A rocket-like aircraft and an air launch system for a combination of rocket and aircraft

Abstract

The present invention discloses an air launch system for a rocket-like aircraft and an arrow machine combination. The system is arranged from the inside to the outside as the innermost layer, the middle layer, and the outermost layer, and is arranged in three layers from top to bottom. The innermost layer is provided with rockets of the launch system held tightly by the middle layer, or a backpack arrow machine combination, or a push-type arrow machine combination. The middle layer is provided with a rolling channel body deformation subsystem that can quickly adapt to the radial changes of the rocket-like aircraft and the arrow machine combination in the innermost layer. The outermost layer is provided with a packaging subsystem that can greatly change the shape and height of the nacelle. The first layer from top to bottom is the rolling channel body deformation subsystem, and an integrated landing buffer device integrating a hatch and landing buffer legs is hingedly installed at its lower end, and a launch platform that cooperates with the pyramid structure of the landing buffer device. The present invention can quickly adapt to the requirements of rocket-like aircraft and arrow machine combinations with different diameters, greatly reduce the height of the nacelle during landing, and ensure safety.

Description

Technical Field

[0001] The present invention belongs to the technical field of launch systems and launch methods, and particularly relates to an air launch system for a rocket-like aircraft and a combination of a rocket and an aircraft. Background Art

[0002] The air launch platform technology refers to the technology of launching vehicles such as launch vehicles, satellites, or unmanned aerial vehicles (collectively referred to as payloads) in the air using an air launch platform, and it is currently a research hotspot in the aerospace field. The air launch technology can make up for the deficiencies caused by the lack of launch centers or geographical and environmental impacts in a country or province. The air launch technology has characteristics such as the rapidity, mobility, and flexibility required for rapid response to space launches, and it is the most potential rapid launch method, which has been increasingly valued by major aerospace powers.

[0003] Currently, the difficulties in realizing an air launch system based on an aerostat are as follows:

[0004] First, it is very difficult to realize an air launch system based on a combination of a rocket and an aircraft, and there is no precedent. The difficulties lie in that the object to be launched is not a conventional single body but a combination body, and the combination body is a heterogeneous structure formed by combining two or more objects. For a heterogeneous structure, the launch channel is required to change accordingly, but the traditional launch channel cannot meet the requirements of launching a combination body. The primary reason is that the traditional method cannot achieve the deformation of the cabin. The reason for the inability to achieve the deformation of the cabin is that the launch channel does not have the performance of elastic deformation. The traditional method uses foam as the launch channel, and a groove with an outer shape is outlined with the foam. The rocket or aircraft is suspended from the sky and hung on it, and it is launched vertically downward by relying on the action of gravity and gravitational acceleration. Since the foam does not have elasticity and cannot change with the shape of the object to be launched, the launch cabin made of foam material does not have the performance of elastic deformation; the second reason is that the launch channel of the traditional method uses sliding friction and has a large frictional force: the existing technology launch channels all use sliding friction. Since the sliding friction coefficient is relatively large, when the surface of the object to be launched is a heterogeneous surface and the launch angle is not limited to vertical launch but is inclined upward or horizontally launched, for example, if it is launched at an angle of 45 degrees inclined upward, due to the generation of a lateral component force and sliding friction, it may be blocked.

[0005] Second, the traditional air launch system based on an aerostat cannot achieve an inclined upward or horizontal launch in the air because for an inclined upward or horizontal launch, not only does the launch channel need to minimize friction and resistance, but also the rocket-like aircraft and the combination of the rocket and the aircraft need to be launched by ignition in the cabin. Launching by ignition in the cabin will cause damage to the electrical system or operating mechanism of the gondola due to the high-temperature flame ejected by the rocket-like aircraft and the combination of the rocket and the aircraft.

[0006] Thirdly, in the pod landing state of the traditional method, since the pod cannot be deformed in the height direction and the center of gravity of the pod is relatively high, there is a risk that the pod will tip over during landing due to the high center of gravity.

[0007] Fourthly, the landing buffer device of the traditional method cannot integrate the functions of opening and closing the air hatch and the landing buffer leg. The opening and closing of the hatch and the landing buffer are each an independent drive mechanism. The difficulty in realizing this lies in that no common mechanism can be found between the two independent mechanisms. Summary of the Invention

[0008] In order to solve the problems existing in the prior art, the present invention provides an air launch system for a rocket-like aircraft and a rocket-aircraft combination, aiming to solve the problems that the air launch of the rocket-aircraft combination cannot be realized by the traditional method, the oblique upward launch and horizontal launch in the air cannot be realized, the center of gravity of the pod cannot be lowered during pod landing, resulting in pod tipping, and the functions of opening and closing the hatch and the landing buffer leg cannot be integrated.

[0009] The present invention adopts the following technical solutions to solve its technical problems:

[0010] An air launch system for a rocket-like aircraft and a rocket-aircraft combination, characterized in that: the system is arranged from the inside to the outside as the innermost layer, the middle layer, and the outermost layer, and is arranged in three layers from top to bottom; the innermost layer is provided with a rocket 5 of the launch system held by the middle layer, or a back-mounted rocket-aircraft combination 11, or a push-type rocket-aircraft combination 12. The middle layer is provided with a rolling channel body deformation subsystem that can quickly adapt to the radial changes of the rocket-like aircraft and the rocket-aircraft combination, and can greatly stretch the pod in the height direction to change the shape of the pod. The outermost layer is provided with a packaging subsystem that can greatly change the shape and height of the pod; the first layer from top to bottom is the above-mentioned rolling channel body deformation subsystem, and at its lower end, a landing multi-stage buffer subsystem that can quickly contract and deform both radially and longitudinally is hinged and installed. The system is arranged from the inside to the outside as the innermost layer, the middle layer, and the outermost layer, and is arranged in three layers from top to bottom; the innermost layer is provided with a rocket 5 of the launch system held by the middle layer, or a back-mounted rocket-aircraft combination 11, or a push-type rocket-aircraft combination 12. The middle layer is provided with a rolling channel body deformation subsystem that can quickly adapt to the radial changes of the innermost rocket-like aircraft and the rocket-aircraft combination. The outermost layer is provided with a packaging subsystem that can greatly change the shape and height of the pod; the first layer from top to bottom is the rolling channel body deformation subsystem, and at its lower end, a landing buffer device 10 that integrates the cabin door and the landing buffer leg, and a launch platform 36 that cooperates with the pyramid structure of the landing buffer device are hinged and installed.

[0011] The rolling channel airframe deformation subsystem capable of quickly adapting to the radial changes of rocket-like aircraft and the rocket-aircraft combination includes: a payload compartment 1, a payload compartment bottom ring 15, a first channel roller support structure 3, a first channel link mechanism 4, and a first channel bottom ring 17; a second channel roller support structure 7, a second channel link mechanism 6, and a second channel bottom ring 20; a third channel roller support structure 9, a third channel link mechanism 8, and a third channel bottom ring 21; the payload compartment 1 is fixedly installed on the upper part of the payload compartment bottom ring 15 by bolts; multiple hinge points at the upper end of the first channel link mechanism 4 are hinged to multiple hinge points at the bottom of the payload compartment bottom ring 15, the first channel roller support structure 3 is fixedly installed on the first channel roller support rod of the first channel link mechanism 4, and multiple hinge points at the lower end of the first channel link mechanism 4 are hinged to multiple hinge points of the first channel bottom ring 17, and a first launch channel with multi-roller support based on the deformation of a multi-parallelogram mechanism is formed; multiple hinge points at the upper end of the second channel link mechanism 6 are hinged to multiple hinge points of the first channel bottom ring 17, the second channel roller support structure 7 is fixedly installed on the second channel roller support rod of the second channel link mechanism 6, and multiple hinge points at the lower end of the second channel link mechanism 6 are hinged to multiple hinge points of the second channel bottom ring 20, and a second launch channel with multi-roller support based on the deformation of a multi-parallelogram mechanism is formed; multiple hinge points at the upper end of the third channel link mechanism 8 are hinged to multiple hinge points at the bottom of the second channel bottom ring 20, the third channel roller support structure 9 is fixedly installed on the third channel roller support rod of the third channel link mechanism 8, and multiple hinge points at the lower end of the third channel link mechanism 8 are hinged to multiple hinge points of the third channel bottom ring 21, and a third launch channel with multi-roller support based on the deformation of a multi-parallelogram mechanism is formed; the first, second, and third launch channels together constitute the rolling channel airframe deformation system of the launch system.

[0012] The encapsulation subsystem capable of greatly changing the shape and height of the pod includes: multiple steel wires 18 and a pod rolling curtain device. The multiple steel wires 18 are evenly distributed in the pod 38, one end extends into the payload compartment 1 and is connected to the wire telescoping mechanism in the payload compartment 1, and the other end is fixedly installed on the lock 28 on the third channel bottom ring 21, forming a mechanism deformation wire rope drive system of the air launch system; one end of the stretched pod rolling curtain 30 is fixedly installed at the bottom of the payload compartment bottom ring 15, and the other end is fixedly installed at the top of the third channel bottom ring 21, and together with the payload compartment 1 and the landing buffer device 10 integrating the cabin door and the landing buffer leg, it constitutes the encapsulation system of the launch system.

[0013] The pod rolling curtain device includes a pod rolling curtain cloth 30 in a stretched state and a pod rolling curtain cloth 31 in a compressed state. The pod rolling curtain cloth 30 in the stretched state adaptively folds and deforms according to different tasks and the height of the pod. The pod rolling curtain cloth 30 in the stretched state is used in the hanging and launching postures of the pod 38, and the pod rolling curtain cloth 31 in the compressed state is used in the landing buffer state of the pod 38.

