A probe that can float in the atmosphere of Venus

Abstract

The application discloses a kind of probes that can float in Venus atmosphere, comprising: big bottom module and back cover module, first connection unlocking device, second connection unlocking device and spring push rod;Wherein, when the probe is launched, big bottom structure and back cover structure are fixedly connected by first connection unlocking device, form cabin;After the probe enters a certain height of Venus atmosphere, first connection unlocking device is unlocked, and the fixed connection of big bottom structure and back cover structure is cancelled, and separation is completed by spring push rod;Inflatable device is installed in the middle position of big bottom structure inner surface;Load cabin is arranged in the clearance part of inflatable device, and is installed on inflatable device by multiple second connection unlocking devices;After the probe enters Venus atmosphere, inflatable device is inflated, second connection unlocking device is unlocked, load cabin and inflatable device are cancelled fixed connection, and load cabin and inflatable device are separated by the lifting force of balloon, and load cabin starts to float and fly to carry out scientific exploration.

Description

Technical Field

[0001] This invention belongs to the field of deep space exploration technology and relates to a probe that can float in the atmosphere of Venus. Background Technology

[0002] Venus is the closest planet to Earth in our solar system, and studying it is of great significance for understanding Earth's evolution. Entering Venus's atmosphere and conducting sustained, aerodynamic exploration allows for long-term scientific missions, yielding a wealth of data that will contribute to our understanding of life and the origins of the universe.

[0003] The mission to bring Venus into the floating probe system system mainly includes three parts:

[0004] 1. Entering Venus's atmosphere at high speed;

[0005] 2. Inflated balloons float in the atmosphere of Venus;

[0006] 3. Carry scientific payloads to achieve scientific exploration of the atmosphere.

[0007] For the Venus reentry mission, the Venus reentry vehicle should be designed with an aerodynamic shape to adapt to the deceleration of the Venusian atmosphere, and equipped with a heat shield to provide thermal protection during high-speed reentry. Internally, it should be equipped with a foldable balloon-like buoyancy device that inflates after aerodynamic deceleration to allow the payload compartment to float, thus enabling floating exploration.

[0008] The main design challenges of Venus entering the buoy are:

[0009] The Venus entry spacecraft will enter the Venusian atmosphere at a speed of approximately 12 km / s, which is greater than the second cosmic velocity. Furthermore, Venus has a denser atmosphere, far exceeding that of Earth. The aerodynamic deceleration requirements for the spacecraft have surpassed those for Earth reentry and Mars entry. Therefore, the aerodynamic shape of the Venus entry spacecraft needs to have good deceleration performance.

[0010] The Venus entry floating probe faces constraints in weight and space, and must also meet special operational requirements such as atmospheric entry, balloon inflation, cabin separation, and floating exploration. Therefore, a highly integrated configuration and layout of the probe must be achieved under these tight weight and space constraints.

[0011] The process of Venus entry into the floater, including entry, deceleration, inflation, and floating, is complex and requires multiple separations of the capsule to achieve the final floating exploration mission. The probe needs to design not only the entry and floating implementation path, but also the entire capsule separation scheme.

[0012] Due to the significant challenges of Venus exploration missions, my country has not yet conducted a Venus exploration mission. Furthermore, the design of its Venus-entry lander has the following shortcomings:

[0013] 1. The aerodynamic shape adopts a relatively basic spherical shape, and the aerodynamic deceleration performance is average;

[0014] The detector's configuration and layout have low integration and insufficient payload carrying capacity;

[0015] The probe uses two sets of parachutes during its entry and floating process, which is costly. Summary of the Invention

[0016] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a probe that can float in the atmosphere of Venus, and can realize functions such as multiple separations in orbit, inflation of air balloons, and floating exploration.

