A fully simulated demonstration model spacecraft integrating solid and water and its usage method

Abstract

The present invention discloses a fully simulated demonstration model spacecraft with integrated solid water, including a rocket body and an adjustable launch rack for supporting the rocket body; the rocket body includes a return capsule and a main capsule which are cooperatively connected, a load is arranged in the return capsule, a first parachute is connected to the load, a second parachute is arranged in the parachute compartment, and the second parachute is connected to the return capsule; a power mechanism is arranged in the main capsule; a through hole is arranged in the middle of the partition piece, a plurality of clamping holes are arranged around the through hole, and a solid fuel is arranged in the clamping holes; the fixing frame is placed on one side of the adjusting plate, and the fixing frame encloses a placement space for placing the rocket body; a plurality of card slots are arranged on the side of the adjusting plate away from the fixing frame. This structure can perform dynamic simulation and can be recycled multiple times; it can ensure that the present invention falls safely and is recovered after separation, and can also facilitate multi-angle and vertical launches.

Description

Technical Field

[0001] The present invention belongs to the technical field of model spacecraft, and particularly relates to a fully simulated demonstration model spacecraft integrated with solid and water. Background Art

[0002] At present, model spacecraft gradually appear in people's vision, and the demonstration effects of model spacecraft can be seen in many universities, science and technology exhibitions and various competitions. However, the demonstration effects of most simulation model spacecraft are single and cannot be demonstrated comprehensively and dynamically. When a small number of simulation spacecraft are demonstrated dynamically, there is a lack of a stable, reliable and portable launch rack and an efficient, stable and strong-load-bearing launch device, resulting in the failure of many model spacecraft launches, material losses and personnel injuries.

[0003] The existing model spacecraft have the following problems:

[0004] 1. It cannot be launched at a large angle with the vertical direction;

[0005] 2. The service life of model rockets is short;

[0006] 3. Most simulation model rockets can only be displayed statically;

[0007] 4. The cost of fully simulated demonstration rocket models is high. Summary of the Invention

[0008] The purpose of the present invention is to provide a fully simulated demonstration model spacecraft integrated with solid and water, so as to solve the problems existing in the existing model spacecraft in the background art, such as not being able to be launched at a large angle with the vertical direction, short service life of model rockets, most simulation model rockets can only be displayed statically, and high cost of fully simulated demonstration rocket models.

[0009] To solve the above technical problems, the technical solution adopted by the present invention is:

[0010] A fully simulated demonstration model spacecraft integrated with solid and water, comprising the rocket body and an adjustable launch rack for supporting the rocket body;

[0011] The rocket body includes a return capsule and a main capsule that are cooperatively connected. On one side of the main capsule close to the return capsule, there is a parachute capsule, and on the other side, there is a power capsule; a load is arranged in the return capsule, and a first parachute is connected to the load. A second parachute is arranged in the parachute capsule, and the second parachute is connected to the return capsule; a power mechanism made of a water storage container is arranged in the main capsule, and an air injection hole is arranged on one side of the water storage container close to the power capsule;

[0012] A partition is arranged between the main capsule and the power capsule. A through hole is arranged in the middle of the partition, and a number of clamping holes are arranged around the through hole. A solid fuel is arranged in the clamping holes; an ignition device is arranged at the contact position between the base and the rocket.

[0013] The adjustable launch rack includes a fixed rack, a sliding plate and an adjusting plate; the fixed rack is placed on one side of the adjusting plate, and a supporting device for supporting and adjusting the inclination angle of the fixed rack is arranged at the bottom of the fixed rack; the fixed rack encloses a placement space for placing the arrow body; several card slots are arranged on the side of the adjusting plate away from the fixed rack, one side of the sliding plate is arranged in the card slots, and the other side of the sliding plate contacts the fixed rack.

[0014] Further, the arrow bodies are all made of plastic.

[0015] Further, a layer of tin foil is arranged outside the arrow body.

[0016] Further, several stabilizing plates are fixedly connected to the outside of the power cabin, and one side of the stabilizing plate is inclined.

[0017] Further, a hatch is arranged on the parachute cabin.

[0018] Further, the water storage container is a plastic water bottle, and at least one plastic water bottle is arranged in the main cabin.

[0019] Further, the fixed rack includes a fixing plate, a first fixed rack and a second fixed rack. The first fixed rack is composed of several connecting plates and a fixed cylinder. The fixed cylinder is fixedly connected to the fixing plate through the connecting plates. Several placement grooves are arranged on the fixed cylinder for placing the stabilizing plates; the second fixed rack includes several connecting rods, one end of the connecting rod is fixedly connected to the fixing plate, and the other end is fixedly connected with a limiting collar.

