 120°. If there are other numbers of spring separation devices 3, they can move along the direction of the center connection line between them and the mounting base plate 1.

[0036] In this application, only 4 spring separation devices 3 are taken as an example, which are evenly distributed at 90° with the center of the mounting base plate 1 as the origin.

[0037] The spring separation devices 3 are installed on the side of the mounting base plate 1 close to the spacecraft. The spring separation devices 3 are not fixedly connected to the spacecraft, and there is no need to leave any parts on the spacecraft, which is convenient for the lightweight flight of the spacecraft.

[0038] As Figures 3 - 5 shown, the spring separation device 3 includes a guide rod 5, a base 4 and a compression spring 6. The guide rod 5 passes through the base 4 and is tightly installed on the base 4 through cooperation with a first nut 7; the compression spring 6 is sleeved on the base 4, and the guide rod 5 and the base 4 cooperate to compress the compression spring 6 tightly. The compression spring 6 is used to provide the kinetic energy required for the separation of the spacecraft. The guide rod 5 provides a guiding function for the compression spring. The first nut 7 is used to fix the guide rod 5 on the ground to determine the spring compression height. When the spacecraft separates, the compression spring 6 pushes the spacecraft to separate, the compression spring 6 releases the stored potential energy, and the spacecraft obtains a relative separation speed and continues to fly to achieve separation.

[0039] The base 4 includes a rectangular plate. Four corners of the base 4 are tightly installed on the mounting base plate 1 through cooperation of screws 11 and second nuts 12. A concave groove 13 is arranged on the mounting base plate 1, and the direction of the concave groove 13 is consistent with the direction of the center connection line between the spring separation device 3 and the mounting base plate 1. Each spring separation device 3 is correspondingly provided with 2 corresponding concave grooves 13 on the base 4, and the screw 11 can move in the concave groove 13. By moving the installation positions of the screw 11 and the second nut 12 in the concave groove 13, the spatial positions of the respective spring separation devices 3 can be adjusted, so as to compensate for the separation disturbance caused by factors such as inconsistent spring processing and the deviation between the actual centroid and the theoretical centroid of the spacecraft.

[0040] The compensation is achieved through the following technical solutions: First, complete the measurement of the centroid of the spacecraft to clarify the deviation value between the actual centroid and the theoretical centroid of the spacecraft. Then measure the working loads of the respective compression springs 6 to clarify the specific distribution of the inconsistency of the respective compression springs 6. Then determine the installation positions of the respective spring separation devices 3 through the self-compensation function of the spring separation device 3, so as to complete the compensation for the separation attitude of the spacecraft.

[0041] As Figure 6 shown, the four spring separation devices 3 are evenly distributed around, namely the first spring 31, the second spring 32, the third spring 33 and the fourth spring 34. The theoretical centroid of the spacecraft projects onto the point O in the plane, and the actual centroid of the spacecraft projects onto the point O1 in the plane. Assume that the actual centroid of the spacecraft has deviations from the theoretical centroid point O in two directions, and the deviation distances are y1 and z1. Assume that at this time, only the first spring 31 and the second spring 32 are moved by y2 and z2, which can compensate for the disturbance caused by the separation due to the centroid deviation. According to the moment conservation, we can get:

[0042]

[0043] where F is the acting force of the four spring separation devices 3, then we have:

[0044]

[0045] That is, moving a certain spring separation device 3 by 4 times the distance in the direction of the centroid of the spacecraft itself can offset the separation disturbance caused by this centroid deviation.

[0046] If the first spring 31 and the third spring 33 in the Y direction are set as a group, and the second spring 32 and the fourth spring 34 in the Z direction are set as a group. Assume that at this time, the first spring 31 and the third spring 33 are moved by y2 and y3, and the second spring 32 and the fourth spring 34 are moved by z2 and z3, which can compensate for the disturbance caused by the separation due to the centroid deviation. According to the moment conservation, we can get:

[0047]

[0048] Then we have:

[0049]

[0050] That is, expanding the distance between a certain group of springs by 4 times the distance of the centroid deviation of the spacecraft itself can also completely offset the separation disturbance caused by the centroid deviation, effectively solving the separation disturbance caused by the centroid deviation of the spacecraft.

[0051] For the problem of separation disturbance caused by inconsistent spring processing, this method can also solve it, and the principle is as follows:

[0052] Assume that the acting forces of the four spring separation devices 3 are F1, F2, F3, and F4 respectively. If the first spring 31 and the third spring 33 in the Y direction are set as a group, and the second spring 32 and the fourth spring 34 in the Z direction are set as a group. Assume that the actual center of mass of the spacecraft coincides with the theoretical center of mass at this time. At this time, the first spring 31 and the third spring 33 need to be moved by y4 and y5, and the second spring 32 and the fourth spring 34 need to be moved by z4 and z5, which can compensate for the separation disturbance caused by inconsistent spring processing. According to the conservation of bending moment, we can get:

[0053]

[0054] Assume that y5 = z5 = 0, and only move one of the spring separation devices 3 in a group, we have:

[0055]

[0056] According to the national standard for spring processing, the spring processing error can generally be controlled within 5%. Then we have:

[0057] y4 ≤ 0.05L

[0058] z4 ≤ 0.05L

[0059] Therefore, only need to move the spring separation device 3 by a small distance, which can save a lot of manpower and material resources wasted by spring selection, and can completely compensate for the separation disturbance caused by inconsistent spring processing.

