A low-cost, high-frequency, reusable, small-load air-space transportation system and method

Abstract

A low-cost, high-frequency reusable, small-payload aerospace transportation system and method belongs to the technical field of overall design of aerospace transportation systems. The present invention solves the main problems existing in the existing reusable space-to-earth round-trip aircraft in terms of energy operation nature, aerodynamic thermal protection cost, and the way of passing through the atmosphere. The launch end of the ground electromagnetic boost launch system of the present invention is connected to a two-stage carrier, and the first-stage orbiter of the two-stage carrier is connected to the second-stage thruster. After the two-stage carrier is launched, the first-stage orbiter separates from the fairing connection cover and the second-stage thruster and enters the orbiter integrated platform. After the first-stage orbiter completes the orbital mission, it enters the orbiter integrated re-entry return platform. A low-cost, high-frequency reusable, small-payload aerospace transportation system and method of the present invention provides initial kinetic energy to achieve a higher take-off speed, which can effectively reduce the propellant and take-off mass, and reduce the wing area requirement.

Description

Technical Field

[0001] The present invention belongs to the technical field of overall design of aerospace transportation systems, and specifically relates to a low-cost, high-frequency reusable, small-load aerospace transportation system and method. Background Art

[0002] Low-cost, reusable space-to-air transport vehicles are one of the key research directions of the world's aerospace powers in the past century. Although a lot of research has been carried out in the field of reusable space-to-air vehicles at home and abroad, such as various propulsion systems, wide-speed aerodynamic layout technology, and hypersonic airframe / propulsion integrated design technology, there are still many problems in the development of such vehicles in the future that need to be solved and considered.

[0003] 1. Existing reusable spacecraft that can travel between the earth and the sky have unavoidable defects in their energy operation nature. During the process of takeoff and climb to orbit, a large amount of fuel chemical energy is consumed to be converted into the desired flight altitude potential energy and extremely high super flight Mach number kinetic energy. However, during the re-entry phase, it is forced to dissipate and waste it as quickly as possible through frictional aerodynamic heating and other means.

[0004] 2. The thermal protection system equipped with existing reusable spacecraft for round-trip travel between the earth and the sky is too expensive. Due to the serious aerodynamic heating problem during the return and re-entry process, the entire spacecraft needs to adopt a matching aerodynamic layout shape, insulation / heat protection structure and related control system that can withstand extremely high heat flux peaks. On the one hand, the insulation / heat protection system directly increases the cost of design, production, manufacturing and maintenance. On the other hand, the complex insulation / heat protection structure and control system also bring greater re-entry safety risks and hidden dangers. In addition, based on multiple factors such as extremely high temperature thermal protection and rapid passive deceleration, its aerodynamic layout needs to adopt more demanding passivation treatment and special shape (high resistance and low lift), which limits the improvement of its low-speed aerodynamic characteristics. The problems such as the mutual matching between the aerodynamic performance requirements and aerodynamic thermal protection seriously restrict the research and development of future large-scale space vehicles for round-trip travel between the earth and the sky.

[0005] 3. Most of the existing reusable spacecraft that can travel between the earth and the sky adopt vertical launch, which is too expensive and is severely restricted by environmental factors. Take the space shuttle as an example. Due to the vertical launch method, the aerodynamic efficiency advantage of the high lift-to-drag ratio layout cannot be utilized. The engine thrust needs to directly match gravity and acceleration, so a high-thrust rocket engine is required during the take-off phase. Since the rocket engine is limited by the working time, it is necessary to directly use high thrust and high overload to accelerate to the required speed as quickly as possible. The violent vibration caused by this super-large thrust and overload acceleration and the impact on the structure require a lot of time to be repaired after each flight, resulting in extremely expensive operating costs. At the same time, due to the low specific impulse of the rocket engine, more fuel is consumed, and the proportion of payload is further reduced.

[0006] 4. The efficiency of the existing propulsion system has reached its limit. At the same time, the aerodynamic layout of the existing reusable spacecraft for round-trip flight between the earth and the sky is solidified in its flight mode through the atmosphere, which seriously restricts the improvement of its overall aerodynamic performance and the reduction of its operating costs.

