Pneumatic cold ejection device of extraterrestrial celestial body ascender

Abstract

The invention discloses a pneumatic cold ejection device of an extraterrestrial celestial body ascender, and belongs to the field of deep space exploration. The device comprises a heat preservation box body, a heat preservation box cover, a pneumatic piston assembly, an air source assembly, a pressing assembly and a launching guiding and adjusting assembly. The pneumatic piston assembly is composed of a second-stage piston, a first-stage piston, a sealing ring, an inflation connector, a first-stage piston blanking cap, a first-stage piston cylinder, a buffering cushion, an exhaust guide cap and a first-stage piston end cover. The pressing assembly is composed of a bullet lifting beam, a bearing beam, a firer unlocking device and an ascender pressing piece. The launching guiding and adjusting assembly is composed of a guiding support, a guiding wheel and a pressure adjusting valve. The ascender is conveyed to a preset height in a pneumatic cold ejection mode, and ignition take-off conditions are provided; the compression problem of the launching section is solved based on a compression-heat preservation integrated device; based on an adjustable pneumatic piston assembly and an air source assembly, power is provided for launching, and adaptation to the terrain is achieved; the ejection device is prevented from rolling based on the guide assembly, and pneumatic cold ejection of the ascender is achieved.

Description

Technical Field

[0001] The invention relates to a pneumatic cold ejection device for an extraterrestrial ascender, belonging to the field of deep space exploration. Background Art

[0002] In the extraterrestrial sampling and return mission, the ascender needs to carry the extraterrestrial samples from the surface of the extraterrestrial body and take off and send it to the predetermined orbit. The sample container will be released at an appropriate time in orbit, and the orbit-return assembly will capture it and transfer it to the returner. Constrained by the configuration layout of the entry module, the ascender is usually arranged in a horizontal state on the landing platform and does not have the conditions for direct ignition and takeoff from the extraterrestrial body. The plan for establishing the take-off state of the extraterrestrial body is constrained by the requirements of the center of mass of the entry module, and it is also necessary to consider the adaptability to the landing attitude and the influence of the plume. The products of the related launch support system must also adapt to the low temperature and dust environment on the surface of the extraterrestrial body. Therefore, the launch plan of the ascender to an extraterrestrial body is a difficult point in the development of the extraterrestrial sampling and return mission.

[0003] At present, there are two main ideas at home and abroad: hot launch and cold ejection. Hot launch refers to erecting the horizontally placed ascender through the erection mechanism and directly igniting and launching it on the landing platform. There are problems such as complex plume and great interference to the landing platform. Ground hot launch is mainly used in box-type missiles, artillery, missile launchers and other occasions; cold ejection refers to the use of cold air, springs and other methods to eject the ascender to a certain height, and then ignite and take off, which does not interfere with the landing platform. Ground cold ejection is widely used in fighter jets, missiles, drones and other equipment.

[0004] For cold ejection, the following problems need to be solved: 1) How to achieve reliable compression of the ascender to resist the vibration during rocket launch. 2) Compared with ground cold ejection, the launch of extraterrestrial objects is usually not guaranteed to be launched on flat ground, but on a sloping terrain. How to ensure that the ascender is ejected to the expected posture (usually the head is higher than the tail) under different terrains is the second problem that needs to be solved. 3) How to achieve anti-rolling during ejection. Summary of the invention

[0005] In order to solve the problem that the existing cold ejection device cannot meet the ejection requirements of an extraterrestrial ascender, the purpose of the present invention is to provide a pneumatic cold ejection device for an extraterrestrial ascender, which sends the ascender to a predetermined height by means of pneumatic cold ejection and provides ignition and take-off conditions; solves the compaction problem of the launch section based on a compaction-insulation integrated device; provides power for launch and adapts to the terrain based on an adjustable pneumatic piston assembly and an air source assembly; and prevents the ejection device from rolling based on a guide assembly.

[0006] The purpose of the present invention is achieved through the following technical solutions.