[0014] The landing multi-stage buffer subsystem that can rapidly contract and deform simultaneously along the radial and longitudinal directions includes: a landing buffer device 10 integrating a hatch and landing buffer legs. Multiple hinge points of this buffer device are hingedly installed on multiple hinge points at the bottom of the bottom ring 21 of the third channel. Multiple synchronous shock absorbers 2 are evenly installed at the bottom of the bottom ring 15 of the payload compartment. The landing buffer device 10 integrating the hatch and landing buffer legs and the synchronous shock absorbers 2 cooperate with each other to jointly form the landing buffer system of the launch system and complete the landing multi-stage buffer function of the launch system.

[0015] The first-channel link mechanism 4, the second-channel link mechanism 6, and the third-channel link mechanism 8 each include an upper link and a lower link, an inner link and an outer link; the upper link of each is arranged singly, the lower link is arranged in a double configuration, and the gap between the double-arranged lower links can embed the upper link, thereby increasing the deformation angle of the mechanism and avoiding interference between the upper and lower links; a parallelogram arrangement is adopted between the inner and outer links of each. The inner and outer links are both arc-shaped links with a certain angle, and the obtuse-angle faces of the arc-shaped links are placed facing each other, thereby greatly increasing the deformation angle of the mechanism and avoiding interference between the left and right links. At the same time, by reasonably designing the angle, mechanical limit for deformation collision can be achieved.

[0016] The first-channel roller support structure 3 is composed of four first-channel roller supports 16, which are respectively fixedly installed on four first-channel roller support rods. Multiple rollers of it hold tightly the outer surface of the rocket 5, or the back-mounted rocket machine combination 11 or the push-type rocket machine combination 12, ensuring the safety and stability of the hanging and launching of the rocket 5, or the back-mounted rocket machine combination 11, or the push-type rocket machine combination 12;

[0017] The second-channel roller support structure 7 is composed of four second-channel roller supports 19, which are respectively fixedly installed on four second-channel roller support rods. Multiple rollers of it hold tightly the outer surface of the rocket 5, or the back-mounted rocket machine combination 11 or the push-type rocket machine combination 12, ensuring the safety and stability of the hanging and launching of the rocket 5, or the back-mounted rocket machine combination 11 or the push-type rocket machine combination 12;

[0018] The third-channel roller support structure 9, for the launch system of the launch rocket 5, is composed of four evenly distributed third-channel roller supports 14, which are respectively and fixedly installed on four third-channel roller support rods; for the launch system of the launch backpack arrow machine combination 11, it is composed of four non-uniformly distributed third-channel roller supports 14, which are respectively and fixedly installed on four third-channel roller support rods; for the launch system of the launch push-type arrow machine combination 12, it is composed of six non-uniformly distributed third-channel roller supports 14, which are respectively and fixedly installed on two third-channel roller support rods; its multiple rollers hold the outer surface of the rocket 5, or the launch backpack arrow machine combination 11 or the launch push-type arrow machine combination 12, ensuring the safety and stability of the suspension and launch of the rocket 5, the launch backpack arrow machine combination 11 or the launch push-type arrow machine combination 12.

[0019] The landing buffer device 10 integrating the cabin door and the landing buffer leg includes four single-leg structures of the multi-functional landing buffer system; each single-leg structure of the multi-functional landing buffer system is respectively hinged to the third-channel bottom ring 21 of the nacelle 38 through a two-way shock absorber fixing pin and a shock leg fixing pin, and each two of the single-leg structures of the multi-functional landing buffer system are spliced together into a conical shape. At this time, the nacelle 38 is in the encapsulated suspension state of the rocket 5, or the launch backpack arrow machine combination 11 or the launch push-type arrow machine combination 12; when the four single-leg structures of the multi-functional landing buffer system are in the petal-shaped open state, according to the attitude and tasks of the nacelle 38, the nacelle 38 is respectively in the waiting-for-launch state of the rocket 5, or the launch backpack arrow machine combination 11 or the launch push-type arrow machine combination 12, or the launch state of the rocket 5, the launch backpack arrow machine combination 11 or the launch push-type arrow machine combination 12, or the landing buffer state of the nacelle (38).

[0020] The single-leg structure of the multi-functional landing buffer system includes a cabin door 22, a shock leg 23, a leg support 25, a two-way shock absorber 24, a locking strap 29, etc. Among them, the shock leg 23 is hinged and installed on the ear on the third-channel bottom ring 21 through a shock leg fixing pin. One end of the two-way shock absorber 24 is hinged and installed on the ear on the third-channel bottom ring 21 through a two-way shock absorber fixing pin two, and the other end is hinged and installed on the ear of the shock leg 23 through a two-way shock absorber fixing pin one. The leg support 25 is hinged and installed at the bottom of the shock leg 23 through a leg support fixing pin. The cabin door 22 is fixedly installed on the shock leg 23 through bolts, so that the single-leg structure of the multi-functional landing buffer system can not only complete the landing shock absorption function, but also complete the closing and opening functions of the cabin door 22. The locking strap 29 is fixedly installed at the corresponding position on the inner upper part of the shock leg 23 through bolts, and is used to lock the single-leg structure of the multi-functional landing buffer system.

[0021] On the integrated landing buffer device 10 where the integrated hatch and the landing buffer leg are integrated, a contact sensor 26 is also installed. The contact sensor 26 is fixedly installed on the contact sensor fixing plate 27 on the bottom ring 21 of the third channel. The steel wire rope 18 passes through the through hole on the contact sensor fixing plate 27 and is fixedly installed on the locking device 28. The locking device 28 passes through two through holes of the third channel bottom ring 21. When the shock-absorbing leg 23 is in the locked state and the hatch 22 is not opened at this time, since the steel wire rope 18 is in a taut state, the locking strap 29 is locked with the locking device 28, and the locking device 28 does not touch the contact sensor 51. At this time, the rocket 5, the back-mounted arrow machine combination 11 or the push-type arrow machine combination 12 is in the closed hanging state inside the cabin. When receiving the command signal to open the hatch 22, the steel wire rope 18 is relaxed, and the locking strap 29 is separated from the locking device 28 under the elastic potential energy of the bi-directional shock absorber 24, and the shock-absorbing leg 23 is released. At this time, it is in the state where the hatch 22 is opened and the rocket 5, the back-mounted arrow machine combination 11 or the push-type arrow machine combination 12 is waiting to be launched. When the steel wire rope 18 is taut again, if all the locking devices 28 are in contact with the contact sensor 26, it means that all the hatches 22 are fully opened. At this time, a launch command for the rocket 5, the back-mounted arrow machine combination 11 or the push-type arrow machine combination 12 is issued, and the rocket 5, the back-mounted arrow machine combination 11 or the push-type arrow machine combination 12 is launched along the launch channel. The contact sensor 26 can monitor the various states of the landing buffer device with functions such as integrated launch and hatch opening in real time, thereby improving the launch safety and reliability, and can give early warnings for dangerous situations such as launching with the hatch 22 not opened.

[0022] The rolling channel airframe deformation subsystem that can greatly stretch the pod in the height direction to change the shape of the pod is specifically as follows: In the launch state of rocket-like aircraft and arrow machine combinations, the height of the pod can be increased, so as to realize the encapsulation, hanging and launch of various large rocket-like aircraft and arrow machine combinations; in the landing and recovery state, the height and center of gravity of the pod can be greatly reduced, ensuring the safety and anti-overturning performance of the pod during landing.

[0023] On the top of the payload compartment 1 of the pod 38, a parachute 32, a floating balloon 53 and a pod hanging mechanism 33 are installed to form a complete floating launch system. When it is released on the ground, the leg supports 25 are in contact with each other in pairs to jointly form a pyramid structure, which can be effectively locked with the pod release locking block 35 on the ground and the launch platform 36. By adjusting the position of the pod release locking block 35, the ground locking and release of the pod can be realized. At the same time, due to the pyramid-shaped bottom structure, different from other conical bottom cabins, the entire pod 38 can be placed vertically on the horizontal ground.

[0024] In addition to constructing and vertically launching the vertical launch channels for the rocket-like aircraft and the combined rocket and arrow machine launch system for the rocket 5, the backpack-mounted arrow machine assembly 11, or the push-type arrow machine assembly 12, it can also construct the downwardly inclined launch channels for the rocket 5, the backpack-mounted arrow machine assembly 11, or the push-type arrow machine assembly 12 and conduct air launches at an acute angle B to the vertical line, and can also construct the upwardly inclined air launch channels for the rocket 5, the backpack-mounted arrow machine assembly 11, or the push-type arrow machine assembly 12 and conduct air launches at an obtuse angle D to the vertical line, and can also construct the horizontal launch channels for the rocket 5, the backpack-mounted arrow machine assembly 11, or the push-type arrow machine assembly 12 and conduct air launches at a right angle C to the vertical line, so as to meet the requirements of launching the rocket 5, the backpack-mounted arrow machine assembly 11, or the push-type arrow machine assembly 12 in the air under different working conditions.

[0025] When the rocket-like aircraft and the combined rocket and arrow machine launch system launch the rocket 5, the backpack-mounted arrow machine assembly 11, or the push-type arrow machine assembly 12 upwardly inclined and horizontally, it is necessary to launch the rocket 5, the backpack-mounted arrow machine assembly 11, or the push-type arrow machine assembly 12 for ignition and launch in the cabin. Therefore, it is necessary to protect the gondola 38, especially the payload compartment 1 and the steel wire rope 18. Therefore, a distributed volcanic-shaped air diversion device 55 is installed at the bottom ring of the payload compartment to prevent the gondola 38 from being damaged by the high-temperature flame ejected by the rocket 5, the backpack-mounted arrow machine assembly 11, or the push-type arrow machine assembly 12, resulting in damage to the electrical system or operating mechanism. The gondola rolling curtain is in a compressed state and retracts at the bottom ring 20 of the second channel to ensure that the high-temperature flame ejected by the rocket 5, the backpack-mounted arrow machine assembly 11, or the push-type arrow machine assembly 12 can be smoothly discharged.

