A multifunctional integrated Mars entry probe

Abstract

A multifunctional integrated Mars reentry probe relates to the technical field of Mars exploration, and mainly comprises a probe body, a rotor, a nose cone cover, a rotating device and a heat shield, etc. When launched, the rotor is in a compressed and folded state, and the probe body, the nose cone cover and the heat shield serve as a fairing. In the initial reentry stage, the heat shield is used to protect the rotor blades from aerodynamic heating, and can be further unfolded to a certain angle after descending to a certain speed, and the heat shield serves as a deceleration plate for further deceleration. When the speed is reduced to subsonic speed, the rotor blades are unlocked and released, and are stretched out through the internal telescopic mechanism, and the blades are driven to rotate by the relative airflow, so that the rotating kinetic energy is converted into electric energy for storage while providing lift and deceleration. In the landing stage, the rotor is switched to the active working mode, and the stored electric energy is used to provide rotating power for the rotating device, so that the probe can autonomously hover and avoid obstacles; and the heat shield is fully unfolded to provide stable support and buffer for the probe body.

Description

Technical Field

[0001] This invention relates to a multifunctional integrated Mars reentry probe, and relates to the field of Mars exploration technology. Background Technology

[0002] Mars, being very similar to Earth, is the first choice for understanding Earth's past and present and for exploring extraterrestrial life. It has always been an important target for humankind's exploration of the universe. When a spacecraft re-enters a celestial body with an atmosphere (such as Mars or Earth), it generally goes through three phases: entry, descent, and landing. During entry, the aerodynamic drag generated by the spacecraft's own shape moving through the atmosphere is mainly used for deceleration. During descent and landing, parachutes, engines, and other methods are mainly used for deceleration.

[0003] On Mars, with its relatively thin atmosphere, facing supersonic speeds, low density, and low dynamic pressure, parachute-based deceleration is relatively inefficient, and the mass and size of the parachute itself are strictly limited. Powered deceleration requires a main engine and multiple attitude control engines for precise control of hovering, obstacle avoidance, and slow descent. This places higher demands on engine performance and propellant loading, and approaching the landing point too close can cause the probe to overturn under the combined effects of engine thrust and plume. Furthermore, using only a "parachute + engine" deceleration method cannot achieve the final soft landing requirement; the probe's remaining landing velocity needs to be consumed using special landing buffering techniques, and there is a risk of an uneven landing or an incorrect attitude. Of course, in such a multi-mode deceleration probe, each component is interconnected, and a problem in any process can lead to mission failure. Even with a safe soft landing, the probe lacks the capability for multiple takeoffs and landings, multi-site reconnaissance, and fixed-point hovering.

[0004] Besides the challenge of a reliable and safe soft landing on the Martian surface, the Martian environment is also extremely harsh, with frequent dust storms. These massive dust storms have a significant impact on solar-powered probes, potentially leading to insufficient energy for the entire spacecraft.

[0005] Overall, current spacecraft reentry technologies feature relatively independent and dispersed functions, which can easily lead to a loss of launch capacity. Given the characteristics of the Mars reentry process and the requirements for landing and exploration, how to fully utilize launch capacity, integrate and expand the functions of various components, reduce overall mission costs, and improve overall mission efficiency is an increasingly important issue. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to overcome the shortcomings of the prior art and provide a multifunctional integrated Mars reentry probe.

[0007] The objective of this invention is achieved through the following technical solutions:

[0008] A multifunctional integrated Mars reentry probe includes a probe body, rotors, nose cone, rotating device, and heat shield.

[0009] The rotor comprises three blades, evenly distributed around the circumference of the detector body, with clamping points on them, and is in a clamped and retracted state during launch.

[0010] The nose cone is installed on the top of the detector body and is used for aerodynamic protection and aerodynamic heating during the launch of the entire device.

[0011] The rotating device is connected to the rotor and is used for rotor self-rotation energy recovery and control of blade rotation drive.

[0012] The heat shield and the three rotor blades are located in the same position and are evenly distributed around the circumference of the detector body. During launch, they are in a compressed and retracted state to protect the rotor blades from aerodynamic heating during reentry.

[0013] Preferably, when the rotor's reentry speed drops to subsonic, the rotor blades can be released via explosive bolts;

[0014] Preferably, the rotor can be extended to a high aspect ratio state through an internal retractable mechanism to further improve lift;

[0015] Preferably, the rotor first uses the relative flow to drive the blades to rotate, providing lift and deceleration while converting rotational kinetic energy into electrical energy for storage; during the landing phase, the rotor can switch to active working mode, using the stored electrical energy to provide rotational power for the rotating device and thus drive the rotor, enabling autonomous hovering and obstacle avoidance, and achieving precise soft landing; when working after landing, the probe body can use the rotor to complete multiple take-offs and landings, multi-site surveys, etc.