[0007] The invention discloses a pneumatic cold ejection device for an extraterrestrial ascender, comprising a heat preservation box, a heat preservation box cover, a pneumatic piston assembly, a gas source assembly, a clamping assembly, and a launch guide and adjustment assembly. The pneumatic piston assembly is composed of a secondary piston, a primary piston, a sealing ring, an inflatable joint, a primary piston plugging cover, a primary piston cylinder, a cushion, an exhaust guide cap, and a primary piston end cover; the gas source assembly is composed of a helium cylinder, a helium adding and discharging valve A, a high-pressure normally closed electric explosion valve, a helium adding and discharging valve B, and a pipeline; the clamping assembly is composed of a lifting beam, a bearing beam, a pyrotechnic unlocking device, and an ascender clamping member; the launch guide and adjustment assembly is composed of a guide bracket, a guide wheel, and a pressure regulating valve.

[0008] The ascender is placed in an insulated box; the insulated box is fixed on the launch platform; the ascender is compressed by the compression components fixed on the cover and the box when the rocket is launched from the earth to the extraterrestrial body. When the ascender is ejected on the surface of the extraterrestrial body, the air source component fixed on the launch platform is used to supply energy to the four groups of pneumatic piston components fixed on both sides of the ascender, and the launch guide and adjustment component is used to prevent the ascender from rolling during ejection, so as to realize the pneumatic cold ejection process of the ascender;

[0009] In order to solve the compression problem in the launch stage, the ascender is compressed by the launch platform, load-bearing beam, lifting beam, ascender compression parts, insulation box cover and insulation box body to resist the vibration load in the rocket launch phase and realize integrated compression and insulation.

[0010] Furthermore, in addition to being used to press the ascender, the lifting beam is also used for ejecting the ascender. The shape of the side in contact with the ascender is an arc, which fits the outer surface of the ascender. At the same time, a tungsten carbide high-friction coating is sprayed to ensure stable pressing of the ascender and uniform ejection force.

[0011] Furthermore, before the pneumatic ejection, the pyrotechnic unlocking device is unlocked by electric explosion to release the compressed state, and at the same time, the heat preservation box cover is opened to avoid the pneumatic ejection channel.

[0012] Furthermore, after the compression state is released, the air source assembly starts to supply air to the pneumatic piston assembly, and the movement of the piston drives the lifting beam to realize the ejection of the ascender.

[0013] Furthermore, the pneumatic piston assembly uses a high-pressure gas source as power and is a two-stage design. By reusing the strokes of the first-stage and second-stage pistons, it has the characteristic of a large thrust stroke compared to a single-stage pneumatic piston. After the first-stage piston is in place, the second-stage piston cavity is connected to the first-stage piston cavity, and the second-stage piston continues to move.

[0014] Furthermore, the gas source assembly includes a helium cylinder, two sets of helium filling and exhaust valves, two sets of high-pressure normally closed electric explosion valves and pipelines, which are connected in parallel to synchronously supply gas to two groups of four pneumatic piston assemblies. It has the advantages of large instantaneous expansion of compressed gas, high power density, stable ejection pressure change, low working fluid temperature without thermal protection measures, simple and reliable, and low cost.

[0015] Furthermore, there are a total of 4 sets of pneumatic piston assemblies, divided into 2 groups, front and rear, and each set of pneumatic piston assemblies is connected to a lifting beam. A pressure regulating valve is set at the air source inlet of the pneumatic piston assembly. When on track, according to the actual posture, under the same air supply condition, the pressure of the 4 sets of pneumatic piston assemblies is fine-tuned respectively to achieve a similar ejection head angle when ejecting under different slope terrains.

[0016] Furthermore, in order to prevent rolling, the launch guide and adjustment assembly is provided with two sets of guide devices, which are respectively placed on both sides of the ascender. Each set of guide devices includes a guide bracket and a plurality of guide wheels, and the guide wheels form a plane. At the same time, a small plane is also provided on the side of the ascender of the ejected object to prevent the ascender from rolling during the ejection process.

[0017] Beneficial effects:

[0018] 1. The present invention discloses an aerodynamic cold ejection device for an extraterrestrial ascender, which resists the vibration load of the rocket launch phase by reusing the insulation box cover and the insulation box with insulation function, and the ejection lifting beam for compression, thereby realizing the integration of insulation and compression, being simple, reliable and effectively reducing the total weight of the system.

