Lift fan matrix vertical lifting high-altitude rocket launching platform and use method

Abstract

The invention discloses a lift fan matrix vertical lifting high-altitude rocket launching platform and a using method, and belongs to the technical field of aerospace. The launching platform comprises at least two platform modules, electric ducted lift fans, a battery pack, a rocket docking clamping lock, a high-pressure push rod push-away system, a platform module docking locking mechanism and a flight control system, wherein the platform modules can be separated and docked, and the electric ducted lift fans are installed in the platform modules in a distributed mode. During use, the platform vertically ascends and descends to carry the rocket to a preset high altitude, the rocket is safely separated from the platform in a mode of pushing away first and then separating / descending, and then the rocket is ignited and launched. The electric lift fan matrix is adopted for providing power, the rocket launching platform has the advantages of being high in loading capacity, high in platform stability, capable of being repeatedly used, low in launching cost and the like, and the rocket launching efficiency can be effectively improved.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a vertical lift-fan matrix high-altitude rocket launch platform, as well as a method of using the vertical lift-fan matrix high-altitude rocket launch platform. Background Technology

[0002] Currently, launch vehicles are typically launched from ground-based launch sites or sea-based launch platforms. The rocket must rely on its own first stage or bundled boosters to provide enormous thrust to overcome Earth's gravity and the drag of the dense atmosphere to deliver the payload into space. This traditional launch method has the following inherent drawbacks:

[0003] 1. Huge energy loss: When a rocket flies through the densest lower atmosphere, it not only has to withstand enormous aerodynamic drag, dynamic pressure, and heat flow, but also has to contend with 100% of Earth's gravity. The propellant used to overcome gravity and atmospheric drag accounts for the vast majority of the rocket's liftoff mass.

[0004] 2. Low structural efficiency: In order to withstand the extreme mechanical environment of ground launch, the first stage structure of the rocket must be exceptionally robust, resulting in excessive structural mass.

[0005] 3. High cost: Due to the above reasons, the cost of the first stage of a rocket is high, and launch costs have remained high for a long time.

[0006] To overcome the limitations of ground-based launches, various alternative solutions have been proposed in the prior art. For example, Chinese Patent Application Publication No. CN105857636A, published on August 17, 2016, discloses a near-space satellite launch platform and method, which utilizes an airship as a launch vehicle. This solution fixes the launch vehicle's launch device in the center of the airship, which then carries the rocket to near-space at an altitude of over 30 kilometers before launch. Although CN105857636A reduces the rocket's flight distance in the dense atmosphere to some extent by increasing the launch altitude, it still has the following significant drawbacks:

[0007] (1) Limited carrying capacity: Airships (such as airships) rely on static buoyancy to take off. Their carrying capacity and wind resistance stability are limited by their own volume and meteorological conditions, making it difficult to meet the launch requirements of large-load, heavy rockets.

[0008] (2) Insufficient platform stability: When the airship releases the rocket, the platform attitude is prone to violent disturbance due to the sudden release of the rocket mass and the reaction force of the cold ejection, which affects the launch accuracy and safety.

[0009] (3) Poor reusability: In this scheme, the airship returns to the ground after completing the launch mission, but its large flexible structure and power system require complex maintenance after recovery, making it difficult to achieve high-frequency, low-cost rapid reuse. In addition, the airship is susceptible to damage from the rocket exhaust during launch, resulting in high maintenance costs.

[0010] Other air-launch options, such as high-altitude balloon-based launch systems (e.g., Chinese patent application publication number CN115900444A) or transport aircraft-based air-launch options (e.g., Chinese patent authorization announcement number CN106767157B), are limited by issues related to payload capacity, platform stability, and the safety of the separation process. While electromagnetic propulsion systems (e.g., Chinese patent application publication number CN110411276A) can provide initial velocity, they cannot fundamentally eliminate aerodynamic losses in the dense atmosphere, and orbital construction costs are extremely high.

[0011] Therefore, there is an urgent need for a launch platform that can directly transport rockets to near space, has high payload capacity, good platform stability, and is reusable. Summary of the Invention

[0012] The purpose of this invention is to overcome the above-mentioned shortcomings and provide a lift fan matrix high-altitude rocket launch platform with high load capacity, high platform stability, reusability, low launch cost, and effective improvement of launch efficiency.

[0013] Another object of the present invention is to provide a method of using the lift fan matrix high-altitude rocket launch platform.