[0020] Further, the supporting device is a set of supporting blocks with different inclination angles.

[0021] Further, the cross section of the supporting block is a right triangle.

[0022] A method for using a solid-water integrated full-scale simulation demonstration model spacecraft includes ground debugging, launching into the air and recovering heavy objects;

[0023] Ground debugging: Fill 1 / 4 to 2 / 5 of water into the water storage container, and place the arrow body into the placement space; place the supporting block at the bottom of the fixed rack; use the sliding plate to support the inclined fixed rack, and adjust the position of the sliding plate according to different inclination angles of the fixed rack so that the sliding plate is stuck into different card slots on the adjusting plate;

[0024] Launching into the air: Connect the air pump to the air injection hole, and use the air pump to inflate and pressurize the water storage device; pull out the air pump, and the rocket takes off; after the rocket takes off, use the ignition device to ignite the solid fuel for secondary propulsion;

[0025] Heavy object recovery: After the rocket loses power, due to inertia, the return capsule with the heavy object separates from the main capsule. The second parachute opens, and the return capsule begins to decelerate. The heavy object separates from the return capsule due to inertia, and the first parachute opens.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] The rocket body includes a return capsule and a main capsule that are connected and cooperate with each other. On one side of the main capsule close to the return capsule, there is a parachute compartment, and on the other side, there is a power compartment. Inside the return capsule, there is a heavy object, and a first parachute is connected to the heavy object. Inside the parachute compartment, there is a second parachute, and the second parachute is connected to the return capsule. After the rocket is launched into the air, due to inertia, the return capsule separates from the main capsule, and then due to inertia, the heavy object separates from the return capsule. This structure enables the present invention to perform dynamic simulation and can be recycled multiple times. Through the design of the first parachute and the second parachute, it can ensure that the present invention lands safely and can be recovered after separation.

[0028] The present invention is also provided with an adjustable launch rack, which includes a fixed rack, a sliding plate, and an adjusting plate. The fixed rack can stably limit the position of the fully simulated demonstration model spacecraft integrated with solid water. By adjusting the inclination angle of the fixed rack, the launch angle can be controlled, and multi-angle and vertical launches can be conveniently carried out.

[0029] The mechanism of the present invention is reasonable, with fewer components, and it is convenient to carry and transport. Description of the Drawings

[0030] Figure 1 It is the first structural schematic diagram of the present invention;

[0031] Figure 2 It is the second structural schematic diagram of the present invention;

[0032] Figure 3 It is the internal structural schematic diagram of the present invention;

[0033] Figure 4 For Figure 3 The partial enlarged schematic diagram at point A of

[0034] Markings in the figure: 1 - return capsule, 2 - hatch, 3 - main capsule, 4 - sliding plate, 5 - card slot, 6 - adjusting plate, 7 - stabilizer plate, 8 - support block, 9 - connecting plate, 10 - fixed cylinder, 11 - connecting rod, 12 - limit collar, 13 - parachute compartment, 14 - fixing plate, 15 - water storage container, 16 - power compartment, 17 - through hole, 18 - clamping hole, 19 - partition piece. Detailed Embodiment

[0035] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts belong to the scope of protection of the present invention.

[0036] Embodiment

[0037] A fully simulated demonstration model spacecraft that integrates solid and water includes a rocket body and an adjustable launch rack for supporting the rocket body;

[0038] The rocket body includes a return capsule 1 and a main capsule 3 that are cooperatively connected. Here, the cooperative connection can adopt the way of concave-convex cooperation. The return capsule 1 and the main capsule 3 are an integral whole before launch and can be separated by inertia after launch. On one side of the main capsule 3 close to the return capsule 1, there is a parachute compartment 13, and on the other side, there is a power compartment 16; there is a load in the return capsule 1, and a first parachute is connected to the load. A second parachute is arranged in the parachute compartment 13, and the second parachute is connected to the return capsule 1; a power mechanism made of a water storage container 15 is arranged in the main capsule 3, and an air injection hole is arranged on one side of the water storage container 15 close to the power compartment 16;

[0039] During use, the water storage container 15 is pre-filled with 1 / 4 to 2 / 5 of water, and an air pump is used to pump air into the water storage container 15 through the air injection hole. As the air pump continuously pumps air, the pressure in the water storage container 15 increases. The air pump is removed, and under the action of the high pressure in the water storage container 15, the water in the water storage container 15 sprays out, and the water storage container 15 obtains power. The water storage container 15 drives the rocket body to take off. When the water in the water storage container 15 is completely sprayed out, the power disappears, and the rocket body begins to decelerate. Since there is a load in the return capsule 1 and the weight of the load is relatively heavy and the inertia is relatively large, the inertia of the return capsule 1 is greater than that of the main capsule 3. The return capsule 1 and the main capsule 3 are separated by inertia, the second parachute opens, the return capsule 1 begins to decelerate, and under the action of inertia, the load is separated from the return capsule 1, and the first parachute opens, and the load lands smoothly.