[0019] 2. The present invention discloses a pneumatic cold ejection device for an extraterrestrial ascender, which uses a pressure regulating valve to adjust the pressure of four pneumatic piston assemblies to ensure that when an angle exists between the ejection platform and the local horizontal plane of the extraterrestrial body, the thrust is adjusted by adjusting the pressure to obtain the expected ejection angle. Compared with relying on the center of mass matching or mechanical adjustment method, the energy cost is smaller and the terrain adaptability is stronger.

[0020] 3. The present invention discloses a pneumatic cold ejection device for an extraterrestrial ascender. The pneumatic piston assembly uses a high-pressure gas source as power and is a two-stage design. By reusing the strokes of the first-stage and second-stage pistons, it has the characteristics of large thrust stroke compared to a single-stage pneumatic piston. The gas source assembly includes a helium cylinder, two sets of helium filling and exhaust valves, two sets of high-pressure normally closed electric explosion valves and pipelines, which are connected in parallel to synchronously supply gas to two groups of four pneumatic piston assemblies, thereby improving gas supply reliability. The combination of the pneumatic piston assembly and the gas source assembly makes the present invention have the advantages of high power density, stable ejection pressure change, low working fluid temperature without the need for thermal protection measures, simplicity, reliability, and low cost compared to thermal launch or gas ejection.

[0021] 4. The present invention discloses a pneumatic cold ejection device for an extraterrestrial ascender. The launch guide and adjustment assembly is provided with two sets of guide devices, which are respectively placed on both sides of the ascender, thereby preventing the ascender from rolling during the ejection process, improving the attitude stability of the ascender after ejection, and avoiding the influence of rolling on the attitude control of the ascender.

[0022] 5. The present invention discloses a pneumatic cold ejection device for an extraterrestrial ascender, in which the lifting beam and the ascender clamping piece have arc shapes on the contact surface with the ascender, fitting with the outer surface of the ascender, and are sprayed with a tungsten carbide high-friction coating. The high friction and increased contact area are utilized to effectively improve the axial clamping capacity and the uniformity of ejection force. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0024] Figure 1 It is a schematic diagram of the overall composition of the cold ejection device;

[0025] Figure 2 It is a schematic diagram of the composition of the pneumatic piston assembly;

[0026] Figure 3 This is a schematic diagram of the gas source component;

[0027] Figure 4 It is a schematic diagram of the cross section of the compression component composition and compression state;

[0028] Figure 5 A schematic diagram showing a comparison between a compressed state and a released compressed state;

[0029] Figure 6 It is a schematic diagram of the launch guidance and adjustment components;

[0030] Figure 7 It is a schematic diagram of the ejection process;

[0031] In the figure, 1-launching platform, 2-insulation box, 3-ascender, 4-insulation box cover, 5-pneumatic piston assembly, 6-gas source assembly, 7-compression assembly, 8-launching guide and adjustment assembly, 9-secondary piston, 10-first-stage piston, 11-sealing ring, 12-inflating joint, 13-first-stage piston plugging cover, 14-first-stage piston cylinder, 15-buffer pad, 16-exhaust guide cap, 17-first-stage piston end cover, 18-helium cylinder, 19-helium adding and discharging valve A, 20-high-pressure normally closed electric explosion valve, 21-helium adding and discharging valve B, 22-pipeline, 23-lifting beam, 24-bearing beam, 25-pyrotechnic unlocking device, 26-ascender pressing piece, 27-guide bracket, 28-guide wheel, 29-pressure regulating valve. DETAILED DESCRIPTION

[0032] The embodiments are described to explain the present invention, but are not limited to the present invention. In order to make the public have a better understanding of the present invention, the following description is some specific details.

