TR2021014519A2 - ROCKET, MISSILE AND SATELLITE COMPONENTS SPRING RELEASE SYSTEM - Google Patents
ROCKET, MISSILE AND SATELLITE COMPONENTS SPRING RELEASE SYSTEMInfo
- Publication number
- TR2021014519A2 TR2021014519A2 TR2021/014519A TR2021014519A TR2021014519A2 TR 2021014519 A2 TR2021014519 A2 TR 2021014519A2 TR 2021/014519 A TR2021/014519 A TR 2021/014519A TR 2021014519 A TR2021014519 A TR 2021014519A TR 2021014519 A2 TR2021014519 A2 TR 2021014519A2
- Authority
- TR
- Turkey
- Prior art keywords
- spring
- separation mechanism
- feature
- latches
- payload
- Prior art date
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 76
- 238000000926 separation method Methods 0.000 claims abstract description 52
- 230000005540 biological transmission Effects 0.000 claims abstract description 8
- 230000033001 locomotion Effects 0.000 claims description 13
- 238000000034 method Methods 0.000 claims description 9
- 241001070941 Castanea Species 0.000 claims description 3
- 235000014036 Castanea Nutrition 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 3
- 230000006378 damage Effects 0.000 description 11
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 10
- 230000001960 triggered effect Effects 0.000 description 9
- 239000003721 gunpowder Substances 0.000 description 8
- 238000012546 transfer Methods 0.000 description 6
- 229910002092 carbon dioxide Inorganic materials 0.000 description 5
- 239000001569 carbon dioxide Substances 0.000 description 5
- 238000011084 recovery Methods 0.000 description 4
- 235000015842 Hesperis Nutrition 0.000 description 3
- 235000012633 Iberis amara Nutrition 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 208000003251 Pruritus Diseases 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 230000007803 itching Effects 0.000 description 2
- 241001061260 Emmelichthys struhsakeri Species 0.000 description 1
- 241000566137 Sagittarius Species 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 230000000670 limiting effect Effects 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000001338 self-assembly Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/641—Interstage or payload connectors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Connection Of Plates (AREA)
Abstract
Buluş; bilimsel amaçlı kullanılan faydalı roket (1), faydalı füze gibi bileşen ayırma görevleri olan aracın ana yapısı olan araç gövdesi (10) ile fırlatma sonrasında ayrılacak olan faydalı yük (20), faydalı yük paraşütü (30) ve burun konisi (50) vb. bileşenleri iterek araç gövdesinden (10) tahliye edilmesini sağlayan; bahsedilen araç gövdesinin (10) en üst kısmına yerleştirilen, ayırma mekanizmasının ana gövdesini oluşturan mekanizma gövdesi (61); bahsedilen mekanizma gövdesi (61) üzerine geçirilip sıkıştırılan yay (62); bahsedilen yayın (62) boşa düşmesi için gerekli unsurlara hareket veren tahrik elemanı (66); Bahsedilen tahrik elemanının (66) takılacağı, mekanizma gövdesi (61) içine yerleştirilen bağlantı plakaları (67); bahsedilen bağlantı plakaları (67) içine yerleştirilen, yayın (62) sıkıştırıldıktan sonra sabit bir şekilde durmasını mandalların (681) takıldığı aktarma parçası (68) sahip ayırma mekanizması (60) ile ilgilidir.Meet; The vehicle body (10), which is the main structure of the vehicle, which has component separation tasks such as useful rocket (1) used for scientific purposes, useful missile, and the payload (20), payload parachute (30) and nose cone (50) etc. to be separated after launch. allowing the components to be evacuated from the vehicle body (10) by pushing; the mechanism body (61), which is placed on the topmost part of said vehicle body (10), forming the main body of the separation mechanism; spring (62) which is inserted and compressed on said mechanism body (61); the actuating element (66) that moves the elements necessary for said spring (62) to fall into disrepair; Connection plates (67) placed inside the mechanism body (61) to which said drive element (66) will be attached; it relates to the separating mechanism (60) which has a transmission part (68) placed in said connection plates (67), to which the latches (681) are attached so that the spring (62) stays stationary after being compressed.
Description
TARIFNAME ROKET, FUZE VE UYDU BILESENLERI YAYLI TAHLIYE SISTEMI Teknik Alan Bulus; genelde faydali (bilimsel amaçli) roket, füze gibi belirli bir göreve tabi hava araçlarinin, görevlerini yerine getirmesini ve görevi yerine getirdikten sonra yeryüzüne zarar görmeden inmesini saglayan ayirma sistemi ile ilgilidir. DESCRIPTION ROCKET, FUZE AND SATELLITE COMPONENTS SPRING RELEASE SYSTEM Technical Area Meet; generally useful (scientific) aircraft, such as rockets, missiles, which are subject to a specific mission, fulfill their duties and without harming the earth after fulfilling the task. It is related to the separation system that allows it to descend.
Bulus özellikle; gelistirilen yayli mekanizma sayesinde komut verildigi anda ateslemeye gerek kalmadan ayirma islemini baslatan bu sayede hasarsiz ve emniyetli sekilde görevini yerine getiren ayirma sistemi ile ilgilidir. The invention especially; Thanks to the developed spring mechanism, there is no need to fire when the command is given. which starts the separation process without any damage and thus performs its duty safely and without damage. related to the separation system.