[0014] This invention discloses a high-altitude rocket launch platform with a lift fan matrix, comprising platform module A, platform module B, an electric ducted lift fan, a rocket docking clamp lock, a high-pressure push rod push-off system, and a flight control system, wherein:

[0015] At least two platform modules, A and B, that can be separated and connected to each other, and platform modules A and B are combined to form an overall load-bearing structure;

[0016] Multiple electrically powered ducted lift fans are distributed and installed inside platform module A and platform module B;

[0017] The battery pack is installed inside platform module A and platform module B and is used to power the electric ducted lift fan.

[0018] The rocket docking clamp lock is located at the center of the platform module A and platform module B assembly;

[0019] The high-pressure push rod separation system is located below the rocket docking clamp lock;

[0020] A platform module docking and locking mechanism is provided on the docking surface of platform module A and platform module B to achieve rigid connection and rapid separation between platform module A and platform module B.

[0021] The flight control system is electrically connected to the electric ducted lift fan, the platform module docking and locking mechanism, and the high-pressure push rod push-off system.

[0022] The aforementioned vertical lifting and lowering high-altitude rocket launch platform with a lift fan matrix includes a platform module docking and locking mechanism that employs a dual locking structure of electromagnetic lock and mechanical lock.

[0023] The present invention discloses a method for using a vertical lift-and-drop high-altitude rocket launch platform with a lift fan matrix, comprising the following steps:

[0024] Step 1: Connect and lock the top of the launch vehicle to the rocket docking clamp lock, so that the launch vehicle is vertically suspended at the center of the platform module A and platform module B assembly;

[0025] Step 2: Control the start of the electric ducted lift fan to make the launch platform take off vertically and climb to the preset height;

[0026] Step 3: After reaching the predetermined altitude, activate the high-pressure push rod pushing system to push the launch vehicle upwards, then control the platform module docking locking mechanism to unlock and cause platform module A and platform module B to separate horizontally;

[0027] Step 4: After confirming that platform module A and platform module B have moved far away, the launch vehicle engine is ignited and launched.

[0028] The above-mentioned method of using the vertical lifting high-altitude rocket launch platform with lift fan matrix includes the following step: In step three, the platform module A and platform module B are separated horizontally by accelerating horizontally to the left and right sides respectively.

[0029] The present invention discloses a method for using a vertical lift-and-drop high-altitude rocket launch platform with a lift fan matrix, comprising the following steps:

[0030] Step 1: Connect and lock the bottom of the launch vehicle to the rocket docking clamp lock, so that the launch vehicle is positioned at the center of the platform module A and platform module B assembly;

[0031] Step 2: Control the start of the electric ducted lift fan to make the launch platform take off vertically and climb to the preset height;

[0032] Step 3: After reaching the predetermined altitude, the high-pressure push rod pushing system is activated to push the launch vehicle upwards, while the thrust of all electric ducted lift fans is reduced, so that the launch platform descends vertically as a whole.

[0033] Step 4: After confirming that the launch platform has descended to a safe distance, the launch vehicle engine is ignited and launched.

[0034] The above-mentioned method of using the vertical take-off and landing high-altitude rocket launch platform with lift fan matrix also includes a platform recovery step: the separated platform modules A and B return to base and land under the control of the flight control system.

[0035] The above-mentioned method of using a vertically ascending and descending high-altitude rocket launch platform with a lift fan matrix includes the following steps: In the platform recovery step, platform modules A and B approach, dock, and lock together in mid-air to form a complete launch platform before descending vertically.

[0036] Compared with the prior art, the present invention has significant advantages, as can be seen from the above technical solution:

[0037] 1. Significantly Reduced Launch Costs: This invention utilizes a lift fan matrix to propel the rocket to altitudes exceeding 10,000 meters. The required power primarily comes from electricity, resulting in operating costs far lower than the propellant costs of rocket ignition and takeoff. Since the launch altitude significantly exceeds the dense atmosphere, aerodynamic drag and gravity losses are significantly reduced during rocket ignition. Simultaneously, the rocket's structure can be simplified, leading to lower manufacturing costs. Theoretical estimates suggest that, while maintaining the same rocket payload capacity, launch costs can be significantly reduced (theoretically estimated at approximately 40%-60%); if the rocket size and propellant dosage remain unchanged, the payload capacity is theoretically expected to increase by 100%-150%.