[0007] Taking into account the main problems of current reusable spacecraft for round-trip travel between the earth and the sky in terms of the nature of energy operation, aerodynamic thermal protection costs, and ways of crossing the atmosphere, as well as the future development and improvement of emerging disciplines and technologies, this application proposes a low-cost, high-frequency reusable, small-payload space transportation system and method to solve the above problems. Summary of the invention

[0008] The purpose of the research and development of the present invention is to solve the main problems existing in the existing reusable spacecraft in terms of energy operation nature, aerodynamic thermal protection cost and mode of passing through the atmosphere. A brief overview of the present invention is given below to provide a basic understanding of certain aspects of the present invention. It should be understood that this overview is not an exhaustive overview of the present invention. It is not intended to determine the key or important parts of the present invention, nor is it intended to limit the scope of the present invention.

[0009] The technical solution of the present invention:

[0010] Option 1: A low-cost, high-frequency reusable small-payload aerospace transportation system, including a ground-based electromagnetic boost launch system, a two-stage carrier, an orbiter integrated platform and an orbiter integrated re-entry return platform. The launching end of the ground-based electromagnetic boost launch system is connected to the two-stage carrier. The ground-based electromagnetic boost launch system is used to launch the two-stage carrier into space. The two-stage carrier includes a first-stage orbiter, a fairing connection cover and a second-stage thruster. The first-stage orbiter is connected to the second-stage thruster through the fairing connection cover. After the two-stage carrier is launched, the first-stage orbiter is separated from the fairing connection cover and the second-stage thruster and then enters the orbiter integrated platform. After the first-stage orbiter completes its orbital mission, it enters the orbiter integrated re-entry return platform.

[0011] Furthermore, after the second-stage thruster completes propulsion, it is received by a recovery system, and the recovery system is an ocean recovery system or a ground recovery system.

[0012] Furthermore, the orbiter integrated re-entry return platform is composed of multiple orbiter receiving parts, each orbiter receiving part includes a high-strength connection mechanism and a flexible connection mechanism, and the high-strength connection mechanism and the flexible connection mechanism are arranged in a circle with the orbiter receiving point as the center point.

[0013] Furthermore, the angle of attack between the two-stage carrier and the ground electromagnetic boost launch system is greater than 60°.

[0014] Solution 2: A low-cost, high-frequency, reusable, small-load space transportation method, which is based on the low-cost, high-frequency, reusable, small-load space transportation system described in Solution 1, and includes the following steps:

[0015] Step 1: The two-stage carrier is launched from the ground at a high angle of attack by a ground-based electromagnetic boost launch system. According to the electric boost and dynamic pressure limit, the take-off speed ranges from 1.3 Ma to 1.6 Ma;

[0016] Step 2: According to the formula Calculate the altitude of the two-stage vehicle, where E is energy altitude, H is flight altitude, V is flight speed, and g is gravitational acceleration;

[0017] The two-stage vehicle reaches an altitude of 9km by inertia at takeoff speed, and the first-stage orbiter combined engine ignites. After climbing to an altitude of 45km and reaching a speed of about 5.0Ma, the engine is shut down.

[0018] Step 3: The two-stage vehicle continues to climb by inertia until it reaches an altitude of 55 km, and part of the kinetic energy of the two-stage vehicle is converted into altitude potential energy;

[0019] Step 4: The rocket engine of the second stage booster is ignited to bring the two-stage vehicle to an altitude of 80 km;

[0020] Step 5: The second-stage booster separates from the first-stage orbiter, discards the fairing cover, and the first-stage orbiter rocket engine ignites to relay into orbit. The second-stage booster uses energy management to achieve unpowered gliding descent and return to the field, and is received by the recovery system.