[0026] Advantages and effects of the present invention

[0027] 1. The present invention organically combines the rolling channel body deformation subsystem, the encapsulation subsystem, and the landing buffer device, which support and depend on each other: The outermost encapsulation subsystem and the parallelogram link deformation mechanism in the middle layer must synchronously expand and contract in the height direction to minimize the center of gravity of the gondola when the gondola lands to avoid risks; The two-way function of the two-way spring of the landing buffer subsystem also depends on the deformation of the rolling channel body deformation subsystem and the steel wire rope. Because the rolling channel body deformation subsystem and the landing buffer subsystem are linked by the steel wire rope, the two-way shock absorber of the landing buffer subsystem is in a compressed state when the cabin door is closed, and at this time the rolling channel body deformation subsystem is in an extended state. At the moment of landing, it is in a stretched state, and at this time the rolling channel body deformation subsystem is in a compressed state; Similarly, if only relying on the deformation function of the rolling channel body deformation subsystem without the two-way spring of the landing buffer subsystem, the functions of the cabin door opening and closing and the buffer leg cannot be integrated either. In short, each part supports and depends on each other, achieving superior effects after combination.

[0028] 2. Compared with the traditional sliding launch channel, the elastic rolling launch channel of the present invention has the following advantages: 1) It can reduce the friction between the rocket-like aircraft and the launch channel, better protect the outer surface of the rocket-like aircraft and the rocket-aircraft combination, and make the launch smoother; 2) It can adapt to the complex shape changes of the surface of the rocket-like aircraft and the rocket-aircraft combination, and can ensure reliable contact between the launch channel and the rocket-like aircraft and the rocket-aircraft combination at all times, improving the launch safety. 3) Compared with the traditional sliding launch channel, due to the very low friction coefficient, in addition to realizing the construction of a rolling vertical launch channel, it can also realize the construction of a large-angle oblique rolling channel and a horizontal launch channel, which is suitable for different launch conditions.

[0029] 3. Compared with the traditional sliding launch channel, the multi-parallelogram link pod deformation mechanism of the present invention has the following advantages: 1) According to the radial changes of the rocket-like aircraft and the rocket-aircraft combination, it deforms through the multi-parallelogram link pod deformation mechanism to quickly adapt to the launch and fixation of rocket-like aircraft and rocket-aircraft combinations with different diameters. 2) It can change the shape and height of the pod in a large range. In the launch state of the rocket-like aircraft and the rocket-aircraft combination, the pod height can be increased to realize the encapsulation, hanging and launch of various large rocket-like aircraft and rocket-aircraft combinations. In the landing and recovery state, the pod height and center of gravity can be greatly reduced, ensuring the safety and anti-tipping performance of the pod during landing; 3) The pod deformation driving device in the payload compartment of the present invention drives the mechanism deformation driving rope to rise and fall, thereby driving the multi-parallelogram link pod deformation mechanism to deform, realizing the construction and deformation of the pod roller launch channel, realizing the overall deformation and maintenance of the pod body, realizing the fixation and maintenance of the rocket-like aircraft and the rocket-aircraft combination, and thus realizing the rise and fall of the mechanism deformation driving rope through the driving mechanism to realize the body deformation, maintenance, rolling launch channel construction, deformation, and the fixation and maintenance of the rocket-like aircraft and the rocket-aircraft combination. 4) The rolling curtain-type enclosure cloth and the cabin door encapsulate the rocket-like aircraft and the rocket-aircraft combination in the pod, and can change with the multi-parallelogram link pod deformation mechanism, realizing the encapsulation and shielding of the rocket-like aircraft and the rocket-aircraft combination while realizing the deformation following of the pod body.

[0030] 4. Compared with traditional landing buffer devices, the landing buffer device of the present invention has the following advantages: 1) The landing buffer legs and the hatch are ingeniously combined into one, and a two-way shock absorber is designed. While meeting the requirement of cooperating with the synchronous shock absorber shock system to complete multi-stage landing buffer shock absorption, it can also achieve the complete encapsulation of rocket-like aircraft and the combined body of rocket and aircraft, as well as the synchronous opening function of the hatch. 2) The synchronous shock absorber and the two-way elastic support legs are coupled for shock absorption, which can greatly improve the landing buffer capacity of the pod, and enable the pod to achieve damage-free landing, damage-free recovery, and reusable recovery; 3) The leg supports of the landing buffer device of the present invention are in contact with each other in pairs to form a pyramid structure, which can be effectively locked on the ground and the launch platform, realizing the ground locking and release of the pod. At the same time, due to the pyramid-shaped bottom structure, different from other conical bottom cabins, the entire pod can be placed vertically on the horizontal ground. 4) The landing buffer device of the present invention also designs a locking device and a locking strap structure. When the steel wire rope is in a taut state, the locking strap is locked with the locking device, and the shock-absorbing legs can be locked. When the steel wire rope is in a relaxed state, the locking device moves downward under the drive of elastic potential energy, and the locking strap is separated from the locking device under the drive of the elastic potential energy of the spring, realizing the release of the shock-absorbing legs.

[0031] 5. Compared with traditional launch angles, the launch angle of the aerial launch vehicle of the present invention has the following advantages: 1) The aerial launch method of the present invention can realize the aerial vertical, downward inclination, upward inclination, and horizontal launch of various aircraft such as rocket-like aircraft, backpack rocket and aircraft combined bodies, and push-type rocket and aircraft combined bodies to meet the requirements of different launch missions. At the same time, the pod can realize the repeatable recovery of leg parachute landing buffer, the aircraft can realize airport return or parachute horizontal landing, and the rocket can realize vertical recoil recovery, thus realizing the repeatable multiple launch and recovery of the whole system. 2) The aerial launch system is also equipped with a distributed volcanic-shaped air diversion device. When the pod launches rocket-like aircraft and the combined body of rocket and aircraft in an upward inclination and horizontal direction, it is necessary to launch the rocket-like aircraft and the combined body of rocket and aircraft by ignition in the cabin. The air diversion device adopts a distributed volcanic-shaped configuration, which can prevent the pod from being damaged by the high-temperature flame ejected by the rocket-like aircraft and the combined body of rocket and aircraft, and the pod rolling curtain is in a compressed state and shrinks at the bottom ring of the second channel to ensure that the high-temperature flame ejected by the rocket-like aircraft and the combined body of rocket and aircraft can be discharged smoothly.

[0032] 6. Compared with the traditional method of launching floating air balloons using ground cranes, 1) the ground launching method described in the present invention adopts the fitting separation of the pyramid configuration of the launching platform and the locking and unlocking method of the inclined plane locking slider, which can achieve firm ground locking of the air launching system. At the same time, the launching platform and the ground are fixed as a whole through anchor bolts, thus ensuring the safety, reliability and convenience of the ground launching of the air launching system, and preventing dangerous situations such as the launching system being bumped and overturned due to side winds and changes in weather conditions. 2) Compared with the on-site ground loading method of the aircraft launch site of the traditional air launching system, the ground loading, transportation and docking method of the air launching system described in the present invention can realize functions such as factory horizontal loading, factory horizontal packaging, horizontal transportation by transport vehicles and hoisting and installation at the launch site. It can complete the accurate loading of the rocket-like assembly loading rack in the factory to ensure the accuracy, safety and standardization of the aircraft loading. At the same time, it can realize horizontal container or flatbed truck transportation to ensure the standardization, passability and safety of transportation. In addition, on-site, only the docking of the nacelle and the launching platform needs to be completed to quickly complete the launching task, greatly saving the launching time, improving the launching efficiency and avoiding the occurrence of launching weather, environment and unknown risks due to too long launching time. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a composition diagram of the rocket-like aircraft launch system in the present invention;

[0034] Figure 2 It is a three-dimensional schematic diagram of the rocket-like aircraft launch system in the present invention;

[0035] Figure 3 It is a composition diagram of the backpack arrow machine combination launch system in the present invention;

[0036] Figure 4 It is a three-dimensional schematic diagram of the backpack arrow machine combination launch system in the present invention;

[0037] Figure 5 It is a composition diagram of the push-type arrow machine combination launch system in the present invention;

[0038] Figure 6 It is a three-dimensional schematic diagram of the push-type arrow machine combination launch system in the present invention;

[0039] Figure 7 It is a composition diagram of the landing buffer device in the present invention;

[0040] Figure 8 It is a schematic diagram of the locked state of the landing buffer device in the present invention;

[0041] Figure 9 It is a pre-launch state diagram of the rocket-like aircraft and the arrow machine combination launch system in the present invention;

[0042] Figure 10 It is the launch status diagram of the rocket - type aircraft launch system in the present invention;

[0043] Figure 11 It is the launch status diagram of the backpack - type arrow machine assembly launch system in the present invention;

[0044] Figure 12 It is the launch status diagram of the push - type arrow machine assembly launch system in the present invention;

[0045] Figure 13 It is the landing status diagram of the rocket - type aircraft and arrow machine assembly launch system in the present invention;

[0046] Figure 14 It is the schematic diagram of the pod being locked with the launch platform before release in the present invention;

[0047] Figure 15 It is the schematic diagram of the launch system horizontally assembling the rocket - type aircraft in the present invention;

[0048] Figure 16 It is the schematic diagram of the launch system horizontally assembling the backpack - type arrow machine assembly in the present invention;