[0038] 2. Significantly Enhanced Payload Capacity and Stability: This invention employs a high thrust-to-weight ratio electric ducted lift fan matrix as its power source, overcoming the limitations of airships that rely on static buoyancy, and enabling it to support heavier and larger launch vehicles. Simultaneously, through precise control of multiple fans by the flight control system, the platform's hovering and wind resistance stability are far superior to those of airships, providing a more stable launch platform for the rocket.

[0039] 3. The platform is reusable and highly safe: The platform uses a battery-powered electric ducted lift fan, which has a simple structure and is easy to maintain. Through a two-step strategy of "push away first, then separate / descend," the platform is ensured to be far away from the danger zone when the rocket ignites, avoiding thermal and impact damage from the rocket jet and ensuring the platform's reusable service life.

[0040] 4. Strong Dual-Mode Adaptability: This invention provides two mounting modes for the first-stage rocket: top-suspended and bottom-supported, adaptable to launch vehicles with different structures and launch requirements. The suspended mode utilizes the pendulum principle to achieve natural stability, significantly reducing the risk of tipping over during ascent; the bottom-supported mode has a simple structure and strong compatibility.

[0041] 5. All-electric clean propulsion: The battery-powered system is zero-emission and low-noise, requiring no refueling, simplifying launch site facilities and reducing operating costs and maintenance complexity. The application of high-energy-density power sources such as battery packs further enhances the platform's carrying capacity and range.

[0042] 6. High-precision attitude control and redundancy: Multiple electric ducted lift fans in a distributed layout, combined with an advanced flight control system, can achieve centimeter-level hovering accuracy; the large number of fans and high power redundancy ensure the platform's safety even if individual fans fail.

[0043] 7. High launch flexibility: It is free from the limitations of fixed launch sites and can be used in any location with take-off and landing conditions, enabling mobile launch. Attached Figure Description

[0044] Figure 1 This is a schematic diagram of the structure of the present invention;

[0045] Figure 2 for Figure 1 A bottom view;

[0046] Figure 3 for Figure 1 AA view;

[0047] Figure 4 for Figure 3 A magnified view of part B;

[0048] Figure 5 This is a schematic diagram of the rocket mounted on the top of the device on the launch pad.

[0049] Figure 6 This is a schematic diagram of the rocket mounted on top of the invention rising vertically after leaving the launch pad;

[0050] Figure 7 This is a schematic diagram illustrating the separation of the invention from the rocket mounted on top;

[0051] Figure 8 for Figure 7 A magnified view of part C;

[0052] Figure 9 This is a schematic diagram of the rocket ignition and launch after separation according to the present invention;

[0053] Figure 10 This is a schematic diagram of the rocket being supported at the bottom and mounted on the launch pad according to the present invention;

[0054] Figure 11 This is a schematic diagram illustrating the vertical ascent of the rocket supported at the bottom of the launch pad according to the present invention.

[0055] Figure 12This is a schematic diagram of the rocket ignition and launch after it separates from the bottom support of the present invention.

[0056] Marked in the image:

[0057] 1. Platform Module A, 2. Platform Module B, 3. Electric Ducted Lift Fan, 4. Battery Pack, 5. Rocket Docking Clamp Lock, 6. High-Pressure Push Rod Push-Off System, 7. Platform Module Docking Locking Mechanism, 8. Flight Control System, 9. Rocket, 10. Launch Pad, 11. Suspension Arm. Detailed Implementation

[0058] To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0059] Example 1:

[0060] like Figure 1 As shown, the present invention discloses a vertical lift-and-drop high-altitude rocket launch platform with a lift fan matrix, comprising a platform module A1, a platform module B2, an electric ducted lift fan 3, a battery pack 4, a rocket docking clamp lock 5, a high-pressure push rod release system 6, a platform module docking locking mechanism 7, and a flight control system 8. The two platform modules A1 and B2, which can be separated and docked, are combined to form an integral load-bearing structure. The rocket docking clamp lock 5 is located at the center of the platform module A1 and platform module B2 assembly and is used to mount and release the rocket 9. The flight control system 8 is electrically connected to the electric ducted lift fan 3, the platform module docking locking mechanism 7, and the high-pressure push rod release system 6, and is used to control the platform's takeoff, flight, separation, return, and landing.