[0060] Thus, through this device, the two main interference items, namely the offset of the spacecraft's center of mass that causes disturbance to the spacecraft separation attitude and the insufficient spring consistency, have been completely compensated, and it can ensure that the spacecraft separation attitude disturbance is within 1° / s. For the separation disturbance caused by other error sources, it can also be compensated by this device. However, since the separation attitude disturbance is small, it will not be elaborated in detail in this application.

[0061] The separation attitude is not sensitive to the mass of the spacecraft itself and is applicable to various small spacecraft. There is no high requirement for the center of mass of the spacecraft, which is convenient for spacecraft design. The spacecraft separation attitude is not affected by the separation speed and can quickly complete attitude correction. It can compensate and adjust the center of mass distribution of the separated spacecraft and can offset the separation disturbance caused by the deviation between the measured center of mass and the theoretical value of the spacecraft. It can completely compensate for the separation disturbance caused by inconsistent spring processing and does not require the selection and matching of multiple springs, significantly saving manpower and material resources.

[0062] Working principle

[0063] The pyrotechnic actuating device 2 follows the traditional multi-point interstage connection device for realizing interstage connection and unlocking. The interior of the pyrotechnic actuating device 2 is provided with pyrotechnic explosive bolts, which are fixed by loading nuts and can withstand various flight loads during flight. When the pyrotechnic device receives the separation signal, the explosive bolts break, unlocking between the spacecraft and the carrier, and the spacecraft is reliably separated under the action of the spring force. The interior of the pyrotechnic actuating device 2 is also provided with a honeycomb buffer box for reducing the impact of the pyrotechnic device on the spacecraft. The compression spring 6 is used to provide the kinetic energy required for the separation of the spacecraft, the guide rod 5 provides a guiding function for the compression spring, and the first nut 7 is used to fix the guide rod 5 on the ground to determine the spring compression height. When the spacecraft separates, the compression spring 6 pushes the spacecraft to separate, the compression spring 6 releases the stored potential energy, and the spacecraft obtains a relative separation speed and continues to fly to achieve separation. By moving the installation positions of the moving screw 11 and the second nut 12 in the concave groove 13, the spatial positions of each spring separation device 3 can be adjusted, so as to compensate for the separation disturbances caused by factors such as inconsistent spring processing and the deviation between the actual center of mass and the theoretical center of mass of the spacecraft.

[0064] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0065] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other.

Claims

1. A compensation type spacecraft separation device, characterized in that, Comprising: An installation base plate (1), a pyrotechnic actuating device (2) and a spring separation device (3), wherein the pyrotechnic actuating device (2) and the spring separation device (3) are both installed on the installation base plate (1); One end of the pyrotechnic actuating device (2) is connected to the spacecraft, and the other end passes through the installation base plate (1) and is connected to the launch vehicle; The spring separation devices (3) are evenly distributed along the circumferential direction of the installation base plate (1), and the spring separation devices (3) can move along the direction of the central connection line between them and the installation base plate (1); The spring separation device (3) is used to drive the separation of the spacecraft and the launch vehicle; There are 4 spring separation devices (3), which are evenly distributed at 90° with the center of the installation base plate (1) as the origin; By moving the positions of one or more of the spring separation devices (3), the separation disturbance caused by the deviation between the measured centroid of the spacecraft and the theoretical value can be offset; The spring separation device (3) includes a guide rod (5), a base (4) and a compression spring (6), the guide rod (5) passes through the base (4) and is fixedly installed on the base (4) through cooperation with a first nut (7); The compression spring (6) is sleeved on the base (4), and the guide rod (5) and the base (4) cooperate to compress the compression spring (6); The base (4) includes a rectangular plate, and the four corners of the base (4) are fixedly installed on the installation base plate (1) through cooperation of screws (11) and second nuts (12); A concave groove (13) is provided on the installation base plate (1), and the direction of the concave groove (13) is consistent with the direction of the central connection line between the spring separation device (3) and the installation base plate (1), and the screw (11) can move in the concave groove (13); The spring separation device (3) is installed on the side of the installation base plate (1) close to the spacecraft, and the spring separation device (3) has no fixed connection with the spacecraft.

2. The compensating spacecraft separation device according to claim 1, wherein The pyrotechnic actuating device (2) and the spring separation device (3) are arranged at the same height.

3. The compensation type spacecraft separation device according to claim 1, characterized in that A plurality of the pyrotechnic actuating devices (2) are evenly arranged on the installation base plate (1).

4. The compensation type spacecraft separation device according to claim 1, characterized in that, The interior of the pyrotechnic actuating device (2) is provided with a pyrotechnic explosive bolt and a honeycomb buffer box. The pyrotechnic explosive bolt is used to disconnect the connection between the spacecraft and the launch vehicle, and the honeycomb buffer box is used to reduce the impact of the pyrotechnics on the spacecraft.

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