A tug and method for rapidly deploying a large space mechanism

Abstract

A large-scale space mechanism rapid deployment tractor and method, the tractor comprises a head, an ignition device, a shell, a solid propellant grain, an end face flame retardant layer, a central flame retardant layer, an insulation layer, a cooling column and a tail nozzle; an ignition device is arranged in the middle of the head, the end face flame retardant layer, the solid propellant grain, the central flame retardant layer, the insulation layer and the cooling column are arranged in the shell between the head and the tail nozzle, the cooling column is installed between the solid propellant grain and the tail nozzle, the solid propellant grain is coated on the outer side of the central flame retardant layer, the heating ignition head of the ignition device extends from the central flame retardant layer and is attached to the end face of the solid propellant connected to the cooling column, an end face flame retardant layer is arranged between the solid propellant grain and the head, and the insulation layer is coated on the outer side of the solid propellant. The invention has a compact structure, is easy to install and use, can achieve a propulsion force of ten Newtons and an effective working time of seconds, and improves the driving efficiency of the mechanism deployment.

Description

Technical Field

[0001] The invention relates to a large-scale space mechanism rapid deployment tug and method, belonging to the field of space propulsion. Background Art

[0002] At present, common driving technologies for deployable space mechanisms mainly include distributed motor drive, distributed elastic drive, disk-pressure elastic drive, and mass block ejection deployment. They usually have problems such as complex structure, large mass, large volume, and slow response speed, and it is difficult to meet application requirements in scenarios that require rapid response. Common propulsion systems mainly include cold gas propulsion, electric propulsion, and chemical propulsion technologies, but cold gas propulsion and electric propulsion technology systems are complex, large in volume, and have low driving efficiency. Chemical propulsion technologies include solid propulsion and liquid propulsion, and their common thrusts are all in the kilonewton level. In addition, the temperature of the gas ejected from the tail nozzle is very high, making them difficult to apply to the deployment and expansion of space mechanisms. Summary of the invention

[0003] The present invention overcomes the shortcomings of the prior art and provides a tug and method for rapidly deploying a large space mechanism. The tug has a compact structure, can avoid excessively high exhaust gas temperature of the propeller, can improve the use efficiency of the shell space, and can reduce the exhaust gas temperature of the tug from both chemical and physical aspects to meet the deployment and deployment requirements of a large deployable space mechanism.

[0004] A large-scale space mechanism rapid deployment tractor comprises a head, an ignition device, a shell, a solid propellant charge, an end face flame retardant layer, a central flame retardant layer, an insulating layer, a cooling column and a tail nozzle; the head and the tail nozzle are respectively sealed and fixed at both ends in the shell, an ignition device is arranged in the middle of the head, the end face flame retardant layer, the solid propellant charge, the central flame retardant layer, the insulating layer and the cooling column are arranged in the shell between the head and the tail nozzle, the cooling column is installed between the solid propellant charge and the tail nozzle, the solid propellant charge is coated on the outer side of the central flame retardant layer, the heating ignition head of the ignition device extends from the central flame retardant layer and is attached to the end face of the solid propellant charge connected to the cooling column, an end face flame retardant layer is arranged between the solid propellant charge and the head, and the insulating layer is coated on the outer side of the solid propellant.

[0005] A method for installing a large-scale space mechanism rapid deployment tractor, the method steps are as follows: first install a first sealing ring in a first groove on the outer side surface of a head, place the head in one end of a shell, make a front retaining ring snap into the front groove of the shell 6, an ignition device is connected to the head by a thread, a solid propellant grain, an end face flame retardant layer, a central flame retardant layer 8 and a heat insulation layer are assembled as a whole and installed into the shell from the other end of the shell, an ignition head of the ignition device is passed through the central channel of the central flame retardant layer and is tightly attached to the end face of the solid propellant grain, a cooling column is installed into the shell from the other end of the shell and is tightly attached to the end face of the solid propellant grain, a second sealing ring is installed into the second groove on the outer side surface of the tail nozzle, the nozzle of the tail nozzle is installed into the other end of the shell, a gasket is installed into the shell tightly attached to the step end face of the tail nozzle, a rear retaining ring is snapped into the rear groove of the shell, and assembly is completed.

