CN217260632U - High-altitude balloon platform capable of realizing wide-amplitude transition - Google Patents
High-altitude balloon platform capable of realizing wide-amplitude transition Download PDFInfo
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- CN217260632U CN217260632U CN202220754281.XU CN202220754281U CN217260632U CN 217260632 U CN217260632 U CN 217260632U CN 202220754281 U CN202220754281 U CN 202220754281U CN 217260632 U CN217260632 U CN 217260632U
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Abstract
The utility model provides a high-altitude balloon platform capable of wide transition. The wide-amplitude jump high-altitude balloon platform comprises an air bag, a cutter, a parachute, a truss, a nacelle and a counterweight cabin for releasing sand iron to perform height adjustment, wherein the truss is connected to the bottom of the parachute, and the nacelle is arranged at the bottom of the truss; the counterweight cabins are symmetrically arranged at two ends of the truss; the pod comprises an electrical pod for placing avionics equipment on the upper part and a launch cabin for loading the aircraft on the lower part. The utility model discloses possess and carry on the ability reinforce, the regional ability of dwelling of long term to can realize in the ten minutes from closing on space 20km elevation of sea level and jump to 35km elevation of sea level fast.
Description
Technical Field
The utility model relates to an aviation technical field especially relates to a high altitude balloon platform that can broad width jump is applied to the aircraft transmission.
Background
The conventional aerial launching platform is an aviation airplane, but cannot meet the requirements of large load and high altitude due to limited flight height and load capacity. The high-altitude balloon is used as an aircraft which is lifted by filling buoyancy gas, the load-carrying capacity can reach dozens of tons at most, and the lifting height can reach more than 30 km. Compared with other launching modes, the aerial launching based on the high-altitude balloon has the advantages of low cost, strong carrying capacity, short development period, relatively high technical maturity and the like.
The high-altitude balloon launching platform can provide certain initial altitude and speed for the aircraft, is favorable to carrying on the wholeness ability promotion of aircraft: 1) the speed increment required by the aircraft to enter the orbit can be reduced by launching the aircraft at the high altitude with thin air. Zero 2Infinity Inc estimated the 8% speed increment required to lower the orbit using high-altitude balloon rocket launch energy than ground launch using the european space Agency Software Tool (ASTOS), and a change in the speed increment would have a significant impact on carrying capacity; 2) when the aircraft is launched at high altitude, the thermal environment of the aircraft is also greatly improved, the heat flux can be reduced by 10 times by virtue of high-altitude launching, and the requirement on the heat-proof design of the aircraft is greatly reduced, so that the optimization of the structural quality is realized; 3) after the launching of the aircraft is completed, the high-altitude balloon can also serve as a C4ISR platform to perform high-altitude detection, communication, interference and other battle tasks.
The main disadvantages of the existing high-altitude balloon launching platform are as follows: 1) the flying height of the platform is limited, and the performance of the aircraft is improved to a limited extent; 2) once the launching is carried out, the launching aircraft can be launched quickly to complete the launching task, the high-altitude on-duty capability is not available, the high-altitude balloon platform cannot execute other tasks, and the use cost is low.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a but wide width transition high altitude balloon platform that possesses carrying capacity reinforce, ability long term region dwell ability.
The technical scheme of the utility model is that: a high-altitude balloon platform capable of jumping in a wide range comprises an air bag, a cutter, a parachute, a truss, a nacelle and a counterweight cabin, wherein the counterweight cabin is used for releasing sand iron to perform height adjustment; the counterweight cabins are symmetrically arranged at two ends of the truss;
the pod comprises an electrical pod for placing avionics equipment on the upper part and a launch cabin for loading the aircraft on the lower part.
Preferably, the electric pod and the launch cabin are of an integrated structure.
Preferably, the bottom of the launching capsule is provided with a plurality of groups of compression springs.
Preferably, the truss is a cross truss.
Preferably, the truss is hollow inside, and a solar cell array is laid on the top of the truss.
Preferably, the air bag is of a water drop type zero-pressure structure, and a deflation valve is installed on a flange at the top of the air bag.
Preferably, the weight chamber is funnel-shaped.