[0049] Figure 17 It is the schematic diagram of the launch system horizontally assembling the push - type arrow machine assembly in the present invention;

[0050] Figure 18 It is the schematic diagram of the launch system placed after horizontal assembly completion in the present invention;

[0051] Figure 19 It is the schematic diagram of the launch system being transported by container or flatbed truck in the present invention;

[0052] Figure 20 It is the composition diagram of the launch platform in the present invention;

[0053] Figure 21 It is the three - dimensional schematic diagram of the launch platform in the present invention;

[0054] Figure 22 It is the 45 - degree rotation side view of the launch platform in the present invention;

[0055] Figure 23 It is the side view of the launch platform in the present invention;

[0056] Figure 24 It is the schematic diagram of using a crane to lock and install the pod with the launch platform in the present invention;

[0057] Figure 25 It is the schematic diagram of the pod being locked with the launch platform before release in the present invention;

[0058] Figure 26 It is the schematic diagram of the launch platform unlocking when the pod is released in the present invention;

[0059] Figure 27 Schematic diagram of the separation between the pod and the launch platform after the pod is released in the present invention;

[0060] Figure 28 Schematic diagram of the airborne suspension state with the hatch of the launch system closed in the present invention;

[0061] Figure 29 Schematic diagram of the state of the aircraft to be launched with the hatch of the launch system open in the present invention;

[0062] Figure 30 Schematic diagram of the separation state between the launched aircraft and the launch system in the present invention;

[0063] Figure 31 Schematic diagram of the state of the launch system after the aircraft is launched in the present invention;

[0064] Figure 32 Schematic diagram of the state before landing with the center of gravity reduced by the deformation of the balloon separation pod mechanism in the present invention;

[0065] Figure 33 Three - dimensional schematic diagram of the landing state of the launch system in the present invention;

[0066] Figure 34 Three - dimensional schematic diagram of the internal mechanism of the launch system in the landing state in the present invention;

[0067] Figure 35 Schematic diagram of the state of the rocket - type aircraft accelerating downward by gravity after vertical dropping in the present invention;

[0068] Figure 36 Schematic diagram of the state of the rocket - type aircraft flying horizontally after being pulled up horizontally in the present invention;

[0069] Figure 37 Schematic diagram of the vertical landing state of the rocket - type aircraft in the present invention;

[0070] Figure 38 Schematic diagram of the state of the backpack - type arrow machine combination accelerating downward by gravity after vertical dropping in the present invention;

[0071] Figure 39 Schematic diagram of the state of the backpack - type arrow machine combination flying horizontally after being pulled up horizontally in the present invention;

[0072] Figure 40 Schematic diagram of the airborne separation state of the backpack - type arrow machine combination in the present invention;

[0073] Figure 41 Schematic diagram of the flight state of the aircraft after the airborne separation of the backpack - type arrow machine combination in the present invention;

[0074] Figure 42This is the diagram of the rocket flight state after the aerial separation of the backpack arrow machine combination in the present invention;

[0075] Figure 43 This is the diagram of the horizontal landing state of the aircraft in the backpack arrow machine combination in the present invention;

[0076] Figure 44 This is the diagram of the vertical landing state of the rocket in the backpack arrow machine combination in the present invention;

[0077] Figure 45 This is the diagram of the state of the push - type arrow machine combination accelerating downward by gravity after vertical release in the present invention;

[0078] Figure 46 This is the diagram of the horizontal flight state of the push - type arrow machine combination after being horizontally pulled up in the present invention;

[0079] Figure 47 This is the diagram of the aerial separation state of the push - type arrow machine combination in the present invention;

[0080] Figure 48 This is the diagram of the flight state of the aircraft after the aerial separation of the push - type arrow machine combination in the present invention;

[0081] Figure 49 This is the diagram of the rocket flight state after the aerial separation of the push - type arrow machine combination in the present invention;

[0082] Figure 50 This is the diagram of the horizontal landing state of the aircraft in the push - type arrow machine combination in the present invention;

[0083] Figure 51 This is the diagram of the vertical landing state of the rocket in the push - type arrow machine combination in the present invention;

[0084] Figure 52 This is the diagram of the oblique - downward launch state of the aircraft launch system in the present invention;

[0085] Figure 53 This is the diagram of the horizontal launch state of the aircraft launch system in the present invention;

[0086] Figure 54 This is the diagram of the oblique - upward launch state of the aircraft launch system in the present invention;

[0087] Figure 55 This is the internal diagram of the oblique - upward launch of the aircraft launch system in the present invention;

[0088] Figure 56 This is the internal diagram of the horizontal launch of the aircraft launch system in the present invention.

[0089] Among them, 1. Payload compartment; 2. Synchronous shock absorber; 3. First-channel roller support structure; 4. First-channel connecting rod mechanism; 5. Rocket; 6. Second-channel connecting rod mechanism; 7. Second-channel roller support structure; 8. Third-channel connecting rod mechanism; 9. Third-channel roller support structure; 10. Landing buffer device integrating cabin door and landing buffer leg; 11. Backpack rocket-machine combination; 12. Pushing rocket-machine combination; 13. Aircraft; 14. Third-channel roller support; 15. Bottom ring of payload compartment; 16. First-channel roller support; 17. Bottom ring of first channel; 18. Steel wire rope; 19. Second-channel roller support; 20. Bottom ring of second channel; 21. Bottom ring of third channel; 22. Cabin door; 23. Shock-absorbing leg; 24. Bidirectional shock absorber; 25. Leg support; 26. Contact sensor; 27. Contact sensing fixing plate; 28. Locking device; 29. Locking strap; 30. Suspension cabin rolling curtain cloth in stretched state; 31. Suspension cabin rolling curtain cloth in compressed state; 32. Parachute; 33. Suspension cabin hanging mechanism; 34. Suspension cabin main body; 35. Suspension cabin release locking block; 36. Release platform; 37. Container; 38. Suspension cabin; 39. Transport vehicle; 40. Top plate of launch pad; 41. Conical groove of launch pad; 42. Pyramid fixing block of launch pad; 43. Legs of launch pad; 44. Sliding base of locking block; 45. Bottom plate of launch pad; 46. Anchor base of launch pad; 47. Archimedes spiral disk; 48. Sliding pin; 49. Motor; 50. Slider locking inclined plane; 51. Inclined plane of pyramid fixing block of launch pad; 52. Crane; 53. Floating air balloon; 54. Top surface of suspension cabin leg support; 55. Distributed volcanic-shaped air diversion device; 56. Bottom surface of suspension cabin leg support. Detailed implementation mode

[0090] Design principle of the present invention:

[0091] 1. Design principle of the multi-parallelogram linkage pod deformation mechanism: 1) A parallelogram arrangement is adopted between the inner and outer linkages. Both the inner and outer linkages are arc-shaped linkages with a certain angle, and the obtuse-angle faces of the arc-shaped linkages are placed facing each other, thus greatly increasing the deformation angle of the mechanism, avoiding interference between the left and right linkages, and at the same time, reasonable design of the angle can achieve mechanical limit for deformation collision; 2) The upper linkage is arranged singly, and the lower linkage is arranged in a double configuration. Moreover, the gap between the double-arranged lower linkages can accommodate the upper linkage, thus greatly increasing the deformation angle of the mechanism and avoiding interference between the upper and lower linkages. 3) The pod deformation driving device in the load cabin drives the mechanism deformation driving rope to rise and fall, thereby driving the deformation of the multi-parallelogram linkage pod deformation mechanism, realizing the construction and deformation of the pod roller launch channel, the overall deformation and maintenance of the pod body, the fixation and maintenance of rocket-like aircraft and the combination of rocket and aircraft, and thus realizing the rise and fall of the mechanism deformation driving rope through the driving mechanism to achieve body deformation, maintenance, construction and deformation of the rolling launch channel, and fixation and maintenance of rocket-like aircraft and the combination of rocket and aircraft; 4) The roll-up type enclosing cloth and the cabin door encapsulate the rocket-like aircraft and the combination of rocket and aircraft in the pod, and can change along with the multi-parallelogram linkage pod deformation mechanism. While realizing the encapsulation and shielding of the rocket-like aircraft and the combination of rocket and aircraft, it also realizes the deformation following of the pod body.

[0092] 2. Design principle of the launch channel based on rolling friction and deformation mechanism: Multiple rollers are attached to the deformation mechanism. An elastic device is provided inside the rollers. A launch channel is constructed for the rollers by a parallelogram mechanism, enabling the rocket-like aircraft and the combination of rocket and aircraft to roll and slide out along the launch channel; Comparison with the prior art: Hanging a rocket or an aircraft from the sky, using foam to create a groove in the shape, hanging the aircraft or the rocket on it, and relying on the action of gravity to launch vertically by gravitational acceleration. In the present invention, rollers are used to change sliding friction into rolling friction, and these rollers can also be constructed according to the different shapes of the rocket-like aircraft and the combination of rocket and aircraft; at the same time, the rolling channel can be sent obliquely, while previously it could only be sent vertically. For example, if it was launched obliquely at 45 degrees before, due to sliding friction, it might get stuck.