[0006] A method for using a tug for rapidly deploying a large space mechanism comprises fixing the tug to a position of the large space mechanism that needs to be deployed, a computer sending an ignition command to an ignition device, the ignition head of the ignition device heats up, and when the ignition point of a solid propellant grain is reached, the solid propellant grain burns to generate a large amount of high-temperature and high-pressure combustion gas, which is filtered and cooled by a cooling column and then discharged through a tail nozzle to pull the large space mechanism to deploy.

[0007] Compared with the prior art, the present invention has the following beneficial effects:

[0008] 1. The present invention has a compact structure and is easy to install and use. Under the same conditions, it reduces the volume and mass of the space mechanism rapid deployment tractor and improves the driving efficiency of the mechanism deployment.

[0009] 2. Under the premise of small mass and volume, it can achieve a propulsion force of ten Newtons and an effective working time of seconds. The gas temperature ejected by the solid propellant column is low, which will not cause damage to the towed and deployed space mechanism, and can realize the rapid deployment of large space mechanisms.

[0010] 3. The startup time is very short, meeting the space agency’s needs for rapid response.

[0011] 4. The modular design of the tractor itself or the tail nozzle structure can meet the deployment requirements of space mechanisms.

[0012] The technical solution of the present invention is further described below in conjunction with the accompanying drawings and embodiments: BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 A three-dimensional diagram of a large-scale spatial mechanism for rapidly unfolding a tug of the present invention viewed from one direction;

[0014] Figure 2 A three-dimensional view of the large-scale spatial mechanism for rapidly deploying the tug of the present invention viewed from another direction;

[0015] Figure 3 It is a main cross-sectional view of the large-scale spatial mechanism rapid deployment tug of the present invention;

[0016] Figure 4 This is the structural diagram of the tail nozzle. DETAILED DESCRIPTION

[0017] The following embodiments of the technical solution of the present invention are described in detail in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present invention, and are therefore only used as examples, and cannot be used to limit the protection scope of the present invention.

[0018] It should be noted that, unless otherwise specified, the technical terms or scientific terms used in this application should have the common meanings understood by those skilled in the art to which the present invention belongs.

[0019] like Figure 1-Figure 3 As shown, a large-scale space mechanism rapid deployment tractor comprises a head 1, an ignition device 2, a shell 6, a solid propellant charge 7, an end surface flame retardant layer 3, a central flame retardant layer 8, an insulation layer 9, a cooling column 10 and a tail nozzle 11;

[0020] The end cap 1 and the tail nozzle 11 are sealed and fixed at both ends of the shell 6, respectively. An ignition device 2 is arranged in the middle of the end cap 1. The end face flame retardant layer 3, the solid propellant grain 7, the central flame retardant layer 8, the insulation layer 9 and the cooling column 10 are arranged in the shell 6 between the end cap 1 and the tail nozzle 11. The cooling column 10 is installed between the solid propellant grain 7 and the tail nozzle 11. The solid propellant grain 7 is coated on the outer side of the central flame retardant layer 8. The heating ignition head of the ignition device 2 extends from the central flame retardant layer 8 and is attached to the end face of the solid propellant grain 7 connected to the cooling column 10. The end face flame retardant layer 3 is arranged between the solid propellant grain 7 and the end cap 1, and the insulation layer 9 is coated on the outer side of the solid propellant 7. A threaded hole for installing the ignition device 2 is opened in the center of the end cap 1.

[0021] The rapid deployment of the tug for large space structures based on the above implementation scheme can greatly improve the utilization efficiency of the shell space. At the same time, a gas-producing agent with low combustion temperature and slow burning rate is used as a solid propellant, and a cooling layer is added in the combustion chamber to reduce the temperature of the exhaust gas from the tug from both chemical and physical aspects to meet the deployment requirements of large space deployable structures.

