A pneumatic cold ejection device for an extraterrestrial ascender

Abstract

A pneumatic cold ejection device for an extraterrestrial ascender belongs to the field of deep space exploration. The present invention includes a heat-insulating box body, a heat-insulating box cover, a pneumatic piston assembly, an air 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 inflation joint, a primary piston plug cover, a primary piston cylinder, a buffer pad, an exhaust guide cap, and a primary piston end cover; the clamping assembly is composed of a lifting beam, a load-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. The ascender is sent to a predetermined height by means of pneumatic cold ejection, and the conditions for ignition and takeoff are provided; the compression problem of the launch section is solved based on the compression-insulation integrated device; based on the adjustable pneumatic piston assembly and the air source assembly, power is provided for the launch and adaptation to the terrain is achieved; based on the guide assembly, the ejection device is prevented from rolling, and the ascender pneumatic cold ejection 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 an extraterrestrial sampling and return mission, the ascender needs to carry the extraterrestrial samples from the surface of the extraterrestrial body and take off to a 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 of the entry module, the ascender is usually placed in a horizontal state on the landing platform and does not have the conditions for direct ignition and takeoff from an extraterrestrial body. The plan for establishing the extraterrestrial body's takeoff state is constrained by the requirements of the entry module's center of mass, and it is also necessary to consider the adaptability to the landing attitude and the influence of the plume. The products of the relevant 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 catapult. Hot launch refers to erecting a horizontally placed ascender through an erection mechanism and directly igniting and launching it on the landing platform. There are problems with complex plumes and greater interference with the landing platform. Ground hot launch is mainly used in box-type missiles, artillery, missile launchers and other occasions; cold catapult refers to using cold air, springs and other methods to catapult the ascender to a certain height, and then ignite and take off, which does not interfere with the landing platform. Ground cold catapult is widely used in fighter jets, missiles, drones and other equipment.

[0004] Cold ejection requires addressing the following challenges: 1) How to reliably hold the ascender in place to resist vibration during launch. 2) Unlike ground-based cold ejection, extraterrestrial launches typically require more than flat ground, often involving sloping terrain. Ensuring the ascender is ejected to the desired orientation (typically with the nose higher than the tail) regardless of terrain is a second challenge. 3) How to prevent roll 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 through 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 realizes anti-rolling of the ejection device based on a guide assembly.

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

[0007] The present invention discloses a pneumatic cold ejection device for an extraterrestrial ascender, comprising a heat-insulating housing, a heat-insulating housing cover, a pneumatic piston assembly, an air source assembly, a clamping assembly, and a launch guide and adjustment assembly. The pneumatic piston assembly comprises a secondary piston, a primary piston, a sealing ring, an inflation joint, a primary piston plugging cap, a primary piston cylinder, a cushion, an exhaust guide cap, and a primary piston end cap; the air source assembly comprises a helium cylinder, a helium supply and discharge valve A, a high-pressure normally closed electric explosion valve, a helium supply and discharge valve B, and pipelines; the clamping assembly comprises a lifting beam, a load beam, a pyrotechnic unlocking device, and an ascender clamping member; and the launch guide and adjustment assembly comprises a guide bracket, a guide wheel, and a pressure regulating valve.

[0008] The ascender is placed in an insulated box, which is fixed to the launch platform. During the rocket's launch from Earth to an extraterrestrial body, the ascender is compressed by a compression assembly fixed to the insulated box cover and the box itself. When the ascender is ejected from the surface of an extraterrestrial body, the air source assembly fixed to the launch platform supplies energy to the four pneumatic piston assemblies fixed on both sides of the ascender. The launch guide and adjustment assembly prevents the ascender from rolling during ejection, thus achieving the ascender's pneumatic cold ejection process.

[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 during the rocket launch phase and achieve integrated compression and insulation.

[0010] Furthermore, in addition to being used to press the ascender, the lifting beam is also used to eject 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 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. This has the advantages of large instantaneous expansion of compressed gas, high power density, stable ejection pressure changes, low working fluid temperature without the need for thermal protection measures, simplicity, reliability, and low cost.

[0015] Furthermore, there are four pneumatic piston assemblies, divided into two front and rear groups, each connected to a single launch beam. A pressure regulating valve is installed at the air source inlet of each pneumatic piston assembly. While on orbit, the pressure of each of the four pneumatic piston assemblies is fine-tuned based on the actual posture and the uniform air supply, achieving similar launch head-up angles when launching from terrains of varying slopes.

[0016] Furthermore, to prevent rollover, the launch guidance and adjustment assembly features two sets of guide devices, one on each side of the ascender. Each set includes a guide bracket and several guide wheels, which form a flat surface. The side of the ascender of the object being launched is also equipped with small flat surfaces to prevent the ascender from rolling during launch. Beneficial effects

[0017] 1. The present invention discloses an aerodynamic cold ejection device for an extraterrestrial ascender. By reusing the insulation box cover and the insulation box for thermal insulation, as well as the ejection beam for compression, it resists the vibration load during the rocket launch phase, achieving integrated insulation and compression. This is simple, reliable, and effectively reduces the total weight of the system.