[0061] like Figure 1-2 As shown, several electrically driven ducted lift fans 3 are evenly distributed and installed inside platform modules A1 and B2 to provide the lift required for vertical ascent and descent in this invention. Each fan is driven by an independent motor and its speed can be adjusted individually. A high-energy-density battery pack 4 is installed inside platform modules A1 and B2 to power all the electrically driven ducted lift fans 3. The total capacity of the battery pack 4 meets the energy consumption requirements for platform modules A1 and B2 to ascend vertically to a preset height at full load and then return.

[0062] like Figure 3-4 As shown, the platform module docking locking mechanism 7 is disposed on the docking surface of platform module A1 and platform module B2, and is used to achieve rigid connection and rapid separation between platform module A1 and platform module B2. The platform module docking locking mechanism 7 preferably adopts a double locking of electromagnetic lock and mechanical lock to ensure structural rigidity in the combined state. During separation, the electromagnetic lock unlocks first, and the mechanical lock disengages subsequently.

[0063] like Figure 4 , Figure 8 As shown, the rocket docking clamp lock 5 is used to connect to the suspension arm 11 located at the top of the first stage of rocket 9. Below the docking clamp lock 5 is a high-pressure push rod separation system 6, which pushes the rocket upward during separation, giving rocket 9 an initial upward velocity relative to the platform.

[0064] Example 2:

[0065] A method for using a lift fan matrix high-altitude rocket launch platform (top-suspended type for the first-stage rocket) includes the following steps:

[0066] like Figure 5 As shown, the suspension arm 11 of the first stage of the launch vehicle 9 is connected to and locked with the rocket docking clamp lock 5 of the present invention, so that the rocket 9 is vertically suspended at the center of the platform module A1 and platform module B2 assembly. The present invention, with the rocket 9 mounted, is placed on the launch base 10, the system is checked, and the rocket 9 is fully fueled;

[0067] like Figure 6 As shown, the present invention, with rocket 9 suspended, takes off vertically from launch base 10 and climbs to a preset altitude (such as 20,000 meters, which is significantly lower than the dense atmosphere and can greatly reduce aerodynamic losses). Because the rocket's center of gravity is lower than the suspension arm, a natural stabilizing pendulum is formed, and rocket 9 maintains a vertical attitude throughout the ascent.

[0068] like Figure 7 As shown, after reaching the predetermined altitude, the present invention, with rocket 9 suspended, maintains the set ascent speed. The flight control system 8 triggers the rocket docking clamp lock 5 to unlock and the high-pressure push rod push-away system 6 to start. The high-pressure push rod pushes rocket 9 upward away from the present invention. Then, the platform module docking locking mechanism 7 of platform module A1 and platform module B2 unlocks. Under the thrust of the electric ducted lift fan 3, platform module A1 and platform module B2 accelerate horizontally to the left and right respectively and quickly move away from the area directly below rocket 9.

[0069] like Figure 9 As shown, after confirming that platform module A1 and platform module B2 have moved away, the rocket's 9 engine ignites and launches.

[0070] Under the control of flight control system 8, platform modules A1 and B2 decelerate and turn, re-approach in the air, precisely dock and lock, restoring the complete invention. Subsequently, the invention descends smoothly and vertically, landing on launch pad 10.

[0071] Another option is for platform modules A1 and B2 to land independently in the designated area without docking in the air.

[0072] Ground personnel inspected the invention, rapidly charged battery pack 4, and replenished the high-pressure push rod ejection system with high-pressure gas, after which the invention was ready for the next launch mission.

[0073] Example 3:

[0074] A method for using a lift fan matrix high-altitude rocket launch platform (bottom-lifting mounting mode) includes the following steps:

[0075] like Figure 10 As shown, the bottom of rocket 9 is vertically mounted on the rocket docking clamp lock 5 of the present invention and locked. Rocket 9 is located at the center of the platform module A1 and platform module B2 assembly. The present invention, with rocket 9 mounted, is placed on the launch base 10.

[0076] like Figure 11 As shown, after the inspection is normal and the rocket 9 is fully fueled, the launch platform takes off vertically from the launch pad 10 and climbs to the preset altitude (e.g., 20,000 meters).

[0077] like Figure 12 As shown, after reaching the predetermined altitude, the present invention, equipped with rocket 9, maintains the set ascent speed. The flight control system 8 triggers the unlocking of the rocket docking clamp lock 5 and the activation of the high-pressure push rod release system 6, pushing the rocket upwards to give it an initial upward velocity relative to the present invention. At the same time, the flight control system 8 rapidly reduces the thrust of all lift fans, causing the present invention to descend rapidly and vertically, quickly moving away from the area below the rocket.