[0017] The technical solution of this invention is:

[0018] This invention discloses a probe capable of floating in the atmosphere of Venus, comprising: a base module and a back cover module, a first connection unlocking device, a second connection unlocking device, and a spring push rod; wherein, the base module includes a base structure, an inflation device, and a payload compartment; the back cover module includes a back cover structure and a balloon; when the probe is launched, the base structure and the back cover structure are fixedly connected by the first connection unlocking device to form a compartment; after the probe enters a certain altitude in the Venusian atmosphere, the first connection unlocking device unlocks, the fixed connection between the base structure and the back cover structure is released, and separation is completed by the spring push rod installed between the base structure and the back cover structure; the inflation device is installed in the middle of the inner surface of the base structure; the payload compartment is arranged in the gap of the inflation device and is installed on the inflation device by multiple second connection unlocking devices; after the probe enters the Venusian atmosphere, the inflation device inflates the balloon, the second connection unlocking device unlocks, the payload compartment is released from the inflation device, and the lift of the balloon separates the payload compartment from the inflation device, and the payload compartment begins to float and fly to conduct scientific exploration.

[0019] Furthermore, in the aforementioned detector, the base module adopts a spherical-head frustum configuration.

[0020] Furthermore, in the aforementioned detector, the back cover module adopts a ball table configuration.

[0021] Furthermore, in the aforementioned detector, the base module also includes: electronic products and a main beam; wherein, the main beam is disposed on the mounting interface between the back cover structure and the base structure, is fixedly connected to the base structure, and is used to support the electronic products and limit the balloon to prevent the balloon from sliding downward.

[0022] Furthermore, in the aforementioned detector, the base module also includes a landing extension detection device, which is installed at the bottom of the inner surface of the base structure. The landing extension detection device is a small detector that can work independently. After the base structure and the back cover structure are separated, it lands on the surface of Venus with the base structure to achieve Venus landing extension detection.

[0023] Furthermore, in the aforementioned detector, the back cover module also includes a parachute compartment, a parachute, a balloon compartment, and a parachute compartment cover; wherein, the parachute compartment is arranged on the top of the back cover structure and installed on the back cover structure, the parachute is fixed inside the parachute compartment, the parachute and the parachute compartment cover are connected by thin ropes, and the parachute compartment cover is connected to the parachute compartment through multiple ejectors; the balloon compartment is installed on the top of the compartment inside the back cover structure and is fixedly connected to the back cover structure.

[0024] Furthermore, in the aforementioned detector, the balloon is fixed inside the balloon chamber, and its lower surface is limited by a beam structure. The balloon is connected to the base structure, the back cover structure, and the payload chamber via connecting ropes. Rope cutters are installed on the ropes connecting the balloon to the base structure and the back cover structure.

[0025] Furthermore, in the aforementioned detector, the outer side of the base structure is a heat-resistant structure, and the inner side is a load-bearing structure, with the heat-resistant structure and the load-bearing structure being fixedly connected.

[0026] Furthermore, in the aforementioned detector, the inflation device includes an annular gas cylinder, a valve, a pipeline, and a pipeline connection / separation device. The annular gas cylinder is connected to the balloon via the valve, the pipeline, and the pipeline connection / separation device to provide a gas source for inflating the balloon in orbit.

[0027] Furthermore, in the aforementioned detector, the back cover structure serves both heat protection and load-bearing functions, with the outer side being the heat protection structure and the inner side being the load-bearing structure, and the heat protection structure and the load-bearing structure being fixedly connected.

[0028] The advantages of this invention compared to the prior art are:

[0029] (1) The present invention provides an aerodynamic shape that can enter the atmosphere of Venus at high speed and safely, which has good aerodynamic deceleration capability and can adapt to the entry into the atmosphere of Venus.

[0030] (2) The present invention provides a highly integrated configuration layout scheme, whose configuration and outer surface can form a good aerodynamic shape, and can realize functions such as multiple separations in orbit, inflation of air balloons, and floating detection; the detector layout is compact and optimized, realizing an integrated layout of small container and high capacity;

[0031] (3) The present invention provides a multi-system integrated overall design scheme. Its annular gas cylinder is not only used as a gas cylinder, but also as the main structure to support the load chamber and improve the rigidity of the whole device. Its beam structure is not only used to support electronic equipment, but also as a limiting device for folding balloons. This scheme realizes the miniaturized design of Venus entering the floating device.