[0021] Step 6: After the first-stage orbiter mission is completed, the orbiter integrated re-entry return platform formed by multiple first-stage orbiters via high-strength connection mechanisms and flexible connection mechanisms will be separated from the orbiter integrated platform, which will greatly increase the windward area of ​​the single first-stage orbiter during its return and re-entry, and reduce the aerodynamic heat load by controlling the flight trajectory through a jumping circling deceleration at the edge of the dense atmosphere for concentrated return.

[0022] 1. A low-cost, high-frequency reusable small-load aerospace transportation system and method of the present invention adopts a ground-based electromagnetic boost launch system. The launch support system is a two-stage carrier, which provides initial kinetic energy to achieve a higher take-off speed, can effectively reduce the propellant and take-off mass, and reduce the wing area requirement.

[0023] 2. The low-cost, high-frequency reusable small-payload aerospace transportation system of the present invention adopts high-speed and high-angle launch, and the initial climb phase utilizes the take-off kinetic energy to convert into altitude potential energy to pass through the low-altitude and high-density area within 10km without power and at a low speed. Combined with shortening the flight time in the atmosphere and reducing the flight speed in the high-density and low-altitude area, it effectively reduces the drag loss and aerodynamic thermal protection requirements.

[0024] 3. The orbiter-integrated re-entry and return platform of the low-cost, high-frequency reusable small-payload aerospace transportation system of the present invention integrates and returns the first-stage orbiter combination, greatly increases the frontal area, and reduces the aerodynamic heat load by controlling the flight trajectory of "jumping" circling deceleration at the edge of the dense atmosphere.

[0025] 4. The low-cost, high-frequency reusable small-payload aerospace transportation system of the present invention adopts a new operating mode of "breaking the whole into parts" decomposed two-stage orbital entry and "gathering the parts into a whole" modular integrated combined re-entry and return, which can effectively reduce the cost of the thermal protection system, and provide the possibility for relaxing the aerodynamic thermal protection design of the orbiter aerodynamic layout and adopting a higher lift-to-drag ratio aerodynamic layout to improve the low-speed aerodynamic performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of a low-cost, high-frequency reusable small-load space transportation system;

[0027] Figure 2 It is a schematic diagram of a two-stage vehicle;

[0028] Figure 3 It is a schematic diagram of Mach number-altitude flight trajectory control during the takeoff and climb phase of a two-stage carrier;

[0029] Figure 4 This is a schematic diagram of the orbiter integrated re-entry platform.

[0030] In the figure: 1-first-stage orbiter, 2-fairing connection cover, 3-second-stage thruster, 4-ground electromagnetic boost launch system, 5-two-stage carrier, 6-orbiter integration platform, 7-orbiter integrated re-entry return platform, 8-recovery system, 9-high-strength connection mechanism, 10-flexible connection mechanism, 11-orbiter receiving point. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is described below by the specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0032] The connection mentioned in the present invention is divided into fixed connection and detachable connection. The fixed connection (i.e., non-detachable connection) includes but is not limited to conventional fixed connection methods such as folding connection, rivet connection, bonding connection and welding connection. The detachable connection includes but is not limited to conventional detachable methods such as threaded connection, snap connection, pin connection and hinge connection. When the specific connection method is not clearly defined, it is assumed that at least one connection method can always be found in the existing connection methods to achieve the function. Those skilled in the art can choose according to their needs. For example: welding connection is selected for fixed connection, and hinge connection is selected for detachable connection.

[0033] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0034] Embodiment 1, combination Figure 1-Figure 4The present embodiment is described. A low-cost, high-frequency, reusable, small-payload aerospace transportation system of the present embodiment includes a ground-based electromagnetic boost launch system 4, a two-stage carrier 5, an orbiter integrated platform 6, and an orbiter integrated re-entry return platform 7. The launch end of the ground-based electromagnetic boost launch system 4 is connected to the two-stage carrier 5. The ground-based electromagnetic boost launch system 4 is used to launch the two-stage carrier 5 into space. The two-stage carrier 5 includes a first-stage orbiter 1, a fairing connection cover 2, and a second-stage thruster 3. The first-stage orbiter 1 is connected to the second-stage thruster 3 through the fairing connection cover 2. After the two-stage carrier 5 is launched, the first-stage orbiter 1 is separated from the fairing connection cover 2 and the second-stage thruster 3 and enters the orbiter integrated platform 6. After the first-stage orbiter 1 completes its orbital mission, it enters the orbiter integrated re-entry return platform 7.