Compared with the prior art, the beneficial effects of the utility model are that: possess diversified task ability, can promote the cost-effectiveness ratio of high altitude balloon platform's use. As a launching platform, the high-altitude balloon platform capable of wide amplitude transition has the launching capability of 20km and 35km altitudes, can reside in a long-term area with 20km altitude to wait for launching opportunity, and can quickly respond when receiving tasks; as a high-altitude carrying platform, the system can carry different loads (such as visible light, communication and scientific observation loads) to execute corresponding tasks.
Drawings
Fig. 1 is a schematic view of the wide-range jump high-altitude balloon platform in an altitude stagnation state of 20km at high altitude;
fig. 2 is a schematic diagram of the wide-range jump high-altitude balloon platform in an altitude stagnation state of 35km at high altitude;
fig. 3 is a schematic view of the working principle of the wide-jump high-altitude balloon platform provided by the present invention.
In the drawings: 1. an air bag; 2. a deflation valve; 3. a cutter; 4. a parachute; 5. a truss; 6. a nacelle; 7. a counterweight cabin; 8. a binding tape.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments. It should be noted that, in the present invention, the embodiments and features of the embodiments may be combined with each other without conflict. For convenience of description, the words "upper", "lower", "left" and "right" in the following description are used only to indicate the correspondence with the upper, lower, left and right directions of the drawings, and do not limit the structure.
As shown in FIG. 1, the embodiment provides a high-altitude balloon platform air bag 1 capable of wide-amplitude transition, an air release valve 2, a cutter 3, a parachute 4, a truss 5, a nacelle 6 and a counterweight cabin 7.
The air bag 1 is made of light high-strength film material, and the comprehensive surface density of the air bag is not more than 50g/m 2 The bag is filled with buoyancy gas. Be equipped with the constraint hole of ligature area 8 on gasbag 1, be used for arranging ligature area 8 before the platform jumps in order to restrain the gasbag to keep good pneumatic appearance, then unblock through steering wheel or initiating explosive device after beginning to jump. Be equipped with gas tube and blast pipe on the gasbag 1, the blast pipe is provided with six, is respectively at the lower extreme and the bottom of gasbag 1 for discharge unnecessary gas. Two inflation tubes are symmetrically arranged at two sides of the air bag 1. In order to realize rapid ground inflation, the diameter of the inflation pipe is required to be not less than phi 400mm, and the length of the inflation pipe is required to be not less than 100 m.
The bleed valve 2 is installed on the top flange of gasbag 1, adopts the design of perpendicular push-down automatically controlled valve, and the power supply is protected through the tiny cell in the top instrument case. Heating sheets with power not lower than 10W are adhered on an actuating motor of the air release valve 2, and lubricating grease with the temperature of 70 ℃ below zero is smeared on the contact part of a valve body and a valve cover and the sealing ring of the air release valve 2.
The bottom of the air bag 1 is connected with a parachute top rope ring of a parachute 4 through a rope, and the cutter 3 is arranged on the rope. The cutter 3 adopts an electric heating type initiating explosive device and adopts a double backup design, and the cutter can be detonated simultaneously at the moment of electrifying.
The parachute 4 adopts a first-level circular parachute, and the parachute opening mode is open parachute opening. The parachute 4 comprises a canopy and a parachute cord, the canopy is made of a light fabric material, and the constituent units below the parachute bottom cord ring can be safely recycled. The parachute opening height of the parachute 4is not less than 35km, the stable descending speed after descending and inflating is not more than 7m/s, and the overload is not more than 5 g.
The truss 5 is of a cross truss structure and is made of carbon fibers or other light rigid materials, the truss 5 is hollow, and the upper portion of the truss is used for laying a solar cell array. The truss 5 is connected with rope rings at the bottom of the parachute 4 through four groups of high-strength polyethylene ropes (2 ropes in each group). The bottom of the truss 5 is provided with a connecting hanging point of the nacelle 6, and the hanging point can be limited left and right (if an annular structure is adopted), so that reliable connection is ensured.
The nacelle 6 is designed by adopting a structure of a rigid framework and a heat insulation material, and the upper layer is an electrical equipment cabin for mounting avionics equipment such as a computer, a sensor, communication and a storage battery; the lower layer is a launching cabin, the launching cabin is custom-designed according to the use requirements and the working environment requirements of the launched aircraft, and for example, according to the category of the launched aircraft, the cabin body is designed into a structure in a horizontal or vertical layout. The aircraft in the launching cabin is launched in a gravity launching mode. During recovery, in order to prevent the nacelle 6 from hard landing, a plurality of groups of compression spring shock absorbers are symmetrically arranged on two sides of the launching cabin contacting the ground.