[0032] (4) This invention provides a design scheme for Venus atmospheric entry, inflation and floating. This scheme uses only one parachute throughout the entire process. The design scheme is optimized and reduces system cost and system complexity. Attached image description:

[0033] Figure 1 This is the shape of the Venus floating probe of the present invention;

[0034] Figure 2 This is the exploded configuration of the Venus floating probe of the present invention;

[0035] Figure 3 This is a cross-sectional view of the Venus floating probe of the present invention;

[0036] Figure 4 This is a schematic diagram of the Venus floating probe of the present invention entering the Venusian atmosphere and floating process;

[0037] Figure 5 This is a dimensional diagram of the Venus floating probe of the present invention.

[0038] Among them, 1-base module, 2-back cover module, 3-parachute compartment cover, 4-parachute, 5-parachute compartment, 6-balloon compartment, 7-balloon, 8-main beam, 10-inflation device, 11-payload compartment, 12-landing extension detection device, 13-electronic equipment, 91-base structure, 92-back cover structure. Detailed Implementation

[0039] The working principle and process of the present invention will be further explained and described below with reference to the accompanying drawings.

[0040] This invention provides a probe capable of floating in the atmosphere of Venus. (See attached image) Figure 2 As shown, the detector is structurally divided into a base module 1 and a back cover module 2. The base module 1 adopts a spherical-head frustum configuration, and the back cover module 2 adopts a spherical-head frustum configuration. The outer surfaces of the base module 1 and the back cover module 2 together constitute the outer shape of the detector, i.e., the aerodynamic shape of the detector, as shown in the attached figure. Figure 1 As shown. The connection relationship is as follows:

[0041] Four first connection unlocking devices and four spring push rods are installed between the base module 1 and the back cover module 2. When the probe is launched, the first connection unlocking devices fix the base module 1 and the back cover module 2 together; after the probe enters a certain altitude in the Venusian atmosphere, the first connection unlocking devices are unlocked, the fixation between the base module 1 and the back cover module 2 is released, and separation is completed by the spring push rods installed between the base structure 91 and the back cover structure 92.

[0042] As attached Figure 3 As shown, the base module 1 includes: a base structure 91, an inflation device 10, a payload compartment 11, a main beam 8, and a landing extension detection device 12. The base structure 91 serves both heat protection and load-bearing functions; its outer side is the heat-protective structure, and its inner side is the load-bearing structure, which are fixed together by adhesive bonding and screwing. The inflation device 10 includes an annular gas cylinder, valves, pipelines, and pipeline connection and separation devices, used to provide an air source for inflating the balloon in orbit. The main beam 8 is located near the mounting interface between the back cover structure 92 and the base structure 91, and is fixed to the base structure 91 by screwing. It mainly supports the electronic product 13 and limits the folded balloon 7 on the back cover module 2 to prevent the balloon 7 from sliding downwards. The payload compartment 11 is a small, independently operating detector that houses scientific payloads for scientific exploration during buoyancy. The landing extension probe 12 is a small, independently operating probe that can be installed depending on mission requirements. After the base module 1 and the back cover module 2 are separated, it lands on the surface of Venus with the base module 1, enabling Venus landing extension exploration. The connection relationship of the components of the base module 1 is as follows: the inflation device 10 is screwed to the middle of the inner surface of the base structure 91; the landing extension probe 12 is screwed to the head of the inner surface of the base structure; the payload compartment 11 is arranged in the gap of the inflation device 10 and is installed on the structure of the inflation device 10 through three second connection unlocking devices. After the base module 1 and the back cover module 2 are separated, the second connection unlocking devices fix the payload compartment 11 and the inflation device 10 together when the probe is launched; after the probe enters the Venusian atmosphere and the balloon is fully inflated, the second connection unlocking devices unlock, the fixed connection between the payload compartment 11 and the inflation device 10 is released, and the load compartment 11 is separated from the structure of the inflation device 10 by the lift of the balloon 7.

