Integrated space shuttle based on two-stage rocket
By integrating the two-stage rocket with the space shuttle design, the problems of limited functionality and high maintenance costs of existing spacecraft have been solved, enabling multiple uses and flexible landing site selection, thus improving safety and economy.
Patent Information
- Application Number
- CN202520051052.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-09
- Publication Date
- 2025-12-23
- Estimated Expiration
- 2035-01-09
AI Technical Summary
Existing spacecraft launch methods are limited in function, rocket fairings are prone to detachment and damage, space shuttles have high maintenance costs, and landing sites are fixed and easily detected, resulting in insufficient safety.
It adopts an integrated design of a two-stage rocket and a space shuttle. After the rocket's nose cone is jettisoned, the space shuttle returns autonomously to dock with the space station for cargo transfer. The rocket body serves as a thermal protection structure, and the wings and tail are retractable, enabling it to be a multi-purpose spacecraft.
It enables reusable spacecraft, solves the problem of rocket fairing detachment, reduces maintenance costs, and improves safety and landing site flexibility.
Smart Images
Figure CN223702971U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the field of spacecraft technology, in particular to an integrated space shuttle based on a two-stage rocket. BACKGROUND
[0002] With the pace of human exploration of space extending, on-orbit construction technology has become a hot spot in space technology research, low-cost, reusable and highly reliable space-to-ground shuttle technology is an effective means to solve space cargo transportation, and the space shuttle has once again entered people's field of vision.
[0003] The existing spaceship is launched in a rocket fairing, and the rocket fairing is thrown after being launched into orbit, and the rocket-ship separation mode is used for upward flight, and the rocket cannot carry other satellites or spacecraft for upward flight during launch, and the single launch function is single.
[0004] When the return type spaceship uses a parachute or a glide parachute deceleration method, the landing site or range is relatively fixed, and it is easy to be discovered and destroyed by hostile forces.
[0005] The existing space shuttle has once been abandoned due to the problems of more external curved surfaces, easy falling of the laid heat insulation tiles, high maintenance cost, and low safety. CONTENT OF THE INVENTION
[0006] The embodiment of the present application provides an integrated space shuttle based on a two-stage rocket, which integrates the space shuttle and the two-stage rocket, sends the carried satellite to a predetermined orbit first, and then throws away the shell at the head of the rocket; then the space shuttle and the on-orbit space station and other orbital vehicles complete on-orbit docking to perform cargo transfer and other work; finally, the space shuttle re-enters the atmosphere and returns to the ground autonomously.
[0007] The embodiment of the present application provides an integrated space shuttle based on a two-stage rocket, which includes a two-stage rocket and a docking device, wherein,
[0008] The front end of the two-stage rocket includes a rocket fairing, and a plurality of satellites are arranged in the rocket fairing;
[0009] The rocket body of the two-stage rocket includes a space shuttle cabin, the rocket fairing and the space shuttle cabin are connected through the docking device, the space shuttle cabin can accommodate a space shuttle, and the space shuttle is provided with telescopic wings;
[0010] In the case that the space shuttle is placed in the space shuttle cabin, the telescopic wings of the space shuttle are in a contracted state, a telescopic wing locking ring is arranged on the space shuttle cabin to lock the telescopic wings of the space shuttle, and telescopic wing sliding rails are arranged at both ends of the space shuttle cabin.
[0011] Optionally, the tail of the space shuttle is further provided with a retractable tail wing.
[0012] Optionally, the docking device is installed in the head protection cover of the space shuttle, and after the structure carrying the satellite ascending part on the front end of the second-stage rocket is thrown away, the docking device is exposed, the head protection cover of the space shuttle is unlocked, and the space shuttle is docked with other devices.
[0013] Optionally, the landing gear system is further included, and the landing gear system is retracted in the belly of the space shuttle.
[0014] Optionally, the first retractable wing sliding track is arranged on one side of the cabin of the space shuttle facing the rocket fairing.
[0015] The retractable wing locking ring includes a middle retractable wing locking ring arranged on the first retractable wing sliding track to lock the retractable wing of the head of the space shuttle.
[0016] Optionally, the second retractable wing sliding track is further arranged at the tail of the cabin of the space shuttle.
[0017] The retractable wings of the head and the tail of the space shuttle are locked based on the first retractable wing sliding track and the second retractable wing sliding track respectively.