Mevcut Teknik Günümüzde faydali (bilimsel amaçli) roket, füze gibi belirli bir göreve tabi hava araçlarinin, istenilen anda faydali yük birakma görevinin yerine getirilmesini saglayarak sonrasinda sistemin kullanildigi aracin tekrar kullanilabilir bir halde yeryüzüne inmesini saglayan ayirma ve kurtarma sistemleri kullanilmaktadir. Bahsedilen faydali yük uydu, meteorolojik ölçüm cihazlari, deney düzenekleri, rover vb. araçlardir. Current Technique Today, useful (scientific) aircraft such as rockets and missiles, which are subject to a specific mission, by ensuring that the duty of leaving a useful load at the desired moment is fulfilled, and then the system separation and rescue, which allows the vehicle in which it is used to descend to the earth in a reusable state systems are used. The aforementioned payload satellite, meteorological measuring devices, experiment assemblies, rover etc. are tools.
Ayirma sistemi olarak günümüzde barutlu kurtarma sistemi, karbondioksit tüplü kurtarma sistemi ve elektrikli dogrusal aktüatör gibi sistemler kullanilmaktadir. Today, as a separation system, gunpowder recovery system, carbon dioxide tube recovery system and systems such as electric linear actuator are used.
Barutlu kurtarma sistemi: Burada kullanilan barut, ayirma esnasinda araç gövdesine ve aracin alt sistemlerine zarar verebilmektedir. Barut parlayici oldugundan kontrolsüz bir sekilde tetiklenebilir ve uçus esnasinda istenmeyen bir zamanda tetiklenirse projenin basarisiz olmasina sebebiyet verebilmektedir. Yine uçus öncesinde istenmeyen bir anda tetiklenmesi durumunda büyük hasarlar dogurarak, yaralanmalara neden olabilmektedir. Gunpowder recovery system: The gunpowder used here does not damage the vehicle body and subsystems of the vehicle during separation. can give. Since gunpowder is flammable, it can be triggered uncontrollably and during flight If it is triggered at an undesirable time, it may cause the project to fail. Again in case of triggering an undesired moment before the flight, causing great damage, may cause injuries.
Karbondioksit tüplü ayirma sistemleri: Burada kullanilan tüp içerisindeki basinçli gaz salinarak ayrilma gerçeklesmektedir. Bu gaz yüksek basinçlidir ve yaklasik (-25C)'ye ulastigi için aracin gövdesine ve alt sistemlerine zarar vermektedir. Karbondioksit tüplü ayirmada, sistem aktivasyonu tüpün membraninin delinmesi yoluyla gerçeklesir. Delme islemi igne çarptirilarak saglanir. Igne çarptirmanin yollarindan biri de baruttur ve barutun kullanildigi durumlarda yukarida bahsedilen dezavantajlar yine görülebilmektedir. Bu sistemde toplamda yaklasik 250 ms gecikme yasanmaktadir. Carbon dioxide tube separation systems: The separation takes place by releasing the pressurized gas in the tube used here. This gas is high It is pressurized and as it reaches approximately (-25C), it will damage the body and subsystems of the vehicle. gives. In carbon dioxide tube separation, system activation perforation of the tube membrane occurs through. Drilling is achieved by striking the needle. One of the ways to get a needle It is gunpowder and the disadvantages mentioned above are still in use when gunpowder is used. can be seen. A total delay of approximately 250 ms is experienced in this system.
Elektriksel dogrusal aktüatör sistemleri: 0 Bu sistemde ayirma mekanizmasi çok yavas hareket ettiginden istenilen yükseklikte verilen elektriksel tetikleme ne kadar dogru zamanda olsa bile roket serbest düsüse geçer ve hizi parasüt çikana kadar artar. Böylelikle parasütler açilirken olusacak sok çok fazla artmis olur ve hem görev hem de kurtarma isleminin basarisiz olma ihtimali yükselir. Electrical linear actuator systems: 0 Since the separation mechanism moves very slowly in this system, no matter how accurate the electrical trigger is, the rocket will free fall and its speed will increases until the parachute comes out. In this way, the shock that will occur when the parachutes are opened will increase too much. and the probability that both the mission and the recovery process will fail increases.
- Bahsedilen elektriksel dogrusal aktüatör gecikmesi toplamda yaklasik 3200 ms kadardir. Bu gecikme (uçus bilgisayarinin tetiklemesinden parasütün açilmasina kadar geçen süre) oldukça fazladir. Bu nedenle erken tetiklenmesi gerekmektedir. 0 Araç hizli iken aracin karsiladigi hava basinci çok fazla olur, bu da aktüatörün uyguladigi kuvvetin yetersiz gelmesine ve aktüatörün çok fazla akim çekmesine neden olmaktadir.- Said electrical linear actuator delay is approximately 3200 ms in total. This delay (time from triggering the flight computer to opening the parachute) it is quite a lot. Therefore, it needs to be triggered early. 0 When the vehicle is fast, the air pressure that the vehicle meets is too high, which means that the actuator It causes insufficient force and the actuator draws too much current.
Bunun üzerine aktüatör yavas çalistigi için daha çok enerji harcar ve bu da araçta kullanilan bataryanin büyük olmasini gerektirir. Aktüatörün kendisi de agir oldugu için agirlik yönünde de dezavantaj olusur. On top of that, the actuator consumes more energy because it works slowly, and this results in the usage of the vehicle. Requires large battery. Since the actuator itself is heavy, in the weight direction also a disadvantage.