[0018] 2. The present invention discloses a pneumatic cold ejection device for an extraterrestrial ascender. This device utilizes a pressure-regulating valve to adjust the pressure of four pneumatic piston assemblies, ensuring that when an angle exists between the ejection platform and the local horizontal plane of the extraterrestrial object, the desired ejection angle is achieved by adjusting the pressure and, in turn, the thrust. Compared with methods that rely on center-of-mass alignment or mechanical adjustment, this device has a lower energy cost and greater terrain adaptability.

[0019] 3. The present invention discloses a pneumatic cold ejection device for an extraterrestrial ascender. The pneumatic piston assembly utilizes a high-pressure gas source as its power source. It is a two-stage design. By reusing the strokes of the first and second stage pistons, it boasts a greater thrust stroke than a single-stage pneumatic piston. The gas source assembly includes a helium cylinder, two sets of helium supply and discharge valves, two sets of high-pressure normally closed electric explosion valves, and pipelines. These 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 gives the present invention advantages over thermal launch or gas ejection, including high power density, smooth ejection pressure changes, low working fluid temperature without the need for thermal protection measures, simplicity, reliability, and low cost.

[0020] 4. The present invention discloses an aerodynamic cold ejection device for an extraterrestrial ascender. The launch guide and adjustment assembly is provided with two sets of guide devices, one on each side of the ascender, thereby preventing the ascender from rolling during the ejection process, improving the attitude stability of the ascender after ejection, and preventing rolling from affecting the attitude control of the ascender.

[0021] 5. The present invention discloses a pneumatic cold ejection device for an extraterrestrial ascender. The contact surface of the lifting beam and the ascender pressing member with the ascender are both arc-shaped, fitting with the outer surface of the ascender. At the same time, a tungsten carbide high-friction coating is sprayed on it. By utilizing high friction and increased contact area, the axial clamping capacity is effectively improved, and the uniformity of ejection force is enhanced. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments. 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 any creative work.

[0023] Figure 1 This is a schematic diagram of the overall composition of the cold ejection device;

[0024] Figure 2 This is a schematic diagram of the pneumatic piston assembly;

[0025] Figure 3 This is a schematic diagram of the gas source components;

[0026] Figure 4 It is a schematic diagram of the cross section of the compression component composition and compression state;

[0027] Figure 5 Schematic diagram for comparison between the compressed state and the released state before and after;

[0028] Figure 6 This is a schematic diagram of the launch guidance and adjustment components;

[0029] Figure 7 Schematic diagram of the ejection process;

[0030] In the figure, 1-launching platform, 2-insulation box, 3-ascender, 4-insulation box cover, 5-pneumatic piston assembly, 6-air 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-bullet lifting beam, 24-load beam, 25-pyrotechnic unlocking device, 26-ascender pressing part, 27-guide bracket, 28-guide wheel, 29-pressure regulating valve. DETAILED DESCRIPTION

[0031] 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.

[0032] like Figure 1 As shown, the embodiment discloses a pneumatic cold ejection device for an extraterrestrial ascender, comprising a heat-insulating box 2, a heat-insulating 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 inflation 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 pressing assembly 7 is composed of a lifting beam 23, a bearing beam 24, a pyrotechnic unlocking device 25 and a riser pressing member 26; Figure 6 As shown, the launch guide and adjustment assembly 8 consists of a guide bracket 27, a guide wheel 28 and a pressure regulating valve 29.

[0033] Ascender 3 is placed within an insulated enclosure 2, which is secured to launch platform 1. During launch from Earth to an extraterrestrial body, ascender 3 is held in place by a compression assembly 7 secured to the enclosure lid 4 and within enclosure 2. During ejection from the surface of an extraterrestrial body, air source assembly 6, secured to launch platform 1, supplies energy to four pneumatic piston assemblies 5 mounted on either side of the ascender. Launch guide and adjustment assembly 8 prevents ascender 3 from rolling during ejection, achieving a pneumatic cold ejection of ascender 3.

[0034] 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 part 26, the insulation box cover 4, and the insulation box body 2. The fundamental frequency is not less than 50Hz to resist the vibration load during the rocket launch phase. By reusing the insulation box cover 4 and the insulation box body 2, integrated compression and insulation are achieved, which is beneficial to reducing the overall weight of the system.

[0035] like Figure 4 As shown, the lifting beam 23 is not only used to press the ascender 3, but also used to eject 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.

[0036] like Figure 5 As shown, the pyrotechnic unlocking device 25 is unlocked by electric explosion before the pneumatic ejection, releasing the compressed state, and at the same time the heat preservation box cover 4 is opened to avoid the pneumatic ejection channel.