[0033] like Figure 1 As shown, the pneumatic cold ejection device of an extraterrestrial ascender disclosed in this embodiment includes a heat preservation box 2, a heat preservation box cover 4, a pneumatic piston assembly 5, an air source assembly 6, a pressing assembly 7 and a launch guide and adjustment assembly 8. Figure 2 As shown, the pneumatic piston assembly 5 is composed of a secondary piston 9, a primary piston 10, a sealing ring 11, an air charging joint 12, a primary piston plug cover 13, a primary piston cylinder 14, a cushion 15, an exhaust guide cap 16 and a primary piston end cover 17; Figure 3 As shown, the gas source assembly 6 is composed of a helium cylinder 18, a helium adding and discharging valve A19, a high-pressure normally closed electric explosion valve 20, a helium adding and discharging valve B21 and a pipeline 22; the clamping assembly 7 is composed of a lifting beam 23, a bearing beam 24, a pyrotechnic unlocking device 25 and a riser clamping member 26; Figure 6 As shown, the launch guide and adjustment assembly 8 is composed of a guide bracket 17, a guide wheel 28 and a pressure regulating valve 29.

[0034] The ascender 3 is placed in the heat preservation box 2; the heat preservation box 2 is fixed on the launch platform 1; the ascender 3 is compressed by the compression assembly 7 fixed in the heat preservation box cover 4 and the heat preservation box 2 during the rocket launch from the earth to the extraterrestrial body. When the ascender 3 is ejected on the surface of the extraterrestrial body, the air source assembly 6 fixed on the launch platform 1 is used to supply energy to the four groups of pneumatic piston assemblies 5 fixed on both sides of the ascender, and the launch guide and adjustment assembly 8 is used to prevent the ascender 3 from rolling during ejection, so as to realize the pneumatic cold ejection process of the ascender 3.

[0035] like Figure 4As shown, in order to solve the compression problem of the launch stage, the ascender 3 is compressed by the launch platform 1, the load-bearing beam 24, the lifting beam 23, the ascender compression piece 26, the insulation box cover 4, and the insulation box body 2, with a fundamental frequency of not less than 50 Hz to resist the vibration load during the rocket launch phase. Integrated compression and insulation are achieved by reusing the insulation box cover 4 and the insulation box body 2, which is beneficial to reducing the overall weight of the system.

[0036] like Figure 4 As shown, the lifting beam 23 is used not only for pressing the ascender 3, but also for ejecting the ascender 3. The shape of the surface in contact with the ascender 3 is an arc, which fits the outer surface of the ascender 3. At the same time, a tungsten carbide high-friction coating with a friction coefficient of not less than 0.5 is sprayed to ensure stable pressing of the ascender 3 and uniform ejection force.

[0037] like Figure 5 As shown, the pyrotechnic unlocking device 25 is electrically unlocked before pneumatic ejection to release the compressed state, and at the same time, the heat preservation box cover 4 is opened to avoid the pneumatic ejection channel.

[0038] like Figure 7 As shown, after the compression state is released, the air source assembly 6 starts to supply air to the pneumatic piston assembly 5, and the movement of the piston drives the lifting beam 23 to realize the ejection of the ascender 3.

[0039] like Figure 2 As shown, the pneumatic piston assembly 5 uses a high-pressure gas source as power and is a two-stage design. By reusing the strokes of the first-stage and second-stage pistons, it has the characteristics of a large thrust stroke compared to a single-stage pneumatic piston. The stroke is not less than twice the initial height. After the first-stage piston is in place, the second-stage piston cavity is connected to the first-stage piston cavity, and the second-stage piston continues to move.

[0040] like Figure 3 As shown, the gas source assembly 6 includes a helium cylinder, two sets of helium filling and exhaust valves, two sets of high-pressure normally closed electric explosion valves and pipelines, which are connected in parallel to synchronously supply gas to two groups of four pneumatic piston assemblies 5, with a synchronization better than 10ms. It has the advantages of large instantaneous expansion of compressed gas, high power density, stable ejection pressure change, low working fluid temperature, no need for thermal protection measures, simple and reliable, and low cost.

[0041] There are 4 sets of pneumatic piston assemblies 5 in total, divided into 2 groups, front and rear, and each group is connected to a lifting beam 23. A pressure regulating valve 29 is set at the air source inlet of the pneumatic piston assembly 5. When on track, according to the actual posture, under the condition of unified air supply, the detector controller can fine-tune the pressure of the 4 sets of pneumatic piston assemblies 5 respectively, so as to achieve a similar ejection head angle when ejecting under different slope terrains, and the terrain adaptability is not less than 20°, ensuring that the expected function can be achieved under most terrains.