[0035] The two-stage vehicle 5 uses a two-stage small payload carrier for orbiting, including a first-stage orbiter 1 and a second-stage thruster 3, which is mainly used to carry 500kg-class small satellites and 100kg-class micro satellites. The first-stage orbiter 1 has the ability to stay in orbit for a long time and change orbits, and can perform a variety of tasks. The first-stage orbiter 1 uses a combined engine, and the second-stage thruster 3 uses a rocket engine, which can provide commercial launch services.

[0036] The angle of attack between the two-stage carrier 5 and the ground electromagnetic boost launch system 4 is greater than 60°. The high angle of attack launch effectively reduces the drag loss and aerodynamic thermal protection requirements. After the second-stage thruster 3 drives the first-stage orbiter 1 to a certain height through the rocket engine, the second-stage thruster 3 separates from the first-stage orbiter 1 and discards the fairing connection cover 2. The first-stage orbiter 1 continues to rise, and the second-stage thruster 3 descends and returns to the field to be recovered by the recovery system 8. The recovery system 8 is an ocean recovery system or a land recovery system.

[0037] The orbital integrated re-entry return platform 7 is composed of multiple orbiter receiving parts, each orbiter receiving part includes a high-strength connection mechanism 9 and a flexible connection mechanism 10. The high-strength connection mechanism 9 and the flexible connection mechanism 10 are staggered in a circle with the orbiter receiving point 11 as the center point. After the operation of the first-stage orbiter 1 is completed, it is separated from the orbiter collection platform 6 through the orbiter receiving part. The orbital receiving part composed of the high-strength connection mechanism 9 and the flexible connection mechanism 10 can greatly increase the frontal area of ​​the first-stage orbiter 1 when returning and re-entering, and the aerodynamic heat load is reduced by controlling the "jumping" circling deceleration flight trajectory at the edge of the dense atmosphere.

[0038] Embodiment 2, combined Figure 1-Figure 4 This embodiment describes a low-cost, high-frequency, reusable, small-load air-space transportation method, including the following steps:

[0039] Step 1: The two-stage carrier 5 is launched from the ground at a high angle of attack by the ground electromagnetic boost launch system 4. According to the electric boost and dynamic pressure limit, the take-off speed ranges from 1.3 Ma to 1.6 Ma;

[0040] Step 2: According to the formula Calculate the height of the two-stage vehicle 5, where E is energy height, H is flight height, V is flight speed, and g is gravitational acceleration;

[0041] The two-stage vehicle 5 reaches an altitude of 9 km by inertia at takeoff speed, and the combined engine of the first-stage orbiter 1 is ignited. After climbing to an altitude of 45 km and reaching a speed of about 5.0 Ma, the engine is shut down;

[0042] Step 3: The two-stage vehicle 5 continues to climb by inertia until it reaches an altitude of 55 km, and part of the kinetic energy of the two-stage vehicle 5 is converted into altitude potential energy;

[0043] Step 4: The rocket engine of the second-stage booster 3 is ignited to bring the two-stage vehicle 5 to an altitude of 80 km;

[0044] Step 5: The second-stage thruster 3 separates from the first-stage orbiter 1, and the fairing connection cover 2 is discarded. The rocket engine of the first-stage orbiter 1 ignites and relays into orbit. The second-stage thruster 3 uses energy management to achieve unpowered gliding descent and return to the field, and is received by the recovery system 8;

[0045] Step 6: After the mission of the first-stage orbiter 1 is completed, the orbiter integrated re-entry return platform 7 formed by the high-strength connection mechanism 9 and the flexible connection mechanism 10 of multiple first-stage orbiters 1 is separated from the orbiter integrated platform 6, which greatly increases the windward area of ​​the single first-stage orbiter 1 when returning and re-entering, and reduces the aerodynamic heat load through the control of the jumping circling deceleration flight trajectory at the edge of the dense atmosphere for concentrated return.