[0018] Optionally, the rocket body of the second-stage rocket is designed in an integrated manner with the cabin of the space shuttle, the rocket body of the second-stage rocket is taken as the thermal protection structure of the spacecraft entering and exiting the atmosphere, and an installation space for ascending and descending cargos is arranged in the rocket body.
[0019] The embodiment of the present application integrates the space shuttle and the second-stage rocket, first sends the carried satellite to a predetermined orbit, throws away the shell of the head of the rocket after completion, then completes the on-orbit docking with the on-orbit space station and other orbiting spacecraft, and performs cargo transfer and other work, and finally the space shuttle reenters the atmosphere and returns to the ground autonomously, can realize one rocket multiple use, can be reused after landing, simultaneously solves the problem of thermal protection, and can realize precise return landing.
[0020] The above description is only a summary of the technical scheme of the present application, in order to more clearly understand the technical means of the present application, which can be implemented according to the content of the specification, and in order to make the above and other purposes, characteristics and advantages of the present application more obvious and easy to understand, the following specific embodiments of the present application are described. BRIEF DESCRIPTION OF DRAWINGS
[0021] Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The accompanying drawings are included to provide a description of the preferred embodiments and are not meant to limit the present application. Furthermore, the same reference numerals are used throughout the several drawings to represent similar components. In the drawings:
[0022] Figure 1 A schematic diagram of an integrated space shuttle structure according to an embodiment of the present application;
[0023] Figure 2 、 3 A schematic diagram of a partial structure of a cabin of an integrated space shuttle according to an embodiment of the present application;
[0024] Figure 4 A launch process of an integrated space shuttle according to an embodiment of the present application;
[0025] Figure 5 A launch process of an integrated space shuttle according to an embodiment of the present application. DETAILED DESCRIPTION
[0026] Exemplary embodiments of the present disclosure will be described in detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it is understood that the present disclosure can be embodied in various forms without being limited by the embodiments set forth herein. Rather, these embodiments are provided so that the present disclosure will be thorough and complete, and will fully convey the scope of the present disclosure to those skilled in the art.
[0027] An integrated space shuttle based on a two-stage rocket is provided according to an embodiment of the present application, as shown in Figures 1-3 which includes a two-stage rocket, a docking device 5, wherein,
[0028] The front end of the two-stage rocket includes a rocket fairing 1, and a plurality of satellites are arranged in the rocket fairing 1.
[0029] The rocket body of the two-stage rocket includes a space shuttle cabin, the rocket fairing is connected to the space shuttle cabin through the docking device, the space shuttle cabin can accommodate a space shuttle, and the space shuttle is provided with retractable wings, as shown in Figure 1 The space shuttle is also provided with a head protection cover 2. The docking device 5 is arranged in the head protection cover 2.
[0030] In the case where the space shuttle is built into the space shuttle cabin, the retractable wings of the space shuttle are in a retracted state, the space shuttle cabin is provided with a retractable wing locking ring to lock the retractable wings of the space shuttle, and the two ends of the space shuttle cabin are provided with retractable wing sliding tracks. As shown in Figure 1 the retractable wings 4 of the space shuttle in the retracted state, and the space shuttle cabin is provided with an outer shell retractable wing locking ring 3 to achieve locking through the outer shell retractable wing locking ring 3.
[0031] In some embodiments, the tail of the space shuttle is also provided with retractable tail wings 11.
[0032] In a specific example, the telescopic wings 4 are devices for ensuring flight after the space shuttle returns to the atmosphere, and are retracted and fixed in the second-stage rocket body when the rocket ascends, and are extended and pushed out after the space shuttle passes through the atmosphere and slows down through engine reverse thrust, etc., like the extended telescopic wings 10 shown in the figure, the space shuttle changes to level flight, and is navigated to the designated landing site through the command console to land. Figure 2
[0033] The telescopic tail wings 11 are devices for controlling the direction of the space shuttle during the process of changing to level flight after returning to the earth, and can be operated to extend the tail wings at the same time when the telescopic wings 11 are extended after the space shuttle re-enters the atmosphere.
[0034] In some embodiments, the docking device is installed in the head protection cover 2 of the space shuttle, and after the structure of the second-stage rocket carrying the satellite ascending part is thrown off, the docking device 5 is exposed, the head protection cover 2 of the space shuttle is unlocked, and docking of the space shuttle with other devices is realized.