[0043] As attached Figure 3As shown, the back cover module 2 includes a back cover structure 92, a parachute compartment 5, a balloon compartment 6, a parachute 4, a balloon 7, and a parachute compartment cover 3. The back cover structure 92 serves both heat protection and load-bearing functions; its outer side is the heat-protective structure, and its inner side is the load-bearing structure. The heat-protective and load-bearing structures are fixed together by adhesive bonding and screwing. The parachute compartment 5 is located on top of the back cover structure 92 and is screwed onto it. The parachute 4 is fixed inside the parachute compartment 5, and the parachute 4 is connected to the parachute compartment cover 3 by a thin rope. The parachute compartment cover 3 is connected to the parachute compartment 5 via four ejectors. The balloon chamber 6 is installed at the lower part of the back cover structure 92 and is fixed to the back cover structure 92 by screw connection. The balloon 7 is fixed inside the balloon chamber 6, and its lower surface is limited by the main beam structure 8. The balloon 7 is connected to the base structure 91, the back cover structure 92 and the load chamber 11 on the base module 1 by connecting ropes. The ropes connecting the balloon 7 to the base structure 91 and the back cover structure 92 are equipped with rope cutters and are connected to the inflation device of the base module 1 through pipeline connection separation device.

[0044] As attached Figure 5 As shown, the main dimensions of the aerodynamic shape are described as follows: a is the height of Venus entering the floatation device, b is the height of the base structure, c is the radius of the head of the base structure, d is the radius of the back cover structure, e is the angle between the cone section of the base structure and the interface between the base and the back cover, and f is the lateral diameter of the base structure. Here, e is set between 35° and 60°, f is between 1 and 2 times a, and d is between 1 and 2 times c.

[0045] like Figure 4 As shown, the process of the Venus floating probe entering the Venusian atmosphere and completing its floating is as follows:

[0046] S1. Entering Venus's Atmosphere: The Venus floating probe enters the Venusian atmosphere and begins to rotate.

[0047] S2. Parachute Deployment: At a certain altitude, the recovery procedure begins, the ejector operates, deploying the parachute compartment cover 3 and deploying the parachute 4. Subsequently, the thin rope between the parachute compartment cover 3 and the parachute 4 is disconnected.

[0048] S3, Parachute Inflation: Parachute 4 inflates rapidly, and the Venus floating probe begins to decelerate.

[0049] S4. Parachute descends steadily and balloon is pulled out: The Venus floating probe enters a stable descent state. The first connection unlocking device between the base module 1 and the back cover module 2 is unlocked. Under the action of the separation push rod, the base module 1 and the back cover module 2 separate. The separation force of the two pulls the balloon 7 out of the balloon chamber 6 and unfolds.

[0050] S5. The balloon begins to inflate: After the balloon 7 is pulled out, the inflation device 10 works to inflate the balloon 7.

[0051] S6. Balloon inflation complete, parachute separation: After balloon 7 is inflated, the pipeline connection device operates, the pipeline between the inflation device 10 and balloon 7 is disconnected, and then the cutter on the connecting rope between the back cover module 2 and balloon 7 operates, disconnecting the connection between the back cover module 2 and balloon 7, and the parachute 4 carrying the back cover module 2 separates from balloon 7.

[0052] S7. Pull out the sling and throw out the bottom module 1: The cutter on the rope connecting the back cover module 2 and the balloon 7 works to disconnect the connection between the back cover module 2 and the balloon 7, and the bottom module 1 is separated from the balloon 7. The pulling force of the balloon 7 pulls out the sling between the balloon 7 and the load chamber 11.

[0053] S8. Balloon rises to working height: After the base module 1 is released, balloon 7 rises to a certain height, and payload compartment 11 rises to a certain height under the action of the balloon's lift, and begins to carry out aerodynamic scientific exploration.

[0054] The above embodiments are merely explanations of the present invention and should not be construed as limiting the present invention. Therefore, any implementation methods similar to the present invention or implementation methods used in other similar structures but with similar concepts to the present invention are within the protection scope of the present invention.

[0055] The above description is only the best specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the protection scope of the present invention.