Onceki teknikte mekanizmanin kullanilabilecegi araçlarda görevin gerçeklesebilmesi ve ayirmanin saglanabilmesi için kurtarma sisteminin ayrilacak bilesene belirli bir itici kuvvet uygulamasi gerekmektedir. Mevcut sistemlerin bazilari bu itici kuvveti emniyetsiz metotlar gözeterek gerçeklestirmekte ve tehlikeli olarak çalismaktadir. In the vehicles where the mechanism can be used in the previous technique, the task can be realized and the separation A certain driving force must be applied to the component to be separated from the rescue system in order to ensure required. Some of the existing systems use this impetus by considering unsafe methods. performs and operates dangerously.
Teknigin bilinen durumunda kullanilan kurtarma sistemleri uçus esnasinda istenmeyen bir zamanda tetiklenirse projenin basarisiz olmasina sebebiyet verebilir, uçus öncesinde istenmeyen bir anda tetiklenir ise büyük hasarlar dogurabilir, yaralanmalara neden olabilir. Rescue systems used in the state of the art may cause an undesired event during the flight. If it is triggered at the same time, it may cause the project to fail, undesired before the flight. If it is triggered suddenly, it can cause great damage and cause injuries.
Teknigin bilinen durumunda kullanilan barutlu ve karbondioksit tüplü ayirma sistemlerinde ortaya çikan basinç bulundugu ortamda her yöne kuvvet uygular. Bu da aracin alt sistemlerine dogrudan zarar verebilir ve öngörülemeyen problemlere neden olabilir. It occurs in the separation systems with gunpowder and carbon dioxide tube used in the state of the art. The resulting pressure exerts force in all directions in its environment. This is directly into the subsystems of the vehicle. damage and cause unforeseen problems.
Teknigin bilinen durumunda karbondioksit tüpü ve barut kullanilan ayirma sistemlerinde basinçli gaz ile ayrilma gerçeklesir. Bu gaz çok soguk (~-25°C) veya çok sicak ve yüksek basinçli oldu gu için aracin alt sistemlerinde beklenmedik problemlere yol açabilir. In the state of the art, pressurized separation systems using carbon dioxide tube and gunpowder gas separation takes place. This gas may be too cold (~-25°C) or too hot and high pressure. may cause unexpected problems in the vehicle's subsystems.
Teknigin bilinen durumunda elektrikli dogrusal aktüatörler emniyetlidir fakat çok yavas çalistigi için görevini saglikli bir sekilde yerine getiremez. Ayni zamanda uzun süre akim çektigi için diger sistemlerin ihtiyaci olan enerjiyi harcayabilir. In the state of the art, electric linear actuators are safe but because they work very slowly. unable to carry out its duties in a healthy way. At the same time, since it draws current for a long time, other can spend the energy needed by the systems.
Literatürde yapilan arastirmalar neticesinde bahsedilen füze ayirma sistemleri ile ilgili çesitli yapilanmalar karsimiza çikmaktadir. Bunlardan biri “Füzenin en az bir çikarilabilir bölümünün, özellikle bir kaplamasinin firlatilmasina yönelik çalistirma cihazi" baslikli, 2020/02981 basvuru numarali patenttir. Tasnif sinifi F4ZB 15/34 olan bulusun özetinde “Füzenin en az bir çikarilabilir bölümünün, özellikle bir kaplamasinin firlatilmasina yönelik çalistirma cihazi. - Cihaz, bir asiri basinç üretmeye uygun olan bir piroteknik yük içeren bir piroteknik çalistirici ve pistonun uçlarindan biri füzenin çikarilabilir bölümü, en az bir tutma pimi ve en azindan piroteknik yükü isil olarak yalitacak sekilde düzenlenen en az bir isi yalitim elemani üzerinde etki edebilecek biçimde boylamsal bir yönde yer degistirmek üzere yapilandirilan bir piston içeren tek parça bir düzenektir. piroteknik çalistirici, en az bir tutma pimini kirmaya uygun olan bir kuvvetin üretilebilmesi için yapilandirilmaktadir; burada en az bir tutma piminin birinci ucu ve piroteknik çalistiricinin bir ucu, füzenin bir sabitleme elemani üzerine sabitlenmek üzere tasarlanmaktadir ve en az bir tutma piminin birinci uca karsit olan bir ikinci ucu ise füzenin çikarilabilir bölümünün bir sabitleme elemanina sabitlenmek üzere tasarlanmaktadir.” ifadesi yer almaktadir. As a result of the researches in the literature, there are various types of missile separation systems mentioned. configurations appear. One of them is “At least one removable part of the missile, 2020/02981 application, entitled "operating device specifically for the launch of a coating" Patent No. In the summary of the invention, the classification class is F4ZB 15/34, “At least one of the missiles is removable actuating device for launching part, especially a coating. - The device is an overload a pyrotechnic actuator containing a pyrotechnic charge suitable for generating pressure and the removable portion of the missile, at least one retaining pin and at least the pyrotechnic charge in such a way as to act on at least one thermal insulation element arranged to insulate It is a one-piece assembly comprising a piston configured to displace in a longitudinal direction. The pyrotechnic actuator is designed to produce a force suitable for breaking at least one retaining pin. being configured; wherein the first end of the at least one retaining pin and one end of the pyrotechnic actuator, it is designed to be fixed on a fixing member of the missile and has at least one holding a second end of the pin, opposing the first end, is a fixing of the removable portion of the missile. It is designed to be fixed to the element.” statement is included.
Bahsedilen basvuruda firlatma islemi için basinçli sistem kullanilmaktadir. Dolayisiyla bu basvuru yukarida bahsedilen bazi dezavantajlara örnek olarak gösterilebilir. In the aforementioned application, a pressurized system is used for the launching process. Therefore, this reference can be cited as an example of some of the disadvantages mentioned above.
