Manned cargo version space shuttle and booster combination launch vehicle

Abstract

The utility model relates to spaceflight launching and recycling multipurpose technology field provides a manned freight type space shuttle and boost type space shuttle combination launching device, both have the aerodynamic shape of main wing, front wing and tail vertical wing, and engine group, are launched by vertical parallel binding mode combination, are separated at 100 kilometers height from ground after launching and ascending, boost type space shuttle controls flight attitude and lands to ground airport through front wing, manned freight type space shuttle enters the atmosphere after completing the task in outer space, opens telescopic front wing and can turn to attitude control propeller and adjusts flight attitude and lands to ground airport. The utility model is the space device of complete reuse, can carry out manned spaceflight, freight transportation, outer space fuel transportation filling and planet exploration task, also is applicable to large orbit space station construction.

Description

Technical Field

[0001] This utility model relates to the launch and recovery reuse technology of spacecraft. Background Technology

[0002] To reduce the costs of rocket launches and space exploration, countries worldwide have developed various partially reusable launch vehicles, primarily based on traditional bare-barreled tandem multistage rocket technology. These rely on vertical launch and vertical point-to-ground recovery of the first-stage booster rocket, while the second-stage rockets are mostly single-use and lack full reusability. Traditional tandem multistage rockets typically consist of a first-stage booster and a second-stage rocket in series. Limited by their structural design, they cannot be infinitely scaled up to achieve greater thrust, thus limiting their payload capacity. Furthermore, the larger the rocket, the more difficult recovery becomes, relying on specific ground-based facilities. Additionally, bare-barreled launch vehicles face greater control challenges during atmospheric recovery, are prone to tumbling and loss of control during attitude adjustments, and lack maneuverability, especially in the thin atmosphere where rapid descent speeds further complicate attitude control.

[0003] The reusable launch vehicles that have been developed by various countries are generally bare-barreled, single-stage booster launch vehicles. In the event of loss of control during launch or recovery, they are generally disposed of by self-destruction in the air, soft landing at sea, or uncontrollable hard landing on land. If recovery fails due to loss of control or engine thrust failure, the payload will be scrapped along with the launch, and a hard landing on land may cause incalculable loss of life and property.

[0004] In terms of manned spaceflight, since the retirement of the Space Shuttle, manned spaceflight both domestically and internationally has been primarily carried out using spacecraft reentry capsules for return. This has led to the industry phenomenon of separating crew and cargo during the launch process. Furthermore, the reentry capsule has limited carrying capacity. After entering the atmosphere from space, the reentry capsule usually lands without power or uses parachutes for deceleration and cushioning. In particular, the sea splashdown recovery method requires a large amount of manpower and equipment for coordinated recovery. It is evident that reentry capsule-based manned spaceflight has low reliability, low efficiency, and high cost. Summary of the Invention

[0005] To address the problems of high recovery risk, low carrying capacity, low launch efficiency, and inability to fully reuse existing spacecraft, this invention provides a new technology that can improve the safety, carrying capacity, and launch efficiency of spacecraft, thereby solving the problems of high recovery difficulty and inability to fully reuse spacecraft.

[0006] The solution adopted by this utility model to solve its technical problem is:

[0007] A fully reusable manned cargo space shuttle and booster space shuttle launch combination comprises a manned cargo space shuttle and a booster space shuttle. The manned cargo space shuttle has a main wing, a tail fin, and retractable canards. The airframe is primarily constructed of carbon fiber, aluminum-lithium alloy, and austenitic stainless steel. The forward section of the manned cargo space shuttle features a replaceable manned escape cabin, auxiliary cargo bay, or auxiliary fuel bay. Retractable canards are located on both sides. There is a thruster nozzle on each side of the forward section, consisting of two steerable attitude control thrusters. The midsection of the airframe houses an openable main cargo bay. The rear section contains a fuel bay consisting of two compressed tanks for liquid oxygen and liquid methane, and eight reusable booster spacecraft. The engine pack consists of a liquid oxygen methane engine and three reusable liquid oxygen methane vacuum engines. The fuselage has connector devices at the front and rear of the belly for docking with the booster space shuttle. The belly skin is made of austenitic stainless steel and covered with low thermal conductivity heat insulation tiles. There are three openable structures on the belly for the retraction and extension of the landing gear. The front landing gear is located in the center of the belly in front of the connector devices, and the rear landing gear is located outside the liquid oxygen methane vacuum engines on the belly. The three landing gear positions form an isosceles triangle. The booster-type space shuttle has a main wing, a tail fin, and a canard. The airframe is mainly composed of austenitic stainless steel, carbon fiber, and aluminum-lithium alloy. The front of the booster-type space shuttle has an unmanned flight control system cabin and an adjustable canard. The interior of the airframe mainly consists of a fuel tank composed of two compressed tanks for liquid oxygen and liquid methane. The rear of the airframe has 14 reusable liquid oxygen and methane engines. The nose and tail of the fuselage have connector devices for docking with manned cargo space shuttles. The belly skin of the airframe is made of austenitic stainless steel and has three openable structures for the retraction and extension of the landing gear. The front landing gear is located in the middle of the nose belly in front of the connector devices, and the rear landing gear is located on the outer sides of the engines on the belly of the airframe. The three landing gear positions form an isosceles triangle.