[0093] 3. Design principle of the landing buffer device: 1) The landing buffer leg is ingeniously combined with the hatch into one body, and a two-way shock absorber is designed. While meeting the requirement of cooperating with the synchronous shock absorber shock absorption system to jointly complete multi-stage landing buffer shock absorption, it can also achieve the complete encapsulation of rocket-like aircraft and the rocket-aircraft combination, as well as the synchronous opening function of the hatch. 2) The synchronous shock absorber is coupled with the two-way elastic support leg for shock absorption, which can greatly improve the landing buffer capacity of the pod, and enable the pod to achieve damage-free landing, damage-free recovery, and reusable recovery; 3) The leg supports of the landing buffer device are in contact with each other in pairs to form a pyramid structure, which can be effectively locked on the ground and the launch platform, realizing the ground locking and release of the pod. At the same time, due to the pyramid bottom structure, different from other conical bottom cabins, the entire pod can be vertically placed on the horizontal ground. 4) The landing buffer device is also designed with a locking device and a locking strap structure. When the steel wire rope is in a taut state, the locking strap is locked with the locking device, and the shock-absorbing leg can be locked. When the steel wire rope is in a relaxed state, the locking device moves downward under the drive of elastic potential energy, and the locking strap is separated from the locking device under the drive of the spring elastic potential energy, realizing the release of the shock-absorbing leg. 5) The landing buffer device is also designed with a contact sensing structure. When the shock-absorbing leg is in the locked state and the hatch is not opened at this time, because the steel wire rope is in a taut state, the locking strap is locked with the locking device, and the locking device does not touch the contact sensor. At this time, the rocket-like aircraft and the rocket-aircraft combination are in a closed hanging state in the cabin. When receiving the hatch opening command signal, the steel wire rope is relaxed, and the locking strap is separated from the locking device under the drive of the spring elastic potential energy, and the shock-absorbing leg is released. At this time, it is in the state of the hatch opening and the rocket-like aircraft and the rocket-aircraft combination waiting for launch. When the steel wire rope is taut again, if all the locking devices are in contact with the contact sensor, it means that all the hatches are fully opened. At this time, a launch command for the rocket-like aircraft is issued, and the rocket-like aircraft and the rocket-aircraft combination are launched along the launch channel. The contact sensing structure can monitor all states of the hatch in real time, thereby improving the launch safety and reliability, and warning of dangerous situations such as launching with the hatch not opened.

[0094] 4. Design principle of the distributed volcanic-shaped air diversion device: When the pod tilts upward and horizontally launches the rocket-like aircraft and the rocket-aircraft combination, it is necessary to launch the rocket-like aircraft and the rocket-aircraft combination by igniting them in the cabin. The air diversion device adopts a distributed volcanic-shaped configuration, which can prevent the pod from being damaged by the high-temperature flame ejected by the rocket-like aircraft and the rocket-aircraft combination to the electrical system or the operating mechanism. The pod rolling curtain is in a compressed state and shrinks at the bottom ring of the second channel to ensure that the high-temperature flame ejected by the rocket-like aircraft and the rocket-aircraft combination can be discharged smoothly.

[0095] 5. Design principle of the ground loading, transportation and docking method for the air launch system: 1) Realize functions such as horizontal loading, horizontal encapsulation, horizontal transportation in the factory, and hoisting and installation at the launch site, and complete the precise loading of the rocket-like assembly loading vehicle in the factory to ensure the accuracy, safety and standardization of the vehicle loading; at the scene, only the docking of the pod and the launch platform needs to be completed, and the release task can be quickly completed, greatly saving the release time, improving the release efficiency and avoiding the occurrence of release weather, environment and unknown risks due to too long release time; 2) Compared with the traditional ground crane release method for floating air balloons, the ground release method described in the present invention adopts the fitting separation of the pyramid configuration of the launch platform and the locking and unlocking of the inclined plane locking slider, which can realize the firm locking of the air launch system on the ground. At the same time, the launch pad and the ground are fixed as a whole through anchor bolts, so as to ensure the safety, reliability and convenience of the ground release of the air launch system, and prevent dangerous situations such as the collision and overturning of the launch system caused by side winds and changes in weather conditions.

[0096] 6. Design principle of the multi-angle launch method: Compared with the traditional air launch vehicle method, the air launch method described in the present invention can realize the vertical, downward inclined, upward inclined and horizontal launches of various vehicles such as rocket-like vehicles, backpack arrow machine combinations and push-type arrow machine combinations in the air to meet the requirements of different launch tasks. At the same time, the pod can realize the repeated recovery of the landing buffer by the leg parachute, the vehicle can realize the return to the airport or the horizontal landing by parachute, and the rocket can realize the vertical recoil recovery, so as to realize the repeated multiple launches and recoveries of the whole system.

[0097] Based on the above principles, the present invention designs an air launch system for rocket-like vehicles and arrow machine combinations.

[0098] An air launch system for rocket-like vehicles and arrow machine combinations is as Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 and Figure 6 shown. Its characteristics are: The system is arranged from the inside to the outside as the innermost layer, the middle layer, the outermost layer, and from the top to the bottom as three layers; the innermost layer is provided with the rocket 5 of the launch system held by the middle layer, or the backpack arrow machine combination 11, or the push-type arrow machine combination 12. The middle layer is provided with a rolling channel body deformation subsystem that can quickly adapt to the radial changes of rocket-like vehicles and arrow machine combinations, and can greatly stretch the pod in the height direction to change the shape of the pod. The outermost layer is provided with a packaging subsystem that can greatly change the shape and height of the pod; the first layer from the top to the bottom is the above-mentioned rolling channel body deformation subsystem, and a landing buffer device 10 integrating a cabin door and landing buffer legs is hinged and installed at its lower end, and a launch platform 36 that cooperates with the pyramid structure of the landing buffer device.

[0099] As Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 shown, the rolling channel airframe deformation subsystem capable of quickly adapting to the radial changes of rocket-like aircraft and the combination of rocket and aircraft includes: payload compartment 1, payload compartment bottom ring 15, first channel roller support structure 3, first channel link mechanism 4, first channel bottom ring 17; second channel roller support structure 7, second channel link mechanism 6, second channel bottom ring 20; third channel roller support structure 9, third channel link mechanism 8, third channel bottom ring 21; the payload compartment 1 is fixedly installed on the upper part of the payload compartment bottom ring 15 by bolts; multiple hinge points at the upper end of the first channel link mechanism 4 are hinged to multiple hinge points at the bottom of the payload compartment bottom ring 15, the first channel roller support structure 3 is fixedly installed on the first channel roller support rod of the first channel link mechanism 4, multiple hinge points at the lower end of the first channel link mechanism 4 are hinged to multiple hinge points of the first channel bottom ring 17, and a first launch channel based on the deformation of a multi-parallelogram mechanism with multi-roller support is formed; multiple hinge points at the upper end of the second channel link mechanism 6 are hinged to multiple hinge points of the first channel bottom ring 17, the second channel roller support structure 7 is fixedly installed on the second channel roller support rod of the second channel link mechanism 6, multiple hinge points at the lower end of the second channel link mechanism 6 are hinged to multiple hinge points of the second channel bottom ring 20, and a second launch channel based on the deformation of a multi-parallelogram mechanism with multi-roller support is formed; multiple hinge points at the upper end of the third channel link mechanism 8 are hinged to multiple hinge points at the bottom of the second channel bottom ring 20, the third channel roller support structure 9 is fixedly installed on the third channel roller support rod of the third channel link mechanism 8, multiple hinge points at the lower end of the third channel link mechanism 8 are hinged to multiple hinge points of the third channel bottom ring 21, and a third launch channel based on the deformation of a multi-parallelogram mechanism with multi-roller support is formed; the first, second, and third launch channels together constitute the rolling channel airframe deformation system of the launch system;

[0100] The encapsulation subsystem capable of greatly changing the shape and height of the pod includes: multiple steel wires 18 and a pod rolling curtain device. These multiple steel wires 18 are evenly distributed in the pod 38, one end extends into the payload compartment 1 and is connected to the wire rope telescoping mechanism in the payload compartment 1, and the other end is fixedly installed on the lock 28 on the third channel bottom ring 21, forming a mechanism deformation wire rope drive system of the air launch system; one end of the stretched pod rolling curtain 30 is fixedly installed at the bottom of the payload compartment bottom ring 15, and the other end is fixedly installed at the top of the third channel bottom ring 21, and together with the payload compartment 1 and the landing buffer device 10 integrating the cabin door and the landing buffer leg, it constitutes the encapsulation system of the launch system.

[0101] The pod rolling curtain device includes a pod rolling curtain cloth 30 in a stretched state and a pod rolling curtain cloth 31 in a compressed state. The pod rolling curtain cloth 30 in the stretched state adaptively folds and deforms according to different tasks and the height of the pod. The pod rolling curtain cloth 30 in the stretched state is applied in the hanging and launching postures of the pod 38, and the pod rolling curtain cloth 31 in the compressed state is applied in the landing buffer state of the pod 38.

[0102] The integrated hatch and landing buffer leg landing buffer device 10 is integrally formed. A plurality of hinge points of the buffer device are hingedly installed on a plurality of hinge points at the bottom of the bottom ring 21 of the third channel. A plurality of synchronous shock absorbers 2 are evenly installed at the bottom of the load cabin bottom ring 15. The integrated hatch and landing buffer leg landing buffer device 10 cooperates with the synchronous shock absorbers 2 to jointly form the landing buffer system of the launch system and complete the multi-stage landing buffer function of the launch system.

[0103] As Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 and Figure 6 As shown in, the first channel link mechanism 4, the second channel link mechanism 6, and the third channel link mechanism 8 each include an upper link and a lower link, an inner link and an outer link; the upper link of each is arranged singly, the lower link is arranged in a double arrangement, and the gap between the double arrangements of the lower link can embed the upper link, thereby increasing the deformation angle of the mechanism and avoiding interference between the upper and lower links; a parallelogram arrangement is adopted between the inner and outer links of each, and both the inner and outer links are arc-shaped links with a certain angle, and the obtuse-angle faces of the arc-shaped links are placed facing each other, thereby greatly increasing the deformation angle of the mechanism, avoiding interference between the left and right links, and at the same time, reasonable design of the angle can achieve mechanical limit for deformation collision.