[0037] 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 piston movement drives the lifting beam 23 to realize the ejection of the ascender 3.

[0038] 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 and second stage pistons, it has the characteristics of a large thrust stroke compared to a single-stage pneumatic piston, and the stroke is not less than 2 times 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.

[0039] 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 synchronization better than 10ms. This system has the advantages of large instantaneous expansion of compressed gas, high power density, smooth ejection pressure changes, low working fluid temperature without the need for thermal protection measures, simplicity, reliability, and low cost.

[0040] There are four sets of pneumatic piston assemblies 5, divided into two front and rear groups, each connected to a lifting beam 23. A pressure regulating valve 29 is installed at the air source inlet of the pneumatic piston assembly 5. When on orbit, the detector controller can fine-tune the pressure of the four pneumatic piston assemblies 5 according to the actual posture and under the same air supply conditions. This achieves similar ejection head angles when launching on terrains with different slopes, with terrain adaptability of no less than 20°, ensuring that the expected function can be achieved in most terrains.

[0041] 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. Each group includes a guide bracket 27 and 15 guide wheels 28. 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. 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.

[0042] The working method of the pneumatic cold ejection device of an extraterrestrial ascender disclosed in this embodiment is as follows:

[0043] (1) On-orbit launch phase

[0044] During the on-orbit launch phase, the entire system is inoperative. Ascender 3 is held in place by launch platform 1, load-bearing beam 24, lifting beam 23, ascender clamp 26, insulation box cover 4, and insulation box body 2, resisting the vibration loads of the rocket launch phase and achieving integrated compression and insulation. In gas source assembly 6, helium cylinder 18 is filled with high-pressure helium, maintaining high pressure before high-pressure normally closed electric explosion valve 20. The entire system is in a static state.

[0045] (2) Preparation stage

[0046] Pyrotechnic unlocking device 25, electric explosion unlocking;

[0047] The heat preservation box cover 4 and the ascender pressing member 26 are opened to avoid the ejection channel;

[0048] 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;

[0049] 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.

[0050] (3) Ejection stage

[0051] First stage of ejection: The gas in the pipeline 22 supplies the four pneumatic piston assemblies 5 at the same time. The high-pressure cold air enters the first-stage piston chamber through the charging connector 12. The first-stage piston 10 and the second-stage piston 9 start to move together, driving the lifting beam 23 to move, ejecting the ascender 3;

[0052] Second stage of ejection: the first-stage piston 10 moves to the end, the second-stage piston cavity is connected to the first-stage piston cavity, and the second-stage piston 9 drives the lifting beam 23 and the ascender 3 to continue ejecting until the second-stage piston moves to the end;

[0053] The launch guide and adjustment assembly 8 prevents the ascender 3 from rolling.

[0054] (4) Ascent vehicle launch phase

[0055] like Figure 7 As shown, the ascender is ejected to a predetermined height, fire takes off, and the entire ejection process is completed.

[0056] The above is a detailed introduction to the pneumatic 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 intended to help understand the method and core concept of the present invention. It should be pointed out that for those skilled in the art, without departing from the principles of the present invention, several improvements and modifications can be made to the present invention, 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 by: A pneumatic cold ejection device for an extraterrestrial ascender comprises a heat-insulating box (2), a heat-insulating 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 pressing assembly (7) is composed of a bullet lifting beam (23), a load-bearing beam (24), a pyrotechnic unlocking device (25) and an ascender pressing member (26); the launch guide and adjustment assembly (8) is composed of a guide bracket (27), a guide wheel (28) and a pressure regulating valve (29); The ascender (3) is placed in a heat-insulating box (2); the heat-insulating box (2) is fixed on a launch platform (1); the ascender (3) is compressed by a compression assembly (7) fixed in a heat-insulating box cover (4) and the heat-insulating box (2) during the stage of launching the rocket from the earth to an extraterrestrial body; when the ascender (3) is ejected from the surface of the extraterrestrial body, the 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 the launch guide and adjustment assembly (8) is used to prevent the ascender (3) from rolling during ejection, thereby realizing the 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 lifting beam (23), the ascender compression member (26), the insulation box cover (4), and the insulation box body (2) to resist the vibration load during the rocket launch phase, thereby achieving integrated compression and insulation.

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

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 lifting beam (23) to realize the ejection of 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, with the strokes of the first and second pistons being reused; after the first piston is in place, the second piston cavity is connected to the first piston cavity, and the second 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) includes 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. Each set of pneumatic piston assemblies (5) is connected to one ejection beam (23). A pressure regulating valve (29) is provided 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 unified air supply condition, so as to achieve a similar ejection head-up angle 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 sets of guide devices, which are respectively placed on both sides of the ascender; each set of guide devices includes a guide bracket (27) 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 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 (23) and the ascender pressing member (26) are both in arc shape on the contact surface with the ascender; the lifting beam (23) is fitted with 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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