[0040] A partition piece 19 is arranged between the main capsule 3 and the power compartment 16. A through hole 17 is arranged in the middle of the partition piece 19, and a number of clamping holes 18 are arranged around the through hole 17. Solid fuel is arranged in the clamping holes 18; it should be noted that the solid fuel is solid fuel, and in this embodiment, the solid fuel is specifically KNDS rocket solid fuel made of potassium nitrate (KNO3) and glucose (DX) in a ratio of 16:60 by the hot melting method.

[0041] An ignition device is provided at the contact position between the base and the rocket. In this embodiment, the electronic ignition device specifically consists of two short-circuited metal wires, a 2200 mAh model aircraft battery, and a remote control switch to form a circuit. By controlling the remote control switch to close through the remote control device, a short circuit is instantaneously caused after the circuit is powered on to form an electric spark, thereby igniting the rocket fuel to achieve the purpose of ignition. The full-scale simulation demonstration model spacecraft that only uses air pressure as power has insufficient lift-off height. Therefore, a solid fuel is provided on the partition piece 19 to supplement the power. Additionally, it should be noted that the through hole 17 in the middle of the partition piece 19 is for the water sprayed from the bottom of the water storage container 15 to pass through. During use, when it is observed that the power of the full-scale simulation demonstration model spacecraft with integrated solid and water gradually weakens, the ignition device is controlled to ignite the solid fuel. The ejection of the solid fuel drives the rocket body to obtain secondary power, enabling the rocket body to fly higher.

[0042] The adjustable launch rack includes a fixed rack, a slide plate 4, and an adjustment plate 6. The fixed rack is placed on one side of the adjustment plate 6. A support device for supporting and adjusting the inclination angle of the fixed rack is provided at the bottom of the fixed rack. The fixed rack encloses a placement space for placing the rocket body. A number of card slots 5 are provided on the side of the adjustment plate 6 away from the fixed rack. One side of the slide plate 4 is arranged in the card slots 5, and the other side of the slide plate 4 is in contact with the fixed rack. The slide plate 4 is used to support the position of the fixed rack. To ensure that the slide plate 4 can stably support the fixed rack, the contact position between the fixed rack and the slide plate 4 should be treated with roughness to increase the roughness and prevent the slide plate 4 from sliding after contacting the fixed rack, thereby ensuring the stability of the support. Before the rocket body is launched, it is first placed in the placement space. The fixed rack will prevent the rocket body from moving randomly. By adjusting the support device, the inclination angle of the fixed rack can be controlled, that is, the launch angle of the rocket body can be controlled. When vertical launch is required, the support device is not needed. After adjusting the fixed rack, the slide plate 4 is used to support the fixed rack. Since a number of card slots 5 are provided on the adjustment plate 6, the card slots 5 can limit the slide plate 4 and at the same time facilitate the slide plate 4 to support the fixed rack according to the inclination of the fixed rack.

[0043] In a preferred embodiment, a single-chip microcomputer, a timer, an electromagnetic switch, an elastic rope, a signal wire, and a signal lamp are provided in the parachute compartment 13. In the parachute compartment 13, the signal wire is connected to the signal lamp. Before launch, the elastic rope and the parachute are folded and loaded into the hatch 2. After closing the hatch 2, the elastic rope will be stretched and fixed in the parachute compartment 13. At the same time, the parachute will also be restricted by the elastic rope. Then, the electromagnetic switch is controlled to start to lock the hatch 2.

[0044] After being launched into the air, the single-chip microcomputer receives the signal transmitted by the timer. When the time is up, the timer transmits the signal to the single-chip microcomputer, and the single-chip microcomputer controls the opening of the electromagnetic switch, thus pulling the hatch open. After the hatch 2 is opened, the taut elastic cord will immediately eject the parachute out of the parachute compartment 13, and at the same time, the parachute will unfold under the influence of the air flow. It should be noted that the timer in this embodiment can use the PCF8485 clock chip.