The platform pod of the pod 6 and the aircraft launch cabin are of an integrated design and are arranged in the middle of the bottom of the truss 5.
The counterweight cabins 7 are symmetrically arranged at two ends of the bottom of the truss 5 and used for releasing iron sand to perform height adjustment. The counterweight chamber 7 comprises a chamber body, an iron sand releaser, an electromagnetic valve, an electric controller and the like. The counterweight cabin 7 is designed into a funnel shape and is formed by welding antirust aluminum alloy plates. A coil of the electromagnetic valve is connected with a 24V direct-current power supply, the coil generates a magnetic field to suck iron sand, after the power is off, the magnetic field disappears, the iron sand releaser is started, and the iron sand is released under the action of gravity. The iron sand should be selected from large specific gravity weight iron sandThe density is not less than 6.8t/m 3 . The above actions are controlled by an electric controller.
And a plurality of groups of compression springs are arranged at the bottom of the launching cabin and are used for damping the nacelle before the nacelle falls to the ground.
The binding belt 8 is made of an air bag material, and the surface of the binding belt is smooth and burr-free. Before starting the inflation, the tie-up strap 8 is passed through a predetermined buttonhole on the airbag 1 and tightened to effectively prevent the blow-by of gas into the unrestrained airbag portion.
As shown in fig. 3, the working principle of the wide-jump high-altitude balloon platform provided by the present invention is: the high-altitude balloon platform is lifted off by means of buoyancy, flies into a 20km stagnation point, and realizes long-term stagnation in a 200km radius area of the stagnation point by utilizing an stratosphere east-west shear wind zone (as shown in figure 1). Upon receiving a mission command, the large number of weights are released immediately, the restraint of the tie straps 8 of the airbags 1 is released (as shown in fig. 2), and the aircraft is launched to make a large altitude jump, climbing up to 35km of altitude within 15 min. After the aircraft reaches the task height, the aircraft is thrown out in a gravity throwing mode, and the aircraft is ignited to execute the expected task. After the aerial vehicle is launched, the high-altitude balloon platform can continue to execute other tasks, and after the tasks are completed, the units such as the pod and the like are recovered by using the parachute.
The utility model provides a but high altitude balloon platform of broad width transition can be used to carry on aircraft such as rocket or guided missile and carry out high altitude launch, and it is limited to solve conventional high altitude balloon launching platform altitude of flight, lacks the ability on duty and the single scheduling problem of task, can satisfy needs such as the emergent benefit net launching satellite of army and civilian field, target, high altitude investigation surveillance are kept watch on in air, provides low-priced, quick, nimble aerial launching platform for it.
The use of the wide-range-transitive high-altitude balloon platform is further described below with reference to a specific example:
selecting a meteorological window of 2020, 12 and 21 days to 12 and 23 days of Xinjiang for analysis: the local sunrise time is 6:45, and the sunset time is 17: 54; an obvious east-west wind zone exists between 18km and 25km of altitude, the absolute value of the wind speed is less than 4m/s, the wind direction at 20km of altitude is southwest wind, and the wind direction at 19km of altitude is southeast wind.
System design parameters
And (3) total takeoff weight of the system: 10296 kg;
carrying aircraft quantity and weight: 2, 1350kg each;
parking space flight time: 3 d;
standing height: 20 km;
resident empty area range: the radius is 200 km;
transition time: 8 min;
transition height: 15 km.
(II) design of geometric parameters
Total height of the platform: 201.8 m;
maximum width of the platform (maximum diameter of the airbag 1 in plan view): 128 m;
diameter of the umbrella top hole: 3.8 m;
the umbrella is wide: 1.04 m;
truss 5: 8.5 m.times.8.5 m.times.0.8 m;
the nacelle 6: 7.5 m.times.1.2 m.times.1.5 m.