[0022] The end flame retardant layer 3 is in close contact with the end face of the solid propellant charge 7, thereby limiting the effective combustion area of ​​the solid propellant. The central flame retardant layer 8 is installed at the center of the solid propellant to limit the effective combustion area of ​​the solid propellant charge 7. The central channel of the central flame retardant layer 8 is used for the ignition head of the ignition device 2 to pass through and is arranged on the right end face of the solid propellant charge 7. The insulation layer 9 covers the outer cylindrical surface of the solid propellant 7, which limits the effective combustion area of ​​the solid propellant and has a heat-insulating effect. The head 1 and the tail nozzle 11 are respectively sealed with the shell 6 to prevent gas leakage, reduce the pressure, and have no injection effect, which cannot meet the use requirements of driving the deployment of large space mechanisms. The ignition device 2 uses electrode energization to ignite.

[0023] This embodiment uses solid gas-producing powder with low combustion temperature and slow burning speed as the solid propellant powder column 7, which can be ignited and burned violently under high temperature conditions to produce a large amount of non-toxic and non-corrosive gas to meet the requirements of driving the deployment of large space mechanisms.

[0024] Preferably, the solid propellant grain 7 is a mixture of a solid oxidant and a solid reductant, which can be ignited and burn violently under high temperature conditions to produce a large amount of non-toxic and non-corrosive gas.

[0025] As a possible implementation, the solid propellant grain 7 has a low combustion temperature and a slow burning rate, similar to the solid gas generating powder built into the airbag, and the end face of the grain is annular, and the combustion mode is end face combustion. This can meet the use requirements of driving the deployment of large space mechanisms. Optionally, the solid propellant grain 7 uses nitroguanidine type gas generating powder.

[0026] Furthermore, the material of the end face flame retardant layer 3 and the central flame retardant layer 8 is a flame resistant barrier material, such as polyvinyl chloride, polyvinylidene chloride, fluorine-containing plastics and other materials; the material of the insulation layer 9 is a flame resistant insulation barrier material, such as asbestos, slag wool, expanded vermiculite, diatomaceous earth bricks, expanded perlite, high-temperature refractory fibers and other insulating refractory materials.

[0027] Furthermore, based on the above-mentioned flame-resistant heat-insulating barrier material, the shell 6 is made of metal.

[0028] As a possible implementation, the cooling column 10 is a flat columnar structure formed by pressing steel wire, has cooling and filtering functions, and is used to cool the gas generated by the combustion of the solid propellant grain 7 .

[0029] Alternatively, if Figure 3As shown, the shell 6 is a stepped cylindrical barrel structure, and grooves are formed on the inner walls at both ends of the shell 6, which are respectively used to install the front retaining ring 4 and the rear retaining ring 14, and the head 1 and the tail nozzle 11 are respectively clamped by the front retaining ring 4 and the rear retaining ring 14. Based on the above, the solid propellant grain 7 and the cooling column 10 are both cylindrical, and the central flame retardant layer 8 is a hollow cylindrical structure. The central channel is used to arrange the ignition head of the ignition device 2 to pass through so as to be arranged with the right end face of the solid propellant grain 7.

[0030] As another possible implementation, the head 1 and the tail nozzle 11 are respectively interference fit with the shell 6, and the head 1 and the tail nozzle 11 are firmly fixed by the interference fit.

[0031] The shell 6 is a stepped cylindrical barrel structure, and grooves are provided on the inner walls at both ends of the shell 6, which are used to install the front retaining ring 4 and the rear retaining ring 14 respectively. The head 1 and the tail nozzle 11 are clamped by the front retaining ring 4 and the rear retaining ring 14 respectively. The gasket 13 is installed between the tail nozzle 11 and the rear retaining ring 14, and has the functions of pressing and sealing to ensure that the large space mechanism can be driven to unfold.

[0032] Based on the above embodiment, the outer diameter of the housing 6 is 30-35 mm and the length is 150-200 mm. Under the same conditions, the volume and mass of the space mechanism rapid deployment tug are reduced. The tug of the above embodiment can be installed on a steerable base to meet the spatial deployment of large-scale deployable space mechanisms with different deployment requirements.