[0078] After confirming that the invention had descended to a safe distance, the rocket's 9 engine ignited and the rocket was launched into space.

[0079] After the launch of Rocket 9, the invention continues to descend, landing vertically on launch pad 10 for maintenance and charging, in preparation for the next launch mission.

[0080] The above are merely preferred embodiments of the present invention and do not impose any limitations on the present invention. Any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention without departing from any technical solution of the present invention shall still fall within the scope of the technical solution of the present invention.

Claims

1. A vertical lift-and-drop high-altitude rocket launch platform with a lift fan matrix, comprising platform module A (1), platform module B (2), an electric ducted lift fan (3), a rocket docking clamp lock (5), a high-pressure push rod push-off system (6), and a flight control system (8), characterized in that: At least two platform modules A (1) and B (2) that can be separated and connected to each other, and the platform modules A (1) and B (2) are combined to form an overall load-bearing structure; Multiple electric ducted lift fans (3) are distributed and installed inside the platform module A (1) and platform module B (2); The battery pack (4) is installed inside the platform module A (1) and platform module B (2) to power the electric ducted lift fan (3); The rocket docking clamp lock (5) is located at the center of the platform module A (1) and platform module B (2) assembly; The high-pressure push rod pushing system (6) is located below the rocket docking clamp lock (5); The platform module docking locking mechanism (7) is set on the docking surface of the platform module A (1) and the platform module B (2); The flight control system (8) is electrically connected to the electric ducted lift fan (3), the platform module docking and locking mechanism (7), and the high-pressure push rod push-off system (6), respectively.

2. The vertical lift-and-drop high-altitude rocket launch platform with a lift fan matrix as described in claim 1, characterized in that: The platform module docking locking mechanism (7) adopts a dual locking structure of electromagnetic lock and mechanical lock.

3. A method for using a vertical lift-and-drop high-altitude rocket launch platform with a lift fan matrix, characterized in that: Includes the following steps: Step 1: Connect and lock the top of the launch vehicle (9) to the rocket docking clamp lock (5), so that the launch vehicle (9) is vertically suspended at the center of the platform module A (1) and platform module B (2) assembly; Step 2: Control the start of the electric ducted lift fan (3) to make the launch platform take off vertically and climb to the preset height; Step 3: After reaching the predetermined altitude, activate the high-pressure push rod pushing system (6) to push the launch vehicle (9) upwards, then control the platform module docking locking mechanism (7) to unlock, and cause platform module A (1) and platform module B (2) to separate horizontally; Step 4: After confirming that platform module A (1) and platform module B (2) have moved away, the launch vehicle (9) engine is ignited and launched.

4. The method of using the vertical lifting high-altitude rocket launch platform with a lift fan matrix as described in claim 3, characterized in that: In step three, the horizontal separation of platform module A (1) and platform module B (2) is achieved by accelerating horizontal separation to the left and right sides respectively.

5. A method for using a vertical lift-and-drop high-altitude rocket launch platform with a lift fan matrix, characterized in that... The process includes the following steps: Step 1: Connect and lock the bottom of the launch vehicle (9) to the rocket docking clamp lock (5) so that the launch vehicle (9) stands at the center of the platform module A (1) and platform module B (2) assembly; Step 2: Control the start of the electric ducted lift fan (3) to make the launch platform take off vertically and climb to the preset height; Step 3: After reaching the predetermined altitude, the high-pressure push rod pushing system (6) is activated to push the launch vehicle (9) upwards, while reducing the thrust of all electric ducted lift fans (3) to make the launch platform descend vertically as a whole; Step 4: After confirming that the launch platform has descended to a safe distance, the launch vehicle (9) engine is ignited and launched.

6. The method of using the vertical lifting high-altitude rocket launch platform with a lift fan matrix as described in claim 3 or 5, characterized in that... It also includes a platform recovery step: the separated platform modules A (1) and B (2) return to base and land under the control of the flight control system (8).

7. The method of using the vertical lifting high-altitude rocket launch platform with a lift fan matrix as described in claim 6, characterized in that: In the platform recovery step, platform module A (1) and platform module B (2) approach, dock and lock together in the air to form a complete launch platform before descending vertically.

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