[0104] As Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 and Figure 6 As shown in, the first channel roller support structure 3 is composed of four first channel roller supports 16, which are respectively fixedly installed on four first channel roller support rods. A plurality of rollers thereof tightly hold the outer surface of the rocket 5, or the back-mounted arrow machine combination 11 or the push-type arrow machine combination 12, ensuring the safety and stability of the hanging and launching of the rocket 5, or the back-mounted arrow machine combination 11, or the push-type arrow machine combination 12;

[0105] The second-channel roller support structure 7 is composed of four second-channel roller supports 19, which are respectively and fixedly installed on four second-channel roller support rods. Multiple rollers thereof hold tightly the outer surface of the rocket 5, or the backpack arrow machine assembly 11 or the push-type arrow machine assembly 12, ensuring the safety and stability of the hanging and launching of the rocket 5, or the backpack arrow machine assembly 11 or the push-type arrow machine assembly 12;

[0106] The third-channel roller support structure 9, for the launch system of launching the rocket 5, is composed of four third-channel roller supports 14 evenly distributed, and is respectively and fixedly installed on four third-channel roller support rods; for the launch system of launching the backpack arrow machine assembly 11, it is composed of four third-channel roller supports 14 unevenly distributed, and is respectively and fixedly installed on four third-channel roller support rods; for the launch system of launching the push-type arrow machine assembly 12, it is composed of six third-channel roller supports 14 unevenly distributed, and is respectively and fixedly installed on two third-channel roller support rods; multiple rollers thereof hold tightly the outer surface of the rocket 5, or the backpack arrow machine assembly 11 or the push-type arrow machine assembly 12, ensuring the safety and stability of the hanging and launching of the rocket 5, the backpack arrow machine assembly 11 or the push-type arrow machine assembly 12.

[0107] As Figure 7 、 Figure 8 、 Figure 9 、 Figure 10 、 Figure 11 、 Figure 12 and Figure 13 As shown in

[0108] As Figure 7 and Figure 8As shown, the single-leg structure of the multi-functional landing buffer system includes a hatch 22, a shock-absorbing leg 23, a leg support 25, a two-way shock absorber 24, a locking strap 29, etc. Among them, the shock-absorbing leg 23 is hinged and installed on the lug on the bottom ring 21 of the third channel through a shock-absorbing leg fixing pin. One end of the two-way shock absorber 24 is hinged and installed on the lug on the bottom ring 21 of the third channel through a two-way shock absorber fixing pin two, and the other end is hinged and installed on the lug of the shock-absorbing leg 23 through a two-way shock absorber fixing pin one. The leg support 25 is hinged and installed at the bottom of the shock-absorbing leg 23 through a leg support fixing pin. The hatch 22 is fixedly installed on the shock-absorbing leg 23 through bolts. Thus, the single-leg structure of the multi-functional landing buffer system can not only complete the landing shock-absorbing function but also complete the closing and opening functions of the hatch 22. The locking strap 29 is fixedly installed at the corresponding position on the upper inner side of the shock-absorbing leg 23 through bolts and is used to lock the single-leg structure of the multi-functional landing buffer system.

[0109] As Figure 7 , Figure 8 and Figure 9 shown, a contact sensor 26 is also installed on the integrated landing buffer device 10 that integrates the hatch and the landing buffer leg. The contact sensor 26 is fixedly installed on the contact sensor fixing plate 27 on the bottom ring 21 of the third channel. The steel wire rope 18 passes through the through hole on the contact sensor fixing plate 27 and is fixedly installed on the lock 28. The lock 28 passes through two through holes of the bottom ring 21 of the third channel. When the shock-absorbing leg 23 is in the locked state and the hatch 22 is not opened at this time, since the steel wire rope 18 is in a taut state, the locking strap 29 is locked with the lock 28, and the lock 28 does not touch the contact sensor 51. At this time, the rocket 5, the back-mounted arrow machine combination 11 or the push-type arrow machine combination 12 is in the closed hanging state in the cabin. When receiving the command signal to open the hatch 22, the steel wire rope 18 is relaxed, and the locking strap 29 is separated from the lock 28 under the driving of the elastic potential energy of the two-way shock absorber 24, and the shock-absorbing leg 23 is released. At this time, it is in the state where the hatch 22 is opened and the rocket 5, the back-mounted arrow machine combination 11 or the push-type arrow machine combination 12 is waiting to be launched. When the steel wire rope 18 is taut again, if all the locks 28 are in contact with the contact sensor 26, it means that all the hatches 22 are fully opened. At this time, a launch command for the rocket 5, the back-mounted arrow machine combination 11 or the push-type arrow machine combination 12 is issued, and the rocket 5, the back-mounted arrow machine combination 11 or the push-type arrow machine combination 12 is launched along the launch channel. The contact sensor 26 can monitor the various states of the landing buffer device for functions such as integrated launch and hatch opening in real time, thereby improving the launch safety and reliability and warning of dangerous situations such as launching without opening the hatch 22.

[0110] As Figure 10 , Figure 11 , Figure 12 and Figure 13As shown, the rolling channel airframe deformation subsystem that can greatly stretch the nacelle in the height direction to change the shape of the nacelle is specifically as follows: In the launch state of rocket-like aircraft and the combination of rocket and aircraft, the height of the nacelle can be increased, so as to realize the encapsulation, suspension and launch of various large rocket-like aircraft and the combination of rocket and aircraft; In the landing and recovery state, the height and center of gravity of the nacelle can be greatly reduced, ensuring the safety and anti-overturning performance of the nacelle during landing.

[0111] As Figure 52 、 Figure 53 and Figure 54 As shown, in addition to constructing and vertically launching the vertical launch channels for the rocket 5, the backpack-type aircraft-rocket combination 11 or the push-type aircraft-rocket combination 12, the rocket-like aircraft and the aircraft-rocket combination launch system can also construct the downward inclined launch channels for the rocket 5, the backpack-type aircraft-rocket combination 11 or the push-type aircraft-rocket combination 12 and conduct air launches at an acute angle B with the vertical line, and can also construct the upward inclined air launch channels for the rocket 5, the backpack-type aircraft-rocket combination 11 or the push-type aircraft-rocket combination 12 and conduct air launches at an obtuse angle D with the vertical line, and can also construct the horizontal launch channels for the rocket 5, the backpack-type aircraft-rocket combination 11 or the push-type aircraft-rocket combination 12 and conduct air launches at a right angle C with the vertical line, so as to meet the requirements of air-launching the rocket 5, the backpack-type aircraft-rocket combination 11 or the push-type aircraft-rocket combination 12 under different working conditions.

[0112] As Figure 55 and Figure 56 As shown, when the rocket-like aircraft and the aircraft-rocket combination launch system launches the rocket 5, the backpack-type aircraft-rocket combination 11 or the push-type aircraft-rocket combination 12 upward inclined and horizontally, it is necessary to launch the rocket 5, the backpack-type aircraft-rocket combination 11 or the push-type aircraft-rocket combination 12 by igniting inside the nacelle. Therefore, it is necessary to protect the nacelle 38, especially the payload compartment 1 and the steel wire rope 18. Therefore, a distributed volcanic-shaped air diversion device 55 is installed at the bottom ring of the payload compartment to prevent the nacelle 38 from being damaged by the high-temperature flame ejected by the rocket 5, the backpack-type aircraft-rocket combination 11 or the push-type aircraft-rocket combination 12, causing damage to the electrical system or operating mechanism. The nacelle rolling curtain is in a compressed state and shrinks at the bottom ring 20 of the second channel to ensure that the high-temperature flame ejected by the rocket 5, the backpack-type aircraft-rocket combination 11 or the push-type aircraft-rocket combination 12 can be discharged smoothly.

[0113] Embodiment 1: Composition of the pyramid launch platform

[0114] As Figure 20 、 Figure 21 、 Figure 22 and Figure 23As shown, the delivery platform 36 includes a pod delivery locking block 35, a launch pad top plate 40, a launch pad conical groove 41, a launch pad pyramid fixing block 42, launch pad legs 43, a locking block sliding base 44, a launch pad bottom plate 45, a launch pad floor base 46, an Archimedes spiral disk 47, sliding pins 48, a motor 49, a slider locking inclined surface 50, a launch pad pyramid fixing block inclined surface 51, etc.

[0115] Among them, the launch pad conical groove 41 is welded in the circular groove of the launch pad top plate 40. The four launch pad legs 43 are evenly welded to the bottom of the launch pad top plate 40. The four launch pad floor bases 46 are welded to the bottoms of the four launch pad legs 43. The four launch pad floor bases 46 are fixed to the ground through anchor bolts. The launch pad bottom plate 45 is welded to the four launch pad legs 43. The launch pad pyramid fixing block 42 is fixed to the center position at the top of the launch pad bottom plate 45 through bolts. The four locking block sliding bases 44 are evenly fixed to the launch pad bottom plate 45 through bolts. The four pod delivery locking blocks 35 are embedded on the slide rails in the four locking block sliding bases 44. The four slider locking inclined surfaces 50 and the four launch pad pyramid fixing block inclined surfaces 51 are parallel to each other in pairs. The Archimedes spiral disk 47 is arranged at the center position at the bottom of the launch pad bottom plate 45 through bearings. One ends of the four sliding pins 48 are installed at the bottoms of the four pod delivery locking blocks 35, and the other ends are embedded in the Archimedes spiral grooves in the Archimedes spiral disk 47. The motor 49 is installed on the launch pad bottom plate 45, and its output shaft drives the Archimedes spiral disk 47 to rotate, thereby driving the four sliding pins 48 to slide in the Archimedes spiral grooves, further driving the four pod delivery locking blocks 35 to slide, so as to realize the locking and releasing of the pod 38 by the delivery platform 36.