Sonuç olarak; füze ayirma sisteminde gelisen teknolojiye paralel olarak gelistirmelere gidilmekte, bu nedenle yukarida deginilen dezavantajlari ortadan kaldiracak ve mevcut sistemlere çözüm getirecek yeni yapilanmalara ihtiyaç duyulmaktadir. In conclusion; Developments are being made in parallel with the developing technology in the missile separation system, For this reason, it will eliminate the disadvantages mentioned above and provide solutions to existing systems. new structures are needed.
Bulusun Amaci Bulus, mevcut teknikte kullanilan yapilanmalardan farkli olarak, bahsedilen dezavantajlari çözmeye yönelik gelistirilen ve ilave bazi avantajlar getiren füze ayirma sistemi ile ilgilidir. Purpose of the Invention Unlike the embodiments used in the current art, the invention tries to solve the mentioned disadvantages. It is related to the missile separation system that has been developed for the purpose and brings some additional advantages.
Bulusun amaci; faydali bilimsel füzelerde firlatma sonrasinda faydali bölümlerin yayli mekanizma ile gecikme olmaksizin itilerek firlatilmasini saglamaktir. The purpose of the invention; spring mechanism of useful parts after launch in useful scientific missiles It is to ensure that it is thrown by pushing without delay.
Bulusun bir diger amaci; gelistirilen yayli mekanizma sayesinde parlayici ve patlayici madde kullanilmadigindan kontrollü bir sekilde tetiklenmeyi saglamaktir. Another purpose of the invention; Thanks to the spring mechanism developed, combustible and explosive substances It is to ensure that it is triggered in a controlled manner since it is not used.
Bulusun bir diger amaci; itme islemi için dogrusal bir kuvvet uygulayarak, bu uygulanan kuvvetin sadece ayirma sisteminin gövdeye bagli oldugu civatalar ve itmesi gereken bilesenler arasinda uygulanmasini saglamaktir. Bu sayede olusan itme kuvveti diger sistemlere zarar vermez ve ön görülemeyen problemlerle karsilasilma ihtimalini minimuma indirir. Another purpose of the invention; By applying a linear force to the pushing action, this applied force only between the bolts with which the release system is attached to the body and the components that must be pushed. to ensure its implementation. In this way, the thrust force does not damage other systems and It minimizes the possibility of encountering unseen problems.
Bulusun bir diger amaci; itme kuvveti için kullanilan gaz salinimi ihtiyacini ortadan kaldirarak yüksek isidan dolayi aracin altinda olusan zararlari ortadan kaldirmaktir. Another purpose of the invention; eliminating the need for gas release used for propulsion It is to eliminate the damages that occur under the vehicle due to high heat.
Bulusun bir diger amaci; büyük boyutlu batarya ihtiyacinin ortadan kaldirilmasini saglamaktir. Bu sayede hem kurulum maliyeti azaltilmakta hem de araç agirligi olumsuz olarak etkilenmemektedir. Another purpose of the invention; to eliminate the need for large-sized batteries. This In this way, both the installation cost is reduced and the vehicle weight is not adversely affected.
Bulusun yapisal karakteristik özellikleri ve tüm avantajlari asagida verilen sekiller ve bu sekillere atiflar yapilmak suretiyle yazilan detayli açiklama sayesinde daha net olarak anlasilacaktir. Bu nedenle degerlendirmenin de bu sekiller ve detayli açiklama göz önüne alinarak yapilmasi gerekmektedir.Structural characteristics and all advantages of the invention are given in the following figures and these figures. It will be understood more clearly thanks to the detailed explanation written with references. This For this reason, the evaluation should be made by considering these figures and detailed explanation. required.
Bulusun Anlasilmasina Yardimci Olacak Sekillerin Kisaca Açiklanmasi Sekil- 1; Bulus konusu ayirma mekanizmasinin kullanildigi faydali roketin iki boyutlu görünümünü göstermektedir. Brief Description of Figures to Help Understand the Invention Figure 1; Two-dimensional view of the utility rocket in which the separation mechanism of the invention is used. shows.
Sekil - 2; Bulus konusu ayirma mekanizmasinin patlatilmis halinin perspektif görünümünü göstermektedir. Figure - 2; Perspective view of the exploded state of the separation mechanism of the invention. shows.
Sekil- 3; Bulus konusu ayirma mekanizmasinin yari montaj edilmis halinin perspektif sematik görünümünü göstermektedir.Figure-3; Perspective schematic of the semi-assembled version of the inventive separation mechanism shows the view.
Sekil- 4; Bulus konusu ayirma mekanizmasinin monte edilmis halinin perspektif görünümünü göstermektedir. Figure- 4; Perspective view of the inventive separation mechanism assembled shows.
Sekil - 5; Mekanizma gövdesinin içine yerlestirilen baglanti plakalari ve diger unsurlarin monte edilmis halinin perspektif görünümünü göstermektedir.Figure - 5; Mounting plates and other elements placed inside the mechanism body It shows the perspective view of its state.