[0008] The aforementioned fully reusable manned cargo space shuttle and booster space shuttle utilize liquid-fueled engines powered by liquid oxygen and liquid methane. They are launched in a vertical, parallel, bundled configuration. Initially, the booster space shuttle provides primary thrust, with the manned cargo space shuttle providing auxiliary thrust. After liftoff, at an altitude of 100 kilometers, the booster space shuttle shuts off its engines and detaches from the manned cargo space shuttle, which simultaneously accelerates to maximum thrust for entry into space. The booster space shuttle then restarts its engines and uses its canards to adjust its attitude and land at a designated airport, achieving full reuse of the first stage booster. The manned cargo space shuttle, upon reaching its designated orbit and completing spacecraft deployment with its main cargo bay open, enters the atmosphere. After passing through the blackout zone, it decelerates using its steerable attitude control thrusters, restarts its engines, and deploys its retractable canards to adjust its attitude and land at a designated airport, achieving full reuse of the second stage manned cargo space shuttle.

[0009] The aforementioned steerable attitude control thruster is hemispherical in shape and has a nozzle. It rotates to spray propellant at a specified angle to propel the manned cargo space shuttle for attitude adjustment and correction, including attitude adjustment in the atmosphere and outer space, as well as auxiliary thrust when separating from the booster space shuttle.

[0010] The aforementioned manned escape module is a standardized, replaceable modular module. In the event of an emergency during a manned space mission, it can automatically detach from the manned cargo space shuttle and deploy a buffer parachute for landing. The manned escape module can be replaced with an auxiliary cargo compartment to increase payload capacity, or with a liquid oxygen and methane auxiliary fuel compartment to increase range.

[0011] The advantages of this utility model compared with the prior art are:

[0012] 1. Compared with other booster rockets, this utility model of a booster-type space shuttle achieves full recovery and reuse by using wing gliding. During the recovery process, the booster-type space shuttle can be flexibly controlled by the engine propulsion and canard to land at any airport with a runway length of more than 1,800 meters. The recovery process has low requirements for ground facilities, which solves the problems of difficult recovery and easy loss of control of traditional bare rod configuration first-stage booster rockets in the current industry. It can also be launched in parallel with aerodynamically designed payload devices, and has wide applicability.

[0013] 2. Compared to other spacecraft and traditional space shuttles, this novel manned cargo space shuttle possesses full recoverability and reusability, as well as flexible function switching capabilities. The standardized manned escape cabin at the front of the fuselage can be replaced with modular modules according to manned or cargo requirements. During reentry to Earth, the wings can be used to flexibly control the descent speed, solving the problems of excessively rapid descent and inflexible landing site changes inherent in traditional spacecraft return capsules. In particular, it addresses the injury to astronauts and precision equipment caused by the reaction force generated during high-speed descent of traditional spacecraft return capsules. The manned escape cabin has an escape function; in dangerous situations, the entire escape cabin can be deployed to protect the astronauts' lives, solving the problem of astronauts being unable to escape in distress with traditional space shuttles. This novel manned cargo space shuttle comprehensively addresses the shortcomings and problems of both spacecraft return capsules and space shuttles.

[0014] 3. Compared to the traditional bare-bar configuration of first-stage booster launch vehicles and second-stage payload rockets used in various countries, this novel booster-type space shuttle and its manned cargo space shuttle, in the event of engine failure or launch abort during launch, can achieve emergency separation and bundling, using the main wing and canard to control flight attitude and achieve a controlled gliding landing. This solves the problem that traditional bare-bar configuration first-stage booster launch vehicles, when out of control during recovery, can only be destroyed in mid-air or undergo a hard landing, and that the payload can only be destroyed and cannot be recovered.