[0042] To prevent rolling, the launch guide and adjustment assembly 8 is provided with two groups of guide devices, which are placed on both sides of the ascender respectively. Each group includes a guide bracket 17 and 15 guide wheels 28. The guide wheels form a plane. At the same time, a small plane is also arranged on the side of the ascender 3 of the ejected object. The guide length height is not less than the radius of the ascender, so as to prevent the ascender 3 from rolling during the ejection process. The rolling angle of the ascender 3 is not greater than 3° when the ascender 3 is separated from the guide wheel.

[0043] The working method of the pneumatic cold ejection device of an extraterrestrial ascender disclosed in this embodiment is as follows:

[0044] (1) On-orbit launch phase

[0045] The entire device does not work during the on-orbit launch phase. The ascender 3 is compressed by the launch platform 1, the load-bearing beam 24, the lifting beam 23, the ascender clamp 26, the insulation box cover 4, and the insulation box 2 to resist the vibration load during the rocket launch phase and achieve integrated compression and insulation. In the gas source assembly 6, the helium cylinder 18 is filled with high-pressure helium, and the high pressure is maintained before the high-pressure normally closed electric explosion valve 20, and the entire system is in a static state.

[0046] (2) Preparation

[0047] Pyrotechnic unlocking device 25 electric explosion unlocking;

[0048] The heat preservation box cover 4 is opened together with the ascender pressing piece 26 to avoid the ejection channel;

[0049] The detector controller calculates the thrust required by the four pneumatic piston assemblies 5 according to the terrain conditions and completes the setting of the pressure regulating valve 29;

[0050] After the ejection command is issued, the two parallel high-pressure normally closed electric explosion valves 20 are opened at the same time, and the high-pressure gas fills the pipeline 22. The function of the parallel high-pressure normally closed electric explosion valves 20 is to improve reliability. As long as one is opened, it can work normally.

[0051] (3) Ejection stage

[0052] The first stage of ejection: the gas in the pipeline 22 supplies the four pneumatic piston assemblies 5 at the same time, and the high-pressure cold air enters the primary piston chamber through the charging joint 12. The primary piston 10 and the secondary piston 9 start to move together, and drive the lifting beam 4 to move, ejecting the ascender 3;

[0053] The second stage of ejection: the first-stage piston 10 moves to the end, the second-stage piston cavity is connected with the first-stage piston cavity, and the second-stage piston 9 drives the lifting beam 4 and the riser 3 to continue ejection until the second-stage piston moves to the end;

[0054] The launch guide and adjustment assembly 8 prevents the ascender 3 from rolling.

[0055] (4) Ascender launch phase

[0056] like Figure 7 As shown, the ascender is ejected to a predetermined height, fire takes off, and the entire ejection process ends.

[0057] The above is a detailed introduction to the aerodynamic cold ejection device for an extraterrestrial ascender provided by the present invention. This article uses specific examples to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. It should be pointed out that for ordinary technicians in this technical field, without departing from the principle of the present invention, the present invention can also be improved and modified in a number of ways, and these improvements and modifications are still within the scope of protection of the claims of the present invention.