[0045] In a preferred embodiment, the rocket body is made of plastic. The rocket body made of plastic material is light in weight, which is convenient for the rocket body to fly higher during launch.

[0046] In a preferred embodiment, a layer of tin foil is provided outside the rocket body. Since secondary power needs to be provided by solid combustion midway, in order to prevent the rocket body and the water storage container 15 from being melted by high temperature, a layer of tin foil is provided outside the rocket body.

[0047] In a preferred embodiment, a number of stabilizer plates 7 are fixedly connected to the outside of the power compartment 16. One side of the stabilizer plate 7 is inclined. The stabilizer is used to make the fully simulated demonstration model spacecraft fly more stably after being launched into the air, and there will be no large deviation even when the fully simulated demonstration model spacecraft is vertically launched.

[0048] In a preferred embodiment, a hatch 2 is provided on the parachute compartment 13. The design of the hatch 2 on the parachute compartment 13 is to facilitate the storage and placement of the second parachute.

[0049] In a preferred embodiment, the water storage container 15 is a plastic water bottle, and at least one plastic water bottle is provided in the main compartment 3. The plastic water bottle is relatively light in weight. The overall weight of the fully simulated demonstration model spacecraft using plastic water bottles is relatively light, which can facilitate the fully simulated demonstration model spacecraft to fly higher and farther after being launched into the air, and can also ensure that the fully simulated demonstration model spacecraft flies more stably after being launched into the air.

[0050] In a preferred embodiment, the fixing frame includes a fixing plate 14, a first fixing frame and a second fixing frame. The first fixing frame is composed of a number of connecting plates 9 and fixing cylinders 10. The fixing cylinders 10 are fixedly connected to the fixing plate 14 through the connecting plates 9. A number of placement grooves are provided on the fixing cylinders 10 for placing the stabilizer plates 7; the second fixing frame includes a number of connecting rods 11. One end of the connecting rods 11 is fixedly connected to the fixing plate 14, and the other end is fixedly connected with a limiting collar 12. This structure of the fixing structure is convenient for restricting the position of the fully simulated demonstration model spacecraft. The design of the limiting groove can facilitate the placement of the stabilizer plates 7 and can also make the fully simulated demonstration model spacecraft more stable when taking off. After setting the limiting collar 12, it is convenient to align and install the simulated demonstration model spacecraft with the fixing frame, and can effectively ensure that the overall simulated demonstration model spacecraft is perpendicular to the fixing plate 14, which is convenient for adjusting the launch angle of the simulated demonstration model spacecraft.

[0051] In a preferred embodiment, the supporting device is a set of supporting blocks 8 with different inclination angles. The inclination angle of the fixing frame is adjusted by placing supporting blocks 8 with different inclination angles at the bottom of the fixing frame, so as to adjust the overall inclination angle of the fixing frame. When a simulation demonstration type model spacecraft needs to be vertically launched, the supporting blocks 8 do not need to be placed.

[0052] In a preferred embodiment, the cross-section of the supporting block 8 is a right triangle. After such a design, the inclination angle of the fixing frame can be known by checking the slope of the right triangle, which is convenient for accurately adjusting the launch angle of the simulation demonstration type model spacecraft.

[0053] A method for using an all-simulation demonstration type model spacecraft with integrated solid and water includes ground debugging, launching into the air, and recovering heavy objects.

[0054] Ground debugging: Fill 1 / 4 to 2 / 5 of water into the water storage container 15, and place the rocket body into the placement space; place the supporting block 8 at the bottom of the fixing frame; use the skateboard 4 to support the inclined fixing frame, and adjust the position of the skateboard 4 according to different inclination angles of the fixing frame, so that the skateboard 4 is stuck into different card slots 5 on the adjusting plate 6.

[0055] Launching into the air: Connect the air pump to the air injection hole, and use the air pump to inflate and pressurize the water storage device; remove the air pump, and the rocket ascends; after the rocket ascends, use the ignition device to ignite the solid fuel for secondary propulsion.

[0056] Recovering heavy objects: When the rocket loses power, due to inertia, the return capsule 1 with the heavy object separates from the main capsule 3, the second parachute opens, the return capsule 1 starts to decelerate, the heavy object separates from the return capsule 1 due to inertia, and the first parachute opens.