[0033] As a possible implementation, based on the above-mentioned tug, a method for installing a large-scale space mechanism rapid deployment tug is also provided, the method steps are: firstly, a first sealing ring 5 is installed in a first groove on the outer side of the head 1, the head 1 is placed in one end of the shell 6, the front retaining ring 4 is inserted into the front groove of the shell 6, the ignition device 2 is connected to the head 1 by threads, the solid propellant charge 7, the end face flame retardant layer 3, the central flame retardant layer 8 and the insulation layer 9 are assembled as a whole, and the shell 6 is installed from the other end of the shell 6. The ignition head of the ignition device 2 is passed through the central channel of the central flame retardant layer 8 and is closely attached to the end face of the solid propellant grain 7. The cooling column 10 is installed into the shell 6 from the other end of the shell 6 and is closely attached to the end face of the solid propellant grain 7. The second sealing ring 12 is installed into the second groove on the outer side of the tail nozzle 11, and the nozzle of the tail nozzle 11 is installed into the other end of the shell 6. The gasket 13 is installed into the shell 6 and is closely attached to the step end face of the tail nozzle 11. The rear retaining ring 14 is inserted into the rear groove of the shell 6, and the assembly is completed.

[0034] The rapid deployment tug for large space structures obtained based on the above-mentioned implementation method can greatly improve the utilization efficiency of the shell space. At the same time, gas-producing powder with low combustion temperature and slow burning rate is used as solid propellant, and a cooling layer is added in the combustion chamber to reduce the temperature of the exhaust gas of the tug from both chemical and physical aspects to meet the deployment requirements of large space deployable structures.

[0035] A method for using a tractor for rapid deployment of a large space mechanism is also provided. The method for using the tractor is as follows: the tractor is fixed to the position of the large space mechanism that needs to be deployed, and the computer sends an ignition command to the ignition device 2. The ignition head of the ignition device 2 heats up. When the ignition point of the solid propellant grain 7 is reached, the solid propellant grain 7 burns to generate a large amount of high-temperature and high-pressure combustion gas, which is filtered and cooled by the cooling column 10 and then discharged through the tail nozzle 11 to pull the large space mechanism to deploy. The large space mechanism is, for example, a large triangular prism extension arm. The tractor of this embodiment is arranged at both ends of the large space mechanism.

[0036] The tail nozzle 11 based on the above implementation scheme includes a nozzle 11-1 and a discharge pipe 11-2 which are connected as one body. The outer shape of the nozzle 11-1 is cylindrical, and the inner cavity of the nozzle is a conical surface which tapers toward the outlet. The outer shape of the discharge pipe 11-2 is a tapered truncated cone, and the discharge inner cavity is a conical surface which gradually expands toward the outlet. A nozzle 11-3 which connects the inner cavity surface of the nozzle and the inner cavity surface of the discharge pipe is provided between the nozzle 11-1 and the discharge pipe 11-2. A step surface is provided at the joint between the nozzle 11-1 and the discharge pipe 11-2, and a gasket 13 and a rear retaining ring 14 are clamped on the step surface to play a positioning role.

[0037] The combustion of the solid propellant grain 7 generates a large amount of high-temperature and high-pressure combustion gas, which is filtered and cooled by the cooling column 10, and then increases in kinetic energy through the nozzle 11-1 of the tail nozzle 11. After passing through the nozzle 11-3, it is instantly discharged from the discharge cavity with a gradually expanding cross-section, and the kinetic energy is reduced, thereby achieving the purpose of pulling the large space mechanism to unfold.

[0038] The present invention has been disclosed as above with preferred implementation cases, but it is not used to limit the present invention. Any technician familiar with the profession can make slight changes or modifications to equivalent implementation cases with equivalent changes by using the above-disclosed structures and technical contents without departing from the scope of the technical solution of the present invention, which still fall within the scope of the technical solution of the present invention.

Claims

1. A large-scale space mechanism rapid deployment tug, characterized by: It comprises a head (1), an ignition device (2), a shell (6), a solid propellant charge (7), an end surface flame retardant layer (3), a central flame retardant layer (8), a heat insulation layer (9), a cooling column (10) and a tail nozzle (11); The end cap (1) and the tail nozzle (11) are respectively sealed and fixed at two ends of the shell (6); an ignition device (2) is arranged in the middle of the end cap (1); an end surface flame retardant layer (3), a solid propellant grain (7), a central flame retardant layer (8), a heat insulating layer (9) and a cooling column (10) are arranged in the shell (6) between the end cap (1) and the tail nozzle (11); the cooling column (10) is installed between the solid propellant grain (7) and the tail nozzle (11); the solid propellant grain (7) is coated on the outer side of the central flame retardant layer (8); a heating ignition head of the ignition device (2) extends from the central flame retardant layer (8) and is attached to the end surface of the solid propellant (7) connected to the cooling column (10); an end surface flame retardant layer (3) is arranged between the solid propellant grain (7) and the end cap (1); and the heat insulating layer (9) is coated on the outer side of the solid propellant grain (7).