The specific working process of the wide-amplitude jump high-altitude balloon platform is as follows:
the ground atmospheric density is 1.14kg/m 3 Ground assembly and dispensing stage, bladder 1 is filled with a helium volume of 9283m 3 And 286.5kg of ground net buoyancy before rising. After the inflation is finished, the balloon platform is lifted off in a dynamic release mode, the air bag is in a non-shape-preserving state in the lifting-off process, the time of the whole lifting-off process is 45min, and the average lifting speed is about 7.4 m/s;
the atmospheric density at 20km altitude is 0.0902kg/m 3 The volume of the air bag 1 is 10 ten thousand meters 3 The net buoyancy was 3.9kg and the balloon platform began to enter the airborne stage. The air-parking time is 3d, the buoyancy loss of day and night can be caused by the super-heat in the daytime and the super-cold at night of the air bag 1, the weight needs to be adjusted to keep the floating weight balance, the height stability and the area parking are realized, the balance weight of 200kg, 300kg and 400kg needs to be released respectively to offset the net buoyancy loss of three days, and the flying height of the balloon platform can be stabilized at 20km altitude(as shown in fig. 1), the maximum amplitude of nighttime altitude fluctuations is 1.1 km.
After the balloon platform is parked in the air for 3d, when the balloon platform starts to execute a transition task, an aircraft is thrown by gravity, the counterweight cabin 7 releases 750kg of counterweight, meanwhile, the unlocking device is started to unlock the binding belt 8, the buoyancy of the balloon platform is greatly increased, only 8min is needed for the transition from 20km to 35km, and the average ascending speed of the transition reaches 31.2 m/s.
The atmospheric density at 35km altitude is 0.00841kg/m 3 The volume of the air bag 1 is 80 ten thousand meters 3 When the net buoyancy is 53.9kg, the balloon platform begins to fly to the 35km high altitude (as shown in fig. 2), subsequent reconnaissance monitoring and communication relay tasks can be executed, and meanwhile, another aircraft can be launched according to the task requirements.
After the 35km flight task is completed, the balloon platform enters a recovery process, the separation of the balloon and the parachute is realized by starting the cutter 3, and the truss 5, the nacelle 6 and the cabin avionics equipment are recovered. The recovery process takes 53min, the overload of the parachute 4 during inflation and unfolding is 5g, and the stable grounding speed is about 4.72 m/s.
The above-mentioned only be the embodiment of the present invention, not consequently the restriction of the patent scope of the present invention, all utilize the equivalent structure or equivalent flow transform made of the content of the specification and the attached drawings, or directly or indirectly use in other relevant technical fields, all including in the same way the patent protection scope of the present invention.
Claims (7)
1. A high-altitude balloon platform capable of jumping in a wide range comprises an air bag (1), a cutter (3) and a parachute (4), and is characterized by further comprising a truss (5), a nacelle (6) and a counterweight cabin (7) for releasing sand iron to adjust the height, wherein the truss (5) is connected to the bottom of the parachute (4), and the nacelle (6) is arranged at the bottom of the truss (5); the counterweight cabins (7) are symmetrically arranged at two ends of the truss (5);
the pod (6) comprises an electrical pod for placing avionics equipment on the upper part and a launch cabin for loading the aircraft on the lower part.
2. The wide-width-transitionable high-altitude-balloon platform of claim 1, wherein the electrical pod and launch capsule are a unitary, integrated structure.
3. The wide-width-transition high-altitude-balloon platform as claimed in claim 1, wherein the bottom of the launch capsule is provided with a plurality of sets of compression springs.
4. The wide-amplitude-transitionable high-altitude-balloon platform as claimed in claim 1, wherein the truss (5) is a cross truss.
5. The wide-amplitude-transition high-altitude-balloon platform as claimed in claim 1 or 4, wherein the truss (5) is hollow inside and is laid with a solar cell array on top.
6. The wide-amplitude transition high-altitude balloon platform as claimed in claim 1, wherein the air bag (1) is of a water drop type zero-pressure structure, and a deflation valve (2) is mounted on a top flange of the air bag.
7. The wide-width-jump high-altitude-balloon platform according to claim 1, wherein the counterweight cabin (7) is funnel-shaped.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220754281.XU CN217260632U (en) | 2022-04-02 | 2022-04-02 | High-altitude balloon platform capable of realizing wide-amplitude transition |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220754281.XU CN217260632U (en) | 2022-04-02 | 2022-04-02 | High-altitude balloon platform capable of realizing wide-amplitude transition |
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| CN217260632U true CN217260632U (en) | 2022-08-23 |
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| CN202220754281.XU Active CN217260632U (en) | 2022-04-02 | 2022-04-02 | High-altitude balloon platform capable of realizing wide-amplitude transition |
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