[0116] Embodiment 2: The cooperation between the pod buffer leg inclined surface and the pyramid launch platform inclined surface

[0117] Another embodiment of the present invention is as Figure 25 、 Figure 26 and Figure 27As shown in the figure, when the hatch 22 of the pod 38 is closed, the four leg supports 25 contact each other in pairs to form a pyramid structure; the top surfaces 54 of the four pod legs contact the slide locking slopes 50 of the four pod release locking blocks 35, the bottom surfaces 56 of the four pod legs contact the slopes of the four launch pad pyramid fixing blocks 44, and the outer surfaces of the four hatches 22 contact the inner surfaces of the launch pad conical grooves 41. At this time, the pod 38 is locked with the release platform 36; when the four pod release locking blocks 35 slide outwards, the top surfaces 54 of the four pod legs separate from the slide locking slopes 50 of the four pod release locking blocks 35, and at this time the pod 38 is unlocked from the release platform 36; when the bottom surfaces 56 of the four pod legs separate from the slopes of the four launch pad pyramid fixing blocks 44, and the outer surfaces of the four hatches 22 separate from the inner surfaces of the launch pad conical grooves 41, at this time the pod 38 separates from the release platform 36. Compared with the traditional method of launching a floating air balloon 53 using a ground crane 52, the ground release method of the present invention adopts the method of fitting and separating the pyramid configuration of the release platform 36 and locking and unlocking the slide block with the slope, which can achieve firm ground locking of the air launch system. At the same time, the release platform 36 and the ground are fixed together by anchor bolts, so as to ensure the safety, reliability and convenience of the ground release of the air launch system, and prevent dangerous situations such as the launch system being knocked and overturned due to side winds and changes in weather conditions.

[0118] Example 3: At the launch site, only a crane is needed to dock the pod with the pyramid launch platform

[0119] As Figure 15 、 Figure 16 、 Figure 17 、 Figure 18 、 Figure 19 and Figure 24 As shown in the figure, the ground loading, transportation and docking method of the rocket-like aircraft and rocket machine combination launch method can realize functions such as horizontal loading of rockets 5 in the factory, or backpack rocket machine combination 11 or push-type rocket machine combination 12, horizontal transportation of the pod 38 by a transport vehicle, and hoisting and installation of the pod 38 at the launch site. It can complete the accurate loading of the rocket-like assembly loading rack in the factory to ensure the accuracy, safety and standardization of the aircraft loading; at the same time, it can realize the transportation of the pod 38 by the horizontal container 37 or the transport vehicle 39 to ensure the standardization, passability and safety of the transportation; in addition, only the docking of the pod 38 with the release platform 36 needs to be completed on site, and the release task can be quickly completed, greatly saving the release time, improving the release efficiency and avoiding the occurrence of release weather, environment and unknown risks due to too long release time.

[0120] Example 4: Air launch

[0121] As Figure 7 、 Figure 8 、 Figure 28 、 Figure 29, Figure 30 and Figure 31 As shown in Figure 30 and Figure 31 , first, the floating balloon 53 is used to carry the pod 38 from the pyramid launch pad to the launch position in the air. Then, the locking device 28 and the locking tape 29 are unlocked, and the four hatch doors 22 open in a petal shape driven by the elastic potential energy of the bi-directional shock absorber 24. Then, the hanging and releasing of the rocket 5, the backpack rocket machine combination 11 or the push-type rocket machine combination 12 is unlocked, and the rocket 5, the backpack rocket machine combination 11 or the push-type rocket machine combination 12 is launched along the rolling launch channel to achieve the in-air launch of the rocket 5, the backpack rocket machine combination 11 or the push-type rocket machine combination 12.

[0122] Example 5: Recovery

[0123] As Figure 32 , Figure 33 , Figure 34 , Figure 35 , Figure 36 , Figure 37 , Figure 38 , Figure 39 , Figure 40 , Figure 41 , Figure 42 , Figure 43 , Figure 44 , Figure 45 , Figure 46 , Figure 47 , Figure 48 , Figure 49 , Figure 50 and Figure 51 As shown in Figure 32 to Figure 51 , the floating balloon 53 is separated from the parachute 32, and the pod 38 slowly lands driven by the parachute 32. The deformation mechanism in the pod 38 is compressed and deformed driven by the steel wire 18, thereby reducing the center of gravity. The pod 38 realizes buffer landing and repeatable recovery under the combined buffering action of the landing buffer device 10 integrating the integrated hatch door and the landing buffer leg and the synchronous shock absorber 2; the rocket 5 experiences the gravity acceleration of the rocket 5 dropping, the high-altitude pulling up of the rocket 5, the high-altitude flight of the rocket 5, and the vertical recovery of the rocket 5 to achieve buffer landing and repeatable recovery; the backpack rocket machine combination 11 experiences the gravity acceleration of the backpack rocket machine combination 11 dropping, the high-altitude pulling up of the backpack rocket machine combination 11, the high-altitude flight of the backpack rocket machine combination 11, the separation of the backpack rocket machine combination 11, the vertical recovery of the rocket 5, the in-air flight of the aircraft 13, the landing of the flight 13 at the airport or the parachute landing, etc. to achieve the combined system buffer landing and repeatable recovery of the combination; the push-type rocket machine combination 12 experiences the gravity acceleration of the push-type rocket machine combination 12 dropping, the high-altitude pulling up of the push-type rocket machine combination 12, the high-altitude flight of the push-type rocket machine combination 12, the separation of the push-type rocket machine combination 12, the vertical recovery of the rocket 5, the in-air flight of the aircraft 13, the landing of the flight 13 at the airport or the parachute landing, etc. to achieve the combined system buffer landing and repeatable recovery of the combination.

[0124] The above description is not intended to limit the present invention. It should be noted that for those of ordinary skill in the art, without departing from the essence of the present invention, several changes, modifications, additions or substitutions can still be made, and these improvements and refinements should also be regarded as within the protection scope of the present invention.

Claims

1. A rocket-like aircraft and an air launch system for a combination of rocket and aircraft, characterized in that: The system is divided into three layers from the inside out and from top to bottom; the innermost layer is provided with a rocket (5) of the launch system held tightly by the middle layer, or a backpack arrow machine combination (11), or a push-type arrow machine combination (12). The middle layer is provided with a rolling channel body deformation subsystem that can quickly adapt to the radial changes of rocket-like aircraft and arrow machine combinations, and can greatly stretch the pod in the height direction to change the shape of the pod. The outermost layer is provided with a packaging subsystem that can greatly change the shape and height of the pod; the first layer from top to bottom is the rolling channel body deformation subsystem, and at its lower end, a landing buffer device (10) integrating a hatch and landing buffer legs is hingedly installed, and a delivery platform (36) that cooperates with the pyramid structure of the landing buffer device; The rolling channel body deformation subsystem that can quickly adapt to the radial changes of rocket-like aircraft and arrow machine combinations includes: a payload compartment (1), a payload compartment bottom ring (15), a first channel roller support structure (3), a first channel link mechanism (4), a first channel bottom ring (17); a second channel roller support structure (7), a second channel link mechanism (6), a second channel bottom ring (20); a third channel roller support structure (9), a third channel link mechanism (8), a third channel bottom ring (21); the payload compartment (1) is fixedly installed on the upper part of the payload compartment bottom ring (15) by bolts; multiple hinge points of the first channel link mechanism (4) are hinged to multiple hinge points at the bottom of the payload compartment bottom ring (15), the first channel roller support structure (3) is fixedly installed on the first channel roller support rod of the first channel link mechanism (4), and multiple hinge points of the first channel bottom ring (17) are hinged to multiple hinge points of the first channel link mechanism (4), and a first launch channel based on the deformation of a multi-parallelogram mechanism with multi-roller support is formed; multiple hinge points of the second channel link mechanism (6) are hinged to multiple hinge points at the bottom of the first channel bottom ring (17), the second channel roller support structure (7) is fixedly installed on the second channel roller support rod of the second channel link mechanism (6), and multiple hinge points of the second channel bottom ring (20) are hinged to multiple hinge points of the second channel link mechanism (6), and a second launch channel based on the deformation of a multi-parallelogram mechanism with multi-roller support is formed; multiple hinge points of the third channel link mechanism (8) are hinged to multiple hinge points at the bottom of the second channel bottom ring (20), the third channel roller support structure (9) is fixedly installed on the third channel roller support rod of the third channel link mechanism (8), and multiple hinge points of the third channel bottom ring (21) are hinged to multiple hinge points of the third channel link mechanism (8), and a third launch channel based on the deformation of a multi-parallelogram mechanism with multi-roller support is formed; the first, second, and third launch channels together constitute the rolling channel body deformation system of the launch system; The encapsulation subsystem capable of widely changing the shape and height of the nacelle includes: multiple steel wire ropes (18) and a nacelle rolling curtain device. The multiple steel wire ropes (18) are evenly distributed inside the nacelle (38), with one end extending into the payload compartment (1) and connecting to the wire rope telescopic mechanism inside the payload compartment (1), and the other end fixedly installed on the lock (28) on the bottom ring (21) of the third channel, constituting the mechanism deformation rope drive system of the air launch system; One end of the stretched nacelle rolling curtain (30) is fixedly installed at the bottom of the payload compartment bottom ring (15), and the other end is fixedly installed at the top of the third channel bottom ring (21), and together with the payload compartment (1) and the landing buffer device (10) integrating the cabin door and landing buffer legs, constitutes the encapsulation system of the launch system. The nacelle rolling curtain device includes a stretched nacelle rolling curtain (30) and a compressed nacelle rolling curtain (31). The stretched nacelle rolling curtain (30) adaptively folds and deforms according to different tasks and the height of the nacelle. The stretched nacelle rolling curtain (30) is applied in the hanging and launching postures of the nacelle (38), and the compressed nacelle rolling curtain (31) is applied in the landing buffer state of the nacelle (38). The integrated cabin door and landing buffer leg landing buffer device (10), with multiple hinge points of the buffer device hinge-mounted on multiple hinge points at the bottom of the third channel bottom ring (21), and multiple synchronous shock absorbers (2) evenly installed at the bottom of the payload compartment bottom ring (15). The integrated cabin door and landing buffer leg landing buffer device (10) and the synchronous shock absorbers (2) cooperate with each other to jointly constitute the landing buffer system of the launch system and complete the multi-stage landing buffer function of the launch system.