[0015] 4. Based on the above, the beneficial effects of this utility model's booster-type space shuttle and manned cargo space shuttle launch combination are that it changes the traditional single method of separate launch for manned and cargo spacecraft and the single method of spacecraft recovery in the entire aerospace industry, changes the recovery technology of traditional bare rod configuration first-stage booster rockets, solves the problem that existing spacecraft in various countries cannot be fully recovered, reduces manufacturing costs and launch losses, and solves the problems of low launch efficiency and carrying capacity. Attached Figure Description

[0016] Figure 1 This is a top view schematic diagram of the manned cargo spacecraft of this utility model;

[0017] Figure 2 This is a side view of the manned cargo space shuttle of this utility model, showing the manned escape cabin, main cargo cabin, and landing gear in the open state.

[0018] Figure 3 This is a schematic diagram of the fuselage belly arrangement, landing gear doors, and connectors of the manned cargo spacecraft of this utility model.

[0019] Figure 4 This is a schematic diagram of the engine assembly and landing gear of the manned cargo spacecraft of this utility model;

[0020] Figure 5 This is a top view schematic diagram of the manned cargo spacecraft of this utility model;

[0021] Figure 6 This is a side view and a schematic diagram of the manned cargo spacecraft in the present invention with its landing gear in the open state.

[0022] Figure 7 This is a schematic diagram of the fuselage belly arrangement, landing gear bay door, and connectors of the booster-type space shuttle of this utility model;

[0023] Figure 8 This is a schematic diagram of the engine assembly and landing gear of the booster-type space shuttle of this utility model;

[0024] Figure 9 This is a schematic diagram of the parallel launch of the manned cargo spacecraft and the booster spacecraft of this utility model.

[0025] Figure 10 This is a schematic diagram illustrating the launch and recovery of the manned cargo spacecraft and the booster spacecraft of this utility model.

[0026] Label Explanation:

[0027] 1-First observation window, 2-Door / interface, 3-First steerable attitude control thruster, 4-First retractable canard, 5-First main cargo door, 6-First main wing, 7-First flap assembly, 8-First liquid oxygen-methane engine assembly, 9-First tail vertical stabilizer, 10-Second flap assembly, 11-Second main wing, 12-Second main cargo door, 13-Second retractable canard, 14-Second steerable attitude control thruster, 15-Second observation window, 16-Manned escape cabin, 17-First rudder / speed brake, 18-First connector, 19-First landing gear door, 20-First landing gear, 21-Second connector, 22-Second landing gear door, 23-Second landing gear, 24-Third landing gear door, 25-Third landing gear, 26-First liquid oxygen-methane vacuum engine, 27-Second liquid oxygen-methane vacuum engine 28-Third liquid oxygen-methane vacuum engine; 29-Liquid oxygen refueling port; 30-Liquid methane refueling port; 31-Liquid oxygen refueling port / emergency release port; 32-First canard; 33-Third main wing; 34-Third flap assembly; 35-Second liquid oxygen-methane engine assembly; 36-Second tail vertical wing; 37-Fourth flap assembly; 38-Fourth main wing; 39-Second canard; 40-Liquid methane refueling port / emergency release port; 41-Second rudder / speed brake; 42-Third connector; 43-First heavy landing gear door; 44-First heavy landing gear; 45-Fourth connector; 46-Second heavy landing gear door; 47-Second heavy landing gear; 48-Third heavy landing gear; 49-Third heavy landing gear door; 50-Emergency buffer parachute system; 51-Manned cargo space shuttle; 52-Boosted space shuttle. Detailed Implementation

[0028] The technical solution of this utility model will now be described in detail with reference to the accompanying drawings:

[0029] The aforementioned manned cargo space shuttle 51 is dedicated to transporting manned, satellite, and planetary lander spacecraft. During launch, engine group 8 participates in the recoil propulsion upwards. After the cargo is statically loaded horizontally on the ground, liquid oxygen and liquid methane are added through the liquid oxygen filling port 29 and liquid methane filling port 30 in an upright position. After filling, it is connected to the booster space shuttle 52 through the first connector 18 and the second connector 21 to form a parallel bundled state. The booster space shuttle 52 is a powered space shuttle. When the empty cargo is transported horizontally, it is turned to an upright state and filled with liquid oxygen and liquid methane through the liquid oxygen filling port / emergency release port 31 and the liquid methane filling port / emergency release port 40. After filling, it is connected to the manned cargo space shuttle 51 in parallel through the third connector 42 and the fourth connector 45 on the fuselage belly. The manned cargo space shuttle 51 and the booster space shuttle 52 are launched vertically. The first liquid oxygen / methane engine group 8 and the second liquid oxygen / methane engine group 35 are started simultaneously. During the launch process, the first canard 32 and the second canard 39 of the booster space shuttle 52 adjust the launch angle and direction of the space shuttle. Upon reaching an altitude of 100 kilometers, the liquid oxygen-methane fuel of the booster shuttle 52 was consumed to 5%. The booster shuttle 52 shut down its second liquid oxygen-methane engine 35, separated from the manned cargo shuttle 51, and descended to the ground using Earth's gravity. The first canard 32, the second canard 39, and the second rudder / speed brake 41 adjusted their attitude to a horizontal state and began unpowered gliding to reduce altitude. When gliding to an altitude of 10 kilometers, the second liquid oxygen-methane engine 35 of the booster shuttle 52 reignited. The launch and landing command control of the booster shuttle 52 consisted of computer and manual remote control. When the booster shuttle 52's altitude decreased to 500 meters, the first heavy landing gear 44, the second heavy landing gear 47, and the third heavy landing gear 48 on the fuselage belly extended and lowered simultaneously. The first canard 32, the second canard 39, the second rudder / speed brake 41, the third flap assembly 34, and the fourth flap assembly 37 adjusted the angle of attack for landing on the airport runway.

[0030] As the booster space shuttle 52 separates from the manned cargo space shuttle 51, the first liquid oxygen-methane engine 8 of the manned cargo space shuttle 51 enters its orbit at full afterburner. Afterward, the first liquid oxygen-methane engine 8 is shut down, and the first liquid oxygen-methane vacuum engine 26, the second liquid oxygen-methane vacuum engine 27, and the third liquid oxygen-methane vacuum engine 28 are activated. At a designated altitude, the first main cargo door 5 and the second main cargo door 12 are opened, and the payload is deployed. Astronauts exit the spacecraft through the hatch / docking interface 2 to assist with spacecraft deployment or to communicate with spacecraft. After docking with the station and exchanging astronauts, the spacecraft will complete its designated mission and, while maintaining 5% fuel, begin its return to Earth. Upon approaching the atmosphere, the first liquid oxygen-methane vacuum engine 26, the second liquid oxygen-methane vacuum engine 27, and the third liquid oxygen-methane vacuum engine 28 will be shut down. The first steerable attitude control thruster 3 and the second steerable attitude control thruster 14 will simultaneously inject propellant for recoil deceleration, allowing the fuselage, with its heat-resistant underside facing the Earth's surface, to descend into the atmosphere. After passing through the blackout zone, at an altitude of 5 kilometers, the first liquid oxygen-methane engine 8 will reignite, and the first steerable attitude control thruster 3 and the second steerable attitude control thruster 14 will simultaneously inject propellant for further recoil deceleration and attitude adjustment. The first retractable canard wing 4 and the second retractable canard wing 13 will extend, initiating attitude and heading control for the manned cargo spacecraft 51. Simultaneously, the first steerable attitude control thruster 3 and the second steerable attitude control thruster 14 will be shut down, and the spacecraft will fly towards the airport. At an altitude of 500 meters, the first landing gear 20, the second landing gear 23, and the third landing gear 28 will re-enter the atmosphere. The landing gear 25 extends and retracts simultaneously. The first retractable canard 4, the second retractable canard 13, and the first rudder / speed brake 17 adjust the angle of attack for landing on the airport runway. The first rudder / speed brake 17, along with the first flap assembly 7 and the second flap assembly 10, begin to adjust and increase drag to decelerate until landing, after which they retract. The landing phase is controlled by computer and remote manual control or by the astronaut through manual mode to control the landing of the manned cargo space shuttle 51. At this point, the manned cargo space shuttle 51 and the booster space shuttle 52 launch combination have completed full reuse.

[0031] The aforementioned manned escape cabin 16 has an openable hatch and docking interface 2 on its top (which can dock with ground facilities and the space station for astronauts to enter and exit). The top also has two transparent, pressure-resistant, and high-temperature-resistant glass observation windows, namely the first observation window 1 and the second observation window 15. The cabin is equipped with an astronaut life support system for astronauts during manned missions. An emergency buffer parachute device 50 is located at the front of the manned escape cabin 16 where it docks with the airframe. The bottom of the manned escape cabin 16, where it connects with the airframe, has an escape ejection device and an emergency inflatable ring-shaped airbag device for buffering when forced to land on land or sea. The manned escape cabin is mechanically connected to the airframe, and a jet recoil device is located at the bottom for rapid separation from the airframe in an emergency.