Claims

1. A pneumatic cold ejection device for an extraterrestrial ascender, characterized in that: A pneumatic cold ejection device for an extraterrestrial ascender comprises a heat preservation box (2), a heat preservation box cover (4), a pneumatic piston assembly (5), an air source assembly (6), a pressing assembly (7) and a launch guide and adjustment assembly (8); wherein the pneumatic piston assembly (5) comprises a secondary piston (9), a primary piston (10), a sealing ring (11), an air charging joint (12), a primary piston plugging cover (13), a primary piston cylinder (14), a cushion (15), an exhaust guide cap (16) and a The gas source assembly (6) is composed of a helium cylinder (18), a helium adding and discharging valve A (19), a high-pressure normally closed electric explosion valve (20), a helium adding and discharging valve B (21) and a pipeline (22); the clamping assembly (7) is composed of a bullet lifting beam (23), a bearing beam (24), a pyrotechnic unlocking device (25) and an ascender clamping member (26); the launch guide and adjustment assembly (8) is composed of a guide bracket (17), a guide wheel (28) and a pressure regulating valve (29); An ascender (3) is placed in a heat preservation box (2); the heat preservation box (2) is fixed on a launch platform (1); the ascender (3) is compressed by a compression assembly (7) fixed in a heat preservation box cover (4) and the heat preservation box (2) during the stage of launching a rocket from the earth to an extraterrestrial body; when the ascender (3) is ejected on the surface of the extraterrestrial body, an air source assembly (6) fixed on the launch platform (1) is used to supply energy to four groups of pneumatic piston assemblies (5) fixed on both sides of the ascender, and a launch guide and adjustment assembly (8) is used to prevent the ascender (3) from rolling during ejection, thereby realizing a pneumatic cold ejection process of the ascender (3).

2. The pneumatic cold ejection device for an extraterrestrial ascender according to claim 1, characterized in that: The ascender (3) is compressed by the launch platform (1), the bearing beam (24), the bomb lifting beam (23), the ascender compression member (26), the heat preservation box cover (4), and the heat preservation box body (2) to resist the vibration load during the rocket launch phase, thereby achieving integrated compression and heat preservation.

3. The pneumatic cold ejection device for an extraterrestrial ascender according to claim 1, characterized in that: The pyrotechnic unlocking device (25) is electrically unlocked before the pneumatic ejection to release the compressed state, and the heat preservation box cover (4) is opened to avoid the pneumatic ejection passage.

4. The pneumatic cold ejection device for an extraterrestrial ascender according to claim 1, characterized in that: After the compression state is released, the air source assembly (6) starts to supply air to the pneumatic piston assembly (5), and the movement of the piston drives the ejection beam (23) to eject the ascender (3).

5. The pneumatic cold ejection device for an extraterrestrial ascender according to claim 1, characterized in that: The pneumatic piston assembly (5) uses a high-pressure gas source as power and is a two-stage design, through which the strokes of the primary and secondary pistons are reused; after the primary piston is in place, the secondary piston cavity is connected to the primary piston cavity, and the secondary piston continues to move.

6. The pneumatic cold ejection device for an extraterrestrial ascender according to claim 1, characterized in that: The gas source assembly (6) comprises a helium cylinder, two sets of helium filling and exhaust valves, two sets of high-pressure normally closed electric explosion valves and pipelines, and is connected in parallel to synchronously supply gas to two groups of four sets of pneumatic piston assemblies (5).

7. The pneumatic cold ejection device for an extraterrestrial ascender according to claim 1, characterized in that: There are a total of four sets of pneumatic piston assemblies (5), which are divided into two groups, front and rear, and each set of pneumatic piston assemblies (5) is connected to a spring-lifting beam (23). A pressure regulating valve (29) is arranged at the air source inlet of the pneumatic piston assembly (5). When on track, the pressure of the four sets of pneumatic piston assemblies (5) can be fine-tuned according to the actual posture and under the condition of unified air supply, so as to achieve similar ejection head-up angles when ejecting under different slope terrains.

8. The pneumatic cold ejection device for an extraterrestrial ascender according to claim 1, characterized in that: The launch guide and adjustment assembly (8) is provided with two groups of guide devices, which are respectively placed on both sides of the ascender; each group of guide devices includes a guide bracket (17) and a plurality of guide wheels (28), and the guide wheels form a plane. At the same time, a small plane is also provided on the side of the ascender (3) of the ejected object, so as to prevent the ascender (3) from rolling during the ejection process.

9. The pneumatic cold ejection device for an extraterrestrial ascender according to claim 1, characterized in that: The lifting beam (24) and the ascender pressing piece (26) are both in arc shape on the contact surface with the ascender; the lifting beam (24) fits the outer surface of the ascender and is sprayed with a tungsten carbide high friction coating to ensure stable pressing of the ascender (3) and uniform ejection force.

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