Referans Numaralari 1. Faydali roket . Araç gövdesi . Faydali yük . Faydali yük parasütü 40. Araç parasütü 50. Burun konisi 60. Ayirma mekanizmasi 61. Mekanizma gövdesi 611. Mandal delikleri 62. Yay 63. Itici 64. Hareketli yüzük 65. Merkezleme yüzügü 66. Tahrik elemani 661. Sönümleyici 662. Tahrik elemani halkasi 67. Baglanti plakalari 671. Mil yataklama elemani 672. Plaka ayaklari 673. Kestamit parça 674. Döndürme mili 68. Aktarma parçasi 681. Mandallar 69. Yönlendirici Bulusun Bir Drneginin Detayli Olarak Açiklanmasi Bu detayli açiklamada, bulus konusu ayirma mekanizmasinin (60) tercih edilen yapilanmalari, sadece konunun daha iyi anlasilmasina yönelik olarak ve hiçbir sinirlayici etki olusturulmayacak sekilde açiklanmaktadir. Reference Numbers 1. Utility rocket . vehicle body . Useful load . payload parachute 40. Vehicle parachute 50. Nose cone 60. Separation mechanism 61. Mechanism body 611. Latch holes 62. Sagittarius 63. Pusher 64. Moving ring 65. Centering ring 66. Drive element 661. Damper 662. Driver ring 67. Connection plates 671. Shaft bearing element 672. Plate feet 673. Chestnut piece 674. Spindle shaft 68. Transfer part 681. Latches 69. Router A Detailed Description of an Example of the Invention In this detailed description, preferred embodiments of the inventive separation mechanism (60), only for a better understanding of the subject and no limiting effect will be created is explained in the following.
Yapi prensibi'i Bilimsel amaçli kullanilan faydali roketler (1), araç gövdesi (10), faydali yük (20), faydali yük parasütü (30), araç parasütü (40), burun konisi (50) ve bulus konusu ayirma mekanizmasindan (60) olusmaktadir. Sekil 1 faydali roketin (1) iki boyutlu görümünü göstermektedir. construction principle Useful rockets used for scientific purposes (1), vehicle body (10), payload (20), payload parachute (30), vehicle parachute (40), nose cone (50) and separation mechanism of the invention. (60) is formed. Figure 1 shows the two-dimensional view of the utility rocket (1).
Bahsedilen ayirma mekanizmasi (60), atesleme sonrasi gökyüzüne firlatilan faydali roketi (1) olusturan üst bilesenlerin araç gövdesinden (10) tahliye edilmesini saglamaktadir. Said separation mechanism (60) is the useful rocket that is launched into the sky after ignition (1). It ensures that the upper components forming it are evacuated from the vehicle body (10).
Söz konusu ayirma mekanizmasi (60), mekanizma gövdesi (61), yay (62), itici (63), hareketli yüzük yönlendirici (69) ana unsurlarindan olusmaktadir. Sekil 2 ayirma mekanizmasinin (60) demonte edilmis halinin perspektif görünümünü göstermektedir. Said separation mechanism (60), mechanism body (61), spring (62), pusher (63), movable ring router (69) consists of main elements. Figure 2 disassembly of the separation mechanism (60) It shows the perspective view of its state.
Bahsedilen mekanizma gövdesi (61), mekanizmayi olusturan elemanlari üzerinde ya da içerisinde bulunduran ve yayin (62) yataklanmasini saglayan unsurdur. Yay (62) ise mekanizma gövdesi (61) üzerine geçirilerek sikistirilan, sikistirilmis haldeyken barindirdigi enerjinin serbest birakilmasi ile tahliye edilecek bilesenleri itmesi için gerekli kuvvetin uygulanmasini saglayan elemandir. Burada yay (62) yerine pistonlu bir yapi kullanilarak itme kuvveti olusturulabilir. Said mechanism body (61) is on or inside the elements that make up the mechanism. It is the element that contains the spring (62) and provides the bearing. If the spring (62) is the mechanism body (61) with the release of the energy it contains while being compressed, which is compressed by passing it on. It is the element that provides the application of the necessary force to push the components to be discharged. Here The thrust can be generated by using a reciprocating structure instead of the spring (62).
Yayin (62) üzerine konumlandirilan itici (63), tahliye olmasi gereken bilesenlerin yayin (62) içinde hapsolmasini engelleyen ve bu bilesenleri itmeyi saglayan parçadir. Yay (62) ile itici (63) arasinda hareketli yüzük (64) konumlandirilir. Hareketli yüzük (64) yayin (62) itmesi gereken bilesenleri güzel bir sekilde kavrar ve yayin (62) kuvvetinin bu bilesenlere sorunsuz bir sekilde aktarilmasini saglar. Hareketli yüzük (64) ayrica yayin (62) önüne engel olan mandallarin (681) isini saglikli bir sekilde yapmasina yardimci olur. The pusher (63) positioned on the spring (62) is inside the spring (62) of the components that need to be evacuated. It is the part that prevents it from being trapped and allows to push these components. Between spring (62) and pusher (63) the movable ring (64) is positioned. The moving ring (64) spring (62) must push the components. It grips nicely and ensures that the force of the spring (62) is transferred to these components smoothly. it provides. The movable ring (64) also keeps the work of the latches (681) blocking the spring (62) in a healthy way. it will help you to do it.
Bahsedilen merkezleme yüzügü (65), mekanizma gövdesinin (61) araç gövdesine (10) saglam bir sekilde baglanmasini saglayan elemandir. Said centering ring (65) is a solid fit of the mechanism body (61) to the vehicle body (10). It is the element that allows it to be connected in a way.