[0056] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A probe capable of floating in the atmosphere of Venus, characterized in that, include: The system comprises a base module (1) and a back cover module (2), a first connection unlocking device, a second connection unlocking device, and a spring push rod; wherein, the base module (1) includes a base structure (91), an inflation device (10), and a payload compartment (11); the back cover module (2) includes a back cover structure (92) and a balloon (7); when the probe is launched, the base structure (91) and the back cover structure (92) are fixedly connected by the first connection unlocking device to form a compartment; after the probe enters a certain altitude in the Venusian atmosphere, the first connection unlocking device is unlocked, the fixed connection between the base structure (91) and the back cover structure (92) is released, and the probe is launched by a spring push rod installed on the base structure (91). The spring push rod between the back cover structure (92) and the back cover structure (92) is separated; the inflation device (10) is installed in the middle of the inner surface of the base structure (91); the payload compartment (11) is arranged in the gap of the inflation device (10) and is installed on the inflation device (10) through multiple second connection unlocking devices; after the probe enters the atmosphere of Venus, the inflation device (10) inflates the balloon (7), the second connection unlocking devices are unlocked, the payload compartment (11) is decoupled from the inflation device (10), and the payload compartment (11) is separated from the inflation device (10) by the lift of the balloon (7), and the payload compartment (11) begins to float and fly to carry out scientific exploration; The base module (1) also includes: electronic product (13) and main beam (8); wherein, the main beam (8) is set on the mounting interface of the back cover structure (92) and the base structure (91), and is fixedly connected to the base structure (91) to support the electronic product (13) and limit the balloon (7) to prevent the balloon (7) from sliding downward; The base module (1) also includes a landing extension probe (12). The landing extension probe (12) is installed at the bottom of the inner surface of the base structure (91). The landing extension probe (12) is a small probe that can work independently. After the base structure (91) and the back cover structure (92) are separated, it lands on the surface of Venus with the base structure (91) to realize Venus landing extension probe.

2. A probe capable of floating in the atmosphere of Venus according to claim 1, characterized in that: The base module (1) adopts a spherical cone configuration.

3. A probe capable of floating in the atmosphere of Venus according to claim 1, characterized in that: The back cover module (2) adopts a ball table configuration.

4. A probe capable of floating in the atmosphere of Venus according to claim 1, characterized in that: The back cover module (2) also includes a parachute compartment (5), a parachute (4), a balloon compartment (6), and a parachute compartment cover (3); wherein, the parachute compartment (5) is arranged on the top of the back cover structure (92) and installed on the back cover structure (92), the parachute (4) is fixed inside the parachute compartment (5), the parachute (4) is connected to the parachute compartment cover (3) by a thin rope, and the parachute compartment cover (3) is connected to the parachute compartment (5) by multiple catapults; the balloon compartment (6) is installed on the top of the compartment of the back cover structure (92) and is fixedly connected to the back cover structure (92).

5. A probe capable of floating in the atmosphere of Venus according to claim 4, characterized in that: The balloon (7) is fixed inside the balloon chamber (6), and its lower surface is limited by the beam structure (8). The balloon (7) is connected to the base structure (91), the back cover structure (92) and the load chamber (11) by connecting ropes. Rope cutters are provided on the ropes connecting the balloon (7) to the base structure (91) and the back cover structure (92).

6. A probe capable of floating in the atmosphere of Venus according to claim 1, characterized in that: The outer side of the base structure (91) is a heat-resistant structure, and the inner side is a load-bearing structure. The heat-resistant structure and the load-bearing structure are fixedly connected.

7. A probe capable of floating in the atmosphere of Venus according to claim 1, characterized in that: The inflation device (10) includes an annular gas cylinder, valves, pipelines and pipeline connection and separation devices. The annular gas cylinder is connected to the balloon (7) through the valves, pipelines and pipeline connection and separation devices to provide a gas source for the balloon (7) to be inflated in orbit.

8. A probe capable of floating in the atmosphere of Venus according to claim 1, characterized in that: The back cover structure (92) combines heat protection and load-bearing functions. The outer side is a heat protection structure, and the inner side is a load-bearing structure. The heat protection structure and the load-bearing structure are fixedly connected.

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