[0016] Preferably, solar panels are attached to the upper surfaces of the three rotor blades to provide energy for the entire probe's operation when the rotor is stationary after landing, and to store a certain amount of electrical energy. If extreme weather such as sandstorms occurs on the Martian surface, the rotor can be driven by the electrical energy from the rotating device to remove surface dust and ash.

[0017] Preferably, the nose cone can be divided into 12 segments by a deployment mechanism after the probe lands, forming a small-to-medium aperture antenna structure to establish a communication link between the probe body and the Mars orbiter.

[0018] Preferably, sensitive scientific instruments and equipment can be placed inside the nasal cone cover. The scientific instruments and equipment, such as meteorological measuring instruments and gas composition detectors, are fixedly installed on the bottom plate of the nasal cone cover and can be completely retracted to protect the equipment when Mars encounters severe weather such as dust storms.

[0019] Preferably, the heat shield can be deployed to a certain angle during reentry to act as a deceleration plate and increase resistance, thereby further decelerating the entire device.

[0020] Preferably, the heat shield can be fully deployed during the landing phase to provide stable support and cushioning for the probe body.

[0021] Compared with the prior art, the present invention has the following advantages:

[0022] (1) Based on the development needs of low cost and high reliability, this invention fully adopts the integrated design concept. The entire probe has a simple and compact structure. While taking into account aerodynamic protection, reentry deceleration, safe landing, multiple take-off and landing, telemetry and communication, and reliable power generation, it effectively integrates the functions of each component, minimizes the loss and waste of carrying capacity, and ensures that the probe can achieve a soft landing at near-zero speed with high landing accuracy and low impact load. At the same time, the rotation of the rotor blades is also conducive to shaking off the dust on the surface of the solar cells when working on the Martian surface, ensuring a continuous and stable energy supply for the entire device.

[0023] (2) The present invention fully adopts the integrated design concept. The whole device does not need to be equipped with an additional fairing. The nose cone covers both launch aerodynamic protection and landing communication support, the heat shield covers both aerodynamic deceleration and outrigger landing, and the rotor covers both deceleration, take-off and landing and power generation functions. The overall structure has relatively strong reliability, safety and mobility, thereby effectively improving the overall economic benefits of the detector. Attached Figure Description

[0024] Figure 1 This is a flight profile of a multifunctional, integrated Mars reentry probe.

[0025] Figure 2 This is an overall configuration of a multifunctional, integrated Mars reentry probe.

[0026] Figure 3 This represents the operational status of a multifunctional, integrated Mars reentry probe.

[0027] Figure 4 It is a retractable mechanism inside the rotor blade.

[0028] Reference numerals: 1-Detector body; 2-Nose cone; 3-Heat shield; 4-Rotor; 5-Rotation device; 6-Nose cone flap; 7-Flexible membrane; 8-Solar cell. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0030] A multifunctional integrated Mars reentry probe mainly comprises a probe body, rotors, a nose cone, a rotating mechanism, and a heat shield. During launch, the rotors are in a compressed, retracted state, with the probe body, nose cone, and heat shield acting as a fairing for the entire probe. During the initial reentry phase, the heat shield protects the rotor blades from aerodynamic heating. After a certain descent speed, it can be further deployed to a specific angle, acting as a decelerator for further deceleration. When the speed drops to subsonic, the rotor blades unlock and extend via an internal retractable mechanism, using the relative airflow to drive their rotation, providing lift and deceleration while converting rotational kinetic energy into stored electrical energy. During landing, the rotors switch to active mode, using stored electrical energy to power the rotating mechanism for autonomous hovering and obstacle avoidance; the heat shield fully deploys, providing stable support and cushioning for the probe body. After landing, the nose cone can be deployed into multiple petals through the deployment mechanism to form a small-to-medium aperture antenna structure, providing telemetry and communication support for the probe body; after stopping, the surface-mounted solar cells on the rotor blades can also generate electricity to support the operation of the probe body.

[0031] Example 1:

[0032] A multifunctional, integrated Mars reentry probe includes a probe body 1, a nose cone 2, a heat shield 3, rotors 4, a rotating mechanism 5, and solar panels 8. The overall configuration of the Mars reentry probe in its folded and deployed states is as follows: Figure 2 As shown.