[0035] For example, in some examples, the satellites are fixed in the rocket fairing 1 of the second-stage rocket in a multi-satellite stacking manner, the rocket fairing 1 is thrown off after entering the predetermined orbit, then the stacking lock is released, each satellite is separated from the fixed structure of the rocket body and enters the orbit, and after all satellites are separated, the structure of the second-stage rocket carrying the satellite ascending part is thrown off, and the head protection cover 2 of the space shuttle is exposed.
[0036] As the space shuttle ascends, the second-stage rocket body is designed to be integrated with the cabin body of the space shuttle, and the second-stage rocket body is used as a thermal protection structure for the spacecraft to enter and exit the atmosphere, and the installation space for ascending and descending cargo is arranged inside the rocket body. After the structure of the second-stage rocket carrying the satellite ascending part is thrown off, part of the docking device 5 is exposed, and when the space shuttle is ready to dock with the space station, the on-orbit residence spacecraft and other spacecraft, the head protection cover of the space shuttle is unlocked and turned open, and the space shuttle accelerates to dock with the space station, the on-orbit residence spacecraft and other spacecraft. After docking, astronauts can enter the space shuttle on orbit to perform cargo transfer, fuel supply and other work.
[0037] In some embodiments, a landing gear system 12 is also included, which is retracted in the belly of the space shuttle and is designed and constructed the same as a common passenger plane, and when the space shuttle enters the atmosphere and changes to level flight before landing, the landing gear is lowered through remote control instructions to complete the landing action.
[0038] In some embodiments, the side of the space shuttle cabin body facing the rocket fairing is provided with a first telescopic wing sliding rail 6;
[0039] The telescopic wing locking ring includes a middle telescopic wing locking ring 7 arranged on the first telescopic wing sliding rail 6 to lock the telescopic wings at the head of the space shuttle.
[0040] In some embodiments, the tail of the space shuttle cabin is also provided with a second retractable wing sliding track 8;
[0041] The space shuttle head and tail retractable wings are locked based on the first retractable wing sliding track 6 and the second retractable wing sliding track 8 respectively. In a specific example, the tail of the retractable wing 4 is also provided with a retractable wing locking joint 9.
[0042] In some embodiments, the rocket body of the two-stage rocket is designed in an integrated manner with the space shuttle cabin, and the rocket body of the two-stage rocket is used as a heat protection structure for the spacecraft to enter and exit the atmosphere, and an installation space for uplink and downlink cargo is arranged inside the rocket body.
[0043] The application also proposes an implementation case of an integrated space shuttle based on a two-stage rocket, as shown in Figure 4 The integrated space shuttle two-stage rocket, docking device, retractable wing, and landing gear system in this example. The rocket is launched from the ground to ascend, and rocket separation is performed at the separation height of the first and second stages. The first-stage rocket separates and recovers. The second-stage rocket continues to ascend to the satellite orbit, throws away the rocket fairing, and separates the satellite from the rocket into the orbit. After all the satellites carried are separated into the orbit, the head of the second-stage rocket is thrown away. The space shuttle head protection cover is exposed, the space shuttle moves to the space station orbit preparation docking space, the space shuttle head protection cover is turned over and opened and locked, the docking device is exposed outside, the space shuttle captures the space station docking port, and the on-orbit docking is completed. After pressure relief, astronauts enter the space shuttle from the space station to carry out cargo transfer work. After the on-orbit stay task of the space shuttle is completed, the space shuttle releases the docking lock with the space station, separates from the space station, turns over the head protection cover to fold and lock, enters the downlink orbit, and after re-entering the atmosphere, slows down to the specified speed by means of engine reverse thrust, etc. The retractable wing locking joint is unlocked, the retractable wing is locked with the middle retractable wing locking ring, the retractable wing slides along the sliding track to completely expose the rocket body, the wing is converted from the retracted state to the extended state, the locking joint is locked with the shell locking ring, and the retractable tail wing is converted from the retracted state to the extended state. The space shuttle changes to flat flight, slows down, and lowers the landing gear to complete landing.