2. A large-scale space mechanism rapid deployment tug according to claim 1, characterized in that: The solid propellant grain (7) is a mixture of a solid oxidant and a solid reductant, which can be ignited and burn violently under high temperature conditions to produce a large amount of non-toxic and non-corrosive gas.

3. The large-scale space mechanism rapid deployment tug according to claim 1, characterized in that: The solid propellant grain (7) is a solid gas-generating powder with a low combustion temperature and a slow burning rate. The end face of the grain is annular and the combustion mode is end face combustion.

4. The large-scale space mechanism rapid deployment tug according to claim 1, characterized in that: The material of the end surface flame retardant layer (3) and the central flame retardant layer (8) is a flame resistant barrier material, and the material of the heat insulating layer (9) is a flame resistant heat insulating barrier material.

5. The large-scale space mechanism rapid deployment tug according to claim 1, characterized in that: The shell (6) is made of metal.

6. The large-scale space mechanism rapid deployment tug according to claim 1, characterized in that: The cooling column (10) is a flat columnar structure formed by pressing steel wire.

7. The large-scale space mechanism rapid deployment tug according to claim 1, characterized in that: The sealing head (1) and the tail nozzle (11) are respectively interference fit with the shell (6).

8. The large-scale space mechanism rapid deployment tug according to claim 1, characterized in that: The shell (6) is a stepped cylindrical barrel structure. The inner walls at both ends of the shell (6) are provided with grooves for mounting a front retaining ring (4) and a rear retaining ring (14), respectively. The end cap (1) and the tail nozzle (11) are clamped by the front retaining ring (4) and the rear retaining ring (14), respectively.

9. A method for installing a large-scale spatial mechanism rapid deployment tug as claimed in any one of claims 1 to 8, characterized in that: The method comprises the following steps: firstly, installing a first sealing ring (5) in a first groove on the outer side of a sealing head (1), placing the sealing head (1) in one end of a housing (6), allowing a front retaining ring (4) to be inserted into a front groove of the housing (6), connecting an ignition device (2) to the sealing head (1) by means of threads, assembling a solid propellant charge (7), an end surface flame retardant layer (3), a central flame retardant layer (8) and a heat insulating layer (9) as a whole, and inserting the solid propellant charge (7), an end surface flame retardant layer (3), a central flame retardant layer (8) and a heat insulating layer (9) into the housing (6) from the other end of the housing (6), and inserting an ignition head of the ignition device (2) through the central flame retardant layer (8 ) and is closely attached to the end face of the solid propellant grain (7); the cooling column (10) is installed into the shell (6) from the other end of the shell (6) and is closely attached to the end face of the solid propellant grain (7); the second sealing ring (12) is installed into the second groove on the outer side of the tail nozzle (11); the nozzle of the tail nozzle (11) is installed into the other end of the shell (6); the gasket (13) is installed into the shell (6) and is closely attached to the step end face of the tail nozzle (11); the rear retaining ring (14) is inserted into the rear groove of the shell (6); and the assembly is completed.

10. A method for using the large-scale spatial mechanism rapid deployment tug as claimed in any one of claims 1 to 8, characterized in that: The method comprises the following steps: fixing the tractor to the position of the large space structure that needs to be deployed, the computer sending an ignition command to the ignition device (2), the ignition head of the ignition device (2) heating up, and when the ignition point of the solid propellant grain (7) is reached, the solid propellant grain (7) burns to generate a large amount of high-temperature and high-pressure combustion gas, which is filtered and cooled by the cooling column (10) and then discharged through the tail nozzle (11), thereby pulling the large space structure to deploy.

Images