[0046] This embodiment is only an exemplary description of the present invention and does not limit its protection scope. Those skilled in the art may also make partial changes thereto. As long as they do not exceed the spirit of the present invention, they are within the protection scope of the present invention.

Claims

1. A low-cost, high-frequency, reusable, small-load space transportation method, the method is implemented based on a low-cost, high-frequency, reusable, small-load space transportation system, the transportation system comprising a ground electromagnetic boost launch system (4), a two-stage carrier (5), an orbiter integration platform (6) and an orbiter integration re-entry return platform (7), the launch end of the ground electromagnetic boost launch system (4) is connected to the two-stage carrier (5), the ground electromagnetic boost launch system (4) is used to launch the two-stage carrier (5) into space, the two-stage carrier (5) comprises a first-stage orbiter (1), a fairing connection cover (2) and a second-stage thruster (3), the first-stage orbiter (1) is connected to the second-stage thruster (3) by the first-stage thruster (1) The flow connection cover (2) is connected to the second-stage thruster (3). After the two-stage carrier (5) is lifted off, the first-stage orbiter (1) is separated from the fairing connection cover (2) and the second-stage thruster (3) and enters the orbiter integration platform (6). After the first-stage orbiter (1) completes the orbital mission, it enters the orbiter integration re-entry return platform (7). The orbiter integration re-entry return platform (7) is composed of a plurality of orbiter receiving parts, each of which includes a high-strength connection mechanism (9) and a flexible connection mechanism (10). The high-strength connection mechanism (9) and the flexible connection mechanism (10) are arranged in a staggered manner around the orbiter receiving point (11) as the center point. The invention is characterized in that The following steps are involved: Step 1: The two-stage carrier (5) is launched from the ground at a high angle of attack by a ground electromagnetic boost launch system (4). According to the electric boost and dynamic pressure limit, the take-off speed ranges from 1.3 Ma to 1.6 Ma; Step 2: According to the formula Calculate the height of the two-stage vehicle (5), where E is energy height, H is flight height, V is flight speed, and g is gravitational acceleration; The two-stage carrier (5) reaches an altitude of 9 km by inertia at takeoff speed, and the combined engine of the first-stage orbiter (1) is ignited. After climbing to an altitude of 45 km and reaching a speed of 5.0 Ma, the engine is shut down; Step 3: The two-stage vehicle (5) continues to climb by inertia until it reaches an altitude of 55 km, and part of the kinetic energy of the two-stage vehicle (5) is converted into altitude potential energy; Step 4: The rocket engine of the second stage booster (3) is ignited to bring the two-stage vehicle (5) to an altitude of 80 km; Step 5: The second-stage thruster (3) separates from the first-stage orbiter (1), and the fairing connection cover (2) is discarded. The rocket engine of the first-stage orbiter (1) ignites and enters the orbit. The second-stage thruster (3) uses energy management to achieve unpowered gliding descent and return to the field, and is received by the recovery system (8). Step 6: After the mission of the first-stage orbiter (1) is completed, the orbiter integrated re-entry return platform (7) formed by the high-strength connection mechanism (9) and the flexible connection mechanism (10) of multiple first-stage orbiters (1) is separated from the orbiter integrated platform (6), which greatly increases the windward area of ​​the single first-stage orbiter (1) when returning and re-entering, and reduces the aerodynamic heat load through the control of the deceleration flight trajectory at the edge of the dense atmosphere.

2. A low-cost, high-frequency, reusable small-load air-to-space transportation method according to claim 1, characterized in that: After the second-stage propeller (3) completes propulsion, it is received by a recovery system (8), and the recovery system (8) is an ocean recovery system or a ground recovery system.

3. A low-cost, high-frequency, reusable small-load air-space transportation method according to claim 2, characterized in that: The angle of attack between the two-stage carrier (5) and the ground electromagnetic boost launch system (4) is greater than 60°.

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