[0033] like Figure 1 As shown, a flight profile of a multifunctional integrated Mars reentry probe is presented. At launch, the probe has a blunt-nosed shape, with the heat shield 3 and rotors 4 folded and retracted around the probe body 1, close to the cabin wall. The rotors 4 are located inside the heat shield 3. The probe body 1, nose cone 2, and heat shield 3 together act as the probe's fairing. During the initial reentry phase, the heat shield 3 protects the rotors 4 from aerodynamic heating. After a certain descent speed, it can be further deployed to a certain angle, acting as a speed brake to increase aerodynamic drag. When the probe's speed drops to subsonic, the blades of the rotors 4 unlock and extend through an internal retractable mechanism. Utilizing the relative airflow, the blades rotate. The rotors 4 are connected to a rotating device 5. While providing lift and deceleration, the blades convert rotational kinetic energy into electrical energy, which is stored in a battery energy storage module within the probe body 1. During landing, rotor 4 switches to active operating mode, using stored electrical energy to power the rotation of the rotating device 5, enabling rotor 4 to rotate and hover autonomously to avoid obstacles. The heat shield 3 slowly and fully deploys, providing stable support and cushioning for the probe body 1. After landing, the nose cone 2 can unfold into multiple petals through its own deployment mechanism, forming a small-to-medium aperture antenna structure to provide telemetry and communication support for the probe body 1. The surface-mounted solar panels 8 of rotor 4 can also continuously generate electricity after the rotor blades stop rotating, providing power support for the operation of the probe body 1.

[0034] like Figure 3 As shown, in the operational state of a multi-functional integrated Mars reentry probe after landing, the rotor 4 stops rotating, and the solar panels 8 attached to the upper surface of its blades provide energy support for the probe body 1. After encountering extreme weather such as sandstorms, thick dust will cover the solar panels 8, significantly reducing power generation capacity. The probe's stored electrical energy drives the rotating device 5, causing the blades to rotate and shake off the surface dust. The nose cone 2 can be deployed into 12 lobes 6 via its own deployment mechanism. The lobes 6 are connected by a foldable flexible membrane 7, forming a complete sky-to-ground communication antenna structure, establishing a communication link between the probe body 1 and the Mars orbiter. The nose cone 2 can also be completely retracted to protect the equipment inside the hood when the probe encounters extreme weather such as sandstorms.

[0035] like Figure 4 As shown, to increase the lift of rotor 4 and further enlarge the blade radius, rotor 4 blades are equipped with retractable blades and a rhomboid telescopic mechanism. The retractable blades are pre-compressed and retracted inside rotor 4 blades via the rhomboid telescopic mechanism, and the springs inside the rhomboid telescopic mechanism are compressed to store elastic potential energy. When the rhomboid telescopic mechanism is released from its constraint, it returns to its original position and extends under the action of the spring force, achieving linear motion and driving the retractable blades to fully extend.

[0036] Example 2:

[0037] A multifunctional integrated Mars reentry probe includes a probe body 1, rotors 4, nose cone 2, rotating device 5, heat shield 3, and solar panels 8.

[0038] The nose cone 2 is mounted on the detector body 1;

[0039] The rotating device 5 is connected to the rotor 4 and is used to recover the rotational energy of the rotor 4 and control the rotation of the rotor 4; solar cells 8 are attached to the blades of the rotor 4.

[0040] During launch, rotor 4 and heat shield 3 are pressed and folded together and installed around the circumference of probe body 1, close to the bulkhead of probe body 1;

[0041] During the initial reentry phase, rotor 4 is located inside heat shield 3, and the probe body 1, nose cone 2, and heat shield 3 together serve as the fairing for the entire probe.

[0042] Once the entire probe descends to the predetermined speed, the heat shield 3 deploys to the predetermined angle, acting as a speed brake and increasing aerodynamic drag. When the speed of the entire probe drops to subsonic, the blades of the rotor 4 deploy, using the relative airflow to drive the blades to rotate. While providing lift and deceleration, the blades convert rotational kinetic energy into electrical energy through the rotating device 5 and store it in the probe body 1. During the landing phase, the rotor 4 switches to active working mode, using the stored electrical energy to provide rotational power to the rotating device 5 to drive the blades of the rotor 4 to rotate. The heat shield 3 is fully deployed, providing stable support and cushioning for the probe body 1.

[0043] Preferably, after landing, the nose cone 2 unfolds into multiple lobes, forming a small-to-medium aperture antenna structure.

[0044] Further preferred options include small-to-medium aperture antenna structures for telemetry, measurement, and control (TT&C) communications.