[0057] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "coaxial", "bottom", "one end", "top", "middle", "the other end", "upper", "one side", "top", "inner", "front", "center", "both ends", etc. is the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0058] In the present invention, unless otherwise clearly defined and limited, terms such as "installation", "setting", "connection", "fixation", "swivel connection", etc. shall be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components. Unless otherwise clearly defined, for those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0059] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A fully simulated demonstration model spacecraft with integrated solid water, characterized in that: It includes the rocket body and an adjustable launch rack for supporting the rocket body; The rocket body includes a return capsule (1) and a main capsule (3) that are cooperatively connected. On one side of the main capsule (3) close to the return capsule (1), there is a parachute compartment (13), and on the other side, there is a power compartment (16); inside the return capsule (1), there is a load-carrying object, and a first parachute is connected to the load-carrying object. Inside the parachute compartment (13), there is a second parachute, and the second parachute is connected to the return capsule (1); inside the main capsule (3), there is a power mechanism made of a water storage container (15). A gas injection hole is provided on one side of the water storage container (15) close to the power compartment (16); A partition piece (19) is provided between the main capsule (3) and the power compartment (16). A through hole (17) is provided in the middle of the partition piece (19), and several clamping holes (18) are provided around the through hole (17). A solid fuel is provided in the clamping holes (18); An ignition device is provided at the contact position between the base and the rocket; The adjustable launch rack includes a fixed rack, a sliding plate (4), and an adjusting plate (6); The fixed rack is placed on one side of the adjusting plate (6). At the bottom of the fixed rack, there is a supporting device for supporting and adjusting the inclination angle of the fixed rack; The fixed rack encloses a placement space for placing the rocket body; On the side of the adjusting plate (6) away from the fixed rack, there are several card slots (5). One side of the sliding plate (4) is arranged in the card slots (5), and the other side of the sliding plate (4) is in contact with the fixed rack.

2. The all-simulation demonstration model spacecraft with integrated solid water according to claim 1, characterized in that: The rocket body is made of plastic.

3. A fully simulated demonstration model spacecraft with integrated water fixation, characterized in that: A layer of tin foil paper is provided outside the rocket body.

4. A fully simulated demonstration model spacecraft with integrated water-solid state, characterized in that: Several stabilizing plates (7) are fixedly connected to the outside of the power compartment (16), and one side of the stabilizing plates (7) is inclined.

5. A fully simulated demonstration model spacecraft with integrated solid and water, characterized in that: A hatch (2) is provided on the parachute compartment (13).

6. A fully simulated demonstration model spacecraft with integrated water-solid state, characterized in that: The water storage container (15) is a plastic water bottle, and at least one plastic water bottle is provided in the main capsule (3).

7. The all-simulation demonstration model spacecraft with integrated water-solid state according to claim 4, characterized in that: The fixed rack includes a fixed plate (14), a first fixed rack, and a second fixed rack. The first fixed rack is composed of several connecting plates (9) and a fixed cylinder (10). The fixed cylinder (10) is fixedly connected to the fixed plate (14) through the connecting plates (9). Several placement grooves are provided on the fixed cylinder (10) for placing the stabilizing plates (7); The second fixed rack includes several connecting rods (11). One end of the connecting rods (11) is fixedly connected to the fixed plate (14), and the other end is fixedly connected with a limiting collar (12).

8. A fully simulated demonstration model spacecraft with integrated solid water, characterized in that: The supporting device is a set of supporting blocks (8) with different inclination angles.

9. The all-simulation demonstration model spacecraft with integrated water-solid state according to claim 8, characterized in that: The cross-section of the supporting block (8) is a right triangle.

10. A method for using a fully simulated demonstration model spacecraft with integrated water fixation according to any one of claims 1-9, characterized in that: It includes ground debugging, launching into the air, and recovering the heavy object; Ground debugging: Fill 1 / 4 to 2 / 5 of water into the water storage container (15), and place the rocket body into the placement space; Place the supporting block (8) at the bottom of the fixed rack; Use the sliding plate (4) to support the inclined fixed rack, and adjust the position of the sliding plate (4) according to different inclination angles of the fixed rack so that the sliding plate (4) is stuck into different card slots (5) on the adjusting plate (6); Launching into the air: Connect the air pump to the gas injection hole, and use the air pump to pump air into the water storage device to increase the pressure; Pull out the air pump, and the rocket takes off; After the rocket takes off, use the ignition device to ignite the solid fuel for secondary propulsion; Heavy object recovery: After the rocket loses power, due to inertia, the return capsule (1) carrying the heavy object separates from the main capsule (3), the second parachute opens, the return capsule (1) begins to decelerate, the heavy object separates from the return capsule (1) due to inertia, and the first parachute opens.

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