Tahrik elemani (66), tetiklenme gerçeklestigi taktirde döndürme milini (674) çevirerek mandallarin (681) yayin (62) önünden çekilmesine neden olarak mekanizmanin aktive edilmesini saglayan elemandir. Tahrik elemani (66) olarak servomotor kullanilacaktir. Tahrik elemaninin (66) üstüne sönümleyici (661) yerlestirilir ve orta kisimdan döndürme miline (674) baglanir. Tahrik elemaninin (66) üst kisminda bulunan tahrik elemani halkasi (662) ise plaka ayaklarina (672) takilarak baglanti plakalarina (67) montaji saglanir. Sönümleyici (661), tahrik elemani (66) montajinin kusurlu olmasi durumunda kasinti olusmasini engeller. Titresimin tahrik elemanina (66) zarar vermesini engeller. The drive element (66) turns the pivot shaft (674) to close the latches if triggered. (681) spring (62), which causes the mechanism to be activated by causing it to be pulled in front of it. element. Servomotor will be used as the drive element (66). On top of drive element (66) The damper (661) is placed and connected to the rotation shaft (674) from the middle part. of the drive element The drive element ring (662) on the upper part of (66) is attached to the plate feet (672) and the connection is made. plates (67) are provided. Faulty mounting of damper (661), driver (66) It prevents itching in case of itching. It prevents vibration from damaging the drive element (66).
Tahrik elemanindaki (66) titresimin de mekanizmaya aktarilmasini engeller. It also prevents the vibration in the drive element (66) from being transferred to the mechanism.
Mekanizmadaki bilesenlerin mekanizma gövdesine (61) baglanmasi için baglanti plakalari (67) kullanilir. Baglanti plakalarinin (67) orta kisminda mil yataklama elemani (671) yer alir. Mil yataklama elemani (671), döndürme milinin (674) baglanti plakalarina (67) yataklanmasini saglar ve dönme için gerekli kuvvetin minimum düzeye indirgenmesini saglar. Mil yataklama elemani (671) olarak flansli rulman kullanilmaktadir. Connection plates (67) for connecting the components in the mechanism to the mechanism body (61) used. A shaft bearing element (671) is located in the middle of the connection plates (67). Shaft the bearing element (671) enables the pivoting shaft (674) to be guided to the mounting plates (67) and ensures that the force required for rotation is reduced to a minimum. Shaft bearing element As (671) flanged bearing is used.
Bahsedilen baglanti plakalarinin (67) birbirlerine istenilen mesafede konumlandirilmasini saglamak amaciyla plaka ayaklari (672) kullanilir. Plaka ayagi (672) olarak gijon mili tercih edilmistir. To ensure that the mentioned connection plates (67) are positioned at the desired distance from each other. Plate feet (672) are used for this purpose. As the plate foot (672), the shank is preferred.
Yukarida bahsedilen tahrik elemani (66) döndürüldügünde burada olusan dönme hareketini diger elemanlara aktarmak için döndürme mil (674) kullanilir. When the above-mentioned drive element (66) is rotated, the rotational movement that occurs here is transferred to the other. The rotating spindle 674 is used to transfer it to the elements.
Aktarma parçasi (68), döndürme milinin (674) dönme hareketini mandallara (681) dogrusal olacak sekilde aktaran elemanlardir. Mandallar (681) ise sikistirilmis haldeki yayin önündeki engellerdir.The drive member 68 will make the rotational movement of the pivot shaft 674 linear to the latches 681. are transferring elements. The latches (681), on the other hand, are barriers to the compressed spring.
Mekanizma tetiklendiginde tahrik elemani (66) yardimiyla yayin (62) önünden çekilir ve yayi (62) serbest birakarak sistemi aktive eder.When the mechanism is triggered, the spring (62) is pulled in front of the spring (62) by means of the drive element (66). It activates the system by releasing it.
Mandallarin (681) hemen üzerinde mekanizma gövdesinin (61) içerisinde kestamit parça (673) konumlandirilir. Sürtünme katsayisi çok düsük oldugu için mandallarin (681) hareket ettirilmesini büyük ölçüde kolaylastirir. Sekil 5'de görülmektedir. Chestnut piece (673) inside the mechanism body (61) just above the latches (681) is positioned. It is necessary to move the latches (681) because the friction coefficient is too low. greatly facilitated. It is seen in Figure 5.
Son unsur olan yönlendirici (69) sistem kurulumu yapilirken mandallari (681) yayin (62) önüne engel olacak sekilde yönlendiren elemandir. The last element, the router (69), latches (681) in front of the spring (62) while the system is being set up. It is the element that directs it in a way that will prevent it.
Bulus konusu ayirma mekanizmasi (60) sekil 1*de görüldügü üzere araç gövdesinin (10) en üst kismina monte edilmektedir. Ayirma mekanizmasi (60) üzerine sirasiyla faydali yük (20), faydali yük parasütü (30), araç parasütü (40), burun konisi (50) monte edilecektir. As seen in Figure 1, the separation mechanism (60) which is the subject of the invention is at the top of the vehicle body (10). part is mounted. The useful load (20), the useful load on the release mechanism (60), respectively. cargo parachute (30), vehicle parachute (40), nose cone (50) will be mounted.