[0045] More preferably, the nasal cone 2 includes flaps 6 and flexible membranes 7. After the nasal cone 2 is deployed, the multiple flaps 6 are connected to each other by multiple foldable flexible membranes 7.

[0046] Preferably, after the rotor blades of rotor 4 stop rotating, the surface-mounted solar cells 8 continue to generate electricity to provide power support for the operation of the detector body 1.

[0047] Preferably, the nasal cone 2 has a built-in measuring instrument.

[0048] Preferably, the rotor blades are provided with clamping points that are connected to the detector body 1, and the blades are unlocked in orbit through an unlocking mechanism.

[0049] Preferably, the rotor also includes retractable blades and a diamond-shaped retractable mechanism, which is used to drive the retractable blades to fully extend, increasing the aspect ratio and improving lift.

[0050] Preferably, the rotating device 5 can drive the rotor 4 to rotate, removing dust from the surface of the solar cell.

[0051] Preferably, during the landing phase, the stored electrical energy is used to power the rotation of the rotating device 5, which in turn drives the blades of the rotor 4 to rotate, allowing the rotor to hover and avoid obstacles autonomously.

[0052] The contents not described in detail in this specification are common knowledge to those skilled in the art.

[0053] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A multifunctional integrated Mars reentry probe, characterized in that, It includes the detector body (1), rotor (4), nose cone (2), rotating device (5), heat shield (3), and solar cells (8); The nose cone (2) is mounted on the detector body (1); The rotating device (5) is connected to the rotor (4) and is used to recover the rotational energy of the rotor (4) and control the rotation of the rotor (4); solar cells (8) are attached to the blades of the rotor (4); During launch, the rotor (4) and heat shield (3) are pressed and folded together and installed around the probe body (1), close to the bulkhead of the probe body (1); During the initial reentry phase, the rotor (4) is located inside the heat shield (3), and the probe body (1), nose cone (2), and heat shield (3) together serve as the fairing for the entire probe. After the entire probe descends to the predetermined speed, the heat shield (3) unfolds to the predetermined angle, acting as a speed brake and increasing aerodynamic drag. When the speed of the entire probe drops to subsonic speed, the blades of the rotor (4) unfold, using the relative flow to drive the blades to rotate. While providing lift and deceleration, the blades convert rotational kinetic energy into electrical energy through the rotating device (5) and store it in the probe body (1). During the landing phase, the rotor (4) switches to active working mode, using the stored electrical energy to provide rotational power for the rotating device (5) to drive the blades of the rotor (4) to rotate. The heat shield (3) is fully unfolded, providing stable support and buffer for the probe body (1).

2. The multifunctional integrated Mars reentry probe according to claim 1, characterized in that, After landing, the nose cone (2) unfolds into multiple lobes, forming a small-to-medium aperture antenna structure.

3. The multifunctional integrated Mars reentry probe according to claim 2, characterized in that, Small and medium aperture antenna structures are used for telemetry, measurement and control communication.

4. The multifunctional integrated Mars reentry probe according to claim 2, characterized in that, The nasal cone mask (2) includes flaps (6) and flexible membranes (7). After the nasal cone mask (2) is deployed, multiple flaps (6) are connected to each other by multiple foldable flexible membranes (7).

5. The multifunctional integrated Mars reentry probe according to claim 1, characterized in that, After the rotor blades (4) stop rotating, the surface-mounted solar cells (8) continue to generate electricity to provide power support for the operation of the detector body (1).

6. The multifunctional integrated Mars reentry probe according to claim 1, characterized in that, Nasal cone (2) with built-in measuring instruments.

7. The multifunctional integrated Mars reentry probe according to claim 1, characterized in that, The rotor blades are equipped with clamping points that connect to the detector body (1), and the blades are unlocked in orbit through an unlocking mechanism.

8. The multifunctional integrated Mars reentry probe according to claim 1, characterized in that, The rotor (4) also includes retractable blades and a diamond-shaped telescopic mechanism. The diamond-shaped telescopic mechanism is used to drive the retractable blades to fully extend, increase the aspect ratio and improve lift.

9. The multifunctional integrated Mars reentry probe according to claim 1, characterized in that, The rotating device (5) can drive the rotor (4) to rotate and remove dust from the surface of the solar cell.

10. The multifunctional integrated Mars reentry probe according to claim 1, characterized in that, During the landing phase, the stored electrical energy is used to power the rotation of the rotating device (5) to drive the rotor blades (4) to rotate, and the rotor hovers and avoids obstacles autonomously.

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