2. The air launch system for a rocket-like aircraft and a rocket engine combination according to claim 1, wherein: The first channel link mechanism (4), the second channel link mechanism (6), and the third channel link mechanism (8) each include an upper link and a lower link, an inner link and an outer link; the upper link of each is arranged singly, the lower link is arranged in a double configuration, and the gap between the double-arranged lower links can embed the upper link, thereby increasing the deformation angle of the mechanism and avoiding interference between the upper and lower links; a parallelogram arrangement is adopted between the inner and outer links of each. The inner and outer links are both arc-shaped links with a certain angle, and the obtuse-angle faces of the arc-shaped links are placed facing each other, thereby greatly increasing the deformation angle of the mechanism, avoiding interference between the left and right links, and at the same time, reasonable design of the angle can achieve mechanical limit for deformation collision.

3. The air launch system of a rocket-like aircraft and a rocket-aircraft combination according to claim 1, characterized in that: The first channel roller support structure (3) is composed of four first channel roller supports (16), which are respectively fixedly installed on four first channel roller support rods. Multiple rollers of it hold tightly the outer surface of the rocket (5), or the back-mounted rocket-aircraft combination (11) or the push-type rocket-aircraft combination (12), ensuring the safety and stability of the hanging and launching of the rocket (5), or the back-mounted rocket-aircraft combination (11), or the push-type rocket-aircraft combination (12). The second-channel roller support structure (7) is composed of four second-channel roller supports (19), which are respectively and fixedly installed on four second-channel roller support rods. A plurality of its rollers hold the outer surface of the rocket (5), or the backpack-type arrow machine assembly (11) or the push-type arrow machine assembly (12), ensuring the safety and stability of the hanging and launching of the rocket (5), or the backpack-type arrow machine assembly (11) or the push-type arrow machine assembly (12); The third-channel roller support structure (9), for the launch system of launching the rocket (5), is uniformly composed of four third-channel roller supports (14), which are respectively and fixedly installed on four third-channel roller support rods; for the launch system of launching the backpack-type arrow machine assembly (11), it is non-uniformly composed of four third-channel roller supports (14), which are respectively and fixedly installed on four third-channel roller support rods; for the launch system of launching the push-type arrow machine assembly (12), it is non-uniformly composed of six third-channel roller supports (14), which are respectively and fixedly installed on two third-channel roller support rods; a plurality of its rollers hold the outer surface of the rocket (5), or the backpack-type arrow machine assembly (11) or the push-type arrow machine assembly (12), ensuring the safety and stability of the hanging and launching of the rocket (5), the backpack-type arrow machine assembly (11) or the push-type arrow machine assembly (12).

4. The air launch system of a rocket-like aircraft and a rocket engine combination according to claim 1, wherein: The integrated landing buffer device (10) integrating the hatch and the landing buffer legs includes four single-leg structures of the multi-functional landing buffer system; each single-leg structure of the multi-functional landing buffer system is respectively hinged to the third-channel bottom ring (21) of the nacelle (38) through a two-way shock absorber fixing pin and a shock leg fixing pin, and each two of the single-leg structures of the multi-functional landing buffer system are spliced together to form a conical shape. At this time, the nacelle (38) is in the state of being encapsulated and hung with the rocket (5), or the backpack-type arrow machine assembly (11) or the push-type arrow machine assembly (12); when the four single-leg structures (10-1) of the multi-functional landing buffer system are in the petal-shaped open state, according to the attitude and tasks of the nacelle (38), the nacelle (38) is respectively in the state of waiting to launch the rocket (5), or the backpack-type arrow machine assembly (11) or the push-type arrow machine assembly (12), or the launch state of the rocket (5), the backpack-type arrow machine assembly (11) or the push-type arrow machine assembly (12), or the landing buffer state of the nacelle (38).

5. The air launch system for a rocket-like aircraft and a rocket-machine combination according to claim 4, characterized in that: The single-leg structure of the multi-functional landing buffer system includes a hatch (22), a shock-absorbing leg (23), a leg support (25), a two-way shock absorber (24), and a locking strap (29); among them, the shock-absorbing leg (23) is hinged and installed on the ear on the bottom ring (21) of the third channel through a shock-absorbing leg fixing pin. One end of the two-way shock absorber (24) is hinged and installed on the ear on the bottom ring (21) of the third channel through a two-way shock absorber fixing pin two, and the other end is hinged and installed on the ear of the shock-absorbing leg (23) through a two-way shock absorber fixing pin one. The leg support (25) is hinged and installed at the bottom of the shock-absorbing leg (23) through a leg support fixing pin. The hatch (22) is fixedly installed on the shock-absorbing leg (23) by bolts, so that the single-leg structure of the multi-functional landing buffer system can not only complete the landing shock-absorbing function but also complete the functions of closing and opening the hatch (22); the locking strap (29) is fixedly installed at the corresponding position on the upper inner side of the shock-absorbing leg (23) by bolts and is used to lock the single-leg structure of the multi-functional landing buffer system.

6. The air launch system of a rocket-like aircraft and a rocket machine combination according to claim 1, wherein: A contact sensor (26) is also installed on the landing buffer device (10) that integrates the hatch and the landing shock-absorbing leg. The contact sensor (26) is fixedly installed on the contact sensor fixing plate (27) on the bottom ring (21) of the third channel. The steel wire rope (18) passes through the through hole on the contact sensor fixing plate (27) and is fixedly installed on the lock (28). The lock (28) passes through two through holes in the bottom ring (21) of the third channel. When the shock-absorbing leg (23) is in the locked state and the hatch (22) is not opened at this time, since the steel wire rope (18) is in a taut state, the locking strap (29) is locked with the lock (28), and the lock (28) does not touch the contact sensor (26). At this time, the rocket (5), or the back-mounted rocket machine combination (11), or the push-type rocket machine combination (12) is in a closed hanging state in the cabin. When receiving the command signal to open the hatch (22), the steel wire rope (18) is relaxed, and the locking strap (29) is separated from the lock (28) under the driving of the elastic potential energy of the two-way shock absorber (24), and the shock-absorbing leg (23) is released. At this time, the hatch (22) is opened, and the rocket (5), or the back-mounted rocket machine combination (11), or the push-type rocket machine combination (12) is in a waiting-to-launch state. When the steel wire rope (18) is taut again, if all the locks (28) are in contact with the contact sensor (26), it means that all the hatches (22) are fully opened. At this time, a launch command for the rocket (5), or the back-mounted rocket machine combination (11), or the push-type rocket machine combination (12) is issued, and the rocket (5), or the back-mounted rocket machine combination (11), or the push-type rocket machine combination (12) is launched along the launch channel. The contact sensor (26) can monitor the various states of the landing buffer device (10) that integrates functions such as integrated launch and hatch opening in real time, thereby improving the launch safety and reliability and warning of dangerous situations such as launching with the hatch (22) not opened.

7. The air launch system for a rocket-like aircraft and a rocket machine combination according to claim 1, characterized in that: The rolling channel airframe deformation subsystem capable of greatly stretching the nacelle in the height direction to change the nacelle shape is specifically as follows: In the launch state of rocket-like aircraft and the rocket-aircraft combination, the nacelle height can be increased to achieve the encapsulation, suspension, and launch of various large rocket-like aircraft and rocket-aircraft combinations; in the landing and recovery state, the nacelle height and center of gravity can be greatly reduced, ensuring the safety and anti-overturning performance of the nacelle during landing.

8. The air launch system of a rocket-like aircraft and a rocket machine combination according to claim 1, characterized in that: The launch system of the rocket-like aircraft and the rocket-aircraft combination can not only construct and vertically launch the vertical launch channels of the rocket (5), or the back-mounted rocket-aircraft combination (11), or the push-type rocket-aircraft combination (12), but also construct the downward inclined launch channels of the rocket (5), or the back-mounted rocket-aircraft combination (11), or the push-type rocket-aircraft combination (12) and conduct air launches at an acute angle B with the vertical line, and can also construct the upward inclined air launch channels of the rocket (5), or the back-mounted rocket-aircraft combination (11), or the push-type rocket-aircraft combination (12) and conduct air launches at an obtuse angle D with the vertical line.

9. The air launch system of a rocket-like aircraft and a rocket machine combination according to claim 1, wherein: A distributed volcanic-shaped air diversion device (55) is installed at the bottom ring of the payload compartment to prevent the nacelle (38) from being damaged by the high-temperature flames ejected by the rocket (5), or the back-mounted rocket-aircraft combination (11), or the push-type rocket-aircraft combination (12), which may cause damage to the electrical system or operating mechanism. The nacelle rolling curtain is in a compressed state and retracts at the bottom ring (20) of the second channel to ensure that the high-temperature flames ejected by the rocket (5), or the back-mounted rocket-aircraft combination (11), or the push-type rocket-aircraft combination (12) can be smoothly discharged.

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