[0032] The aforementioned auxiliary cargo compartment is a detachable cargo compartment with the same external structure as the manned escape cabin 16. The auxiliary cargo compartment has a swing-out hatch on the top, used for supplementing cargo transport space in the unmanned state of the manned cargo space shuttle 51. The aforementioned liquid oxygen methane auxiliary fuel compartment is a detachable fuel compartment with two fuel tanks composed of liquid oxygen and liquid methane. It is used for high-orbit missions or to extend the range of the manned cargo space shuttle 51 in the unmanned state. The external structure of the liquid oxygen methane auxiliary fuel compartment is the same as that of the manned escape cabin 16. There is a liquid oxygen methane modular interface at the bottom where it connects to the main cargo compartment of the manned cargo space shuttle 51, used for connecting the liquid oxygen methane auxiliary fuel compartment to the main fuel compartment, which can be adjusted according to the actual flight mission.

[0033] In the event of an engine failure during launch, the aforementioned manned cargo space shuttle 51 will be urgently recovered when the launch altitude exceeds 10 kilometers. It will then separate from the booster space shuttle 52 via the first connector 18 and the second connector 21. The manned cargo space shuttle 51 will glide and hover directly to the airport runway, while the booster space shuttle 52 will continue to fly vertically and consume fuel.

[0034] In the event of an engine failure during launch (when the launch altitude exceeds 10 kilometers), the booster-type space shuttle 52 will attempt emergency recovery by separating from the manned cargo space shuttle 51 via the third connector 42 and the fourth connector 45. The booster-type space shuttle 52 will release liquid oxygen and liquid methane through the liquid oxygen refueling / emergency release ports 31 and 40 on both sides of the front of the fuselage. Simultaneously, it will maintain its hovering position by controlling the first canard 32, the second canard 39, the second rudder / speed brake 41, the third flap assembly 34, and the fourth flap assembly 37. When the liquid oxygen and liquid methane are consumed to 5%, the space shuttle will glide and hover to land on the airport runway. The liquid oxygen refueling / emergency release ports 31 and 40 will form a 13° angle with the left and right sides of the fuselage.

[0035] Both the second connector 21 and the fourth connector 45 have two mechanical connection points. The two connection points of the second connector 21 are snap-fit ​​telescopic rods, which withstand shear and tensile forces. The fourth connector 45 has two concave bayonets that correspond to and engage with the second connector 21. It contains an openable / closeable locking device. When the manned cargo space shuttle 51 and the booster space shuttle 52 are linked and strapped together, the openable / closeable locking device is in the open state. Both the second connector 21 and the fourth connector 45 are equipped with electromagnetic ejection devices, which are activated during the release phase. The third connector 42 and the first connector 18 each have three mechanical connection points. The four connection points of the first connector 18 are snap-fit ​​telescopic rods, which withstand shear and tensile forces. The third connector 42 has four concave bayonets that correspond to and engage with the first connector 18. It contains an openable and closable engagement device. When the manned cargo space shuttle 51 and the booster space shuttle 52 are strapped together, the openable and closable engagement device is in the open state. Both the third connector 42 and the first connector 18 are equipped with electromagnetic ejection devices. During the separation phase, the openable and closable engagement device is closed. The second connector 21, the fourth connector 45, the third connector 42 and the first connector 18 simultaneously activate the electromagnetic ejection, and the manned cargo space shuttle 51 and the booster space shuttle 52 are separated from the parallel strapping state. The surfaces of the devices of the second connector 21, the fourth connector 45, the third connector 42 and the first connector 18 are all coated with a low thermal conductivity heat insulation coating.

[0036] The aforementioned first steerable attitude control thruster 3 and second steerable attitude control thruster 14 are both hemispherical reaction force flight attitude adjustment and control system devices. Each has a circular injection port and is mechanically linked with a motor and gears. The motor controls the injection angle, and propellant is injected at the same time as the set steering angle to obtain reaction force, adjust various flight attitudes of the manned cargo space shuttle 51 and reverse thrust when it is detached from the parallel binding of the booster space shuttle 52. The propellant type is chemical propellant. Combustion chambers are set inside the first steerable attitude control thruster 3 and the second steerable attitude control thruster 14, respectively, to mix and burn with oxidizer to generate high temperature and high pressure gas, which is then accelerated and ejected from the injection port.