Ayirma mekanizmasi (60) montaii: Sekil 2ide demonte edilmis hali görülen ayirma mekanizmasinin (60) montaji için öncelikle aktarma parçasi (68) baglanti plakalari (67) arasina yerlestirilir. Yönlendirici (69) plaka ayaklarindan (672) geçirilerek baglanti plakalarina (67) ve aktarma parçasina (68) irtibatlandirilir. Sonrasinda tahrik elemani (66) baglanti plakalarinin (67) alt kismina gelecek sekilde yerlestirilir ve sönümleyici (661) döndürme miline (674) geçirilir. Tahrik elemani halkasi (662) plaka ayaklarina (672) takilarak sabitlendirilir. Ortaya çikan bu yapi sekil 5'de perspektif olarak gösterilmektedir. Bu yapi mekanizma gövdesi (61) içine yerlestirilir. Bu yerlestirme gerçeklestirildiginde mandallar (681), mekanizma gövdesi (61) üst kisminda formlandirilan mandal deliklerine (611) girer. Sekil 3 baglanti plakalarinin (67) mekanizma gövdesi (61) içine yerlestirilmis halini ve yayin (62) mekanizma gövdesi (61) üzerine geçirilip bastirilmamis halini göstermektedir. Burada mandallarin (681) mandal deliklerinden (611) çikmasi net olarak görülmektedir. Release mechanism (60) mounted: For the assembly of the separation mechanism (60), which is seen disassembled in Figure 2, first of all, the transfer part (68) is placed between the connection plates (67). Router (69) from plate feet (672) It is connected to the connection plates (67) and the transmission part (68) by passing it through. propulsion after element (66) is placed under the connecting plates (67) and the damper (661) is threaded onto the rotation shaft 674. The driver ring (662) is attached to the plate feet (672). is fixed. This resulting structure is shown in perspective in Figure 5. this structure It is placed inside the mechanism body (61). When this insertion is performed, the latches (681) The mechanism body (61) enters the latch holes (611) formed on its upper part. Figure 3 the connection plates (67) placed in the mechanism body (61) and the spring (62) shows the mechanism body (61) in its unpressed state. Here are your pegs (681) coming out of the latch holes (611) is clearly seen.
Mekanizma gövdesinin (61) alt kismina merkezleme yüzügü (65) takilir. Sonrasinda mekanizma gövdesi (61) üzerine yay (62) geçirilir. Yay (62) üstten hareketli yüzük (64) vasitasiyla bastirilip sikistirilir ve üzerine itici (63) yerlestirilir. Hareketli yüzük (64) mandal deliklerinin (611) hizasinin altina indiginde sistem aktif edilerek mandallarin (681) disari çikmasi saglanir. Bu sayede hareketli yüzük (64) bu seviyede sabit kalarak yayin (62) sikistirilmis sekilde sabit kalmasini saglar. A centering ring (65) is attached to the lower part of the mechanism body (61). mechanism after spring (62) is passed on its body (61). The spring (62) is pressed by the top acting ring (64). It is compressed and a pusher (63) is placed on it. Align the movable ring (64) latch holes (611). When it goes under, the system is activated and the latches (681) come out. In this way, mobile the ring (64) remains fixed at this level, ensuring that the spring (62) remains compressed and fixed.
Bahsedilen merkezleme yüzügü (65) ile ayirma mekanizmasi (60) araç gövdesine (10) monte edilerek ayirma mekanizmasinin (60) montaj islemi tamamlanir. Sekil 4=de kendi içinde montaji tamamlanan ayirma mekanizmasinin (60) perspektif görünümünü göstermektedir. Sonrasinda yukarida bahsedildigi gibi faydali yük (20), faydali yük parasütü (30), araç parasütü (40) ve burun konisi (50) üst üste monte edilerek faydali roketin (1) montaji tamamlanmis olur. Sekil 1'de montaji tamamlanan faydali roketin (1) iki boyutlu görünümü gösterilmektedir. Çalisma prensibi; Ayirma mekanizmasinin (60) kullanilabilecegi araçlarda görevin gerçeklesebilmesi ve tahliyenin saglanabilmesi için ayirma mekanizmasinin (60) ayrilacak bilesenlere belirli bir itici kuvvet uygulamasi gerekmektedir. Bu itici kuvvet bu bulusta yaya (62) depolanmis olan potansiyel enerjinin salinimiyla gerçeklesmektedir. The said centering ring (65) and the separation mechanism (60) are mounted on the vehicle body (10). The assembly process of the separation mechanism (60) is completed. Figure 4 = self-assembly shows a perspective view of the completed separation mechanism (60). After that As mentioned above, payload (20), payload parachute (30), vehicle parachute (40) and nose The cone (50) is mounted one above the other and the assembly of the useful rocket (1) is completed. Installation in Figure 1 The two-dimensional view of the completed utility rocket (1) is shown. Working principle; In vehicles where the separation mechanism (60) can be used, the task can be accomplished and the evacuation In order to ensure that the separation mechanism (60), a certain driving force is applied to the components to be separated. application is required. This driving force is the potential stored in the spring 62 in this invention. realized by the release of energy.
Yukarida montaj isleminde anlatildigi gibi ayirma mekanizmasi (60) kurulurken yay (62) mekanizma gövdesine (61) etrafina geçirilerek asagida dogru bastirilip sikistirilir ve üzerine hareketli yüzük (64) konumlandirilir. Sonrasinda kurulum devresinden tahrik elemanina (66) sinyal gönderilir. Bu sinyal ile dönen tahrik elemani (66) dönme hareketini sönümleyiciye (661) aktarir.As the release mechanism (60) is installed, as described in the assembly procedure above, the spring (62) It is passed around the mechanism body (61) and is pressed downwards and tightened on it. the movable ring (64) is positioned. Then the signal from the setup circuit to the driver (66) sent. With this signal, the rotating drive element (66) transfers its rotational motion to the damper (661).
Sönümleyici de (661) tahrik elemanindan (66) gelen dönme hareketini döndürme miline (674) aktaracaktir. Sonrasinda döndürme mili (674) dönme hareketini aktarma parçasina (68) iletir.In the damper (661), the rotational movement coming from the drive element (66) is transferred to the rotation shaft (674). will transfer. Afterwards, the rotation shaft (674) transmits the rotational movement to the transmission part (68).