[0044] The application also proposes another implementation case of an integrated space shuttle based on a two-stage rocket, as shown in Figure 5 The process from ground launch to throwing away the head of the second-stage rocket is the same as in the previous embodiment, and the specific operation is as follows:
[0045] The space shuttle rises to a lunar orbit, the space shuttle's retractable wings are unlocked and turned into an extended state and locked, considering the special environment of the moon without an atmosphere, the space shuttle is turned into a flat flight, the landing gear is lowered and landed on the landing field of the lunar base, and the lunar exploration work is carried out, after the corresponding task is completed, the space shuttle takes off and prepares to return to the earth; first, it is lowered to the space station docking orbit, the space shuttle head protection cover is unlocked and turned before docking, and then the space station docking operation is the same as the foregoing embodiment, when preparing to return to the ground after the on-orbit task is completed, the retractable wings are unlocked by electricity in advance from the extended state, and are retracted to the retracted state and locked, the landing gear is retracted and locked, then the space shuttle is unlocked from the space station docking, and the subsequent return to the ground process is the same as the foregoing embodiment.
[0046] The embodiment of the present application integrates the space shuttle and the two-stage rocket, first sends the carried satellite to a predetermined orbit, and then throws away the shell at the head of the rocket after completion; then the space shuttle and the on-orbit space station complete on-orbit docking and perform cargo transfer and other work; finally, the space shuttle reenters the atmosphere and returns to the ground autonomously, which can realize one rocket with multiple uses, can be reused after landing, and solves the problem of thermal protection, and can realize precise return to the landing field and solve the problem of thermal protection.
[0047] It should be noted that in the embodiments of the present application, the terms "comprise", "contain" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or device. Without more limitations, the element defined by the statement "comprises a" does not exclude the presence of another identical element in the process, method, article or device including the element.
[0048] The serial numbers of the above embodiments of the present application are only for description, and do not represent the advantages and disadvantages of the embodiments.
[0049] The embodiments of the present application are described above in combination with the drawings, but the present application is not limited to the above specific embodiments, the above specific embodiments are only illustrative and not restrictive, and those skilled in the art can make many forms under the inspiration of the present application without departing from the scope of the present application and the protection scope of the claims.
Claims
1. An integrated space shuttle based on a two-stage rocket, characterized in that, Including the second stage rocket and docking device, among which, The front end of the second-stage rocket includes a rocket fairing, and multiple satellites are arranged inside the rocket fairing; The second-stage rocket body includes a space shuttle cabin. The rocket fairing is connected to the space shuttle cabin via a docking device. The space shuttle cabin can accommodate the space shuttle, and the space shuttle is equipped with retractable wings. When the space shuttle is housed within the space shuttle cabin, the space shuttle's telescopic wings are in a retracted state. The space shuttle cabin is equipped with telescopic wing locking rings to lock the space shuttle's telescopic wings, and telescopic wing sliding tracks are provided at both ends of the space shuttle cabin.
2. The integrated space shuttle based on a two-stage rocket as described in claim 1, characterized in that, The space shuttle is also equipped with a retractable tail fin.
3. The integrated space shuttle based on a two-stage rocket as described in claim 1, characterized in that, The docking device is installed inside the nose shield of the space shuttle. After the structure carrying the satellite's ascent section at the front of the second-stage rocket is jettisoned, the docking device is exposed, the nose shield of the space shuttle is unlocked, and the space shuttle can dock with other equipment.
4. The integrated space shuttle based on a two-stage rocket as described in claim 1, characterized in that, It also includes a landing gear system that retracts into the belly of the space shuttle.
5. The integrated space shuttle based on a two-stage rocket as described in claim 1, characterized in that, The space shuttle cabin is provided with a first telescopic wing sliding track on the side facing the rocket fairing; The telescopic wing locking ring includes a central telescopic wing locking ring, which is disposed on the first telescopic wing sliding track to lock the telescopic wing at the nose of the space shuttle.
6. The integrated space shuttle based on a two-stage rocket as described in claim 5, characterized in that, The tail section of the space shuttle also features a second telescopic wing sliding track. The nose and tail retractable wings of the space shuttle are locked based on the first retractable wing sliding track and the second retractable wing sliding track, respectively.
7. The integrated space shuttle based on a two-stage rocket as described in claim 1, characterized in that, The second-stage rocket's body is integrated with the space shuttle's cabin design, with the second-stage rocket's body serving as the spacecraft's thermal protection structure for entering and exiting the atmosphere. The rocket's interior contains space for loading cargo for both up and down journeys.