[0037] The aforementioned manned cargo space shuttle 51 has a non-powered, electrically folding landing gear on its fuselage belly. It consists of a single set of two-wheeled second landing gear 23 and two sets of four-wheeled landing gear (first landing gear 20 and third landing gear 25). The second landing gear 23 can be electrically folded into the fuselage belly and then the second landing gear door 22 is closed. The first landing gear 20 and the third landing gear 25 can be electrically folded into the fuselage belly and then the first landing gear door 19 and the third landing gear door 24 are closed.

[0038] The aforementioned booster-type Space Shuttle 52's belly landing gear is a non-powered, electrically folding landing gear, consisting of a single set of dual-wheel second heavy landing gear 47 and two sets of four-wheel landing gear (first heavy landing gear 44 and third heavy landing gear 48). The second heavy landing gear 47 can be electrically folded into the belly of the fuselage, and the second heavy landing gear door 46 is closed. The first heavy landing gear 44 and the third heavy landing gear 48 can be electrically folded into the belly of the fuselage, and the first heavy landing gear door 43 and the third heavy landing gear door 49 are closed.

Claims

1. A combined launch system for a manned cargo space shuttle and a booster space shuttle, comprising a manned cargo space shuttle and a booster space shuttle, characterized in that: The manned cargo space shuttle and the booster space shuttle are connected via a connector device. The manned cargo space shuttle has a main wing, a tail fin, and retractable canards. The front of the fuselage has a replaceable manned escape cabin, auxiliary cargo bay, or auxiliary fuel bay, which is connected to the fuselage and the main cargo bay. There are retractable canards on both sides. There is a steerable attitude control thruster on each side of the front of the fuselage. The main cargo bay is located between the manned escape cabin and the liquid oxygen / methane fuel bay. The liquid oxygen / methane fuel bay is connected to the liquid oxygen / methane engine. There are connector devices at the front and rear of the fuselage. The fuselage belly has three sets of landing gear. The landing gear is electrically folding, consisting of a single landing gear and two identical landing gear sets. The booster-type space shuttle has a main wing, a tail fin, and a canard. The front of the fuselage has a fuel loading port / emergency release port and a canard. The interior of the fuselage contains a fuel tank composed of two compressed tanks for liquid oxygen and liquid methane. The rear of the fuselage contains a liquid oxygen / methane engine assembly. There are connector devices at the front and rear of the fuselage belly. The fuselage belly has three sets of landing gear, which are electrically folding, consisting of a single landing gear and two identical landing gear sets. The connector devices are used for the bunkering and separation of the manned cargo space shuttle and the booster-type space shuttle.

2. The combined launch system for the manned cargo space shuttle and the booster space shuttle according to claim 1, characterized in that, The connector device consists of a snap-fit ​​telescopic rod and a recessed bayonet. The snap-fit ​​telescopic rod is fitted into the recessed bayonet, and the recessed bayonet has an openable and closable engagement device.

3. The combined launch system for the manned cargo space shuttle and the booster space shuttle according to claim 1, characterized in that, The replaceable manned escape cabin, auxiliary cargo compartment, or auxiliary fuel compartment is connected to the manned cargo space shuttle as one unit. It has an emergency buffer parachute device on the top, an emergency inflatable ring-shaped airbag device around the bottom, and an escape ejection jet recoil device in the middle. The auxiliary cargo compartment and auxiliary fuel compartment have the same shape as the manned escape cabin. The bottom of the auxiliary fuel compartment has an interface for connecting with the fuel compartment of the manned cargo space shuttle.

4. The combined launch system for a manned cargo space shuttle and a booster space shuttle according to claim 1, characterized in that, The steerable attitude control thruster is connected to the combustion chamber and injects high-temperature gas through the injection port. The injection port of the steerable attitude control thruster is a hemisphere and is mechanically linked with the motor and gears. The angle of the hemisphere injection port is controlled by the motor. The combustion chamber is an oxidant mixing combustion chamber that generates high-temperature and high-pressure gas and accelerates it out of the injection port.

5. The combined launch system for a manned cargo space shuttle and a booster space shuttle according to claim 1, characterized in that, The fuel filling port / emergency release port is connected to the fuel tank, and the fuel filling port / emergency release port forms a 13° angle with the left and right sides of the fuselage, allowing fuel to be released outwards.

Images