Aktarma parçasi (68) bu dönme hareketini dogrusal harekete dönüstürerek mandallarin (681) mekanizma gövdesi (61) üzerinde formlandirilan mandal deliklerinden (611) disina çikmasini saglar. Dolayisiyla hareketli yüzügün (64) önünde engel olusturarak yayin (62) sikismis halde kalmasini saglar. Bu islemler ile kurulan ayirma mekanizmasi (60) faydali roketin (1) görevini tamamlayabilecek sekilde firlatilmaya müsait hale getirilmesini saglar. The transmission part (68) converts this rotational motion into linear motion, thereby ensuring that the latches (681) protruding from the latch holes (611) formed on the mechanism body (61). it provides. Therefore, the spring (62) is stuck, creating an obstacle in front of the movable ring (64). lets it stay. The separation mechanism (60) established with these processes performs the task of the useful rocket (1). It ensures that it is made available for launch in such a way that it can be completed.
Ayirma mekanizmasinda (60) bulunan mandallar (681) 120 derecelik açi araliklari verilmis sekilde simetrik olarak konumlandirilmistir. Bu konumlandirmanin sebebi, yayda (62) depolanan enerjinin salinimi gerçeklestiginde yayin (62) dengeli bir sekilde açilmasini saglamak ve takilmalarin önüne geçmektir. Latches (681) on the release mechanism (60) with 120 degree angle ranges is positioned symmetrically. The reason for this positioning is that the energy stored in the spring 62 is to ensure that the spring (62) opens in a balanced way when it oscillates and to prevent snags. is to pass.
Faydali roket (1) firlatildiktan sonra aracin gövdesine (10) monte edilen mekanizma, ihtiyaç duyulan zamanda tetiklenir. Tetiklenme vesilesiyle tahrik elemani (66) döner. Tahrik elemani (66) dönme hareketi sönümleyiciye (661), oradan da döndürme miline (674) aktarilir. Ayni sekilde döndürme mili (674) dönme hareketini aktarma parçasina (68) iletir. Aktarma parçasi (68) bu dönme hareketini dogrusal harekete dönüstürerek mandallarin (681) mekanizma gövdesi (61) içerisine çekilmesini saglar. Mandallar (681) mandal deliklerinden (611) içeri girdiginde hareketli yüzügünün (64) önündeki engel ortadan kalkmis olur. Sonrasinda ise sikismis olan yay (62) serbest kalir. Yayda (62) depolanan enerjinin açiga çikmasiyla yaydan (62) gelen kuvvet, mekanizmadaki hareketli yüzük (64) vasitasiyla iticiye (63), itici (63) vasitasiyla da ayrilma için kuvvet uygulanmasi gereken bilesenlere iletilerek bahsi geçen bilesenleri tahliye eder. The mechanism mounted on the body (10) of the vehicle after the utility rocket (1) is launched, triggered at the given time. Upon triggering, the drive element 66 rotates. Drive element (66) the rotational motion is transferred to the damper 661, and from there to the rotational shaft 674. Same way the rotation shaft (674) transmits the rotational movement to the transmission part (68). Transfer piece (68) this the mechanism body (61) of the latches (681) by converting the rotational motion into linear motion. allows it to be drawn in. The latches (681) move through the ratchet holes (611). The obstacle in front of the ring (64) is removed. Then the spring (62) is stuck remains free. With the release of the energy stored in the spring (62), the force from the spring (62) is for separation to the pusher (63) via the movable ring (64) in the mechanism, and to the pusher (63) via the pusher (63) the force is transmitted to the components that need to be applied and evacuates the said components.
Claims (1)
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| TR2021/014519A TR2021014519A2 (en) | 2021-09-16 | 2021-09-16 | ROCKET, MISSILE AND SATELLITE COMPONENTS SPRING RELEASE SYSTEM |
| PCT/TR2022/051000 WO2023059288A2 (en) | 2021-09-16 | 2022-09-16 | Rocket, missile and satellite components spring release system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| TR2021/014519A TR2021014519A2 (en) | 2021-09-16 | 2021-09-16 | ROCKET, MISSILE AND SATELLITE COMPONENTS SPRING RELEASE SYSTEM |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| TR2021014519A2 true TR2021014519A2 (en) | 2021-09-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| TR2021/014519A TR2021014519A2 (en) | 2021-09-16 | 2021-09-16 | ROCKET, MISSILE AND SATELLITE COMPONENTS SPRING RELEASE SYSTEM |
Country Status (2)
| Country | Link |
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| TR (1) | TR2021014519A2 (en) |
| WO (1) | WO2023059288A2 (en) |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2729117B1 (en) * | 1995-01-10 | 1997-04-04 | Aerospatiale | METHOD FOR STEERING A MACHINE AND A MACHINE FOR IMPLEMENTING THE METHOD |
| RU2568965C1 (en) * | 2014-10-22 | 2015-11-20 | Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" (АО "ВПК "НПО машиностроения") | Device for separation and jettison of payload fairing of carrier missile |
| CN105711860B (en) * | 2016-02-05 | 2017-10-20 | 大连理工大学 | A kind of non-firer's point type separator of modified |
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2021
- 2021-09-16 TR TR2021/014519A patent/TR2021014519A2/en unknown
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| WO2023059288A2 (en) | 2023-04-13 |
| WO2023059288A3 (en) | 2023-07-20 |
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